CN1138685A - Air circulating plane environmental control system able to fully utilizing energy - Google Patents
Air circulating plane environmental control system able to fully utilizing energy Download PDFInfo
- Publication number
- CN1138685A CN1138685A CN95112822A CN95112822A CN1138685A CN 1138685 A CN1138685 A CN 1138685A CN 95112822 A CN95112822 A CN 95112822A CN 95112822 A CN95112822 A CN 95112822A CN 1138685 A CN1138685 A CN 1138685A
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- Prior art keywords
- air
- control system
- environmental control
- passenger cabin
- bleed
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- 230000007613 environmental effect Effects 0.000 title claims description 40
- 238000001816 cooling Methods 0.000 claims abstract description 15
- 238000009423 ventilation Methods 0.000 claims description 27
- 238000005057 refrigeration Methods 0.000 claims description 8
- 239000002699 waste material Substances 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 230000001447 compensatory effect Effects 0.000 description 4
- 239000007788 liquid Substances 0.000 description 2
- 230000001172 regenerating effect Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000007791 dehumidification Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Abstract
An airplane environment control system of air circulation type for full use of energy mainly features that the inlet pressure of air compressor of engine is used as inlet pressure of said system; atmosphere pressure is used as outlet pressure of said system to make the pressure ratio of inlet to outlet tob e equal to boost ratio of said air compressor; two-stage are used for turbines expension, doing wok and cooling; the output work from two turbines is transmitted to one air compressor to form a boosting system, and ram air turbine and air compressor constitute a reverse boosting system for using energy of ram air and reducing temp of ram air.
Description
What the air circulating plane environmental control system that makes full use of the energy of the present invention was related is the aircraft environment control technology.
The present air circulating plane environmental control system that generally uses aboard, the employed energy mainly are HTHP air of being drawn by engine compressor and the ram-air of being introduced by atmosphere.
For the HTHP air that engine compressor is drawn, plane environmental control system mainly is to utilize energy in it, by the turbine expansion acting, air themperature is reduced freeze.But the system that present plane environmental control system and patent US5086622-A and patent US5014518-A are proposed does not all make full use of the energy that the engine compressor bleed is had.For example, when modern fighter plane flew with the speed of Mach number 0.9 at sea level altitude, the pressure of engine compressor bleed was 16kg/cm
2, the pressure ratio of compressor bleed is 15.49.And the inlet pressure of plane environmental control system is the outlet pressure of bleed pressure regulator, and it is limited in 7kg/cm usually
2Below; The outlet pressure of plane environmental control system is a cockpit pressure, is about 1.033kg/cm when sea level altitude flies
2Therefore the actual pressure ratio of utilizing had only 6.78 between plane environmental control system was imported and exported, far below the pressure ratio 15.49 of engine compressor bleed.Table 1 provided the pressure ratio of the engine compressor bleed of modern fighter plane when the differing heights different Mach number and plane environmental control system the actual pressure ratio of utilizing.Can find out that from table 1 the present pressure ratio that plane environmental control system utilized is all well below the pressure ratio of engine compressor bleed.And high highly more, utilization rate is low more.The size of engine compressor bleed pressure ratio has reflected that engine gives the energy size of bleed.The size of the energy that the size of plane environmental control system inlet and outlet pressure ratio is then represented plane environmental control system and utilized.The latter shows that much smaller than the former present plane environmental control system is far from making full use of the energy of engine compressor bleed institute tool.
Table 1 fighter plane is in aloft bleed parameter in hot day
The system that patent US5014518-A proposes inlet pressure is brought up to level near bleed pressure, but outlet pressure remains cockpit pressure.Therefore it does not make full use of the energy of bleed yet.
The ram-air of being introduced by atmosphere also has energy.The pressure ratio of ram-air when table 2 has provided differing heights and Mach number.But the system that present plane environmental control system and patent US5086622-A and patent US5014518-A are proposed does not all fully utilize this part energy.
Another problem that present air circulating plane environmental control system exists is, do not distinguish cabin ventilation ventilation required air and passenger cabin, electronics bay freeze required air different characteristics and treat respectively, but both are integrated.Draw one air from the engine compressor hiigh pressure stage, both be used for the cabin ventilation ventilation, also be used for passenger cabin and electronics bay refrigeration.This design is another main root that plane environmental control system wastes energy.Reason has two, and the one, if the air that is used to freeze is used for the cabin ventilation ventilation simultaneously, then the outlet pressure of refrigeration system can not be lower than cockpit pressure, thereby can not make full use of the energy that bleed has, and causes waste.The 2nd, the required pressure of air that only is used for the cabin ventilation ventilation merely is very low, as long as add the pipeline pressure drop greater than cockpit pressure.If this part air is also from the bleed of engine compressor hiigh pressure stage, the engine power loss that then causes thus will increase several times, tens times even more than quoting low-pressure air.For example summer, certain machine flew at sea level altitude with the speed of M=0.9 when temperature is 40 ℃, and this moment, the pressure of engine compressor hiigh pressure stage bleed was about 16kg/cm
2, temperature is about 474 ℃.If the pressure of the low-pressure air of quoting is 1.75kg/cm
2, temperature is 90.73 ℃, then the engine power loss that causes of high-pressure bleed air is about 8.6 times of low pressure bleed.This is sizable waste.For the passenger plane of cabin ventilation ventilation required air flow much larger than passenger cabin, electronics bay refrigeration required air flow, this waste especially severe that seems.
The parameter of table 2 ram-air
| Flying height H (km) | ??0 | ??11 | ??18 |
| Flight Mach number M | ??0.9 | ??2 | ??2 |
| Atmospheric pressure p H(kg/cm 2) | ??1.033 | ??0.242 | ??0.0809 |
| The ram-air pressure p H *(kg/cm 2) | ??1.747 | ??1.894 | ??0.633 |
| The ram-air pressure ratio | ??1.69 | ??7.82 | ??7.82 |
The object of the present invention is to provide a kind of can the energy that energy and ram-air had that the engine compressor bleed is had being fully utilized, the air circulating plane control system that the coefficient of performance Cop of plane environmental control system is further increased substantially.
The present invention makes full use of the technical scheme of the energy that the engine compressor bleed had, and is engine compressor bleed pressure p
0Inlet pressure p as plane environmental control system
In, atmospheric pressure p
HOutlet pressure p as plane environmental control system
Ex, make the plane environmental control system inlet and outlet pressure compare ε
AEqual the pressure ratio π of engine compressor bleed
0Thereby the energy that the engine compressor bleed is had is used fully.For effectively utilizing the energy that the engine compressor bleed is had, the present invention adopts two stage turboexpansion acting, cooling.The power output of two turbines all sends a compressor to, constitutes a boost type system with compressor of two turbines.In order to adapt to the needs that turbine inlet pressure changes and regulate flow, two turbines all adopt the adjustable variable geometry turbocharger of nozzle sectional area.In order to obtain dry air, constitute the high pressure water separation regenerative air cycle cooling system system with first order turbine and condenser, regenerator and High Pressure Water Separator.For preventing that condenser from freezing, the outlet temperature of first order turbine is not less than 2 ℃ when the low latitude.For the cooling of passenger cabin and electronics bay, the present invention adopts heat exchanger, and the cold air with second level turbine outlet cools off passenger cabin and electronics bay.
Ram-air is used as the low-temperature receiver (heat-absorbing medium) of radiator in plane environmental control system, the temperature that reduces it helps improving the coefficient of performance Cop of plane environmental control system.For this reason, the technical scheme that the present invention makes full use of the energy that ram-air has is to adopt ram-air turbine and compressor to constitute the reverse-bootstrap system, utilizes the energy of ram-air with it, drives the turbocompressor unit, by the turbine expansion acting, reduce the temperature of ram-air.In order to adapt to the needs that ram-air pressure changes and regulate flow, ram-air turbine also adopts the adjustable variable geometry turbocharger of nozzle sectional area.
According to the freeze different characteristics of required air of cabin ventilation ventilation required air and passenger cabin, electronics bay, for cutting the waste, the present invention changes the air that is used for cabin ventilation ventilation merely from the bleed of engine compressor low-pressure stage into, only being used for the cooling air of passenger cabin, electronics bay from the bleed of engine compressor hiigh pressure stage.For the air that is used for passenger cabin, electronics bay refrigeration and cabin ventilation ventilation simultaneously, from the bleed of engine compressor hiigh pressure stage, then take out and infeed passenger cabin from the porch of second level turbine, be used for the cabin ventilation ventilation.
In addition, in order to make full use of energy, the present invention also takes and cooled off the air of discharging after passenger cabin and the electronics bay cold wind source as the primary heat sink of the HTHP bleed of engine compressor.
The present invention can have various specific embodiments.
Accompanying drawing 1 is used for a kind of embodiment of modern fighter plane for the present invention.
Accompanying drawing 2 is used for a kind of embodiment of modern passenger plane for the present invention.
T among the figure
1, T
2, T
3Be turbine, C
a, C
bBe compressor.T wherein
1, T
2, C
aBe a turbocompressor unit, T
3, C
bBe another turbocompressor unit.Number in the figure 1,2,3,5 is air a---air heat exchanger, and 4 is air---liquid heat exchanger, the A among the figure, B
1, B
2, C
1, C
2, C
3, C
4, C
5, D, E be by-pass valve control, f is a check valve, Ra is a ram-air.
Accompanying drawing 1 is that with the difference of accompanying drawing 2 air of the ventilation of the passenger cabin CB in the accompanying drawing 1 is from turbine T
2The porch draw portion of air and infeed passenger cabin, the cold air duct of heat exchanger (4) is then sent in the passenger cabin exhaust, is used for the cooling electronic apparatus cabin.And the air of the ventilation of the passenger cabin CD in the accompanying drawing 2 is the low-pressure stage bleed from engine compressor EC, then utilizes heat exchanger (5) and passenger cabin exhaust to carry out heat exchange, makes its temperature near cabin temperature.In addition, accompanying drawing 1 is identical with accompanying drawing 2, now is described in detail as follows by accompanying drawing 1:
When passenger cabin need cool off, the HTHP air of being drawn by engine compressor EC at first passed through heat exchanger (1), and the cold air of being discharged by heat exchanger (4) cools off, and then enters compressor C
aThe intensification of boosting by heat exchanger (2), is cooled off by ram-air then.The temperature of ram-air is by turbine T
3Compressor C
bThe reverse-bootstrap system that constitutes lowers the temperature, and in this system, ram-air is earlier by turbine T
3Expand and lower the temperature, then pass through the cold air duct of heat exchanger (2), at last by compressor C
bBoost outside the discharge machine of back.Enter by turbine T by the cooled air of heat exchanger (2)
1, the high pressure water separation regenerative air cycle cooling system system that constitutes of regenerator RH, condenser CD and High Pressure Water Separator WE.Undertaken after the decrease temperature and pressure dehumidification dewaters by this system, again by turbine T
2Further decrease temperature and pressure becomes the very low cold air of temperature, is used to cool off passenger cabin CB and electronics bay EL.Wherein a part of cold air cools off passenger cabin recirculation air that is driven by blower fan (6) and the fresh air that infeeds passenger cabin by heat exchanger (3); Cold air that another part cold air and heat exchanger (3) are discharged and passenger cabin exhaust mix then cools off by the liquid of heat exchanger (4) to the circulation cooling electronic apparatus of electronics bay.The cold air of being discharged by heat exchanger (4) is again by the cold air duct of heat exchanger (1), and bleed is cooled off to engine compressor EC hiigh pressure stage, discharges outside the machine then.
System is in service, and engine compressor hiigh pressure stage bleed flow is mainly by changing turbine T
1And T
2The nozzle sectional area control, valve A is standard-sized sheet as a rule, only plays auxiliary control action under a few cases.Cabin temperature is by valve B
1And B
2Control.This moment, valve E closed.The cabin ventilation flow is controlled by valve D.Valve C
1, C
2, C
3, C
4, C
5Control method for the cold air duct of heat exchanger (2) is as follows: when ground or flying speed when very low, open valve C
3, C
5, valve-off C
1, C
4, open and regulate C
2Valve, the high-pressure bleed air of drawing right quantity drives turbine T
3, drive compressor C
b, the cold air duct of heat exchanger (2) is bled, make it to produce the cold air duct flow that closes the symbol needs; In high-speed flight, valve-off C
2, C
3, C
5, open valve C
1, C
4, utilize ram-air to produce the cold air duct flow, utilize the energy drives turbine T of ram-air simultaneously
3, drive compressor C
b,, reduce the temperature of ram-air by the turbine expansion acting.This moment, the cold air duct flow was by changing turbine T
3The nozzle sectional area control.In some low-speed operations, directly quote ram-air if desired, then can valve-off C
2, C
5, open and control valve C
3, make it to produce the cold air duct flow that closes the symbol needs.This moment valve C
1, C
4Open and close, can determine as required.
When passenger cabin need be heated, valve-off B
1, open valve B fully
2, make turbine T
2The cold air duct of the outlet whole inflow heat exchangers of cold air (4).Regulate turbine T simultaneously
1And T
2The nozzle sectional area, make flow meet the needs of electronics bay cooling.Meanwhile open and control valve E, the high temperature air that draws right quantity infeeds passenger cabin, and passenger cabin is heated.This moment, cabin temperature was controlled by valve E.
All controlling organizations are controlled according to will seeking unification of optimum operation by the microcomputer-based intelligent controller.
For feasibility of the present invention and advantage are described, be foundation to adopt existing components and parts, the embodiment of accompanying drawing 1 of the present invention has been carried out designing and calculating.That calculates mainly the results are shown among the table 3.
By table 3 data as can be seen, the performance system Cop that reaches of this system is very high.Compare with present fighter plane environmental control system, at H=0, during M=0.9, Cop has improved about 1.5 times; At H=11km, during M=2, Cop has improved about 2.9 times; At H=18km, during M=2, Cop has improved about 2.8 times.This proves absolutely that under the identical condition of device level, the present invention can improve the coefficient of performance Cop of plane environmental control system significantly, exponentially.This is a major advantage of the present invention.In addition, the present invention also has following advantage:
(1) the present invention can reduce compensatory loss significantly.
Data by engine compressor bleed flow in the table 3 and ram-air flow can be tried to achieve, this system compares with the present fighter plane plane environmental control system with same refrigerating capacity, the compensatory loss that causes by bleed and ram-air, at H=0, during M=0.9, can reduce about 69% approximately; At H=11km, during M=2, can reduce about 83% approximately; At H=18km, during M=2, can reduce about 81% approximately.And increase seldom by the compensatory loss that system weight causes.Therefore generally speaking, remain and reduced compensatory loss significantly.
Table 3 accompanying drawing 1 system's designing and calculating data
(2) the present invention goes for the aircraft of modern high Mach number flight.
Improving flight Mach number is one of developing direction of present generation aircraft, also is that present generation aircraft is different from one of principal character of older aircraft.But the raising of flight Mach number will make ram air temperature improve thereupon.After height arrives to a certain degree, ram-air will no longer be the cold wind source, and radiator can not utilize ram-air to dispel the heat, thereby make system lose refrigerating capacity.Therefore present plane environmental control system can not be suitable for the higher aircraft of flight Mach number.The present invention is then different, and it can utilize the energy drives turbocompressor unit of ram-air, by the turbine expansion acting, the temperature of ram-air is lowered, and makes it still can serve as radiator when high Mach number flight effective cold wind source.For example at H=11km, during M=2, ram air temperature is up to 156 ℃, and by after the turbine cooling, the cold air duct inlet temperature of radiator (2) has only about 4.4 ℃.Therefore, the present invention goes for the aircraft of modern high Mach number flight.Mach number is high more, and advantage of the present invention is obvious more.
(3) feasibility of the present invention is good.
The present invention is not adopted over and does not have now, and needs the device of development again.The adjustable variable geometry turbocharger of nozzle sectional area that the present invention adopts used on Boeing 707 aircrafts.The compressor that the present invention adopts, heat exchanger, High Pressure Water Separator or the like all are employed devices in the present plane environmental control system.There is not special requirement.Therefore, realize that the present invention does not have unsurmountable difficulty, the present invention can realize fully.
Claims (9)
1. air circulating plane environmental control system that makes full use of the energy, it is characterized in that getting the inlet pressure of engine compressor bleed pressure as plane environmental control system, get the outlet pressure of atmospheric pressure as plane environmental control system, make the plane environmental control system inlet and outlet pressure than the pressure ratio that equals the engine compressor bleed and adopt ram-air turbine to utilize the energy of ram-air, reduce ram air temperature.
2. the air circulating plane environmental control system that makes full use of the energy according to claim 1, it is characterized in that energy for effectively utilizing the engine compressor bleed to be had, adopt two stage turboexpansion, acting, cooling, the output work of two turbines all sends a compressor to, constitute a boost type system that forms by compressor of two turbines, and two turbines all adopt the adjustable variable geometry turbocharger of nozzle sectional area.
3. the air circulating plane environmental control system that makes full use of the energy according to claim 1 and 2, it is characterized in that adopting ram-air turbine and compressor to constitute the reverse-bootstrap system, utilize the energy of ram-air with it, drive turbocompressor, do work by turbine expansion, reduce ram air temperature, and ram-air turbine adopts the adjustable variable geometry turbocharger of nozzle sectional area.
4. the air circulating plane environmental control system that makes full use of the energy according to claim 1 and 2, it is characterized in that being used for the air of passenger cabin, electronics bay refrigeration, from the bleed of engine compressor hiigh pressure stage, and be used for the air that cabin ventilation is taken a breath merely, from the bleed of engine compressor low-pressure stage; The air that is used for passenger cabin, electronics bay refrigeration and cabin ventilation ventilation usefulness simultaneously from the bleed of engine compressor hiigh pressure stage, then takes out from turbine porch, the second level and infeeds passenger cabin.
5. the air circulating plane environmental control system that makes full use of the energy according to claim 3, it is characterized in that being used for the air of passenger cabin, electronics bay refrigeration, from the bleed of engine compressor hiigh pressure stage, and be used for the air that cabin ventilation is taken a breath merely, from the bleed of engine compressor low-pressure stage; The air that is used for passenger cabin, electronics bay refrigeration and cabin ventilation ventilation usefulness simultaneously from the bleed of engine compressor hiigh pressure stage, then takes out from turbine porch, the second level and infeeds passenger cabin.
6. the air circulating plane environmental control system that makes full use of the energy according to claim 1 and 2, it is characterized in that, heat exchanger is all adopted in cooling to passenger cabin and electronics bay, cools off passenger cabin and electronics bay with the cold air of second level turbine outlet.
7. the air circulating plane environmental control system that makes full use of the energy according to claim 3, it is characterized in that, heat exchanger is all adopted in cooling to passenger cabin and electronics bay, cools off passenger cabin and electronics bay with the cold air of second level turbine outlet.
8. the air circulating plane environmental control system that makes full use of the energy according to claim 4, it is characterized in that, heat exchanger is all adopted in cooling to passenger cabin and electronics bay, cools off passenger cabin and electronics bay with the cold air of second level turbine outlet.
9. the air circulating plane environmental control system that makes full use of the energy according to claim 5, it is characterized in that, heat exchanger is all adopted in cooling to passenger cabin and electronics bay, cools off passenger cabin and electronics bay with the cold air of second level turbine outlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 95112822 CN1078558C (en) | 1995-12-28 | 1995-12-28 | Air circulating plane environmental control system able to fully utilizing energy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 95112822 CN1078558C (en) | 1995-12-28 | 1995-12-28 | Air circulating plane environmental control system able to fully utilizing energy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1138685A true CN1138685A (en) | 1996-12-25 |
| CN1078558C CN1078558C (en) | 2002-01-30 |
Family
ID=5079783
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 95112822 Expired - Fee Related CN1078558C (en) | 1995-12-28 | 1995-12-28 | Air circulating plane environmental control system able to fully utilizing energy |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1078558C (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390538A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet |
| CN102390536A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Three-wheel pressure-boosting refrigerating and liquid cooling composite thermal energy managing system |
| CN101511675B (en) * | 2006-09-11 | 2012-06-20 | 空中客车德国运营有限责任公司 | Air supply system of an aircraft and method for mixing two air streams in an air supply system |
| CN103723276A (en) * | 2013-12-04 | 2014-04-16 | 中国飞行试验研究院 | Electronic equipment ventilation cooling system based on Y7 aircraft environment control system |
| CN104850153A (en) * | 2015-05-06 | 2015-08-19 | 江苏科技大学 | Stratospheric airship electronic equipment cabin temperature control system and control method |
| CN107303951A (en) * | 2016-04-22 | 2017-10-31 | 哈米尔顿森德斯特兰德公司 | Utilize the environmental control system of enhanced compressor |
| CN108216642A (en) * | 2017-12-06 | 2018-06-29 | 中国科学院工程热物理研究所 | A kind of Reheat-type cooling turbine unit system applied to aircraft pod |
| US10017032B2 (en) | 2016-02-16 | 2018-07-10 | The Boeing Company | Thermal management systems and methods |
| CN109502035A (en) * | 2017-09-14 | 2019-03-22 | 空中客车运营简化股份公司 | A kind of heat-exchange device and aircraft pylon and aircraft |
| US10239624B2 (en) | 2017-02-15 | 2019-03-26 | The Boeing Company | Reverse air cycle machine (RACM) thermal management systems and methods |
| US10399683B2 (en) | 2016-02-16 | 2019-09-03 | The Boeing Company | Thermal management systems and methods |
| CN111332477A (en) * | 2020-02-21 | 2020-06-26 | 中国电子科技集团公司第二十九研究所 | Reverse boosting turbine bypass control device and method |
-
1995
- 1995-12-28 CN CN 95112822 patent/CN1078558C/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101511675B (en) * | 2006-09-11 | 2012-06-20 | 空中客车德国运营有限责任公司 | Air supply system of an aircraft and method for mixing two air streams in an air supply system |
| CN102390538A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet |
| CN102390536A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Three-wheel pressure-boosting refrigerating and liquid cooling composite thermal energy managing system |
| CN103723276A (en) * | 2013-12-04 | 2014-04-16 | 中国飞行试验研究院 | Electronic equipment ventilation cooling system based on Y7 aircraft environment control system |
| CN104850153A (en) * | 2015-05-06 | 2015-08-19 | 江苏科技大学 | Stratospheric airship electronic equipment cabin temperature control system and control method |
| US10399683B2 (en) | 2016-02-16 | 2019-09-03 | The Boeing Company | Thermal management systems and methods |
| US10017032B2 (en) | 2016-02-16 | 2018-07-10 | The Boeing Company | Thermal management systems and methods |
| CN107303951A (en) * | 2016-04-22 | 2017-10-31 | 哈米尔顿森德斯特兰德公司 | Utilize the environmental control system of enhanced compressor |
| US10239624B2 (en) | 2017-02-15 | 2019-03-26 | The Boeing Company | Reverse air cycle machine (RACM) thermal management systems and methods |
| CN109502035A (en) * | 2017-09-14 | 2019-03-22 | 空中客车运营简化股份公司 | A kind of heat-exchange device and aircraft pylon and aircraft |
| CN109502035B (en) * | 2017-09-14 | 2022-04-05 | 空中客车运营简化股份公司 | Heat exchange device, aircraft hanging rack and aircraft |
| CN108216642A (en) * | 2017-12-06 | 2018-06-29 | 中国科学院工程热物理研究所 | A kind of Reheat-type cooling turbine unit system applied to aircraft pod |
| CN111332477A (en) * | 2020-02-21 | 2020-06-26 | 中国电子科技集团公司第二十九研究所 | Reverse boosting turbine bypass control device and method |
| CN111332477B (en) * | 2020-02-21 | 2022-09-20 | 中国电子科技集团公司第二十九研究所 | Reverse boosting turbine bypass control device and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1078558C (en) | 2002-01-30 |
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