CN117469187A - Airborne electric control air cooling system based on counter-rotating compressor - Google Patents
Airborne electric control air cooling system based on counter-rotating compressor Download PDFInfo
- Publication number
- CN117469187A CN117469187A CN202311622218.6A CN202311622218A CN117469187A CN 117469187 A CN117469187 A CN 117469187A CN 202311622218 A CN202311622218 A CN 202311622218A CN 117469187 A CN117469187 A CN 117469187A
- Authority
- CN
- China
- Prior art keywords
- air
- compressor
- rotating
- counter
- compressors
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 55
- 230000006835 compression Effects 0.000 claims abstract description 11
- 238000007906 compression Methods 0.000 claims abstract description 11
- 238000005057 refrigeration Methods 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 4
- 239000003570 air Substances 0.000 description 108
- 230000007613 environmental effect Effects 0.000 description 8
- 239000012080 ambient air Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- 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
- F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
-
- 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
- B64D13/06—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
- B64D13/08—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 the air being heated or cooled
-
- 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
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
- F04D25/045—Units comprising pumps and their driving means the pump being fluid-driven the pump wheel carrying the fluid driving means, e.g. turbine blades
-
- 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
-
- 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
-
- 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
- B64D2013/0614—Environmental Control Systems with subsystems for cooling avionics
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a motor-mounted electric annular control air cooling system based on a counter-rotating air compressor, which comprises an engine surface annular control air inlet, two axial-flow air compressors, a counter-rotating air compressor casing, a motor, a cooling turbine and an air radiator, wherein the counter-rotating air compressor is connected with the cooling turbine through a bearing, and the cooling turbine drives the counter-rotating air compressor to rotate to compress air when doing work; the other reversing compressor is connected with the motor through a bearing, and the motor drives the reversing compressor to rotate to compress air when doing work; the sleeve compressors are arranged in the compressor casing, the air outlet of the reversing compressor is connected with the inlet of the forward rotating compressor, and when the rotation directions of the two compressors are opposite, a set of reverse rotating compressors is formed. The invention is based on the technology of the contra-rotating compressor, and utilizes the characteristics of high air compression efficiency and compact structure of the contra-rotating compressor to improve the compression efficiency of the electric air cooling system, thereby improving the refrigerating capacity of the system and reducing the power consumption.
Description
Technical Field
The invention relates to the field of aircraft environmental control systems, in particular to an aircraft electric environmental control air cooling system based on a counter-rotating compressor.
Background
The annular control air cooling system provides cooling air for the aircraft electronic equipment and the cabin, and the improvement of the efficiency of the annular control air cooling system is an important requirement of the future aircraft annular control system along with the increase of the heat dissipation power of the aircraft cabin and the electronic equipment and the improvement of the long-term navigation and long-distance navigation index of the aircraft.
The basic principle of a typical air cooling system of an onboard system is that a high-temperature and high-pressure air source is obtained from a high-pressure compressor of an engine, isobaric cooling is carried out through an air or liquid radiator, and then the air enters a refrigeration turbine to be expanded and cooled, so that low-temperature normal-pressure air is obtained. If the high temperature and high pressure air source is not obtained from the engine, but is obtained by directly compressing air by an electric compressor, the system is called a multi-electric ring control air cooling system.
Because the temperature of the high-pressure compressed air source of the engine is too high, the environmental control system generally needs to use a plurality of radiators in series to meet the requirement of the inlet temperature of the turbine, so that the weight of the system is large, and the oil consumption of the engine is increased. In order to solve the problem of energy waste of engine bleed air, a multi-motor-mounted system represented by a B787 aircraft starts to use an electric compressor to replace the engine bleed air to provide a high-pressure air source for an environmental control system so as to reduce engine oil consumption and increase range, but because of the limitation of the motor power ratio and the efficiency of the electric compressor, the volume and the weight of the electric air-cooled environmental control system are still large, comprehensive fuel consumption benefits can be formed only on high-lift-drag ratio and long-range aircraft (such as civil airliners), and the electric air-cooled environmental control system cannot be applied to high-speed aircraft.
Disclosure of Invention
The invention aims to provide an onboard electric annular controlled air cooling system based on a counter-rotating compressor, which utilizes the characteristic of high air compression efficiency of the counter-rotating compressor, integrates an electric compressor and a turbine load compressor into a counter-rotating compressor, reduces the volume of the system, improves the inlet pressure of a turbine under the same rotating speed and external atmospheric conditions, improves the refrigeration power under the same electric power consumption, or reduces the electric power consumption under the same refrigeration power.
In order to realize the tasks, the invention adopts the following technical scheme:
an airborne electric control air cooling system based on a counter-rotating air compressor comprises an air inlet of an airborne electric control, two axial-flow air compressors, a counter-rotating air compressor casing, a motor, a cooling turbine and an air radiator, wherein the counter-rotating air compressor is connected with the cooling turbine through a bearing, and the cooling turbine drives the counter-rotating air compressor to rotate to compress air when expansion work is performed; the other reversing compressor is connected with the motor through a bearing, and the motor drives the reversing compressor to rotate to compress air when doing work; the sleeve compressors are arranged in the compressor casing, the air outlet of the reversing compressor is connected with the inlet of the forward rotating compressor, and when the rotation directions of the two compressors are opposite, a set of reverse rotating compressors is formed.
Further, the engine surface ring control air introducing port introduces normal temperature and normal pressure air from an aircraft environment or an engine low pressure rotor, the air enters the air compressor casing through a pipeline, the air in the casing firstly passes through an air inlet of a reverse dynamic pressure machine carried by a motor, the pressure and the temperature are increased after the reverse dynamic pressure machine rotates to do work, and the air is discharged from an air outlet of the reverse dynamic pressure machine and then directly enters an air inlet of a forward rotating air compressor; and after flowing out from an air outlet of the forward rotation compressor, the high-temperature and high-pressure air formed after secondary compression enters an air heat exchanger through a casing outlet pipeline, is cooled by normal-temperature and normal-pressure air introduced from a casing ring-control air introducing port, forms normal-temperature and high-pressure air through the thermodynamic process of isobaric heat extraction, then enters a cooling turbine through a pipeline, forms normal-pressure and low-temperature air after expansion and cooling, and finally enters a cabin or an electronic equipment cabin to realize air refrigeration.
Further, the two axial-flow compressors include a counter-rotating compressor and a forward-rotating compressor.
Further, the inlet pressure of the reversing compressor is 50-100 Kpa, and the temperature is-10-15 ℃.
Further, the inlet pressure of the forward rotating compressor is 80-150 Kpa, the temperature is 9-40 ℃, and the total outlet pressure of the forward rotating compressor is not less than 300Kpa.
Further, the flow rate of the outlet of the cooling turbine is more than or equal to 1000kg/h.
Further, the power consumption of the motor is 10-15 kw, and the refrigerating capacity of the whole system is 3-5 kw.
An aircraft employing an on-board electric controlled air cooling system based on counter-rotating compressors.
Compared with the prior art, the invention has the following technical characteristics:
1. compared with the traditional two-compressor serial architecture, the two compressors run in opposite rotation, so that the pressure ratio is higher, and the efficiency is higher.
2. The two compressors are integrated in 1 casing, and the volume and weight of the compressor are smaller than those of the traditional two-compressor serial architecture.
3. The two compressors are driven by the motor and the turbine respectively, and are not required to be coaxially installed, so that the difficulty in system design, manufacturing and control is reduced.
4. The air flow is compressed in the casing by the compressor driven by the motor, which is beneficial to system starting and control.
5. Because the second-stage airflow inlet vector angle of the contra-rotating compressor is large, the load is higher, and the turbine is used for driving, so that the turbine load is improved, and the turbine refrigeration efficiency is improved.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the system of the present invention.
Detailed Description
The air circulation refrigeration has the advantages of using air as a refrigeration medium, having high refrigeration temperature gradient, having no risk of leakage of liquid medium and the like, and is an important implementation mode of the airborne refrigeration function. The electric air-cooling environmental control system utilizes an electric compressor to replace air bleed directly from a high-pressure compressor of an engine, reduces oil consumption and thrust loss of the engine, and all advanced civil aircraft such as B787, A350 and the like adopt the electric air-cooling environmental control system. With the increase of the refrigerating power requirement and the flying speed requirement of the airplane, the electric ring control air cooling system has the defects of low efficiency of the compressor and high power requirement of the motor under the working condition of high power and high temperature difference. The invention provides a circular control air cooling scheme based on a motor and a cooling turbine for driving a counter-rotating compressor based on a counter-rotating compressor technology, and the characteristics of high air compression efficiency and compact structure of the counter-rotating compressor are utilized to improve the compression efficiency of an electric air cooling system, so that the refrigerating capacity of the system is improved, and the power consumption is reduced.
Referring to the attached drawings, the invention provides an airborne electric ring controlled air cooling system based on a counter-rotating air compressor, which comprises an engine surface ring controlled air inlet 1, two axial-flow air compressors, a counter-rotating air compressor casing 3, a motor 5, a cooling turbine 13 and an air radiator 10, wherein 1 forward-rotating air compressor 8 is connected with the cooling turbine 13 through a bearing 12, and the cooling turbine 13 drives the forward-rotating air compressor 8 to rotate to compress air when expanding and doing work (the turbine, the bearing and the air compressor form a turbine air compressor); the other reversing compressor 4 is connected with a motor 5 through a bearing 6, and the motor 5 drives the reversing compressor 4 to rotate to compress air when doing work (the motor, the bearing and the compressor form an electric compressor); the 2 sets of compressors are arranged in the compressor casing 3, the air outlet of the reversing compressor 4 is connected with the inlet of the forward rotating compressor 8, and when the rotation directions of the two compressors are opposite, a set of reverse rotating compressors is formed; the air inlet 1 can introduce normal temperature and pressure air 2 from an aircraft environment or a low-pressure rotor of an engine, and enters a compressor casing through a pipeline, wherein air in the casing firstly passes through an air inlet of a reverse rotation compressor 4 carried by a motor 5, increases pressure and temperature after rotating to do work through the reverse rotation compressor 4, is discharged from an air outlet of the reverse rotation compressor 4 and directly enters an air inlet of a forward rotation compressor 8, and according to the principle of the reverse rotation compressor, because the rotation directions of the two compressors are opposite, the included angle between an air flow velocity vector flowing out from the air outlet of the reverse rotation compressor 4 and an air inlet blade of the forward rotation compressor 8 is larger than that of the conventional two-stage compressor, so that the efficiency of the reverse rotation compressor is improved; after flowing out from an air outlet of the forward rotation compressor 8, the high-temperature high-pressure air 9 formed after 2 times of compression enters an air heat exchanger 10 through a casing outlet pipeline, is cooled by normal-temperature normal-pressure air 16 introduced from a casing ring-control air inlet 1, forms normal-temperature high-pressure air 11 through the thermodynamic process of isobaric heat removal, then enters a cooling turbine 13 through a pipeline, forms normal-pressure low-temperature air 14 after expansion and cooling, and finally enters a cabin or an electronic equipment cabin to realize air refrigeration.
In the scheme, the inlet pressure of the reversing compressor 4 is 50-100 Kpa, and the temperature is-10-15 ℃; the inlet pressure of the forward rotation compressor 8 is 80-150 Kpa, the temperature is 9-40 ℃, and the total outlet pressure of the forward rotation compressor 8 is not less than 300Kpa.
The flow rate of the outlet of the cooling turbine 13 is more than or equal to 1000kg/h.
The power consumption of the motor 5 is 10-15 kw, and the refrigerating capacity of the whole system is 3-5 kw.
Examples:
in the following description of the present patent, fig. 1 is a schematic diagram of an airborne electric control air cooling system based on a contra-rotating compressor, where the system is used to introduce normal temperature and normal pressure air from the outside environment of the aircraft, and form low temperature and normal pressure air after compression, heat dissipation, expansion and refrigeration, and then enter an electronic equipment cabin to cool electronic equipment. The system comprises a ring control machine table punching air inlet 1, a counter-rotating compressor casing 3, a counter-rotating axial compressor 4, a forward-rotating axial compressor 8, a motor 5, a motor bearing 6, a turbine cooler 13, a turbine bearing 12 and an air heat exchanger 10. Wherein the counter-rotating axial compressor 4 and the forward-rotating axial compressor 8 are installed in the counter-rotating compressor casing 3; the two flow channels are formed together, the reversing axial flow compressor 4 is connected with the motor 5 through the motor bearing 6, and rotates anticlockwise during working; the forward rotation shaft flow compressor 8 is connected with the turbine cooler 13 through the turbine bearing 12, and rotates clockwise when in operation.
The working principle of the system is that after ambient air enters the system from an aircraft surface ring control air inlet 1, the ambient air is divided into two normal temperature and pressure airflows, wherein the normal temperature and pressure air 2 directly enters a reverse rotation compressor 4 in a reverse rotation compressor casing 3, a motor 5 drives the reverse rotation compressor 4 to rotate to do work on the airflows to finish the first compression of the airflows, then the high temperature and high pressure air 7 which completes the first compression continuously enters a forward rotation compressor 8, a cooling turbine 13 drives the forward rotation compressor 8 to rotate to do work on the airflows to form high temperature and high pressure air 9, the high temperature and high pressure air 9 enters an air radiator 10, the air radiator 10 utilizes the normal temperature and pressure air 16 introduced from the aircraft surface ring control air inlet 1 to cool the high temperature and pressure air 9 to form normal temperature and high pressure air 11, the normal temperature and high pressure air 11 enters a cooling turbine 13 to do expansion work, the internal energy is converted into machinery in the expansion process of the cooling turbine 13, on one hand, the temperature of the motor is reduced to realize air refrigeration, on the other hand, the converted mechanical work is the driving energy of the forward rotation compressor 8, and the system is maintained to operate; the low-pressure ambient air 14 formed after passing through the cooling turbine 13 is supplied to the electronic equipment compartment 15 of the aircraft.
In the invention, two axial-flow compressors are adopted to compress air, the two compressors are integrated in 1 casing, and air flow directly enters one compressor outlet from the other compressor outlet, and the rotation directions are opposite to form a contra-rotating compressor; one compressor is driven by a motor bearing, the other compressor is driven by an expansion turbine bearing, and the two compressors do not share the bearing; air is introduced into the compressor casing from the air-entraining port, passes through the compressor driven by the electric bearing and then passes through the compressor driven by the turbine bearing.
The above embodiments are only for illustrating the technical solution of the present application, and are not limiting thereof; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced equally; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present application, and are intended to be included in the scope of the present application.
Claims (8)
1. The on-board electric control air cooling system based on the counter-rotating air compressor is characterized by comprising an on-board annular control air inlet (1), two axial-flow air compressors, a counter-rotating air compressor casing (3), a motor (5), a cooling turbine (13) and an air radiator (10), wherein the (1) counter-rotating air compressor (8) is connected with the cooling turbine (13) through a bearing (12), and the cooling turbine (13) drives the counter-rotating air compressor (8) to rotate to compress air when expanding to do work; the other reversing compressor (4) is connected with the motor (5) through a bearing (6), and the motor (5) drives the reversing compressor (4) to rotate to compress air when doing work; (2) The sleeve compressors are arranged in the compressor casing (3), the air outlet of the reverse rotation compressor (4) is connected with the inlet of the forward rotation compressor (8), and when the rotation directions of the two compressors are opposite, a set of reverse rotation compressors is formed.
2. The on-board electric annular controlled air cooling system based on the counter-rotating compressor according to claim 1, wherein the air inlet (1) of the engine surface annular controlled air inlet introduces normal temperature and pressure air (2) from the aircraft environment or the low-pressure rotor of the engine, and enters the compressor casing through a pipeline, wherein the air in the casing firstly passes through the air inlet of the counter-rotating compressor (4) carried by the motor (5), increases the pressure and temperature after rotating to do work through the counter-rotating compressor (4), and directly enters the air inlet of the counter-rotating compressor (8) after being discharged from the air outlet of the counter-rotating compressor (4); after flowing out from an air outlet of a forward rotation compressor (8), high-temperature and high-pressure air (9) formed after the compression for (2) enters an air heat exchanger (10) through a casing outlet pipeline, is cooled by normal-temperature and normal-pressure air (16) introduced from a casing ring control air-introducing port (1), forms normal-temperature and high-pressure air (11) through the thermodynamic process of isobaric heat removal, then enters a cooling turbine (13) through a pipeline, forms normal-pressure and low-temperature air (14) after expansion and cooling, and finally enters a cabin or an electronic equipment cabin (15) to realize air refrigeration.
3. The onboard electric controlled air cooling system based on counter-rotating compressors according to claim 1, characterized by the fact that the two axial compressors comprise a counter-rotating compressor (4) and a forward rotating compressor (8).
4. An onboard electric controlled air cooling system based on counter-rotating compressors according to claim 1, characterized by the fact that the inlet pressure of the counter-rotating compressor (4) is 50-100 Kpa and the temperature is-10-15 ℃.
5. The onboard electric controlled air cooling system based on the counter-rotating compressor according to claim 1, wherein the inlet pressure of the forward rotating compressor (8) is 80-150 Kpa, the temperature is 9-40 ℃, and the total outlet pressure of the forward rotating compressor (8) is not less than 300Kpa.
6. The onboard electric controlled air-cooling system based on counter-rotating compressors according to claim 1, characterized by the fact that the flow at the outlet of the cooling turbine (13) is not less than 1000kg/h.
7. The onboard electric controlled air-cooling system based on a counter-rotating compressor according to claim 1, characterized in that the power consumption of the electric motor (5) is 10-15 kw and the refrigerating capacity of the whole system is 3-5 kw.
8. An aircraft characterized in that it employs an onboard electric controlled air cooling system based on counter-rotating compressors according to any of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311622218.6A CN117469187A (en) | 2023-11-29 | 2023-11-29 | Airborne electric control air cooling system based on counter-rotating compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311622218.6A CN117469187A (en) | 2023-11-29 | 2023-11-29 | Airborne electric control air cooling system based on counter-rotating compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117469187A true CN117469187A (en) | 2024-01-30 |
Family
ID=89636261
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311622218.6A Pending CN117469187A (en) | 2023-11-29 | 2023-11-29 | Airborne electric control air cooling system based on counter-rotating compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117469187A (en) |
-
2023
- 2023-11-29 CN CN202311622218.6A patent/CN117469187A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11077949B2 (en) | Dual turbine thermal management system (TMS) | |
| US10584635B2 (en) | All CO2 aircraft | |
| US10207809B2 (en) | Integrated air and vapor cycle cooling system | |
| US10677195B2 (en) | Engine driven by Sc02 cycle with independent shafts for combustion cycle elements and propulsion elements | |
| US20100263405A1 (en) | Cryogenic Refrigeration Method And Device | |
| US20230044056A1 (en) | Multi-stage turbocharging compressor for fuel cell systems | |
| US9885283B2 (en) | Gas turbine engine driven by supercritical power generation system | |
| EP3260688A1 (en) | Compartment cooling for a gas turbine engine | |
| US5555745A (en) | Refrigeration system | |
| CN111441960A (en) | Magnetic suspension centrifugal air compressor two-stage compression system | |
| US3477226A (en) | Heat pump heat rejection system for a closed cycle hot gas engine | |
| CN108216642A (en) | A kind of Reheat-type cooling turbine unit system applied to aircraft pod | |
| US2571256A (en) | Refrigerant cooled intercooler | |
| CN113028670B (en) | Full fresh air conditioning system and method | |
| CN104612764A (en) | Turbine cooler provided with three coaxial impellers and capable of expanding in two ways | |
| CN117469187A (en) | Airborne electric control air cooling system based on counter-rotating compressor | |
| US20210278107A1 (en) | Air cycle machines and methods of communicating fluid through air cycle machines | |
| CN110733645A (en) | high-speed aircraft thermal management system supporting multi-heat-sink reconstruction | |
| CN216198320U (en) | Multi-shaft turbine compression expander | |
| US5042970A (en) | Fast recharge compressor | |
| CN113863996A (en) | Multi-shaft turbine compression expander | |
| CN113483985A (en) | Temporary-impulse wind tunnel system adopting reverse Brayton cycle to control temperature and test method | |
| CN111472879A (en) | Novel two-stage supercharger | |
| CN112478181A (en) | Airborne integrated cooling system | |
| US11912417B2 (en) | Air conditioning system with cabin air recovery |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |