US20120114463A1 - Motor driven cabin air compressor with variable diffuser - Google Patents
Motor driven cabin air compressor with variable diffuser Download PDFInfo
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- US20120114463A1 US20120114463A1 US12/939,740 US93974010A US2012114463A1 US 20120114463 A1 US20120114463 A1 US 20120114463A1 US 93974010 A US93974010 A US 93974010A US 2012114463 A1 US2012114463 A1 US 2012114463A1
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- air
- motor
- cycle machine
- compressor section
- machine according
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
- F04D25/0606—Units comprising pumps and their driving means the pump being electrically driven the electric motor being specially adapted for integration in the pump
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
Definitions
- the subject matter disclosed herein relates to a motor driven cabin air compressor with a variable diffuser.
- Aircraft environmental control systems incorporate turbomachines, commonly referred to as air cycle machines (ACMs), to help facilitate cooling and dehumidifying air for supply to a cabin of an aircraft.
- Air cycle machines can include two or more wheels having at least one compressor and at least one turbine disposed axially along the same shaft.
- the air to be conditioned in the air cycle machine is generally either compressed air bled from one or more of the compressor stages of the gas turbine engine or air diverted from another location on the aircraft. With either system, the air is passed through the compressor(s) of the air cycle machine where it is further compressed and then passed through a heat exchanger to cool the compressed air sufficiently to condense moisture therefrom.
- the dehumidified air continues through the environmental control system back to the turbine(s) of the air cycle machine.
- the air is expanded to both extract energy from the compressed air so as to drive the shaft and the compressor(s) coupled thereto and cool the air for use in the cabin as conditioned cooling air.
- an air cycle machine includes a compressor section having a variable area diffuser, a turbine section having an inlet nozzle with a variable size, a motor to drive the compressor and a common rotating shaft on which the compressor section, the turbine section and the motor are mounted, the turbine section driving rotation of the shaft to drive the compressor section with the motor.
- an air cycle machine includes a compressor section having a variable area diffuser to compress inlet air, a turbine section having an inlet nozzle with a variable size to receive the compressed air from the compressor section and to expand the air for use in an aircraft cabin, a motor to drive the compressor and a common rotating shaft on which the compressor section, the turbine section and the motor are operably mounted, the turbine section driving rotation of the shaft to provide additional drive power to the compressor section along with that of the motor.
- FIG. 1 is a schematic view of an air cycle machine for an environmental control system of an aircraft
- FIG. 2A is an enlarged view of a turbine inlet nozzle of the air cycle machine with a poppet member in a first position
- FIG. 2B is an enlarged view of the turbine inlet nozzle of the air cycle machine with the poppet member in a second position;
- FIG. 3 is a partially broken view of a variable area diffuser in the direction of arrows 2 - 2 of FIG. 4 ;
- FIG. 4 is an enlarged cross-sectional view of a variable area diffuser
- FIG. 5 is a schematic illustration of the air cycle machine.
- FIG. 1 shows a schematic view of an environmental control system (ECS) 10 .
- the environmental control system 10 includes an air cycle machine 12 that receives air 14 that is conditioned by various devices symbolically indicated as 16 A, 16 B, and 16 C to produce air flow at a desired temperature and pressure for aircraft cabin C.
- the air cycle machine 12 includes a compressor section 18 , a shaft 20 , and a turbine section 22 .
- the compressor section 18 has a compressor inlet 24 , a compressor wheel 26 and a compressor outlet 28 .
- the turbine section 22 includes a turbine inlet 30 , turbine inlet nozzle 32 , turbine wheel 34 and turbine outlet 36 .
- System air 14 is bled from one or more of the compressor stages of the gas turbine engines of the aircraft or directed from an air source at another location on the aircraft.
- One or more devices 16 A can condition (e.g., preheat, acoustically treat) the air 14 prior to its entry into the air cycle machine 12 .
- the air 14 enters the air cycle machine 12 at the compressor section 18 through the compressor inlet 24 .
- the air 14 is compressed to a higher pressure by the compressor wheel 26 , which is mounted on the shaft 20 for rotation about axis A.
- the compressed air 14 is output to the remainder of the environmental control system 10 via the compressor outlet 28 .
- Air 14 output from the compressor section 18 is conditioned by various devices 16 B to change the characteristics of the air 14 that enters the turbine section 22 via the turbine inlet 30 .
- These devices 16 B can include heat exchangers, condensers, and/or water extractors/collectors that condition the air 14 to a desired pressure and temperature.
- the turbine inlet nozzle 32 receives air 14 entering the air cycle machine 12 through the inlet 30 and is disposed adjacent the turbine wheel 34 to direct the flow of air 14 thereto.
- the air cycle machine 12 is configured with a valve to vary the size of turbine inlet nozzle 32 as desired to better optimize the efficiency of the environmental control system 10 .
- the selectively variable turbine inlet nozzle 32 disclosed herein allows the power consumption of the environmental control system 10 to be reduced, for example, by operating only a single air conditioning pack to condition the cabin rather than operating two air conditioning packs in some instances.
- the turbine wheel 34 is mounted on the shaft 20 to drive rotation of the shaft 20 and compressor wheel 26 about axis A. After passing through the turbine inlet nozzle 32 the air 14 is expanded to both extract energy from the air 14 so as to drive the shaft 20 and the compressor wheel 26 (in combination with a motor 38 mounted along the shaft 20 in some embodiments) and to cool the air 14 to prepare it for the cabin. After expansion, the air 14 passes through the turbine outlet 36 out of the air cycle machine 12 .
- the air 14 can pass through one or more devices 16 C (e.g., heat exchangers, compact mixers, and/or acoustic treatment devices) before reaching the cabin C at the desired temperature and pressure.
- FIG. 2A is an enlarged view of the turbine section 22 with a poppet member 40 disposed in a first position extending into the turbine inlet nozzle 32 .
- the turbine section 22 includes a shroud 42 , a first cavity 44 , a valve body 46 , and a second cavity 48 .
- the shroud 42 has a passage 50 .
- the poppet member 40 includes a main body 52 and seals 41 A and 41 B.
- An arcuate plate 54 is fixed within the turbine inlet nozzle 32 .
- the poppet member 40 is slidably mounted on the stator shroud 42 and is configured to seal the first cavity 44 from the turbine inlet nozzle 32 .
- seals 41 A and 41 B are disposed between the poppet member 40 and the shroud 42 to allow for pressurization of the first cavity 44 .
- the first cavity 44 serves as an annular plenum that is defined by portions of the shroud 42 , the poppet member 40 , the valve body 46 , and other portions of the casing of the air cycle machine 12 .
- the valve body 46 is mounted in fluid communication with the first cavity 44 .
- the valve body 46 can be any valve commonly known in the art for selectively communicating air from two ports (two pressure sources) to a third port.
- the valve body 46 can be controlled to move a member between a first position that blocks a first of the three ports and allows the second and third ports to be in fluid communication, and a second position that blocks the second port and allows the first and third ports to be in fluid communication.
- the valve body 46 is controlled to vary the pressure in the first cavity 44 between a first pressure P 1 , equal to or about equal to the pressure P t within the turbine inlet 30 (illustrated in FIG. 2A ), and a second lower pressure P 2 , equal to or about equal to an ambient pressure P a external to the environmental control system 10 and air cycle machine 12 (illustrated in FIG. 2B ).
- the valve body 46 is selectively controlled to allow for fluid communication between the first cavity 44 and either the turbine inlet 30 or the ambient air source external to the air cycle machine 12 .
- the first cavity 44 In the first position shown in FIG. 2A , the first cavity 44 is in fluid communication with the turbine inlet 30 .
- the higher first pressure P 1 that results from this arrangement forces the poppet member 40 outward expanding the volume of the first cavity 44 .
- the poppet member 40 extends from the first cavity 44 into the turbine inlet nozzle 32 to reduce the size (volume and/or cross-sectional area) of the inlet turbine nozzle 32 that receives air 14 from the turbine inlet 30 .
- the poppet member 40 restricts the flow of air 14 to the turbine wheel 34 .
- the reduced air flow to the turbine wheel 34 maybe desirable in some instances, for example, if it is necessary to operate both air conditioning packs to maintain the cabin at a desired pressure and temperature.
- the second cavity 48 is defined by the shroud 42 and the poppet member 40 and is positioned radially outward of the turbine wheel 34 with respect to axis A.
- the poppet member 40 separates the first cavity 44 from the second cavity 48 .
- the passage 50 through shroud 42 allows the second cavity 48 to be in fluid communication with the turbine inlet nozzle 32 immediately adjacent to the turbine wheel 34 . This arrangement allows the second cavity 48 to be maintained at or about the static pressure experienced within the turbine inlet nozzle 32 immediately adjacent to the turbine wheel 34 .
- This static pressure is lower than the pressure at the turbine inlet 30 (and selectively the pressure of the first cavity 44 ) but greater than the ambient pressure external to the air cycle machine 12 (and selectively the pressure of the first cavity 44 ), which allows for actuation of the poppet valve 40 .
- the poppet valve 40 includes a main body 52 that is mounted on the shroud 42 and configured to seal and separate the first cavity 44 from the second cavity 48 .
- the main body 52 is actuated as discussed to slide relative to shroud 42 .
- the main body 52 In the first position shown in FIG. 2A , the main body 52 extends from the first cavity 44 and shroud 42 into the turbine inlet nozzle 32 .
- the arcuate plate 54 is fixed to the turbine inlet nozzle 32 and divides the turbine inlet nozzle into two sections. The plate 54 is aligned within the turbine inlet nozzle 32 so as to minimally interfere with the direction of airflow toward the turbine wheel 34 .
- the plate 54 is configured with a small cross-sectional area interfacing the airflow and has a larger surface that extends generally parallel to one of the walls of the turbine inlet nozzle 32 .
- the plate 54 extends generally radially to immediately adjacent the turbine wheel 34 , thereby, dividing the turbine inlet nozzle 32 into a primary section (through which air 14 flows when the poppet member 40 is in the first position illustrated in FIG. 2A ) and a secondary section (through which air 14 generally does not pass when the poppet member 40 is in the first position).
- FIG. 2B is an enlarged view of the turbine section 22 with the poppet member 40 disposed in a second position.
- the first cavity 44 is in fluid communication with the ambient air source external to the air cycle machine 12 .
- the pressure within the second cavity 48 exceeds the second pressure P 2 within the first cavity 44 and the poppet member 40 moves decreasing the volume of the first cavity 44 and increasing the volume of the second cavity 48 .
- the movement of the main body 52 of the poppet member 40 within the first cavity 44 retracts main body 52 from at least a portion of the turbine inlet nozzle 32 , allowing airflow through the secondary section of the turbine inlet nozzle 32 , thereby increasing the size (volume and/or cross sectional area) of the turbine inlet nozzle 32 through which air 14 flows to the turbine wheel 34 .
- the entire airflow passes through the turbine inlet nozzle 32 unrestricted by the poppet member 40 to the turbine wheel 34 .
- the efficiency of the environmental control system 10 can be improved.
- selectively moving the poppet member 40 to vary the size of the turbine inlet nozzle 32 when desired allows the power consumption of the environmental control system 10 to be reduced, for example, by operating only a single air conditioning pack to condition the cabin rather than operating both air conditioning packs.
- the compressor section 18 may include a variable area diffuser 322 with an actuator 323 (see FIG. 1 ) to vary the inlet throat 352 (see FIG. 3 ) to vary a flow rate through the ECS 10 .
- the variable area diffuser 322 includes a backing plate 328 that is isolated from deflection, D. In conventional devices, the backing plate 328 would be secured directly to the housing 316 contributing to the diffuser vanes binding. Instead, the inventive diffuser 322 employs a mounting plate 330 that supports the backing plate 328 . The inner and outer periphery of the backing plate 328 is supported by the mounting plate 330 , but is also permitted to move axially independently of the mounting plate 330 .
- a shroud 336 is supported by the housing 316 and may deflect axially under load. Multiple vanes 338 are retained between the backing plate 328 and shroud 336 and, typically, a few thousandths of an inch of clearance is provided between the vane 338 and the backing plate 328 and shroud 336 . In the example system shown, there are 323 vanes that are modulated between full open and 40% of full open.
- the vanes 338 include an inlet end 348 and an outlet end 350 .
- the inlet end 348 provides an adjustable throat 352 , shown in FIG. 2 , which is provided by pivoting the vanes 338 .
- the present invention includes an aperture 344 arranged between the inlet and outlet ends 348 and 350 .
- the aperture is elongated in the direction of the length of the vane 338 .
- Protrusions 346 extend from the backing plate 328 through the aperture 344 . In the example shown, the protrusions 346 are integral with the backing plate 328 and extend to engage the shroud 336 .
- Bolts 340 shown in FIG.
- the additional bolts 340 and protrusions 346 of the present invention provide improved containment of the vanes 338 in the event of a failure.
- the mounting plate 330 includes a boss 342 for each vane 338 .
- Each vane 338 includes a hole 355 for receiving a pivot pin 354 .
- the pivot pin 354 extends through an opening in the shroud to the mounting plate 330 to secure the vane 338 between the shroud 336 and backing plate 328 .
- An end of the pivot pin 354 is secured into the boss 342 .
- Openings in the backing plate 328 , vane 338 and shroud 336 are in a slip fit relationship relative to the pivot pin 354 to permit the shroud 336 and backing plate 328 to deflect axially without binding the vane 338 .
- the shroud 336 is shown broken along planes J, K and L in FIG. 3 to better illustrate the interrelationship of diffuser components.
- the vanes 338 include a slot that receives a drive pin 358 .
- the drive pins 358 are mounted on a drive ring 356 that is rotated by the actuator 323 to rotate the vanes 338 about the pivot pins 354 .
- the drive ring 356 includes a bearing 357 supporting the drive ring 356 in the housing 316 .
- the drive pin 358 is received in a slot in the shroud 336 that defines the positional limits of the vanes 338 .
- the turbine section 22 , the compressor section 18 and the motor 38 are each mounted on the shaft 20 , which acts as a common rotating shaft, and each is supported on foil air bearings 500 (see FIG. 1 ).
- the compressor section 18 may have a continuously variable area diffuser 322 used to provide compressed air utilized for aircraft cabin pressurization and the turbine section 22 may includes a dual nozzle turbine, as described above, with control not limited to turbine pressure ratio in which the poppet member 40 actuates to control turbine nozzle area based upon whether 1 or 2 packs are in operation. Expansion through the turbine section 22 may be utilized for supply of cooling air to aircraft cabin C and to generate shaft power to assist the motor 38 in driving the compressor section 18 .
- the motor 38 may include an integrally cooled motor that is disposed in communication with a RAM heat exchanger 501 whereby a pressure differential across the RAM heat exchanger 501 is used to generate cooling flow.
- a cooling flow may be tapped from the compressor inlet 24 upstream of the RAM heat exchanger 501 and exited to the RAM ducting downstream of the RAM heat exchanger 501 .
- bearing cooling supply air may be tapped from the compressor outlet 28 and/or after cooling through the RAM heat exchanger 501 .
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Abstract
An air cycle machine is provided and includes a compressor section having a variable area diffuser, a turbine section having an inlet nozzle with a variable size, a motor to drive the compressor and a common rotating shaft on which the compressor section, the turbine section and the motor are mounted, the turbine section driving rotation of the shaft to drive the compressor section with the motor.
Description
- The subject matter disclosed herein relates to a motor driven cabin air compressor with a variable diffuser.
- Aircraft environmental control systems incorporate turbomachines, commonly referred to as air cycle machines (ACMs), to help facilitate cooling and dehumidifying air for supply to a cabin of an aircraft. Air cycle machines can include two or more wheels having at least one compressor and at least one turbine disposed axially along the same shaft. On aircraft powered by gas turbine engines, the air to be conditioned in the air cycle machine is generally either compressed air bled from one or more of the compressor stages of the gas turbine engine or air diverted from another location on the aircraft. With either system, the air is passed through the compressor(s) of the air cycle machine where it is further compressed and then passed through a heat exchanger to cool the compressed air sufficiently to condense moisture therefrom. The dehumidified air continues through the environmental control system back to the turbine(s) of the air cycle machine. In the turbine(s), the air is expanded to both extract energy from the compressed air so as to drive the shaft and the compressor(s) coupled thereto and cool the air for use in the cabin as conditioned cooling air.
- To meet required specifications for providing fresh air and maintain pressurization to the cabin during flight, environmental control systems on larger aircraft employ two separate (dual) air conditioning packs. Unfortunately, operating dual air conditioning packs may not be necessary or efficient in some circumstances such as when the plane is on the tarmac. In this instance and others, operating only a single air conditioning pack could accomplish the conditioning of air for the cabin.
- According to one aspect of the invention, an air cycle machine is provided and includes a compressor section having a variable area diffuser, a turbine section having an inlet nozzle with a variable size, a motor to drive the compressor and a common rotating shaft on which the compressor section, the turbine section and the motor are mounted, the turbine section driving rotation of the shaft to drive the compressor section with the motor.
- According to another aspect of the invention, an air cycle machine is provided and includes a compressor section having a variable area diffuser to compress inlet air, a turbine section having an inlet nozzle with a variable size to receive the compressed air from the compressor section and to expand the air for use in an aircraft cabin, a motor to drive the compressor and a common rotating shaft on which the compressor section, the turbine section and the motor are operably mounted, the turbine section driving rotation of the shaft to provide additional drive power to the compressor section along with that of the motor.
- According to yet another aspect of the invention, an air cycle machine for use in a RAM engine in an aircraft is provided and includes a compressor section having a variable area diffuser to compress RAM inlet air, a turbine section having an inlet nozzle with a variable size to receive the compressed air from the compressor section and to expand the air for use in a cabin of the aircraft, a motor to drive the compressor and a common rotating shaft on which the compressor section, the turbine section and the motor are operably mounted, the turbine section driving rotation of the shaft to provide additional drive power to the compressor section along with that of the motor.
- These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
- The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
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FIG. 1 is a schematic view of an air cycle machine for an environmental control system of an aircraft; -
FIG. 2A is an enlarged view of a turbine inlet nozzle of the air cycle machine with a poppet member in a first position; -
FIG. 2B is an enlarged view of the turbine inlet nozzle of the air cycle machine with the poppet member in a second position; -
FIG. 3 is a partially broken view of a variable area diffuser in the direction of arrows 2-2 ofFIG. 4 ; -
FIG. 4 is an enlarged cross-sectional view of a variable area diffuser; and -
FIG. 5 is a schematic illustration of the air cycle machine. - The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
-
FIG. 1 shows a schematic view of an environmental control system (ECS) 10. Theenvironmental control system 10 includes anair cycle machine 12 that receivesair 14 that is conditioned by various devices symbolically indicated as 16A, 16B, and 16C to produce air flow at a desired temperature and pressure for aircraft cabin C. Theair cycle machine 12 includes acompressor section 18, ashaft 20, and aturbine section 22. Thecompressor section 18 has acompressor inlet 24, acompressor wheel 26 and acompressor outlet 28. Theturbine section 22 includes aturbine inlet 30,turbine inlet nozzle 32,turbine wheel 34 andturbine outlet 36. -
System air 14 is bled from one or more of the compressor stages of the gas turbine engines of the aircraft or directed from an air source at another location on the aircraft. One or more devices 16A can condition (e.g., preheat, acoustically treat) theair 14 prior to its entry into theair cycle machine 12. Theair 14 enters theair cycle machine 12 at thecompressor section 18 through thecompressor inlet 24. Theair 14 is compressed to a higher pressure by thecompressor wheel 26, which is mounted on theshaft 20 for rotation about axis A. The compressedair 14 is output to the remainder of theenvironmental control system 10 via thecompressor outlet 28.Air 14 output from thecompressor section 18 is conditioned by various devices 16B to change the characteristics of theair 14 that enters theturbine section 22 via theturbine inlet 30. These devices 16B can include heat exchangers, condensers, and/or water extractors/collectors that condition theair 14 to a desired pressure and temperature. - The
turbine inlet nozzle 32 receivesair 14 entering theair cycle machine 12 through theinlet 30 and is disposed adjacent theturbine wheel 34 to direct the flow ofair 14 thereto. As will be discussed subsequently, theair cycle machine 12 is configured with a valve to vary the size ofturbine inlet nozzle 32 as desired to better optimize the efficiency of theenvironmental control system 10. In particular, the selectively variableturbine inlet nozzle 32 disclosed herein allows the power consumption of theenvironmental control system 10 to be reduced, for example, by operating only a single air conditioning pack to condition the cabin rather than operating two air conditioning packs in some instances. - The
turbine wheel 34 is mounted on theshaft 20 to drive rotation of theshaft 20 andcompressor wheel 26 about axis A. After passing through theturbine inlet nozzle 32 theair 14 is expanded to both extract energy from theair 14 so as to drive theshaft 20 and the compressor wheel 26 (in combination with amotor 38 mounted along theshaft 20 in some embodiments) and to cool theair 14 to prepare it for the cabin. After expansion, theair 14 passes through theturbine outlet 36 out of theair cycle machine 12. Theair 14 can pass through one ormore devices 16C (e.g., heat exchangers, compact mixers, and/or acoustic treatment devices) before reaching the cabin C at the desired temperature and pressure. -
FIG. 2A is an enlarged view of theturbine section 22 with apoppet member 40 disposed in a first position extending into theturbine inlet nozzle 32. In addition to the turbine inlet 30, theturbine inlet nozzle 32, theturbine wheel 34, theturbine outlet 36, and thepoppet member 40, theturbine section 22 includes ashroud 42, afirst cavity 44, avalve body 46, and asecond cavity 48. Theshroud 42 has apassage 50. Thepoppet member 40 includes amain body 52 andseals 41A and 41B. An arcuate plate 54 is fixed within theturbine inlet nozzle 32. - As illustrated in
FIG. 2A , thepoppet member 40 is slidably mounted on thestator shroud 42 and is configured to seal thefirst cavity 44 from theturbine inlet nozzle 32. In particular,seals 41A and 41B are disposed between thepoppet member 40 and theshroud 42 to allow for pressurization of thefirst cavity 44. Thefirst cavity 44 serves as an annular plenum that is defined by portions of theshroud 42, thepoppet member 40, thevalve body 46, and other portions of the casing of theair cycle machine 12. Thevalve body 46 is mounted in fluid communication with thefirst cavity 44. - The
valve body 46 can be any valve commonly known in the art for selectively communicating air from two ports (two pressure sources) to a third port. Thevalve body 46 can be controlled to move a member between a first position that blocks a first of the three ports and allows the second and third ports to be in fluid communication, and a second position that blocks the second port and allows the first and third ports to be in fluid communication. Thevalve body 46 is controlled to vary the pressure in thefirst cavity 44 between a first pressure P1, equal to or about equal to the pressure Pt within the turbine inlet 30 (illustrated inFIG. 2A ), and a second lower pressure P2, equal to or about equal to an ambient pressure Pa external to theenvironmental control system 10 and air cycle machine 12 (illustrated inFIG. 2B ). Thus, thevalve body 46 is selectively controlled to allow for fluid communication between thefirst cavity 44 and either the turbine inlet 30 or the ambient air source external to theair cycle machine 12. In the first position shown inFIG. 2A , thefirst cavity 44 is in fluid communication with theturbine inlet 30. The higher first pressure P1 that results from this arrangement forces thepoppet member 40 outward expanding the volume of thefirst cavity 44. Thus, in the first position, thepoppet member 40 extends from thefirst cavity 44 into theturbine inlet nozzle 32 to reduce the size (volume and/or cross-sectional area) of theinlet turbine nozzle 32 that receivesair 14 from theturbine inlet 30. In this position, thepoppet member 40 restricts the flow ofair 14 to theturbine wheel 34. The reduced air flow to theturbine wheel 34 maybe desirable in some instances, for example, if it is necessary to operate both air conditioning packs to maintain the cabin at a desired pressure and temperature. - The
second cavity 48 is defined by theshroud 42 and thepoppet member 40 and is positioned radially outward of theturbine wheel 34 with respect to axis A. Thepoppet member 40 separates thefirst cavity 44 from thesecond cavity 48. Thepassage 50 throughshroud 42 allows thesecond cavity 48 to be in fluid communication with theturbine inlet nozzle 32 immediately adjacent to theturbine wheel 34. This arrangement allows thesecond cavity 48 to be maintained at or about the static pressure experienced within theturbine inlet nozzle 32 immediately adjacent to theturbine wheel 34. This static pressure is lower than the pressure at the turbine inlet 30 (and selectively the pressure of the first cavity 44) but greater than the ambient pressure external to the air cycle machine 12 (and selectively the pressure of the first cavity 44), which allows for actuation of thepoppet valve 40. - The
poppet valve 40 includes amain body 52 that is mounted on theshroud 42 and configured to seal and separate thefirst cavity 44 from thesecond cavity 48. Themain body 52 is actuated as discussed to slide relative toshroud 42. In the first position shown inFIG. 2A , themain body 52 extends from thefirst cavity 44 andshroud 42 into theturbine inlet nozzle 32. The arcuate plate 54 is fixed to theturbine inlet nozzle 32 and divides the turbine inlet nozzle into two sections. The plate 54 is aligned within theturbine inlet nozzle 32 so as to minimally interfere with the direction of airflow toward theturbine wheel 34. In particular, the plate 54 is configured with a small cross-sectional area interfacing the airflow and has a larger surface that extends generally parallel to one of the walls of theturbine inlet nozzle 32. The plate 54 extends generally radially to immediately adjacent theturbine wheel 34, thereby, dividing theturbine inlet nozzle 32 into a primary section (through whichair 14 flows when thepoppet member 40 is in the first position illustrated inFIG. 2A ) and a secondary section (through whichair 14 generally does not pass when thepoppet member 40 is in the first position). -
FIG. 2B is an enlarged view of theturbine section 22 with thepoppet member 40 disposed in a second position. In the second position, thefirst cavity 44 is in fluid communication with the ambient air source external to theair cycle machine 12. As a result of this arrangement, the pressure within the second cavity 48 (the static pressure) exceeds the second pressure P2 within thefirst cavity 44 and thepoppet member 40 moves decreasing the volume of thefirst cavity 44 and increasing the volume of thesecond cavity 48. The movement of themain body 52 of thepoppet member 40 within thefirst cavity 44 retractsmain body 52 from at least a portion of theturbine inlet nozzle 32, allowing airflow through the secondary section of theturbine inlet nozzle 32, thereby increasing the size (volume and/or cross sectional area) of theturbine inlet nozzle 32 through whichair 14 flows to theturbine wheel 34. Thus, in the second position shown inFIG. 2B virtually the entire airflow passes through theturbine inlet nozzle 32 unrestricted by thepoppet member 40 to theturbine wheel 34. - By varying the pressure of the
first cavity 44 in the manner disclosed to selectively move thepoppet member 40 within theturbine inlet nozzle 32, the efficiency of theenvironmental control system 10 can be improved. In particular, selectively moving thepoppet member 40 to vary the size of theturbine inlet nozzle 32 when desired allows the power consumption of theenvironmental control system 10 to be reduced, for example, by operating only a single air conditioning pack to condition the cabin rather than operating both air conditioning packs. - Referring to
FIGS. 3 and 4 , thecompressor section 18 may include avariable area diffuser 322 with an actuator 323 (seeFIG. 1 ) to vary the inlet throat 352 (seeFIG. 3 ) to vary a flow rate through theECS 10. Thevariable area diffuser 322 includes abacking plate 328 that is isolated from deflection, D. In conventional devices, thebacking plate 328 would be secured directly to thehousing 316 contributing to the diffuser vanes binding. Instead, theinventive diffuser 322 employs a mountingplate 330 that supports thebacking plate 328. The inner and outer periphery of thebacking plate 328 is supported by the mountingplate 330, but is also permitted to move axially independently of the mountingplate 330. - A
shroud 336 is supported by thehousing 316 and may deflect axially under load.Multiple vanes 338 are retained between thebacking plate 328 andshroud 336 and, typically, a few thousandths of an inch of clearance is provided between thevane 338 and thebacking plate 328 andshroud 336. In the example system shown, there are 323 vanes that are modulated between full open and 40% of full open. - The
vanes 338 include aninlet end 348 and anoutlet end 350. Theinlet end 348 provides anadjustable throat 352, shown inFIG. 2 , which is provided by pivoting thevanes 338. To provide improved containment, the present invention includes anaperture 344 arranged between the inlet and outlet ends 348 and 350. The aperture is elongated in the direction of the length of thevane 338.Protrusions 346 extend from thebacking plate 328 through theaperture 344. In the example shown, theprotrusions 346 are integral with thebacking plate 328 and extend to engage theshroud 336.Bolts 340, shown inFIG. 2 , extend through theaperture 344 to secure thevane 338 between theshroud 336 andbacking plate 328. Theadditional bolts 340 andprotrusions 346 of the present invention provide improved containment of thevanes 338 in the event of a failure. - The mounting
plate 330 includes aboss 342 for eachvane 338. Eachvane 338 includes ahole 355 for receiving apivot pin 354. Thepivot pin 354 extends through an opening in the shroud to the mountingplate 330 to secure thevane 338 between theshroud 336 andbacking plate 328. An end of thepivot pin 354 is secured into theboss 342. Openings in thebacking plate 328,vane 338 andshroud 336 are in a slip fit relationship relative to thepivot pin 354 to permit theshroud 336 andbacking plate 328 to deflect axially without binding thevane 338. - The
shroud 336 is shown broken along planes J, K and L inFIG. 3 to better illustrate the interrelationship of diffuser components. Thevanes 338 include a slot that receives adrive pin 358. The drive pins 358 are mounted on adrive ring 356 that is rotated by theactuator 323 to rotate thevanes 338 about the pivot pins 354. Thedrive ring 356 includes abearing 357 supporting thedrive ring 356 in thehousing 316. Thedrive pin 358 is received in a slot in theshroud 336 that defines the positional limits of thevanes 338. - With reference to
FIG. 5 , theturbine section 22, thecompressor section 18 and themotor 38 are each mounted on theshaft 20, which acts as a common rotating shaft, and each is supported on foil air bearings 500 (seeFIG. 1 ). Thecompressor section 18 may have a continuouslyvariable area diffuser 322 used to provide compressed air utilized for aircraft cabin pressurization and theturbine section 22 may includes a dual nozzle turbine, as described above, with control not limited to turbine pressure ratio in which thepoppet member 40 actuates to control turbine nozzle area based upon whether 1 or 2 packs are in operation. Expansion through theturbine section 22 may be utilized for supply of cooling air to aircraft cabin C and to generate shaft power to assist themotor 38 in driving thecompressor section 18. - As shown in
FIG. 5 , themotor 38 may include an integrally cooled motor that is disposed in communication with aRAM heat exchanger 501 whereby a pressure differential across theRAM heat exchanger 501 is used to generate cooling flow. A cooling flow may be tapped from thecompressor inlet 24 upstream of theRAM heat exchanger 501 and exited to the RAM ducting downstream of theRAM heat exchanger 501. Also, bearing cooling supply air may be tapped from thecompressor outlet 28 and/or after cooling through theRAM heat exchanger 501. - While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
Claims (20)
1. An air cycle machine, comprising:
a compressor section having a variable area diffuser;
a turbine section having an inlet nozzle with a variable size;
a motor to drive the compressor; and
a common rotating shaft on which the compressor section, the turbine section and the motor are mounted,
the turbine section driving rotation of the shaft to drive the compressor section with the motor.
2. The air cycle machine according to claim 1 , wherein the compressor section, the turbine section and the motor are each supported on air bearings.
3. The air cycle machine according to claim 1 , wherein the variable size of the inlet nozzle is set according to operation of a predefined number of packs.
4. The air cycle machine according to claim 1 , wherein the motor comprises an integrally cooled motor.
5. The air cycle machine according to claim 4 , further comprising a heat exchanger coupled to the motor.
6. The air cycle machine according to claim 5 , wherein a first cooling flow is tapped from an inlet of the compressor section and exited downstream form the heat exchanger.
7. The air cycle machine according to claim 5 , wherein a second cooling flow is tapped from an outlet of the compressor section for air bearing cooling.
8. An air cycle machine, comprising:
a compressor section having a variable area diffuser to compress inlet air;
a turbine section having an inlet nozzle with a variable size to receive the compressed air from the compressor section and to expand the air for use in an aircraft cabin;
a motor to drive the compressor; and
a common rotating shaft on which the compressor section, the turbine section and the motor are operably mounted,
the turbine section driving rotation of the shaft to provide additional drive power to the compressor section along with that of the motor.
9. The air cycle machine according to claim 8 , wherein the compressor section, the turbine section and the motor are each supported on air bearings.
10. The air cycle machine according to claim 8 , wherein the variable size of the inlet nozzle is set according to operation of a predefined number of packs.
11. The air cycle machine according to claim 8 , wherein the motor comprises an integrally cooled motor.
12. The air cycle machine according to claim 11 , further comprising a heat exchanger coupled to the motor.
13. The air cycle machine according to claim 12 , wherein a first cooling flow is tapped from an inlet of the compressor section and exited downstream form the heat exchanger.
14. The air cycle machine according to claim 12 , wherein a second cooling flow is tapped from an outlet of the compressor section for air bearing cooling.
15. An air cycle machine for use in a RAM engine in an aircraft, comprising:
a compressor section having a variable area diffuser to compress RAM inlet air;
a turbine section having an inlet nozzle with a variable size to receive the compressed air from the compressor section and to expand the air for use in a cabin of the aircraft;
a motor to drive the compressor; and
a common rotating shaft on which the compressor section, the turbine section and the motor are operably mounted,
the turbine section driving rotation of the shaft to provide additional drive power to the compressor section along with that of the motor.
16. The air cycle machine according to claim 15 , wherein the compressor section, the turbine section and the motor are each supported on air bearings.
17. The air cycle machine according to claim 15 , wherein the variable size of the inlet nozzle is set according to operation of a predefined number of packs.
18. The air cycle machine according to claim 15 , wherein the motor comprises an integrally cooled motor.
19. The air cycle machine according to claim 18 , further comprising a heat exchanger coupled to the motor.
20. The air cycle machine according to claim 19 , wherein a first cooling flow is tapped from an inlet of the compressor section and exited downstream form the heat exchanger and a second cooling flow is tapped from an outlet of the compressor section for air bearing cooling.
Priority Applications (1)
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US12/939,740 US20120114463A1 (en) | 2010-11-04 | 2010-11-04 | Motor driven cabin air compressor with variable diffuser |
Applications Claiming Priority (1)
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US12/939,740 US20120114463A1 (en) | 2010-11-04 | 2010-11-04 | Motor driven cabin air compressor with variable diffuser |
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US20120114463A1 true US20120114463A1 (en) | 2012-05-10 |
Family
ID=46019789
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US12/939,740 Abandoned US20120114463A1 (en) | 2010-11-04 | 2010-11-04 | Motor driven cabin air compressor with variable diffuser |
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US20120156027A1 (en) * | 2010-12-21 | 2012-06-21 | Merritt Brent J | Air cycle machine compressor diffuser |
US20150345506A1 (en) * | 2014-05-30 | 2015-12-03 | Hamilton Sundstrand Corporation | Cover plate for cabin air compressor |
US9328734B2 (en) | 2012-12-28 | 2016-05-03 | Hamilton Sundstrand Corporation | Seal plate |
US9341193B2 (en) | 2013-04-04 | 2016-05-17 | Hamilton Sundstrand Corporation | Cabin air compressor diffuser vane drive ring |
US9482277B2 (en) | 2014-12-29 | 2016-11-01 | Hamilton Sundstrand Corporation | Air bearing shaft chrome plating |
US9546669B2 (en) | 2013-01-11 | 2017-01-17 | Hamilton Sundstrand Corporation | Compressor housing for an air cycle machine |
US9656760B2 (en) | 2013-11-07 | 2017-05-23 | Sikorsky Aircraft Corporation | Variable geometry helicopter engine inlet |
US20170204873A1 (en) * | 2016-01-14 | 2017-07-20 | Hamilton Sundstrand Corporation | Weld repair for cabin air compressor housing |
US20170204867A1 (en) * | 2016-01-14 | 2017-07-20 | Hamilton Sundstrand Corporation | Weld repair for an air cycle machine compressor housing |
CN107434047A (en) * | 2016-05-26 | 2017-12-05 | 哈米尔顿森德斯特兰德公司 | Multi-nozzle configuration for the turbine of environmental control system |
US9863439B2 (en) | 2014-09-11 | 2018-01-09 | Hamilton Sundstrand Corporation | Backing plate |
US9873515B2 (en) | 2014-08-13 | 2018-01-23 | Hamilton Sundstrand Corporation | Turbine nozzle with relief cut |
US9890793B2 (en) | 2014-09-23 | 2018-02-13 | Hamilton Sundstrand Corporation | Variable diffuser vane |
US10174765B2 (en) | 2016-01-14 | 2019-01-08 | Hamilton Sundstrand Corporation | Outlet housing for cabin air compressor |
US10190487B1 (en) * | 2017-11-06 | 2019-01-29 | Ford Global Technologies, Llc | Systems and methods for a bi-valved variable inlet device |
US10399694B2 (en) | 2015-09-02 | 2019-09-03 | Ge Aviation Systems Llc | Ram air turbine system |
US10731501B2 (en) | 2016-04-22 | 2020-08-04 | Hamilton Sundstrand Corporation | Environmental control system utilizing a motor assist and an enhanced compressor |
US11511867B2 (en) | 2016-05-26 | 2022-11-29 | Hamilton Sundstrand Corporation | Mixing ram and bleed air in a dual entry turbine system |
US20230340959A1 (en) * | 2018-08-07 | 2023-10-26 | Cryostar Sas | Multi-stage turbomachine |
US11981440B2 (en) | 2016-05-26 | 2024-05-14 | Hamilton Sundstrand Corporation | Energy flow of an advanced environmental control system |
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