US20220297841A1 - Aircraft and method for pre-cooling an environmental control system - Google Patents
Aircraft and method for pre-cooling an environmental control system Download PDFInfo
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- US20220297841A1 US20220297841A1 US17/835,524 US202217835524A US2022297841A1 US 20220297841 A1 US20220297841 A1 US 20220297841A1 US 202217835524 A US202217835524 A US 202217835524A US 2022297841 A1 US2022297841 A1 US 2022297841A1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0618—Environmental Control Systems with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Definitions
- Contemporary aircraft have bleed air systems that take hot air from the engines of the aircraft for use in other systems on the aircraft including environmental control systems (ECS) such as air-conditioning, pressurization, and de-icing.
- ECS environmental control systems
- the ECS can include limits on the pressure or temperature of the bleed air received from the bleed air systems.
- aircraft engine bleed systems make use of a pre-cooler heat exchanger to pre-condition the hot air from the engines to sustainable temperatures, as required or utilized by the other aircraft systems.
- the pre-cooler heat exchangers produce waste heat, which is typically exhausted from the aircraft without utilization.
- FIG. 1 is a perspective view of an aircraft having a bleed air system in accordance with various aspects described herein.
- FIG. 2 is a schematic cross-sectional view of a portion of an exemplary aircraft gas turbine engine that can be utilized in the aircraft of FIG. 1 .
- FIG. 3 is a schematic view of a gas turbine engine bleed air system that can be utilized in the aircraft of FIG. 1 in accordance with various aspects described herein.
- FIG. 4 is a schematic view of a two gas turbine engine bleed air system architectures that can be utilized in the aircraft of FIG. 1 in accordance with various aspects described herein.
- FIG. 5 is a schematic view of a valve that can be utilized in a turbo-ejector as shown in FIGS. 3 and 4 .
- FIG. 6 is an example a flow chart diagram illustrating a method of providing bleed air to the environmental control system in accordance with various aspects described herein.
- FIG. 1 illustrates an embodiment of the disclosure, showing an aircraft 10 that can include a bleed air system 20 , only a portion of which has been illustrated for clarity purposes.
- the aircraft 10 can include multiple engines, such as gas turbine engines 12 , a fuselage 14 , a cockpit 16 positioned in the fuselage 14 , and wing assemblies 18 extending outward from the fuselage 14 .
- the aircraft can also include an environmental control system (ECS) 48 .
- the ECS 48 is schematically illustrated in a portion of the fuselage 14 of the aircraft 10 for illustrative purposes only.
- the ECS 48 is fluidly coupled with the bleed air system 20 to receive a supply of bleed air from the gas turbine engines 12 .
- the bleed air system 20 can be connected to the gas turbine engines 12 such that high temperature, high pressure air, low pressure air, low temperature, or a combination thereof received from the gas turbine engines 12 can be used within the aircraft 10 for environmental control of the aircraft 10 .
- an engine can include a set of bleed ports 24 arranged along the gas turbine engine 12 length or operational stages such that bleed air can be received, captured, or removed from the gas turbine engine 12 as the corresponding set of bleed ports 24 .
- various bleed air characteristics including but not limited to, bleed air mass flow rate (for example, in pounds per minute), bleed air temperature or bleed air pressure, can be selected based on the desired operation or bleed air demand of the bleed air system 20 .
- ambient air can be used within the aircraft 10 for environmental control of the aircraft 10 .
- the environmental control of the aircraft 10 that is, the ECS 48 of the aircraft 10
- the ECS 48 of the aircraft 10 can include subsystems for anti-icing or de-icing a portion of the aircraft, for pressurizing the cabin or fuselage, heating or cooling the cabin or fuselage, and the like.
- the operation of the ECS 48 can be a function of at least one of the number of aircraft 10 passengers, aircraft 10 flight phase, or operational subsystems of the ECS 48 .
- Examples of the aircraft 10 flight phase can include, but is not limited to ground idle, taxi, takeoff, climb, cruise, descent, hold, and landing.
- the demand of the bleed air system 20 by the ECS can be dynamic as, for example, subsystems are needed based on aircraft 10 conditions.
- gas turbine engines 12 While a commercial aircraft 10 has been illustrated, it is contemplated that embodiments of the invention can be used in any type of aircraft 10 . Further, while two gas turbine engines 12 have been illustrated on the wing assemblies 18 , it will be understood that any number of gas turbine engines 12 including a single gas turbine engine 12 on the wing assemblies 18 , or even a single gas turbine engine mounted in the fuselage 14 can be included.
- FIG. 2 illustrates a cross section of the gas turbine engine 12 of the aircraft 10 .
- the gas turbine engine 12 can include, in a serial relationship, a fan 22 , a compressor section 26 , a combustion section 25 , a turbine section 27 , and an exhaust section 29 .
- the compressor section 26 can include, in a serial relationship, a multi-stage low pressure compressor 30 , and a multi-stage high pressure compressor 32 .
- the gas turbine engine 12 is also shown including a low pressure bleed port 34 arranged to pull, draw, or receive low pressure bleed air from the low pressure compressor 30 and a high pressure bleed port 36 arranged to pull, draw, or receive high pressure bleed air from the high pressure compressor 32 .
- the bleed ports 34 , 36 are also illustrated coupled with various sensors 28 , which can provide corresponding output signals.
- the sensors 28 can include respective temperature sensors, respective flow rate sensors, or respective pressure sensors.
- the low pressure compressor 30 can include a set of low pressure bleed ports 34 arranged at multiple stages of the compressor 30 to pull, draw, or receive various bleed air characteristics, including but not limited to, bleed air mass flow rate, bleed air temperature, or bleed air pressure.
- the high pressure compressor 32 can include a set of high pressure bleed ports 36 to pull, draw, or receive various bleed air characteristics, including but not limited to, bleed air mass flow rate, bleed air temperature, or bleed air pressure.
- Non-limiting embodiments of the disclosure can further include configurations wherein at least one of the low or high pressure bleed port 34 , 36 can include a bleed port from an auxiliary power units (APU) or ground cart units (GCU) such that the APU or GCU can provide an augmented pressure and conditioned temperature airflow in addition to or in place of the engine bleed ports 34 , 36 .
- APU auxiliary power units
- GCU ground cart units
- the rotation of the fan 22 draws in air, such that at least a portion of the air is supplied to the compressor section 26 .
- the air is pressurized to a low pressure by the low pressure compressor 30 , and then is further pressurized to a high pressure by the high pressure compressor 32 .
- the low pressure bleed port 34 and the high pressure bleed port 36 draw, respectively low pressure air from the low pressure compressor 30 and high pressure air from the high pressure compressor 32 and supply the air to a bleed air system for supplying air to the ECS 48 .
- High pressure air not drawn by the high pressure bleed port 36 is delivered to the combustion section 25 , wherein the high pressure air is mixed with fuel and combusted.
- the combusted gases are delivered downstream to the turbine section 27 , which are rotated by the gases passing through the turbine section 27 .
- the rotation of the turbine section 27 in turn, rotates the fan 22 and the compressor section 26 upstream of the turbine section 27 .
- the combusted gases are exhausted from the gas turbine engine 12 through the exhaust section 29 .
- FIG. 3 illustrates a schematic view of portions of the aircraft 10 including the gas turbine engine 12 , the bleed air system 20 , and the ECS 48 .
- the bleed air system 20 can include a turbo air cycle machine 38 fluidly coupled upstream with the set of gas turbine engine (shown only as a single gas turbine engine 12 ) and fluidly coupled downstream with the ECS 48 .
- the turbo air cycle machine 38 can include a first turbine section 40 a , a second turbine section 40 b , a first compressor section 42 a , and second compressor section 42 b , all of which can be rotatably coupled on a common shaft 41 .
- the turbo air cycle machine 38 can include four wheels: the first and second turbine sections 40 a , 40 b and the first and second compressor sections 42 a , 42 b .
- the bleed air system 20 of the turbo air cycle machine 38 can include a flow mixer or turbo-ejector 44 located downstream from the turbo air cycle machine 38 .
- the low pressure and high pressure bleed ports 34 , 36 can be fluidly coupled with the turbo air cycle machine 38 by way of a proportional mixing or controllable valve assembly 45 .
- the controllable valve assembly 45 can include mixing, proportional mixing, or non-mixing configurations.
- the proportional mixing assembly can include a proportional mixing-ejector valve assembly.
- the proportional mixing-ejector valve assembly or controllable valve assembly 45 can be arranged to supply the low pressure and high pressure bleed air to the turbo air cycle machine 38 .
- Non-limiting examples of the proportional mixing-ejector valve assembly or controllable valve assembly 45 can include a turbo-ejector or mixing-ejector assembly, wherein the high pressure bleed port 36 entrains at least a portion of the low pressure bleed air of the low pressure bleed port 34 , or “pulls” air from the low pressure bleed port 34 , and provides the mixed, combined, or entrained air to the turbo air cycle machine 38 .
- Embodiments of the disclosure can include aspects wherein the supply ratio of the low pressure bleed air and high pressure bleed air can be selected to never go below, or alternatively, to never exceed, a predetermined ratio.
- the aspects of the supply ratio can include, or can be determined to maintain an energy or power balance between the turbine sections 40 a , 40 b and compressor sections 42 a , 42 b of the turbo air cycle machine 38 .
- Another non-limiting example of the proportional mixing-ejector valve assembly or controllable valve assembly 45 can be included wherein the low pressure bleed port 34 of the gas turbine engine 12 can be fluidly coupled with the first compressor section 42 a and second compressor section 42 b of the turbo air cycle machine 38 by way of a first controllable valve 46 and a valve 86 .
- the high pressure bleed port 36 of the gas turbine engine 12 can be directly fluidly coupled with the first turbine section 40 a of the turbo air cycle machine 38 by way of a second controllable valve 50 .
- first or second controllable valves 46 , 50 or valve 86 can include a fully proportional or continuous valve.
- the controllable valve 46 is illustrated as being combined with a source selection option that includes an integrated check valve 46 a .
- the first controllable valve 46 acts as a source selection valve for supplying an ambient airflow or the low pressure bleed airflow 66 .
- the first controllable valve 46 can operate to supply only one or the other of the ambient airflow or the low pressure bleed airflow 66 .
- the integrated check valve 46 a is selected or configured to provide fluid traversal or selective fluid traversal from the ambient air inlet toward the low pressure bleed airflow 66 .
- the integrated check valve 46 a can be selected or configured such that the integrated check valve 46 a closes, or self-actuates to a closed position under back pressure, that is when the pressure within the low pressure bleed airflow conduit is higher or greater than the air pressure of the ambient air inlet.
- the integrated check valve 46 a can be configured to selected to self-actuate relative to a predetermined air pressure sufficient to operate the turbo air cycle machine 38 In this sense, the integrated check valve 46 a can prevent low bleed pressure air to backflow into the ambient air inlet.
- the integrated check valve can be configured to provide all proportional supplying capabilities described herein.
- valve 86 allows for selective supplying of airflow to the second compressor section 42 b .
- Control of the valve 86 allows for pressure matching from the first compressor section 42 a and the second compressor section 42 b .
- the addition of the second compressor section 42 b in parallel with the first compressor section 42 a increases flow capacity without necessarily increasing outlet pressures or temperatures.
- Dual compressor sections 42 a , 42 b operating in parallel can operably run “cooler” (i.e. at a lower operating temperature) in their combined capacity than a comparably-operating single compressor section.
- the second compressor section 42 b in parallel with the first compressor section 42 a may decrease installation footprint in the aircraft depending on their arrangements.
- utilizing both the first and second compressor sections 42 a , 42 b in parallel allows compressor stages unloading based at least partially on a bleed air demand, such as a mass flow (e.g. airflow) demand.
- a conventional system may have to unload a higher capacity single compressor.
- valve 86 can be eliminated in favor of a compressor outlet diffuser that can be included and configured to modulate the exit pressures of the respective compressor sections 42 a , 42 b .
- the valve 86 can be eliminated in favor of a set of compressor inlet guide vanes that can be configured to vary the flow intake (and thus, capacity) of one compressor section (e.g. the first compressor section 42 a ) compared with the other compressor section (e.g. the second compressor section 42 b ), until the output pressures match, as described herein.
- the compressor outlet diffuser or the inlet guide vanes can be operably controlled by way of the controller module 60 .
- the proportional valve assembly 45 can operate in response to, related to, or as a function of the aircraft flight phase or the rotational speed of the gas turbine engine 12 .
- the rotational speed of the gas turbine engine 12 can vary within an operating cycle, during which the proportional mixing-ejector valve assembly or controllable valve assembly 45 can be adjusted based on gas turbine engine transient or dynamic conditions.
- Embodiments of the disclosure can supply any ratio of low pressure bleed air to high pressure bleed air, such as 100% of first bleed air, and 0% of second bleed air.
- the ratio can be predetermined based on dynamic response to engine conditions and to maintain energy balance, an energy balance bleed air demand, or a power balance between the turbine and compressor sections of the turbo air cycle machine assembly.
- the low pressure bleed air provided by the low pressure bleed port 34 can be further provided to the first turbine section 40 a downstream of the respective first controllable valve 46 and second controllable valve 50 , wherein a fluid coupling providing the low pressure bleed air to the first turbine section 40 a can include a check valve 52 biased in the direction from the low pressure bleed port 34 toward the high pressure bleed port 36 or the first turbine section 40 a of the turbo air cycle machine 38 .
- the check valve 52 is configured such that fluid can only flow from the low pressure bleed port 34 to the high pressure bleed port 36 or the first turbine section 40 a of the turbo air cycle machine 38 .
- Embodiments of the disclosure can be included wherein the check valve 52 is selected or configured to provide fluid traversal from the low pressure bleed port 34 toward the high pressure bleed port 36 under defined or respective pressures of the flow in the respective the low pressure bleed port 34 toward the high pressure bleed port 36 .
- the check valve 52 can be selected or configured to only provide fluid traversal, as shown, the air pressure of the high pressure bleed port 36 is lower or less than the air pressure of the low pressure bleed port 34 .
- the check valve 52 can be selected or configured such that the valve 52 closes, or self-actuates to a closed position under back pressure, that is when the pressure of the high pressure bleed port 36 is higher or greater than the air pressure of the low pressure bleed port 36 .
- embodiments of the disclosure can include a check valve 52 or the turbo-ejector or the mixing-ejector proportional assembly that is controllable to provide selective fluid traversal from the low pressure bleed port 34 toward the high pressure bleed port 36 .
- the first compressor section 42 a and second compressor section 42 b of the turbo air cycle machine 38 can include a compressor output 54 .
- the addition of a check valve 88 prevents backflow or pressure from the first compressor section 42 a to the second compressor section 42 b.
- a decoupler 80 can be operably coupled to the portion of the common shaft 41 between the first compressor section 42 a and the second compressor section 42 b .
- the decoupler 80 can be any suitable mechanism configured to uncouple the second compressor section 42 b from the common shaft 41 or a remainder of the common shaft 41 .
- the decoupler 80 can include, but is not limited to, a clutch or mechanical fuse disconnect. It will be understood that the decoupler 80 can be optional and that the second compressor section 42 b can alternatively always be coupled to the common shaft 41 .
- the decoupler 80 is configured to decouple the second compressor section 42 b from the first compressor section 42 a and allows for reduced capacity as a function of occupancy of the aircraft 10 .
- the decoupler 80 can be controlled automatically by a processor, such as the controller module 60 , or manually before engine start as selected by the crew or by a user, based on the mission requirements or bleed air demand.
- the decoupler 80 can operably de-couple the second compressor section 42 b from the first compressor section 42 a or common shaft 41 while the compressor sections 42 a , 42 b are operating, such as in-flight.
- the decoupler 80 can only operably re-couple the second compressor section 42 b to the first compressor section 42 a or common shaft 41 when the compressor sections 42 a , 42 b are not operating. The re-coupling only while the compressor sections 42 a , 42 b are not operating can be due to, for instance, possible damage caused to bearings, gears, the common shaft 41 , or the like, if re-coupled was enabled during operations.
- the first turbine section 40 a can include a first turbine output 56 defining a cooled airflow 70 .
- the first turbine output 56 can be optionally and proportionally supplied to the second turbine section 40 b . More specifically, the first turbine output 56 is illustrated at being fluidly coupled to the second turbine section 40 b .
- the first turbine output 56 can also be fluidly coupled to a bypass conduit 43 . As illustrated the bypass conduit 43 can fluidly couple the fluid output 56 of the first turbine section 40 a to the downstream turbo-ejector 44 such that the fluid output 56 need not be provided to the second turbine section 40 b .
- a bypass valve 47 is included to selectively control fluid flow through the bypass conduit 43 to the downstream turbo-ejector 44 .
- the bypass valve 47 can be any suitable valve including, but not limited to, a proportional valve or a continuous valve.
- the second turbine section 40 b can include a second turbine output 71 defining an airflow.
- First turbine output 56 that bypasses the second turbine section 40 b has been schematically illustrated with arrows and defines a bypass airflow 73 .
- the compressor output 54 , any second turbine output 71 and any bypass airflow 73 are fluidly combined downstream of the turbo air cycle machine 38 .
- the flow mixer is arranged to fluidly combine the compressor output 54 , any second turbine output 71 , and any bypass airflow 73 to a common mixed flow 74 that is supplied to the bleed air inlet 49 of the ECS 48 .
- the downstream turbo-ejector 44 fluidly combines fluid outputs from the first turbine section 40 a , in the form of bypass airflow 73 , and the second turbine section 40 b , in the form of a second turbine output 71 , with fluid output from the compressor section, in the form of compressor output 54 , into a common flow 74 that is supplied to the bleed air inlet 49 of the ECS 48 .
- the bleed air system 20 preconditions the bleed air before the bleed air is received by the bleed air inlet 49 of the ECS 48 .
- the second turbine output 71 and bypass airflow 73 are fluidly coupled to define a combined turbine output airflow 75 or cooled airflow.
- the turbo-ejector 44 pressurizes the turbine output airflow 75 as it traverses a narrow portion 58 , or “throat” of the turbo-ejector 44 , and fluidly injects the compressor output 54 into the narrow portion 58 of the turbo-ejector 44 .
- the injection of the compressor output 54 into the pressurized turbine output airflow 75 fluidly combines the compressor output 54 with the turbine output airflow 75 .
- the common airflow stream 74 of the turbo-ejector 44 is fluidly coupled downstream with the ECS 48 at a bleed air inlet 49 .
- Embodiments of the disclosure can be included wherein the compressor output 54 , the turbine output airflow 75 , or the turbo-ejector 44 (e.g. downstream from the narrow portion 58 ) can include a set of sensors 28 .
- the turbo-ejector 44 works by injecting air from a higher pressure source into a nozzle at the input end of a venturi restriction, into which a lower pressure air source is also fed. Air from the higher pressure source is emitted downstream into the lower pressure flow at high velocity. Friction caused by the adjacency of the airstreams causes the lower pressure air to be accelerated (“entrained”) and drawn through the venturi restriction. As the higher pressure air ejected into the lower pressure airstream expands toward the lower pressure of the low pressure air source, the velocity increases, further accelerating the flow of the combined or mixed airflow.
- Non-limiting embodiments of the disclosure can be included wherein the high pressure air source is at a higher or greater temperature than the low pressure air source.
- the entrainment and mixing process can occur without the high pressure air source having a higher or greater temperature than the low pressure air source.
- the aircraft 10 or bleed air system 20 can also include a controller module 60 having a processor 62 and memory 64 .
- the controller module 60 or processor 62 can be operably or communicatively coupled to the bleed air system 20 , including its sensors 28 , the first controllable valve 46 , the second controllable valve 50 , the bypass valve 47 , and the ECS 48 .
- the controller module 60 or processor 62 can further be operably or communicatively coupled with the sensors 28 dispersed along the fluid couplings of the bleed air system 20 .
- the memory 64 can include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic memory, such as discs, DVDs, CD-ROMs, etc., or any suitable combination of these types of memory.
- the controller module 60 or processor 62 can further be configured to run any suitable programs. Non-limiting embodiments of the disclosure can be included wherein, for example, the controller module 60 or processor 62 can also be connected with other controllers, processors, or systems of the aircraft 10 , or can be included as part of or a subcomponent of another controller, processor, or system of the aircraft 10 .
- the controller module 60 can include a full authority digital engine or electronics controller (FADEC), an onboard avionic computer or controller, or a module remoted located by way of a common data link or protocol.
- FADEC full authority digital engine or electronics controller
- a computer searchable database of information can be stored in the memory 64 and accessible by the controller module 60 or processor 62 .
- the controller module 60 or processor 62 can run a set of executable instructions to display the database or access the database.
- the controller module 60 or processor 62 can be operably coupled to a database of information.
- a database can be stored on an alternative computer or controller.
- the database can be any suitable database, including a single database having multiple sets of data, multiple discrete databases linked together, or even a simple table of data. It is contemplated that the database can incorporate a number of databases or that the database can actually be a number of separate databases.
- the database can store data that can include, among other things, historical data related to the reference value for the sensor outputs, as well as historical bleed air system 20 data for the aircraft 10 and related to a fleet of aircraft.
- the database can also include reference values including historic values or aggregated values.
- the bleed air system 20 supplies a low pressure bleed airflow 66 along the low pressure bleed port 34 and a high pressure bleed airflow 68 along the high pressure bleed port 36 , as previously explained.
- the high pressure bleed airflow 68 is delivered to the first turbine section 40 a and optionally the second turbine section 40 b of the turbo air cycle machine 38 , which in turn interacts with the turbine(s) to drive the rotation of the first turbine section 40 a and the second turbine section 40 b .
- the high pressure bleed airflow 68 exits the first turbine section 40 a at the first turbine output 56 as a first turbine output airflow.
- a first portion 66 a of the low pressure bleed airflow 66 can be delivered to the first compressor section 42 a
- a second portion 66 b of the low pressure bleed airflow 66 can be delivered to the second compressor section 42 b of the turbo air cycle machine 38
- a third portion of the low pressure bleed airflow 66 can be delivered to the first turbine section 40 a and optionally the second turbine section 40 b of the turbo air cycle machine 38 , depending on the operation of the check valve 52 or upstream turbo-ejector or mixing-ejector proportional assembly, or the respective airflows 66 , 68 of the respective low pressure bleed port 34 and high pressure bleed port 36 , as explained herein.
- embodiments of the disclosure can include operations wherein the airflow delivered to the first turbine section 40 a and optionally the second turbine section 40 b can include entirely low pressure bleed airflow 66 , no low pressure bleed airflow 66 , or a portion therebetween.
- the second portion of the low pressure bleed airflow 66 can also be utilize to drive the rotation of the first turbine section 40 a and the second turbine section 40 b , such as when the controllable valve 50 is set to provide no high pressure bleed airflow 68 .
- the controller module 60 is configured to operate the bypass valve 47 to supply an amount of the first turbine output 56 to the second turbine section 40 b of the turbo air cycle machine 38 . It is contemplated that the controller 60 can operate the bypass valve 47 based on input from any of the sensors 28 including temperature sensors of the combined airflow stream 74 , the turbine output airflow 75 , the first turbine output 56 , any combination thereof, etc. Embodiments of the disclosure can include operations wherein the first turbine output 56 can supply less than 100% of the cooled air stream to the second turbine section 40 b , or wherein the first turbine output 56 can supply 100% of the cooled air stream to the second turbine section 40 b.
- the first portion 66 a of the low pressure bleed airflow 66 can be compressed by the rotation of the first compressor section 42 a .
- the second portion 66 b of the low pressure bleed airflow 66 can be compressed by the second compressor section 42 b , which is rotatably coupled with the first turbine section 40 a and the second turbine section 40 b .
- the compressed low pressure bleed air exits the first compressor section 42 a and second compressor section 42 b at the compressor output 54 as compressor output airflows 72 a and 72 b , which can be combined to form compressed airflow 72 c .
- the turbine output airflow 75 and the compressor output airflow 72 c are combined in the turbo-ejector 44 to form the combined airflow stream 74 , which is further provided to the ECS 48 .
- the combined airflow stream 74 can be expressed as a composition or a ratio of the low pressure and high pressure bleed airflow 66 , 68 , or a composition of a ratio of the combined turbine output and compressor output airflows 75 , 72 c.
- the airflows received by the first turbine section 40 a and the second turbine section 40 b that is, the high pressure airflow 68 and selective low pressure airflow 66 via the check valve 52 via a turbo-ejector or mixing-ejector proportional assembly, generates a lower pressure and a lower temperature turbine output airflow 75 , compared with the first turbine section 40 a and the second turbine section 40 b input airflows 66 , 68 .
- the first compressor section 42 a and second compressor section 42 b outputs or emits a hotter and higher pressure airflow 72 c
- the first turbine section 40 a outputs or emits a cooler and lower pressure airflow 70 , compared with the relative input airflows 66 , 68
- the second turbine section 40 b outputs or emits an even cooler airflow 71 as compared with the airflow 70 .
- the controller module 60 or processor 62 can be configured to operably receive a bleed air demand, generated by, for example, the ECS 48 .
- the bleed air demand can be provided to the controller module 60 or processor 62 by way of a bleed air demand signal 76 , which can include bleed air demand characteristics included, but not limited to, flow rate, temperature, pressure, or mass flow (e.g. airflow).
- a bleed air demand signal 76 can include bleed air demand characteristics included, but not limited to, flow rate, temperature, pressure, or mass flow (e.g. airflow).
- the controller module 60 or processor 62 can operably supply proportional amounts of the low pressure bleed airflow 66 and high pressure bleed airflow 68 to the turbo air cycle machine 38 .
- the proportionality of the low pressure bleed airflow 66 , and the high pressure bleed airflows 68 can be controlled by way of the respective first or second controllable valves 46 , 50 , and by selective operation of the check valve 52 or mixing-ejector proportional assembly.
- the proportional supplying of the low pressure and high pressure bleed airflows 66 , 68 can be directly or geometrically proportional to the turbine output airflow 75 and compressor output airflow 72 c , or the turbine air cycle machine 38 operations.
- the turbine output airflow 75 and compressor output airflow 72 c are combined downstream of the turbo air cycle machine 38 , and the combined airflow stream 74 is provided to the ECS 48 .
- the compressor output airflow 72 c can drive the turbine output airflow 75 into the narrow portion 58 and mix under sonic conditions.
- the mixed flow pressure will recover statically through the combined airflow stream 74 to output the turbo-ejector 44 at desired conditions.
- the combined airflow stream 74 is conditioned by way of operation of the bleed air system 20 , controllable valves 46 , 50 , check valve 52 , turbo-ejector or mixing-ejector proportional assembly, turbo air cycle machine 38 , the combining of the turbine output airflow 75 and the compressor output airflow 72 c , or any combination thereof, to meet or satisfies the ECS 48 demand for bleed air.
- One of the controller module 60 or processor 62 can include all or a portion of a computer program having an executable instruction set for determining the bleed air demand of the ECS 48 , proportionally or selectively supplying the low pressure or high pressure bleed airflows 66 , 68 , operating the controllable valves 46 , 50 , the check valve's 52 or turbo-ejector or mixing-ejector proportional assembly's operation in response to the respective high pressure and low pressure airflows 66 , 68 , or a combination thereof.
- proportionally or selectively supplying” the low pressure or high pressure bleed airflows 66 , 68 can include altering or modifying at least one of the low pressure or high pressure bleed airflows 66 , 68 .
- proportionally or selectively supplying the low pressure or high pressure bleed airflows 66 , 68 can include altering the low pressure bleed airflow 66 without altering the high pressure bleed airflow 68 , or vice versa.
- proportionally or selectively supplying the low pressure or high pressure bleed airflows 66 , 68 can include altering the low pressure bleed airflow 66 and the high pressure bleed airflow 68 .
- “proportionally” supplying the low pressure or high pressure bleed airflows 66 , 68 can include altering or modifying the ratio of low pressure bleed airflow 66 to high pressure bleed airflow 68 , based on the total bleed airflow 66 , 68 supplied. Stated another way, the proportions of low or high pressure bleed airflow 66 , 68 can be altered or modified, and a proportional ratio can be included or described based on the total airflow of the low and high pressure bleed airflows 66 , 68 .
- the program can include a computer program product that can include machine-readable media for carrying or having machine-executable instructions or data structures stored thereon.
- machine-readable media can be any available media, which can be accessed by a general purpose or special purpose computer or other machine with a processor.
- a computer program can include routines, programs, objects, components, data structures, and the like, that have the technical effect of performing particular tasks or implementing particular abstract data types.
- Machine-executable instructions, associated data structures, and programs represent examples of program code for executing the exchange of information as disclosed herein.
- Machine-executable instructions can include, for example, instructions and data, which cause a general-purpose computer, special purpose computer, or special purpose processing machine to perform a certain function or group of functions.
- the controller module 60 or processor 62 can also be configured to operate the bleed air system 20 , as explained herein, in response to receiving a set of sensor input values received by the sensors 28 dispersed along the fluid couplings of the bleed air system 20 .
- the controller module 60 or processor 62 can include predetermined, known, expected, estimated, or calculated values for the set of airflows 66 , 66 a , 66 b , 68 , 70 , 71 , 72 a , 72 b , 72 c , 73 , 74 , 75 traversing the bleed air system 20 .
- the controller module 60 or processor 62 can alter the proportional supplying of the low pressure or high pressure bleed airflows 66 , 68 in order to meet or satisfy the bleed air demand for the ECS 48 .
- the memory 64 can include a database or lookup table such that a proportional supplying values related to the low pressure or high pressure bleed airflows 66 , 68 can be determined in response to the controller module 60 receiving a set or subset of sensor 28 readings, measurements, or the like.
- sensors 28 are described as “sensing,” “measuring,” or “reading” respective temperatures, flow rates, or pressures
- the controller module 60 or processor 62 can be configured to sense, measure, estimate, calculate, determine, or monitor the sensor 28 outputs, such that the controller module 60 or processor 62 interprets a value representative or indicative of the respective temperature, flow rate, pressure, or combination thereof.
- sensors 28 can be included proximate to, or integral with additional components not previously demonstrated.
- embodiments of the disclosure can include sensors 28 located to sense the combined airflow stream 74 , or can include sensors 28 located within the narrow portion 58 , or “throat” of the turbo-ejector 44 .
- the controller module 60 can operate the second controllable valve 50 based on a bleed air demand of the bleed air system 20 .
- the bleed air demand can include, for example, a desired or demanded output airflow stream 74 from the turbo-ejector 44 .
- the controller module 60 can operate the second controllable valve 50 based on a desired or demanded output airflow stream 74 of the turbo-ejector 44 .
- the controller module 60 can further operate, for example, the bypass valve 47 such that the bypass airflow 73 of the first turbine output 56 , when combined with the second turbine output 71 , affects a cooling of the turbine output airflow 75 , which in turn operably affects or controls the temperature of the output airflow stream 74 , based on a bleed air demand of the bleed air system 20 , such as a desired or demanded temperature of the output airflow stream 74 .
- the bypass valve 47 can be operably opened such that air will flow from the first turbine output 56 to the turbine output airflow 75 .
- the opening of the bypass valve 47 can operably raise the temperature of the output airflow stream 74 .
- the bypass valve 47 can be operably closed such that no bypass airflow 73 is provided to the turbine output airflow 75 , and ultimately, the output airflow stream 74 .
- the closing of the bypass valve 47 can operably lower the temperature of the output airflow stream 74 .
- the controller module 60 can operate the second controllable valve 50 based on a bleed air demand including a desired or demanded pressure of the output airflow stream 74 . If the pressure of the output airflow stream 74 , as sensed by a sensor 28 , is below or less than a threshold, demanded, or desired pressure, the second controllable valve 50 can operably open to provide or allow a portion or additional high pressure bleed airflow 68 to the turbo air cycle machine 38 .
- the second controllable valve 50 provides or allows high pressure bleed airflow 68 to the turbo air cycle machine 38 , the turbine sections 40 a 40 b will rotate faster, generating more rotational power, which in turn, affects the total amount of power for the compressor sections 42 a , 42 b to absorb.
- the second controllable valve 50 can be operated to modify or adjust the pressure of the output airflow stream 74 based on a desired or demanded pressure.
- the first controllable valve 46 can be controllably operated by the controller module 60 , and based on the compressor output airflow 72 c , as sensed by the sensor 28 , maintain a power balance between the turbine sections 40 a , 40 b generating power and the compressor sections 42 a , 42 b absorbing power.
- the controller module 60 can be configured to operate the first and second controllable valves 46 , 50 simultaneously.
- valves 46 , 50 , 47 allows for, causes, or affects the adiabatic change in efficiency of the turbo-ejector.
- Embodiments of the disclosure can be included wherein the controller module 60 or processor 62 can be configured to operate the bleed air system 20 to account for sensor 28 measurements in the set or a subset of the airflows 66 , 68 , 70 , 71 , 72 a , 72 b , 72 c , 73 , 74 , 75 .
- the bleed air system 20 can operate without feedback inputs, that is, without the controller module 60 or processor 62 receiving sensed information from the sensors 28 .
- the controller module 60 or processor 62 can be configured to operate the first or second controllable valves 46 , 50 , and the like based on a continuous operation of the aircraft 10 , given the dynamic responses as observed during the aircraft 10 flight phases.
- the above described disclosure with the second stage turbine 40 b allows the turbo air cycle machine 38 to have increased cooling capacity, allows for higher bleed stage extraction from the gas turbine engine 12 , and allows for increased turbine power generation as compared to a turbo air cycle machine with only one turbine section.
- the inclusion of the second stage turbine bypass allows second stage unloading at lower high pressure bleed port extraction stages, reduces unnecessary second turbine stage excess power, and allows second stage turbine exit temperature control.
- FIG. 4 is a schematic view of a two turbine engine bleed air system architecture that can be utilized in the aircraft 10 .
- the bleed air system illustrated in FIG. 3 has been illustrated as being incorporated into both sides of the aircraft 10 .
- Like parts have been identified with like numerals and the above description of such parts applies. It will be understood that such architecture is by way of non-limiting example only.
- FIG. 4 illustrates that the combined airflow stream 74 from left and right turbo-ejectors 44 can be fluidly coupled to the ECS 48 .
- the ECS 48 is illustrated as including both a left air conditioning pack 100 and a right air conditioning pack 102 .
- the combined airflow stream 74 from the turbo-ejectors 44 can be fluidly coupled to such air conditioning packs 100 and 102 through any suitable conduits and valving illustrated schematically.
- the quantity of combined airflow stream 74 to the air conditioning packs 100 and 102 is regulated by the flow control valve 112 .
- One flow control valve 112 is installed for each of the air conditioning packs 100 and 102 .
- An isolation valve 110 is also illustrated as being included.
- the isolation valve 110 is normally closed and prevents air from the left side bleed air system 20 from reaching the right air conditioning pack 102 and vice versa.
- the isolation valve 110 can be opened in the event of loss of one of the bleed air systems 20 .
- the output from the turbo-ejectors 44 can also be supplied through the flow control valve 112 to anti-icing systems 116 via valves 114 .
- the air conditioning packs 100 and 102 can be fluidly coupled to a mixing manifold 104 , which can ultimately provide airflow to the cabin 106 and the flight deck 108 . More specifically, exhaust flows from the air conditioning packs 100 and 102 are fluidly coupled to the mixing manifold 104 where they are typically mixed with filtered air. Airflow from the mixing manifold 104 is directed to distribution nozzles to supply the cabin 106 and the flight deck 108 . Check valves 118 can be included between the air conditioning packs 100 and 102 and the mixing manifold 104 .
- FIG. 5 illustrates in more detail that a valve 130 can be included in the flow mixer or turbo-ejector 44 located downstream from the turbo air cycle machine 38 .
- the valve 130 can include a controllable pintle injector utilized to control the injection of the compressor output 54 into the throat portion 58 of the turbo-ejector 44 .
- the valve 130 can include a slidable needle 132 linearly actuated in either directions as indicated by arrow 134 .
- the slidable needle 132 or pintle can be proportionally & linearly actuated to increase or decrease the nozzle exit flow area discharge into the throat 58 which can in turn operably affect the ratio of entrainment of lower pressure air 75 versus injected higher pressure air 72 c and the overall turbo ejector efficiency as a pumping mechanism.
- the varying of lower pressure mass airflow 75 versus higher pressure mass airflow 72 c ratio increases or decreases the range of operability of the turbo ejector which affects its efficiency. In this sense, efficiency is a function of pressure, temperature, and mass flow ratios. Thus, any variation of pressure, temperature, and mass flow ratios operably affects the efficiency output rating.
- the needle 132 may be controllably operated, for example, via the controller module 60 to maintain a pre-determined mass flow ratio, to maintain an efficiency rating, or to operate the turbo-ejector 44 relative to a predetermined threshold or threshold range.
- Such a valve allows control of turbo ejector efficiency and allows control of the low pressures and high pressure mass flow ratios.
- FIG. 6 illustrates a flow chart demonstrating a non-limiting example method 200 of providing bleed air to the ECS 48 of an aircraft using at least one gas turbine engine 12 .
- the method 200 begins at 210 by determining a bleed air demand for the ECS 48 . Determining the bleed air demand can include determining at least one of an air pressure, an air temperature, or a flow rate demand for the ECS 48 , or a combination thereof.
- the bleed air demand can be a function of at least one of the number of aircraft passengers, aircraft flight phase, or operational subsystems of the ECS 48 .
- the bleed air demand can be determined by the ECS 48 , the controller module 60 , or the processor 62 based on the bleed air demand signal 76 .
- the controller module 60 or the processor 62 operably controls the controllable valve assembly 45 to proportionally supply the low pressure and high pressure bleed air such that turbo air cycle machine 38 emits a cooled air stream from the first turbine section 40 a in the form of bypass airflow 73 or the second turbine section 40 b and a compressed air stream from the compressor sections 42 a , 42 b .
- a “cooled” airstream can describe an airflow having a lower temperature than the airflow received by the first turbine section 40 a .
- Embodiments of the disclosure can include, but are not limited to, supplying up to 100% of the combined airflow stream 74 of one of the low pressure or high pressure bleed airflow and 0% of the corresponding other of the low pressure or high pressure bleed airflow.
- Another example embodiment of the disclosure can include, but is not limited to, proportionally supplying the low pressure and high pressure bleed airflows wherein the proportionally supplying is related to, or is a function of the aircraft flight phase or rotational speed of the gas turbine engine 12 .
- the proportionally supplying of the bleed air can include continuously proportionally supplying the bleed air, that is, repeatedly altering the proportional supplying of the low pressure and high pressure bleed airflows over a period of time, or indefinitely during the flight of the aircraft.
- the bypass valve 47 can be controlled by the controller module 60 or the processor 62 such that output from the first turbine section 40 a is directed to the second turbine section 40 b to create a further cooled air stream or second turbine output 71 or through the bypass conduit 43 to create a bypass airflow 73 .
- “further cooled” air stream describes that the air stream of the second turbine output 71 has a lower temperature than the output of the first turbine section 40 a that is directed to the second turbine section 40 b .
- Embodiments of the disclosure can include, but are not limited to the bypass valve 47 being controlled to supply any amount from 0% to 100% of the first turbine output 56 to the second turbine section 40 b and the remainder to the bypass conduit 43 .
- the controller module 60 or the processor 62 can control the bypass valve 47 in order to control the exit temperature of the combined airflow stream 74 .
- the valve 86 can be controlled by the controller module 60 or the processor 62 such that ambient air 51 or low pressure bleed air 66 can be selectively supplied to the second compressor section 42 b in addition to the first compressor section 42 a . It will be understood that the second compressor section 42 b is supplied in parallel with the first compressor section 42 a . It is contemplated that the controller module 60 or the processor 62 can determine flow rates to be supplied to the first compressor section 42 a and the second compressor section 42 b based on the determined flow rate demand from the ECS 48 and control the valve 86 based thereon such that the supplying is controlled such that the conditioned air stream meets or satisfies the determined bleed air demand.
- the turbo air cycle machine 38 emits a cooled air stream from the first turbine section 40 a in the form of bypass airflow 73 or the second turbine section 40 b in the form of a further cooled airflow 71 and a compressed air stream 72 a from the first compressor section 42 a and optionally a compressed air stream 72 b from the second compressor section 42 b.
- the method 200 continues by combining the cooled air stream, in the form of the bypass airflow 73 , the further cooled airflow stream in the form of the second turbine output 71 and the compressed air stream(s) 72 a , 72 b , 72 c to form a conditioned or combined airflow stream 74 .
- the compressed air stream 72 a from the first compressor section 42 a can be combined with the compressed air stream 72 b from the second compressor section 42 b to form a combined compressed airflow stream 72 c .
- the combined compressed air stream 72 c can then be combined with at least one of the bypass airflow 73 or the second turbine output 71 to form the conditioned air stream 74 .
- the compressed airflow stream 72 a can be combined with at least one of the bypass airflow 73 or the second turbine output 71 to form the conditioned air stream 74 .
- the proportional supplying the ambient air or low pressure and the high pressure bleed air at 220 , the selectively supplying at 230 and selectively supplying the cooled air to the second turbine section 40 b at 240 is controlled by the controller module 60 or processor 62 such that the combined airflow stream 74 meets or satisfies the bleed air demand for the ECS 48 as determined at 210 .
- Aspects of the method can also be included wherein the combined airflow stream 74 can be altered, modified, or the like, by way of operating the controllable pintle injector, the valve 130 , or the slidable needle 132 .
- the method can include receiving an output signal from a temperature sensor 28 related to a temperature of the conditioned air stream or combined airflow stream 74 .
- determining the bleed air demand at 310 can include determining an air temperature demand for the ECS 48 the controller 60 or processor 62 can calculate or otherwise determine an amount of cooled air stream to be supplied to the second turbine section 40 b based on the determined air temperature demand and the output signal from the temperature sensor 28 . It is contemplated that this can include continuously determining the amount of cooled air stream to be supplied to the second turbine section 40 b.
- the method can include proportionally supplying at least one of a first compressor section or a second compressor section based on desired flow capacity.
- the method can also include proportionally supplying low pressure bleed air and high pressure bleed air from a compressor of the gas turbine engine to a turbo air cycle machine to precondition the bleed air according to operational demands of the ECS wherein the preconditioning comprises selectively providing a fluid output emitted from a first turbine section 40 a of the turbo air cycle machine 38 to a second turbine section 40 b of the turbo air cycle machine 38 for further cooling.
- this can be based on temperature demands of the ECS.
- the controller module 60 can control the controllable valve 50 to be opened or closed as a master control to operably control an exit pressure of the combined airflow stream 74 of the turbo-ejector 44 .
- the controller module 60 can also control the first controllable valve 46 as a slave to the master control, to operably control the energy balance between the turbine sections 40 a , 40 b and the compressor sections 42 a , 42 b . This can be considered a master control in baseline system logic.
- the controller module 60 can control the controllable valve 46 to control a total compressor power balance in the turbo air cycle machine 38 and such can be a slave control to that of the controllable valve 50 .
- the controller module 60 can control the source selected by the controllable valve 46 and such a source selection can be set based on the mission schedule of the aircraft 10 .
- the controller module 60 can control the controllable valve 86 to match outlet pressures from the first compressor section 42 a and second compressor section 42 b .
- the check valve 52 can be closed or self-closed by default.
- the controller module 60 can also control the bypass valve 47 , and therefore an exit temperature of the combined airflow stream 74 of the turbo-ejector 44 simultaneously, but independently with the controllable valve 46 .
- the second controllable valve 50 can be included as an override consideration to reduce or lower at least one of the temperature or pressure of the combined airflow stream 74 if operation of the bypass valve 47 is inadequate, insufficient, or otherwise unable to operably control the temperature or pressure of the combined airflow stream 74 , as described herein.
- the system logic can be configured to operate the second controllable valve 50 to alter or adjust the pressure received by the turbine sections 40 a , 40 b , to operably alter or adjust the temperature of the combined airflow stream 74 .
- the controller 60 can control the operation of the valve 130 to operably control the low pressure and high pressure mass flow rates, target efficiency, or the like, as described herein, based on desired efficiency of the turbo-ejector 44 .
- the controller module 60 can operate in an alternate system logic, including but not limited to an emergency operation, for example, such as when the high pressure bleed source is disabled, removed, or shut down.
- an emergency operation for example, such as when the high pressure bleed source is disabled, removed, or shut down.
- the controllable valve 50 is closed and the controller module 60 can control the controllable valve 46 to control an exit pressure of the combined airflow stream 74 of the turbo-ejector 44 as a master control.
- the check valve 52 can be open, allowing or enabling low pressure bleed airflow 66 to flow to the turbine sections 40 a , 40 b .
- the controller module 60 can control the bypass valve 47 to operably control an exit temperature of the combined airflow stream 74 of the turbo-ejector 44 .
- the controller 60 can control the operation of the valve 130 to operably control the energy balance by adjusting the low and high pressure mass flow rations as needed, independent of efficiency considerations.
- the controller 60 can control the operation of the valve 130 as described, but by operably controlling the energy balance or the high pressure/low pressure mass flow ratio as needed, or within a predetermined threshold or threshold range, such as to prevent back flow to the turbine outputs.
- the selectively supplying airflow to the set of compressors can include operating the valve 86 based on a desired compressor output airflow 72 c .
- the controller module 60 can control the valve 86 to be opened or closed based on a sensing or measuring of the compressor output airflows 72 a and 72 b .
- the controller module 60 can control the valve 86 such that the compressor output pressure 72 a , 72 b are matched, even, or similar in temperature, massfow, or a combination thereof.
- the controller module 60 or operation of the valve 86 can take into account for dissimilar or variations in pressure drop resistance in the inlet path to the first compressor section 42 a compared with the resistance in the inlet path to the second compressor section 42 b , and how that can affect the matching of the resulting compressor output pressures 72 a , 72 b , as described herein.
- the controller module 60 can control the valve 86 as a slave to the first controllable valve 46 , to operably control the total compressor output 72 c , dependent upon the controlling of the power balance via the first controllable valve 46 .
- the selectively supplying airflow to the set of compressors can include not supplying air to the second compressor section 42 b .
- the selectively supplying airflow to the set of compressors can include operating the valve 86 , for example, by way of the controller module 60 , based on the occupancy number of passengers on the flight. In this sense, the occupancy number of passengers on the flight can modify the bleed air demand.
- the controllable operation of the valve 86 can thus be set, changed, modified, or enable after the crew or a user enters an occupancy number into an onboard computer system, which can translate, compute, or the like, a bleed air demand, thus enabling a single or dual compressor section 42 a , 42 b operation.
- Selectively supplying airflow to the set of compressors can further include de-coupling the second compressor section 42 b from the common shaft 41 , for instance, prior to flying the aircraft or starting the gas turbine engine.
- the valve 86 can be set to not provide airflow to the second compressor section 42 b , and the decoupler 80 can be activated or enabled to mechanically de-couple the second compressor section 42 b from the common shaft 41 .
- the controller 60 or processor 62 can operate the decoupler 80 so that the second compressor section 42 b is not operably coupled to the common shaft 41 when air is not provided to the second compressor section 42 b , or when no additional flow capacity is needed.
- the second controllable valve 50 could be replaced with a bleed ejector or mixing valve also coupled with the low pressure bleed port 34 .
- the turbo-ejector 44 , the compressor output 54 , or the first turbine output 56 can be configured to prevent backflow from downstream components from entering the turbo air cycle machine 38 .
- the check valve 52 or turbo-ejector proportional assembly can include, or can be replaced by a third controllable valve, and controlled by the controller module 60 as explained herein, to operate or effect a ratio of low pressure bleed airflow 66 and high pressure bleed airflow 68 supplied to the first turbine section 40 a and optionally the second turbine section 40 b .
- the design and placement of the various components such as valves, pumps, or conduits can be rearranged such that a number of different in-line configurations could be realized.
- the embodiments disclosed herein provide a method and aircraft for providing bleed air to an environmental control system.
- the technical effect is that the above described embodiments enable the preconditioning of bleed air received from a gas turbine engine such that the conditioning and combining of the bleed air is selected to meet or satisfy a bleed air demand for the environmental control system.
- the turbo ejector allows for mixing of two different air streams at different pressure while recovering the energy otherwise associated with backpressure of the turbine.
- One advantage that can be realized in the above embodiments is that the above described embodiments have superior bleed air conditioning for the ECS without wasting excess heat, compared with traditional pre-cooler heat exchanger systems.
- Another advantage that can be realized is that by eliminating the waste of excess heat, the system can further reduce bleed extraction from the engine related to the wasted heat. By reducing bleed extraction, the engine operates with improved efficiency, yielding fuel cost savings, and increasing operable flight range for the aircraft.
- the bleed air system can provide variable bleed air conditioning for the ECS.
- the variable bleed air can meet or satisfy a variable demand for bleed air in the ECS due to a variable ECS load, for example, as subsystems are operated or cease to operate.
- Low pressure bleed air pressure and ambient air pressure can be augmented to a desired pressure for the ECS.
- Yet another advantage includes that waste cooling energy can be utilized to further assist cooling temperatures of the air for use in the ECS.
- Yet another advantage includes the capability of operating first and second compressor sections in parallel, which allows compressor stages unloading based at least partially on a bleed air demand, such as a mass flow (e.g. airflow) demand, compared with operating or unloading a higher capacity single compressor in conventional systems.
- a bleed air demand such as a mass flow (e.g. airflow) demand
- Operating a larger compressor or a compressor with a wide range of capacity can include performance characteristics linked to reducing its capacity to more than half during unloading or spooling down.
- the larger compressor may have to spool down below its recommended shaft minimum rotational speed in order to maintain proper balancing of the wheel itself and air bearing support (e.g. to prevent wobbling, or causing stall of the turbo machine itself).
- a larger compressor might be called to operate under less than optimal conditions in order to satisfy a bleed air demand that may entrain failure if below that recommended minimum speed.
- the advantage of running smaller compressors in parallel as described herein is the smaller compressors don't have to unload or spool down to the same low level minimum rotational speeds in order to reduce airflow capacity.
- aspects of the disclosure can include higher performance characteristics under a wider range of bleed air demands.
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Abstract
Description
- This application is a divisional of U.S. patent application Ser. No. 15/244,497, filed Aug. 23, 2016, now allowed, which is incorporated herein by reference in its entirety.
- Contemporary aircraft have bleed air systems that take hot air from the engines of the aircraft for use in other systems on the aircraft including environmental control systems (ECS) such as air-conditioning, pressurization, and de-icing. The ECS can include limits on the pressure or temperature of the bleed air received from the bleed air systems. Currently, aircraft engine bleed systems make use of a pre-cooler heat exchanger to pre-condition the hot air from the engines to sustainable temperatures, as required or utilized by the other aircraft systems. The pre-cooler heat exchangers produce waste heat, which is typically exhausted from the aircraft without utilization.
- In the drawings:
-
FIG. 1 is a perspective view of an aircraft having a bleed air system in accordance with various aspects described herein. -
FIG. 2 is a schematic cross-sectional view of a portion of an exemplary aircraft gas turbine engine that can be utilized in the aircraft ofFIG. 1 . -
FIG. 3 is a schematic view of a gas turbine engine bleed air system that can be utilized in the aircraft ofFIG. 1 in accordance with various aspects described herein. -
FIG. 4 is a schematic view of a two gas turbine engine bleed air system architectures that can be utilized in the aircraft ofFIG. 1 in accordance with various aspects described herein. -
FIG. 5 is a schematic view of a valve that can be utilized in a turbo-ejector as shown inFIGS. 3 and 4 . -
FIG. 6 is an example a flow chart diagram illustrating a method of providing bleed air to the environmental control system in accordance with various aspects described herein. -
FIG. 1 illustrates an embodiment of the disclosure, showing anaircraft 10 that can include ableed air system 20, only a portion of which has been illustrated for clarity purposes. As illustrated, theaircraft 10 can include multiple engines, such asgas turbine engines 12, afuselage 14, acockpit 16 positioned in thefuselage 14, andwing assemblies 18 extending outward from thefuselage 14. The aircraft can also include an environmental control system (ECS) 48. The ECS 48 is schematically illustrated in a portion of thefuselage 14 of theaircraft 10 for illustrative purposes only. The ECS 48 is fluidly coupled with thebleed air system 20 to receive a supply of bleed air from thegas turbine engines 12. - The
bleed air system 20 can be connected to thegas turbine engines 12 such that high temperature, high pressure air, low pressure air, low temperature, or a combination thereof received from thegas turbine engines 12 can be used within theaircraft 10 for environmental control of theaircraft 10. More specifically, an engine can include a set ofbleed ports 24 arranged along thegas turbine engine 12 length or operational stages such that bleed air can be received, captured, or removed from thegas turbine engine 12 as the corresponding set ofbleed ports 24. In this sense, various bleed air characteristics, including but not limited to, bleed air mass flow rate (for example, in pounds per minute), bleed air temperature or bleed air pressure, can be selected based on the desired operation or bleed air demand of thebleed air system 20. Further, it is contemplated that ambient air can be used within theaircraft 10 for environmental control of theaircraft 10. As used herein, the environmental control of theaircraft 10, that is, the ECS 48 of theaircraft 10, can include subsystems for anti-icing or de-icing a portion of the aircraft, for pressurizing the cabin or fuselage, heating or cooling the cabin or fuselage, and the like. The operation of the ECS 48 can be a function of at least one of the number ofaircraft 10 passengers,aircraft 10 flight phase, or operational subsystems of the ECS 48. Examples of theaircraft 10 flight phase can include, but is not limited to ground idle, taxi, takeoff, climb, cruise, descent, hold, and landing. The demand of thebleed air system 20 by the ECS can be dynamic as, for example, subsystems are needed based onaircraft 10 conditions. - While a
commercial aircraft 10 has been illustrated, it is contemplated that embodiments of the invention can be used in any type ofaircraft 10. Further, while twogas turbine engines 12 have been illustrated on thewing assemblies 18, it will be understood that any number ofgas turbine engines 12 including a singlegas turbine engine 12 on thewing assemblies 18, or even a single gas turbine engine mounted in thefuselage 14 can be included. -
FIG. 2 illustrates a cross section of thegas turbine engine 12 of theaircraft 10. Thegas turbine engine 12 can include, in a serial relationship, a fan 22, acompressor section 26, acombustion section 25, aturbine section 27, and anexhaust section 29. Thecompressor section 26 can include, in a serial relationship, a multi-stagelow pressure compressor 30, and a multi-stagehigh pressure compressor 32. - The
gas turbine engine 12 is also shown including a low pressure bleedport 34 arranged to pull, draw, or receive low pressure bleed air from thelow pressure compressor 30 and a high pressure bleedport 36 arranged to pull, draw, or receive high pressure bleed air from thehigh pressure compressor 32. Thebleed ports various sensors 28, which can provide corresponding output signals. By way of non-limiting example, thesensors 28 can include respective temperature sensors, respective flow rate sensors, or respective pressure sensors. While only a single low pressure bleedport 34 is illustrated, thelow pressure compressor 30 can include a set of low pressure bleedports 34 arranged at multiple stages of thecompressor 30 to pull, draw, or receive various bleed air characteristics, including but not limited to, bleed air mass flow rate, bleed air temperature, or bleed air pressure. Similarly, while only a single high pressure bleedport 36 is illustrated, thehigh pressure compressor 32 can include a set of high pressure bleedports 36 to pull, draw, or receive various bleed air characteristics, including but not limited to, bleed air mass flow rate, bleed air temperature, or bleed air pressure. Non-limiting embodiments of the disclosure can further include configurations wherein at least one of the low or high pressure bleedport ports - During
gas turbine engine 12 operation, the rotation of the fan 22 draws in air, such that at least a portion of the air is supplied to thecompressor section 26. The air is pressurized to a low pressure by thelow pressure compressor 30, and then is further pressurized to a high pressure by thehigh pressure compressor 32. At this point in the engine operation, the low pressure bleedport 34 and the high pressure bleedport 36 draw, respectively low pressure air from thelow pressure compressor 30 and high pressure air from thehigh pressure compressor 32 and supply the air to a bleed air system for supplying air to the ECS 48. High pressure air not drawn by the high pressure bleedport 36 is delivered to thecombustion section 25, wherein the high pressure air is mixed with fuel and combusted. The combusted gases are delivered downstream to theturbine section 27, which are rotated by the gases passing through theturbine section 27. The rotation of theturbine section 27, in turn, rotates the fan 22 and thecompressor section 26 upstream of theturbine section 27. Finally, the combusted gases are exhausted from thegas turbine engine 12 through theexhaust section 29. -
FIG. 3 illustrates a schematic view of portions of theaircraft 10 including thegas turbine engine 12, thebleed air system 20, and the ECS 48. As shown, thebleed air system 20 can include a turboair cycle machine 38 fluidly coupled upstream with the set of gas turbine engine (shown only as a single gas turbine engine 12) and fluidly coupled downstream with theECS 48. The turboair cycle machine 38 can include afirst turbine section 40 a, asecond turbine section 40 b, afirst compressor section 42 a, andsecond compressor section 42 b, all of which can be rotatably coupled on acommon shaft 41. In this sense, the turboair cycle machine 38 can include four wheels: the first andsecond turbine sections second compressor sections bleed air system 20 of the turboair cycle machine 38 can include a flow mixer or turbo-ejector 44 located downstream from the turboair cycle machine 38. - The low pressure and high pressure bleed
ports air cycle machine 38 by way of a proportional mixing orcontrollable valve assembly 45. Non-limiting examples of thecontrollable valve assembly 45 can include mixing, proportional mixing, or non-mixing configurations. In another non-limiting example, the proportional mixing assembly can include a proportional mixing-ejector valve assembly. In one aspect, the proportional mixing-ejector valve assembly orcontrollable valve assembly 45 can be arranged to supply the low pressure and high pressure bleed air to the turboair cycle machine 38. Non-limiting examples of the proportional mixing-ejector valve assembly orcontrollable valve assembly 45 can include a turbo-ejector or mixing-ejector assembly, wherein the high pressure bleedport 36 entrains at least a portion of the low pressure bleed air of the low pressure bleedport 34, or “pulls” air from the low pressure bleedport 34, and provides the mixed, combined, or entrained air to the turboair cycle machine 38. - Embodiments of the disclosure can include aspects wherein the supply ratio of the low pressure bleed air and high pressure bleed air can be selected to never go below, or alternatively, to never exceed, a predetermined ratio. For example, the aspects of the supply ratio can include, or can be determined to maintain an energy or power balance between the
turbine sections compressor sections air cycle machine 38. Another non-limiting example of the proportional mixing-ejector valve assembly orcontrollable valve assembly 45 can be included wherein the low pressure bleedport 34 of thegas turbine engine 12 can be fluidly coupled with thefirst compressor section 42 a andsecond compressor section 42 b of the turboair cycle machine 38 by way of a firstcontrollable valve 46 and avalve 86. Additionally, the high pressure bleedport 36 of thegas turbine engine 12 can be directly fluidly coupled with thefirst turbine section 40 a of the turboair cycle machine 38 by way of a secondcontrollable valve 50. Non-limiting examples of the first or secondcontrollable valves valve 86 can include a fully proportional or continuous valve. - The
controllable valve 46 is illustrated as being combined with a source selection option that includes an integratedcheck valve 46 a. In this manner the firstcontrollable valve 46 acts as a source selection valve for supplying an ambient airflow or the low pressure bleedairflow 66. In this sense, the firstcontrollable valve 46 can operate to supply only one or the other of the ambient airflow or the lowpressure bleed airflow 66. Embodiments of the disclosure can be included wherein theintegrated check valve 46 a is selected or configured to provide fluid traversal or selective fluid traversal from the ambient air inlet toward the lowpressure bleed airflow 66. In another example, theintegrated check valve 46 a can be selected or configured such that theintegrated check valve 46 a closes, or self-actuates to a closed position under back pressure, that is when the pressure within the low pressure bleed airflow conduit is higher or greater than the air pressure of the ambient air inlet. In another example, theintegrated check valve 46 a can be configured to selected to self-actuate relative to a predetermined air pressure sufficient to operate the turboair cycle machine 38 In this sense, theintegrated check valve 46 a can prevent low bleed pressure air to backflow into the ambient air inlet. Additionally, the integrated check valve can be configured to provide all proportional supplying capabilities described herein. - The addition of the
valve 86 allows for selective supplying of airflow to thesecond compressor section 42 b. Control of thevalve 86 allows for pressure matching from thefirst compressor section 42 a and thesecond compressor section 42 b. The addition of thesecond compressor section 42 b in parallel with thefirst compressor section 42 a increases flow capacity without necessarily increasing outlet pressures or temperatures.Dual compressor sections second compressor section 42 b in parallel with thefirst compressor section 42 a may decrease installation footprint in the aircraft depending on their arrangements. This is important as such portions of the turboair cycle machine 38 may have limited available space on a pylon of theaircraft 10. In another non-limiting example, utilizing both the first andsecond compressor sections - While a
valve 86 is shown and described, additional control mechanisms can be included in aspects of the disclosure in place of thevalve 86. In one non-limiting example, thevalve 86 can be eliminated in favor of a compressor outlet diffuser that can be included and configured to modulate the exit pressures of therespective compressor sections valve 86 can be eliminated in favor of a set of compressor inlet guide vanes that can be configured to vary the flow intake (and thus, capacity) of one compressor section (e.g. thefirst compressor section 42 a) compared with the other compressor section (e.g. thesecond compressor section 42 b), until the output pressures match, as described herein. The compressor outlet diffuser or the inlet guide vanes can be operably controlled by way of thecontroller module 60. - The
proportional valve assembly 45 can operate in response to, related to, or as a function of the aircraft flight phase or the rotational speed of thegas turbine engine 12. For example, the rotational speed of thegas turbine engine 12 can vary within an operating cycle, during which the proportional mixing-ejector valve assembly orcontrollable valve assembly 45 can be adjusted based on gas turbine engine transient or dynamic conditions. - Embodiments of the disclosure can supply any ratio of low pressure bleed air to high pressure bleed air, such as 100% of first bleed air, and 0% of second bleed air. Similarly, the ratio can be predetermined based on dynamic response to engine conditions and to maintain energy balance, an energy balance bleed air demand, or a power balance between the turbine and compressor sections of the turbo air cycle machine assembly.
- The low pressure bleed air provided by the low
pressure bleed port 34 can be further provided to thefirst turbine section 40 a downstream of the respective firstcontrollable valve 46 and secondcontrollable valve 50, wherein a fluid coupling providing the low pressure bleed air to thefirst turbine section 40 a can include acheck valve 52 biased in the direction from the lowpressure bleed port 34 toward the highpressure bleed port 36 or thefirst turbine section 40 a of the turboair cycle machine 38. In this sense, thecheck valve 52 is configured such that fluid can only flow from the lowpressure bleed port 34 to the highpressure bleed port 36 or thefirst turbine section 40 a of the turboair cycle machine 38. - Embodiments of the disclosure can be included wherein the
check valve 52 is selected or configured to provide fluid traversal from the lowpressure bleed port 34 toward the highpressure bleed port 36 under defined or respective pressures of the flow in the respective the lowpressure bleed port 34 toward the highpressure bleed port 36. For example, thecheck valve 52 can be selected or configured to only provide fluid traversal, as shown, the air pressure of the highpressure bleed port 36 is lower or less than the air pressure of the lowpressure bleed port 34. In another example, thecheck valve 52 can be selected or configured such that thevalve 52 closes, or self-actuates to a closed position under back pressure, that is when the pressure of the highpressure bleed port 36 is higher or greater than the air pressure of the lowpressure bleed port 36. Alternatively, embodiments of the disclosure can include acheck valve 52 or the turbo-ejector or the mixing-ejector proportional assembly that is controllable to provide selective fluid traversal from the lowpressure bleed port 34 toward the highpressure bleed port 36. - The
first compressor section 42 a andsecond compressor section 42 b of the turboair cycle machine 38 can include a compressor output 54. The addition of acheck valve 88 prevents backflow or pressure from thefirst compressor section 42 a to thesecond compressor section 42 b. - A
decoupler 80 can be operably coupled to the portion of thecommon shaft 41 between thefirst compressor section 42 a and thesecond compressor section 42 b. Thedecoupler 80 can be any suitable mechanism configured to uncouple thesecond compressor section 42 b from thecommon shaft 41 or a remainder of thecommon shaft 41. Thedecoupler 80 can include, but is not limited to, a clutch or mechanical fuse disconnect. It will be understood that thedecoupler 80 can be optional and that thesecond compressor section 42 b can alternatively always be coupled to thecommon shaft 41. Thedecoupler 80 is configured to decouple thesecond compressor section 42 b from thefirst compressor section 42 a and allows for reduced capacity as a function of occupancy of theaircraft 10. It is contemplated that thedecoupler 80 can be controlled automatically by a processor, such as thecontroller module 60, or manually before engine start as selected by the crew or by a user, based on the mission requirements or bleed air demand. In one non-limiting example, thedecoupler 80 can operably de-couple thesecond compressor section 42 b from thefirst compressor section 42 a orcommon shaft 41 while thecompressor sections decoupler 80 can only operably re-couple thesecond compressor section 42 b to thefirst compressor section 42 a orcommon shaft 41 when thecompressor sections compressor sections common shaft 41, or the like, if re-coupled was enabled during operations. - The
first turbine section 40 a can include afirst turbine output 56 defining a cooledairflow 70. Thefirst turbine output 56 can be optionally and proportionally supplied to thesecond turbine section 40 b. More specifically, thefirst turbine output 56 is illustrated at being fluidly coupled to thesecond turbine section 40 b. Thefirst turbine output 56 can also be fluidly coupled to abypass conduit 43. As illustrated thebypass conduit 43 can fluidly couple thefluid output 56 of thefirst turbine section 40 a to the downstream turbo-ejector 44 such that thefluid output 56 need not be provided to thesecond turbine section 40 b. Abypass valve 47 is included to selectively control fluid flow through thebypass conduit 43 to the downstream turbo-ejector 44. Thebypass valve 47 can be any suitable valve including, but not limited to, a proportional valve or a continuous valve. Thesecond turbine section 40 b can include asecond turbine output 71 defining an airflow.First turbine output 56 that bypasses thesecond turbine section 40 b has been schematically illustrated with arrows and defines abypass airflow 73. - The compressor output 54, any
second turbine output 71 and anybypass airflow 73 are fluidly combined downstream of the turboair cycle machine 38. The flow mixer is arranged to fluidly combine the compressor output 54, anysecond turbine output 71, and anybypass airflow 73 to a commonmixed flow 74 that is supplied to thebleed air inlet 49 of theECS 48. In this manner, the downstream turbo-ejector 44 fluidly combines fluid outputs from thefirst turbine section 40 a, in the form ofbypass airflow 73, and thesecond turbine section 40 b, in the form of asecond turbine output 71, with fluid output from the compressor section, in the form of compressor output 54, into acommon flow 74 that is supplied to thebleed air inlet 49 of theECS 48. In this sense, thebleed air system 20 preconditions the bleed air before the bleed air is received by thebleed air inlet 49 of theECS 48. - The
second turbine output 71 andbypass airflow 73 are fluidly coupled to define a combinedturbine output airflow 75 or cooled airflow. In the illustrated embodiment of the flow mixer, the turbo-ejector 44 pressurizes theturbine output airflow 75 as it traverses anarrow portion 58, or “throat” of the turbo-ejector 44, and fluidly injects the compressor output 54 into thenarrow portion 58 of the turbo-ejector 44. The injection of the compressor output 54 into the pressurizedturbine output airflow 75 fluidly combines the compressor output 54 with theturbine output airflow 75. Thecommon airflow stream 74 of the turbo-ejector 44 is fluidly coupled downstream with theECS 48 at ableed air inlet 49. Embodiments of the disclosure can be included wherein the compressor output 54, theturbine output airflow 75, or the turbo-ejector 44 (e.g. downstream from the narrow portion 58) can include a set ofsensors 28. - The turbo-
ejector 44, sometimes referred to as an “ejector pump” or an “ejector valve,” works by injecting air from a higher pressure source into a nozzle at the input end of a venturi restriction, into which a lower pressure air source is also fed. Air from the higher pressure source is emitted downstream into the lower pressure flow at high velocity. Friction caused by the adjacency of the airstreams causes the lower pressure air to be accelerated (“entrained”) and drawn through the venturi restriction. As the higher pressure air ejected into the lower pressure airstream expands toward the lower pressure of the low pressure air source, the velocity increases, further accelerating the flow of the combined or mixed airflow. As the lower pressure air flow is accelerated by its entrainment by the higher pressure source, the temperature and pressure of the low pressure source are reduced, resulting in more energy to be extracted or “recovered” from the turbine output. Non-limiting embodiments of the disclosure can be included wherein the high pressure air source is at a higher or greater temperature than the low pressure air source. However, in alternative embodiments of the disclosure, the entrainment and mixing process can occur without the high pressure air source having a higher or greater temperature than the low pressure air source. The above-described embodiments are application to the turbo-ejector 44 illustrated downstream of the turboair cycle machine 38, as well as to the turbo-ejector embodiment of thecontrollable valve assembly 45. - The
aircraft 10 or bleedair system 20 can also include acontroller module 60 having aprocessor 62 andmemory 64. Thecontroller module 60 orprocessor 62 can be operably or communicatively coupled to thebleed air system 20, including itssensors 28, the firstcontrollable valve 46, the secondcontrollable valve 50, thebypass valve 47, and theECS 48. Thecontroller module 60 orprocessor 62 can further be operably or communicatively coupled with thesensors 28 dispersed along the fluid couplings of thebleed air system 20. Thememory 64 can include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic memory, such as discs, DVDs, CD-ROMs, etc., or any suitable combination of these types of memory. Thecontroller module 60 orprocessor 62 can further be configured to run any suitable programs. Non-limiting embodiments of the disclosure can be included wherein, for example, thecontroller module 60 orprocessor 62 can also be connected with other controllers, processors, or systems of theaircraft 10, or can be included as part of or a subcomponent of another controller, processor, or system of theaircraft 10. In one example, thecontroller module 60 can include a full authority digital engine or electronics controller (FADEC), an onboard avionic computer or controller, or a module remoted located by way of a common data link or protocol. - A computer searchable database of information can be stored in the
memory 64 and accessible by thecontroller module 60 orprocessor 62. Thecontroller module 60 orprocessor 62 can run a set of executable instructions to display the database or access the database. Alternatively, thecontroller module 60 orprocessor 62 can be operably coupled to a database of information. For example, such a database can be stored on an alternative computer or controller. It will be understood that the database can be any suitable database, including a single database having multiple sets of data, multiple discrete databases linked together, or even a simple table of data. It is contemplated that the database can incorporate a number of databases or that the database can actually be a number of separate databases. The database can store data that can include, among other things, historical data related to the reference value for the sensor outputs, as well as historicalbleed air system 20 data for theaircraft 10 and related to a fleet of aircraft. The database can also include reference values including historic values or aggregated values. - During
gas turbine engine 12 operation, thebleed air system 20 supplies a lowpressure bleed airflow 66 along the lowpressure bleed port 34 and a highpressure bleed airflow 68 along the highpressure bleed port 36, as previously explained. The highpressure bleed airflow 68 is delivered to thefirst turbine section 40 a and optionally thesecond turbine section 40 b of the turboair cycle machine 38, which in turn interacts with the turbine(s) to drive the rotation of thefirst turbine section 40 a and thesecond turbine section 40 b. The highpressure bleed airflow 68 exits thefirst turbine section 40 a at thefirst turbine output 56 as a first turbine output airflow. Afirst portion 66 a of the lowpressure bleed airflow 66 can be delivered to thefirst compressor section 42 a, asecond portion 66 b of the lowpressure bleed airflow 66 can be delivered to thesecond compressor section 42 b of the turboair cycle machine 38, and a third portion of the lowpressure bleed airflow 66 can be delivered to thefirst turbine section 40 a and optionally thesecond turbine section 40 b of the turboair cycle machine 38, depending on the operation of thecheck valve 52 or upstream turbo-ejector or mixing-ejector proportional assembly, or therespective airflows pressure bleed port 34 and highpressure bleed port 36, as explained herein. For example, embodiments of the disclosure can include operations wherein the airflow delivered to thefirst turbine section 40 a and optionally thesecond turbine section 40 b can include entirely lowpressure bleed airflow 66, no lowpressure bleed airflow 66, or a portion therebetween. The second portion of the lowpressure bleed airflow 66 can also be utilize to drive the rotation of thefirst turbine section 40 a and thesecond turbine section 40 b, such as when thecontrollable valve 50 is set to provide no highpressure bleed airflow 68. - It will be understood that the
controller module 60 is configured to operate thebypass valve 47 to supply an amount of thefirst turbine output 56 to thesecond turbine section 40 b of the turboair cycle machine 38. It is contemplated that thecontroller 60 can operate thebypass valve 47 based on input from any of thesensors 28 including temperature sensors of the combinedairflow stream 74, theturbine output airflow 75, thefirst turbine output 56, any combination thereof, etc. Embodiments of the disclosure can include operations wherein thefirst turbine output 56 can supply less than 100% of the cooled air stream to thesecond turbine section 40 b, or wherein thefirst turbine output 56 can supply 100% of the cooled air stream to thesecond turbine section 40 b. - The
first portion 66 a of the lowpressure bleed airflow 66 can be compressed by the rotation of thefirst compressor section 42 a. Thesecond portion 66 b of the lowpressure bleed airflow 66 can be compressed by thesecond compressor section 42 b, which is rotatably coupled with thefirst turbine section 40 a and thesecond turbine section 40 b. The compressed low pressure bleed air exits thefirst compressor section 42 a andsecond compressor section 42 b at the compressor output 54 as compressor output airflows 72 a and 72 b, which can be combined to formcompressed airflow 72 c. Theturbine output airflow 75 and thecompressor output airflow 72 c are combined in the turbo-ejector 44 to form the combinedairflow stream 74, which is further provided to theECS 48. In this sense, the combinedairflow stream 74 can be expressed as a composition or a ratio of the low pressure and highpressure bleed airflow compressor output airflows - The compression of the
low pressure airflow 66, by thefirst compressor section 42 a andsecond compressor section 42 b, generates a higher pressure and higher temperaturecompressor output airflow 72 c, compared with thelow pressure airflow 66. Additionally, the airflows received by thefirst turbine section 40 a and thesecond turbine section 40 b, that is, thehigh pressure airflow 68 and selectivelow pressure airflow 66 via thecheck valve 52 via a turbo-ejector or mixing-ejector proportional assembly, generates a lower pressure and a lower temperatureturbine output airflow 75, compared with thefirst turbine section 40 a and thesecond turbine section 40b input airflows first compressor section 42 a andsecond compressor section 42 b outputs or emits a hotter andhigher pressure airflow 72 c, while thefirst turbine section 40 a outputs or emits a cooler andlower pressure airflow 70, compared with therelative input airflows second turbine section 40 b outputs or emits an evencooler airflow 71 as compared with theairflow 70. - The
controller module 60 orprocessor 62 can be configured to operably receive a bleed air demand, generated by, for example, theECS 48. The bleed air demand can be provided to thecontroller module 60 orprocessor 62 by way of a bleedair demand signal 76, which can include bleed air demand characteristics included, but not limited to, flow rate, temperature, pressure, or mass flow (e.g. airflow). In response to the bleedair demand signal 76, thecontroller module 60 orprocessor 62 can operably supply proportional amounts of the lowpressure bleed airflow 66 and highpressure bleed airflow 68 to the turboair cycle machine 38. The proportionality of the lowpressure bleed airflow 66, and the high pressure bleed airflows 68 can be controlled by way of the respective first or secondcontrollable valves check valve 52 or mixing-ejector proportional assembly. - The proportional supplying of the low pressure and high
pressure bleed airflows turbine output airflow 75 andcompressor output airflow 72 c, or the turbineair cycle machine 38 operations. Theturbine output airflow 75 andcompressor output airflow 72 c are combined downstream of the turboair cycle machine 38, and the combinedairflow stream 74 is provided to theECS 48. In one non-limiting example, thecompressor output airflow 72 c can drive theturbine output airflow 75 into thenarrow portion 58 and mix under sonic conditions. The mixed flow pressure will recover statically through the combinedairflow stream 74 to output the turbo-ejector 44 at desired conditions. In this sense, the combinedairflow stream 74 is conditioned by way of operation of thebleed air system 20,controllable valves check valve 52, turbo-ejector or mixing-ejector proportional assembly, turboair cycle machine 38, the combining of theturbine output airflow 75 and thecompressor output airflow 72 c, or any combination thereof, to meet or satisfies theECS 48 demand for bleed air. - One of the
controller module 60 orprocessor 62 can include all or a portion of a computer program having an executable instruction set for determining the bleed air demand of theECS 48, proportionally or selectively supplying the low pressure or highpressure bleed airflows controllable valves low pressure airflows pressure bleed airflows pressure bleed airflows pressure bleed airflows pressure bleed airflow 66 without altering the highpressure bleed airflow 68, or vice versa. In another example proportionally or selectively supplying the low pressure or highpressure bleed airflows pressure bleed airflow 66 and the highpressure bleed airflow 68. Also as used herein, “proportionally” supplying the low pressure or highpressure bleed airflows pressure bleed airflow 66 to highpressure bleed airflow 68, based on thetotal bleed airflow pressure bleed airflow pressure bleed airflows - Regardless of whether the
controller module 60 orprocessor 62 controls the operation of thebleed air system 20, the program can include a computer program product that can include machine-readable media for carrying or having machine-executable instructions or data structures stored thereon. Such machine-readable media can be any available media, which can be accessed by a general purpose or special purpose computer or other machine with a processor. Generally, such a computer program can include routines, programs, objects, components, data structures, and the like, that have the technical effect of performing particular tasks or implementing particular abstract data types. Machine-executable instructions, associated data structures, and programs represent examples of program code for executing the exchange of information as disclosed herein. Machine-executable instructions can include, for example, instructions and data, which cause a general-purpose computer, special purpose computer, or special purpose processing machine to perform a certain function or group of functions. - While the bleed air characteristics of the low pressure or high
pressure bleed airflows aircraft 10, varyingaircraft 10 or flight characteristics, such as altitude, speed or idle setting, heading, solar cycle, or geographic aircraft location can produceinconsistent airflows bleed air system 20. Thus, thecontroller module 60 orprocessor 62 can also be configured to operate thebleed air system 20, as explained herein, in response to receiving a set of sensor input values received by thesensors 28 dispersed along the fluid couplings of thebleed air system 20. For example, thecontroller module 60 orprocessor 62 can include predetermined, known, expected, estimated, or calculated values for the set ofairflows bleed air system 20. In response to varyingaircraft 10 or flight characteristics, thecontroller module 60 orprocessor 62 can alter the proportional supplying of the low pressure or highpressure bleed airflows ECS 48. Alternatively, thememory 64 can include a database or lookup table such that a proportional supplying values related to the low pressure or highpressure bleed airflows controller module 60 receiving a set or subset ofsensor 28 readings, measurements, or the like. - While
sensors 28 are described as “sensing,” “measuring,” or “reading” respective temperatures, flow rates, or pressures, thecontroller module 60 orprocessor 62 can be configured to sense, measure, estimate, calculate, determine, or monitor thesensor 28 outputs, such that thecontroller module 60 orprocessor 62 interprets a value representative or indicative of the respective temperature, flow rate, pressure, or combination thereof. Additionally,sensors 28 can be included proximate to, or integral with additional components not previously demonstrated. For example, embodiments of the disclosure can includesensors 28 located to sense the combinedairflow stream 74, or can includesensors 28 located within thenarrow portion 58, or “throat” of the turbo-ejector 44. - In another non-limiting example of responsive operation, the
controller module 60 can operate the secondcontrollable valve 50 based on a bleed air demand of thebleed air system 20. The bleed air demand can include, for example, a desired or demandedoutput airflow stream 74 from the turbo-ejector 44. In this sense, thecontroller module 60 can operate the secondcontrollable valve 50 based on a desired or demandedoutput airflow stream 74 of the turbo-ejector 44. Thecontroller module 60 can further operate, for example, thebypass valve 47 such that thebypass airflow 73 of thefirst turbine output 56, when combined with thesecond turbine output 71, affects a cooling of theturbine output airflow 75, which in turn operably affects or controls the temperature of theoutput airflow stream 74, based on a bleed air demand of thebleed air system 20, such as a desired or demanded temperature of theoutput airflow stream 74. Thus, during operation, if the temperature of theoutput airflow stream 74 is below or less than a threshold, demanded, or desired temperature, as sensed by asensor 28, thebypass valve 47 can be operably opened such that air will flow from thefirst turbine output 56 to theturbine output airflow 75. In this sense, the opening of thebypass valve 47 can operably raise the temperature of theoutput airflow stream 74. During operation, if the temperature of theoutput airflow stream 74 is above or greater than the threshold, demanded or desired temperature of theoutput airflow stream 74, as sensed by asensor 28, thebypass valve 47 can be operably closed such that nobypass airflow 73 is provided to theturbine output airflow 75, and ultimately, theoutput airflow stream 74. In this sense, the closing of thebypass valve 47 can operably lower the temperature of theoutput airflow stream 74. - In another non-limiting example of responsive operation, the
controller module 60 can operate the secondcontrollable valve 50 based on a bleed air demand including a desired or demanded pressure of theoutput airflow stream 74. If the pressure of theoutput airflow stream 74, as sensed by asensor 28, is below or less than a threshold, demanded, or desired pressure, the secondcontrollable valve 50 can operably open to provide or allow a portion or additional highpressure bleed airflow 68 to the turboair cycle machine 38. As the secondcontrollable valve 50 provides or allows highpressure bleed airflow 68 to the turboair cycle machine 38, theturbine sections 40 a 40 b will rotate faster, generating more rotational power, which in turn, affects the total amount of power for thecompressor sections controllable valve 50 can be operated to modify or adjust the pressure of theoutput airflow stream 74 based on a desired or demanded pressure. - In another non-limiting responsive operation, the first
controllable valve 46 can be controllably operated by thecontroller module 60, and based on thecompressor output airflow 72 c, as sensed by thesensor 28, maintain a power balance between theturbine sections compressor sections controller module 60 can be configured to operate the first and secondcontrollable valves - The aforementioned configuration and operation of the
valves - Embodiments of the disclosure can be included wherein the
controller module 60 orprocessor 62 can be configured to operate thebleed air system 20 to account forsensor 28 measurements in the set or a subset of theairflows - In another embodiment of the disclosure, the
bleed air system 20 can operate without feedback inputs, that is, without thecontroller module 60 orprocessor 62 receiving sensed information from thesensors 28. In this alternative configuration, thecontroller module 60 orprocessor 62 can be configured to operate the first or secondcontrollable valves aircraft 10, given the dynamic responses as observed during theaircraft 10 flight phases. - The above described disclosure with the
second stage turbine 40 b allows the turboair cycle machine 38 to have increased cooling capacity, allows for higher bleed stage extraction from thegas turbine engine 12, and allows for increased turbine power generation as compared to a turbo air cycle machine with only one turbine section. The inclusion of the second stage turbine bypass allows second stage unloading at lower high pressure bleed port extraction stages, reduces unnecessary second turbine stage excess power, and allows second stage turbine exit temperature control. -
FIG. 4 is a schematic view of a two turbine engine bleed air system architecture that can be utilized in theaircraft 10. The bleed air system illustrated inFIG. 3 has been illustrated as being incorporated into both sides of theaircraft 10. Like parts have been identified with like numerals and the above description of such parts applies. It will be understood that such architecture is by way of non-limiting example only. -
FIG. 4 illustrates that the combinedairflow stream 74 from left and right turbo-ejectors 44 can be fluidly coupled to theECS 48. TheECS 48 is illustrated as including both a leftair conditioning pack 100 and a rightair conditioning pack 102. The combinedairflow stream 74 from the turbo-ejectors 44 can be fluidly coupled to such air conditioning packs 100 and 102 through any suitable conduits and valving illustrated schematically. The quantity of combinedairflow stream 74 to the air conditioning packs 100 and 102 is regulated by theflow control valve 112. Oneflow control valve 112 is installed for each of the air conditioning packs 100 and 102. - An
isolation valve 110 is also illustrated as being included. Theisolation valve 110 is normally closed and prevents air from the left sidebleed air system 20 from reaching the rightair conditioning pack 102 and vice versa. Theisolation valve 110 can be opened in the event of loss of one of thebleed air systems 20. The output from the turbo-ejectors 44 can also be supplied through theflow control valve 112 toanti-icing systems 116 viavalves 114. - The air conditioning packs 100 and 102 can be fluidly coupled to a mixing
manifold 104, which can ultimately provide airflow to thecabin 106 and theflight deck 108. More specifically, exhaust flows from the air conditioning packs 100 and 102 are fluidly coupled to the mixingmanifold 104 where they are typically mixed with filtered air. Airflow from the mixingmanifold 104 is directed to distribution nozzles to supply thecabin 106 and theflight deck 108. Checkvalves 118 can be included between the air conditioning packs 100 and 102 and the mixingmanifold 104. -
FIG. 5 illustrates in more detail that avalve 130 can be included in the flow mixer or turbo-ejector 44 located downstream from the turboair cycle machine 38. By way of non-limiting example, thevalve 130 can include a controllable pintle injector utilized to control the injection of the compressor output 54 into thethroat portion 58 of the turbo-ejector 44. Thevalve 130 can include aslidable needle 132 linearly actuated in either directions as indicated byarrow 134. Theslidable needle 132 or pintle can be proportionally & linearly actuated to increase or decrease the nozzle exit flow area discharge into thethroat 58 which can in turn operably affect the ratio of entrainment oflower pressure air 75 versus injectedhigher pressure air 72 c and the overall turbo ejector efficiency as a pumping mechanism. The varying of lowerpressure mass airflow 75 versus higher pressuremass airflow 72 c ratio increases or decreases the range of operability of the turbo ejector which affects its efficiency. In this sense, efficiency is a function of pressure, temperature, and mass flow ratios. Thus, any variation of pressure, temperature, and mass flow ratios operably affects the efficiency output rating. Theneedle 132 may be controllably operated, for example, via thecontroller module 60 to maintain a pre-determined mass flow ratio, to maintain an efficiency rating, or to operate the turbo-ejector 44 relative to a predetermined threshold or threshold range. - Such a valve allows control of turbo ejector efficiency and allows control of the low pressures and high pressure mass flow ratios.
-
FIG. 6 illustrates a flow chart demonstrating anon-limiting example method 200 of providing bleed air to theECS 48 of an aircraft using at least onegas turbine engine 12. Themethod 200 begins at 210 by determining a bleed air demand for theECS 48. Determining the bleed air demand can include determining at least one of an air pressure, an air temperature, or a flow rate demand for theECS 48, or a combination thereof. The bleed air demand can be a function of at least one of the number of aircraft passengers, aircraft flight phase, or operational subsystems of theECS 48. The bleed air demand can be determined by theECS 48, thecontroller module 60, or theprocessor 62 based on the bleedair demand signal 76. - Next at 220, the
controller module 60 or theprocessor 62 operably controls thecontrollable valve assembly 45 to proportionally supply the low pressure and high pressure bleed air such that turboair cycle machine 38 emits a cooled air stream from thefirst turbine section 40 a in the form ofbypass airflow 73 or thesecond turbine section 40 b and a compressed air stream from thecompressor sections first turbine section 40 a. Embodiments of the disclosure can include, but are not limited to, supplying up to 100% of the combinedairflow stream 74 of one of the low pressure or high pressure bleed airflow and 0% of the corresponding other of the low pressure or high pressure bleed airflow. Another example embodiment of the disclosure can include, but is not limited to, proportionally supplying the low pressure and high pressure bleed airflows wherein the proportionally supplying is related to, or is a function of the aircraft flight phase or rotational speed of thegas turbine engine 12. The proportionally supplying of the bleed air can include continuously proportionally supplying the bleed air, that is, repeatedly altering the proportional supplying of the low pressure and high pressure bleed airflows over a period of time, or indefinitely during the flight of the aircraft. - At 230, the
bypass valve 47 can be controlled by thecontroller module 60 or theprocessor 62 such that output from thefirst turbine section 40 a is directed to thesecond turbine section 40 b to create a further cooled air stream orsecond turbine output 71 or through thebypass conduit 43 to create abypass airflow 73. As used herein “further cooled” air stream describes that the air stream of thesecond turbine output 71 has a lower temperature than the output of thefirst turbine section 40 a that is directed to thesecond turbine section 40 b. Embodiments of the disclosure can include, but are not limited to thebypass valve 47 being controlled to supply any amount from 0% to 100% of thefirst turbine output 56 to thesecond turbine section 40 b and the remainder to thebypass conduit 43. Thecontroller module 60 or theprocessor 62 can control thebypass valve 47 in order to control the exit temperature of the combinedairflow stream 74. - At 240, the
valve 86 can be controlled by thecontroller module 60 or theprocessor 62 such thatambient air 51 or lowpressure bleed air 66 can be selectively supplied to thesecond compressor section 42 b in addition to thefirst compressor section 42 a. It will be understood that thesecond compressor section 42 b is supplied in parallel with thefirst compressor section 42 a. It is contemplated that thecontroller module 60 or theprocessor 62 can determine flow rates to be supplied to thefirst compressor section 42 a and thesecond compressor section 42 b based on the determined flow rate demand from theECS 48 and control thevalve 86 based thereon such that the supplying is controlled such that the conditioned air stream meets or satisfies the determined bleed air demand. - It will be understood that the turbo
air cycle machine 38 emits a cooled air stream from thefirst turbine section 40 a in the form ofbypass airflow 73 or thesecond turbine section 40 b in the form of a further cooledairflow 71 and acompressed air stream 72 a from thefirst compressor section 42 a and optionally acompressed air stream 72 b from thesecond compressor section 42 b. - At 250, the
method 200 continues by combining the cooled air stream, in the form of thebypass airflow 73, the further cooled airflow stream in the form of thesecond turbine output 71 and the compressed air stream(s) 72 a, 72 b, 72 c to form a conditioned or combinedairflow stream 74. It will be understood that thecompressed air stream 72 a from thefirst compressor section 42 a can be combined with thecompressed air stream 72 b from thesecond compressor section 42 b to form a combinedcompressed airflow stream 72 c. The combinedcompressed air stream 72 c can then be combined with at least one of thebypass airflow 73 or thesecond turbine output 71 to form theconditioned air stream 74. Alternatively, if no airflow is supplied to thesecond compressor section 42 b, then thecompressed airflow stream 72 a can be combined with at least one of thebypass airflow 73 or thesecond turbine output 71 to form theconditioned air stream 74. - The proportional supplying the ambient air or low pressure and the high pressure bleed air at 220, the selectively supplying at 230 and selectively supplying the cooled air to the
second turbine section 40 b at 240 is controlled by thecontroller module 60 orprocessor 62 such that the combinedairflow stream 74 meets or satisfies the bleed air demand for theECS 48 as determined at 210. Aspects of the method can also be included wherein the combinedairflow stream 74 can be altered, modified, or the like, by way of operating the controllable pintle injector, thevalve 130, or theslidable needle 132. - The sequence depicted is for illustrative purposes only and is not meant to limit the
method 200 in any way as it is understood that the portions of the method can proceed in a different logical order, additional or intervening portions can be included, or described portions of the method can be divided into multiple portions, or described portions of the method can be omitted without detracting from the described method. - For example, it is contemplated that the method can include receiving an output signal from a
temperature sensor 28 related to a temperature of the conditioned air stream or combinedairflow stream 74. As determining the bleed air demand at 310 can include determining an air temperature demand for theECS 48 thecontroller 60 orprocessor 62 can calculate or otherwise determine an amount of cooled air stream to be supplied to thesecond turbine section 40 b based on the determined air temperature demand and the output signal from thetemperature sensor 28. It is contemplated that this can include continuously determining the amount of cooled air stream to be supplied to thesecond turbine section 40 b. - The method can include proportionally supplying at least one of a first compressor section or a second compressor section based on desired flow capacity. The method can also include proportionally supplying low pressure bleed air and high pressure bleed air from a compressor of the gas turbine engine to a turbo air cycle machine to precondition the bleed air according to operational demands of the ECS wherein the preconditioning comprises selectively providing a fluid output emitted from a
first turbine section 40 a of the turboair cycle machine 38 to asecond turbine section 40 b of the turboair cycle machine 38 for further cooling. As described above this can be based on temperature demands of the ECS. - In one non-limiting example, the
controller module 60 can control thecontrollable valve 50 to be opened or closed as a master control to operably control an exit pressure of the combinedairflow stream 74 of the turbo-ejector 44. In a non-limiting example, thecontroller module 60 can also control the firstcontrollable valve 46 as a slave to the master control, to operably control the energy balance between theturbine sections compressor sections controller module 60 can control thecontrollable valve 46 to control a total compressor power balance in the turboair cycle machine 38 and such can be a slave control to that of thecontrollable valve 50. Thecontroller module 60 can control the source selected by thecontrollable valve 46 and such a source selection can be set based on the mission schedule of theaircraft 10. Thecontroller module 60 can control thecontrollable valve 86 to match outlet pressures from thefirst compressor section 42 a andsecond compressor section 42 b. In a non-limiting example, thecheck valve 52 can be closed or self-closed by default. - In one non-limiting example, the
controller module 60 can also control thebypass valve 47, and therefore an exit temperature of the combinedairflow stream 74 of the turbo-ejector 44 simultaneously, but independently with thecontrollable valve 46. For instance, in some cases, lowering or reducing the exit pressure of the combinedairflow stream 74 by way of the secondcontrollable valve 50 operation will also lower or reduce the exit temperature of the combinedairflow stream 74. In this sense, the operation of the secondcontrollable valve 50 can be included as an override consideration to reduce or lower at least one of the temperature or pressure of the combinedairflow stream 74 if operation of thebypass valve 47 is inadequate, insufficient, or otherwise unable to operably control the temperature or pressure of the combinedairflow stream 74, as described herein. For instance, if thebypass valve 47 were to fail or be rendered inoperable, or if thebypass valve 47 is fully opened or closed despite the inability to alter the combinedairflow stream 74 as desired, the system logic can be configured to operate the secondcontrollable valve 50 to alter or adjust the pressure received by theturbine sections airflow stream 74. - In another non-limiting example, the
controller 60 can control the operation of thevalve 130 to operably control the low pressure and high pressure mass flow rates, target efficiency, or the like, as described herein, based on desired efficiency of the turbo-ejector 44. - In another non-limiting example the
controller module 60 can operate in an alternate system logic, including but not limited to an emergency operation, for example, such as when the high pressure bleed source is disabled, removed, or shut down. In such an operation thecontrollable valve 50 is closed and thecontroller module 60 can control thecontrollable valve 46 to control an exit pressure of the combinedairflow stream 74 of the turbo-ejector 44 as a master control. In this scenario, thecheck valve 52 can be open, allowing or enabling lowpressure bleed airflow 66 to flow to theturbine sections controller module 60 can control thebypass valve 47 to operably control an exit temperature of the combinedairflow stream 74 of the turbo-ejector 44. With the inclusion of thevalve 130, thecontroller 60 can control the operation of thevalve 130 to operably control the energy balance by adjusting the low and high pressure mass flow rations as needed, independent of efficiency considerations. In another example, thecontroller 60 can control the operation of thevalve 130 as described, but by operably controlling the energy balance or the high pressure/low pressure mass flow ratio as needed, or within a predetermined threshold or threshold range, such as to prevent back flow to the turbine outputs. - In another non-limiting example of the method, the selectively supplying airflow to the set of compressors can include operating the
valve 86 based on a desiredcompressor output airflow 72 c. For example, thecontroller module 60 can control thevalve 86 to be opened or closed based on a sensing or measuring of the compressor output airflows 72 a and 72 b. For instance, thecontroller module 60 can control thevalve 86 such that thecompressor output pressure controller module 60 or operation of thevalve 86 can take into account for dissimilar or variations in pressure drop resistance in the inlet path to thefirst compressor section 42 a compared with the resistance in the inlet path to thesecond compressor section 42 b, and how that can affect the matching of the resultingcompressor output pressures controller module 60 can control thevalve 86 as a slave to the firstcontrollable valve 46, to operably control thetotal compressor output 72 c, dependent upon the controlling of the power balance via the firstcontrollable valve 46. - In yet another non-limiting example, the selectively supplying airflow to the set of compressors can include not supplying air to the
second compressor section 42 b. In this instance, the selectively supplying airflow to the set of compressors can include operating thevalve 86, for example, by way of thecontroller module 60, based on the occupancy number of passengers on the flight. In this sense, the occupancy number of passengers on the flight can modify the bleed air demand. The controllable operation of thevalve 86 can thus be set, changed, modified, or enable after the crew or a user enters an occupancy number into an onboard computer system, which can translate, compute, or the like, a bleed air demand, thus enabling a single ordual compressor section - Selectively supplying airflow to the set of compressors can further include de-coupling the
second compressor section 42 b from thecommon shaft 41, for instance, prior to flying the aircraft or starting the gas turbine engine. Should the bleed air demand result in asingle compressor section 42 a operation, thevalve 86 can be set to not provide airflow to thesecond compressor section 42 b, and thedecoupler 80 can be activated or enabled to mechanically de-couple thesecond compressor section 42 b from thecommon shaft 41. More specifically, thecontroller 60 orprocessor 62 can operate thedecoupler 80 so that thesecond compressor section 42 b is not operably coupled to thecommon shaft 41 when air is not provided to thesecond compressor section 42 b, or when no additional flow capacity is needed. - Many other possible embodiments and configurations in addition to that shown in the above figures are contemplated by the present disclosure. For example, embodiments of the disclosure can be included wherein the second
controllable valve 50 could be replaced with a bleed ejector or mixing valve also coupled with the lowpressure bleed port 34. In another non-limiting example, the turbo-ejector 44, the compressor output 54, or thefirst turbine output 56 can be configured to prevent backflow from downstream components from entering the turboair cycle machine 38. - In yet another non-limiting example embodiment of the disclosure, the
check valve 52 or turbo-ejector proportional assembly can include, or can be replaced by a third controllable valve, and controlled by thecontroller module 60 as explained herein, to operate or effect a ratio of lowpressure bleed airflow 66 and highpressure bleed airflow 68 supplied to thefirst turbine section 40 a and optionally thesecond turbine section 40 b. Additionally, the design and placement of the various components such as valves, pumps, or conduits can be rearranged such that a number of different in-line configurations could be realized. - The embodiments disclosed herein provide a method and aircraft for providing bleed air to an environmental control system. The technical effect is that the above described embodiments enable the preconditioning of bleed air received from a gas turbine engine such that the conditioning and combining of the bleed air is selected to meet or satisfy a bleed air demand for the environmental control system. Further, the turbo ejector allows for mixing of two different air streams at different pressure while recovering the energy otherwise associated with backpressure of the turbine.
- One advantage that can be realized in the above embodiments is that the above described embodiments have superior bleed air conditioning for the ECS without wasting excess heat, compared with traditional pre-cooler heat exchanger systems. Another advantage that can be realized is that by eliminating the waste of excess heat, the system can further reduce bleed extraction from the engine related to the wasted heat. By reducing bleed extraction, the engine operates with improved efficiency, yielding fuel cost savings, and increasing operable flight range for the aircraft.
- Yet another advantage that can be realized by the above embodiments is that the bleed air system can provide variable bleed air conditioning for the ECS. The variable bleed air can meet or satisfy a variable demand for bleed air in the ECS due to a variable ECS load, for example, as subsystems are operated or cease to operate. This includes the advantage of the ability to transform low stage bleed air to air that is suitable for the ECS. Low pressure bleed air pressure and ambient air pressure can be augmented to a desired pressure for the ECS.
- Yet another advantage includes that waste cooling energy can be utilized to further assist cooling temperatures of the air for use in the ECS.
- Yet another advantage includes the capability of operating first and second compressor sections in parallel, which allows compressor stages unloading based at least partially on a bleed air demand, such as a mass flow (e.g. airflow) demand, compared with operating or unloading a higher capacity single compressor in conventional systems. Operating a larger compressor or a compressor with a wide range of capacity can include performance characteristics linked to reducing its capacity to more than half during unloading or spooling down. In some cases, the larger compressor may have to spool down below its recommended shaft minimum rotational speed in order to maintain proper balancing of the wheel itself and air bearing support (e.g. to prevent wobbling, or causing stall of the turbo machine itself). In other words, a larger compressor might be called to operate under less than optimal conditions in order to satisfy a bleed air demand that may entrain failure if below that recommended minimum speed. The advantage of running smaller compressors in parallel as described herein is the smaller compressors don't have to unload or spool down to the same low level minimum rotational speeds in order to reduce airflow capacity. Thus, aspects of the disclosure can include higher performance characteristics under a wider range of bleed air demands.
- To the extent not already described, the different features and structures of the various embodiments can be used in combination with each other as desired. That one feature cannot be illustrated in all of the embodiments is not meant to be construed that it cannot be, but is done for brevity of description. Thus, the various features of the different embodiments can be mixed and matched as desired to form new embodiments, whether or not the new embodiments are expressly described. Moreover, while “a set of” various elements have been described, it will be understood that “a set” can include any number of the respective elements, including only one element. Combinations or permutations of features described herein are covered by this disclosure.
- This written description uses examples to disclose embodiments of the invention, including the best mode, and also to enable any person skilled in the art to practice embodiments of the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and can include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Claims (20)
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US17/835,524 US20220297841A1 (en) | 2016-08-23 | 2022-06-08 | Aircraft and method for pre-cooling an environmental control system |
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US17/835,524 US20220297841A1 (en) | 2016-08-23 | 2022-06-08 | Aircraft and method for pre-cooling an environmental control system |
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CA3033995A1 (en) | 2018-03-01 |
JP2019528213A (en) | 2019-10-10 |
CN109863085B (en) | 2022-07-29 |
EP3504124A1 (en) | 2019-07-03 |
WO2018039289A1 (en) | 2018-03-01 |
CN109863085A (en) | 2019-06-07 |
EP3504124B1 (en) | 2023-10-11 |
US20180057172A1 (en) | 2018-03-01 |
US11377216B2 (en) | 2022-07-05 |
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