CN1078558C - 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
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- CN1078558C CN1078558C CN 95112822 CN95112822A CN1078558C CN 1078558 C CN1078558 C CN 1078558C CN 95112822 CN95112822 CN 95112822 CN 95112822 A CN95112822 A CN 95112822A CN 1078558 C CN1078558 C CN 1078558C
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- 230000007613 environmental effect Effects 0.000 title claims description 37
- 238000001816 cooling Methods 0.000 claims abstract description 19
- 239000007788 liquid Substances 0.000 claims description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 6
- 230000008676 import Effects 0.000 claims 18
- 230000006698 induction Effects 0.000 claims 1
- 230000008450 motivation Effects 0.000 claims 1
- 239000007921 spray Substances 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 2
- 238000009423 ventilation Methods 0.000 description 21
- 239000002699 waste material Substances 0.000 description 5
- 230000001447 compensatory effect Effects 0.000 description 4
- 238000005057 refrigeration Methods 0.000 description 4
- 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
- 230000000694 effects Effects 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
- 230000007246 mechanism Effects 0.000 description 1
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Abstract
The present invention relates to an air cycle type airplane environment control system, which fully utilizes energy resource and belongs to airplane environment control techniques. The present invention is characterized in that the bleed air pressure of an engine compressor is used as the inlet pressure of the airplane environment control system, the atmospheric pressure is used as the outlet pressure of the airplane environment control system, and the ratio of the inlet pressure to the outlet pressure of the airplane environment control system is equal to the pressurization ratio of the bleed air of the engine compressor. The present invention adopts two-stage turbines to carry out expansion, apply work and cooling, the output work of the two turbines is transferred to one compressor, and therefore, a pressure boost type system which is composed of the two turbines and the compressor is formed. The present invention simultaneously adopts a ram air turbine and a compressor to form a reverse pressure boost type system, and utilizes the energy of ram air to reduce the temperature of the 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 High Temperature High Pressure air of being drawn by engine compressor and the ram air of being introduced by atmosphere.
For the High Temperature High Pressure 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 rate of supercharging of air compressor bleed is 15.49.And the inlet pressure of plane environmental control system is the delivery pressure of bleed pressure regulator, and it is limited in 7kg/cm usually
2Below; The delivery 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 rate of supercharging 15.49 of engine compressor bleed.Table 1 provided the rate of supercharging 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 rate of supercharging of engine compressor bleed.And high highly more, degree of utilization is low more.The size of engine compressor bleed rate of supercharging has reflected that driving 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 delivery 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 rate of supercharging 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 high-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 delivery 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 high-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 high-pressure stage bleed was about 10kg/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 |
| Bar 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 rate of supercharging | 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, bar pressure p
HDelivery pressure p as plane environmental control system
Ex, make the plane environmental control system inlet and outlet pressure compare ε
AEqual the rate of supercharging 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 horsepower output of two turbines all sends an air compressor to, constitutes a boost type system with air 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 temperature out 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 H Exch, and the cold air with second stage 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 air compressor to constitute the reverse-bootstrap system, utilizes the energy of ram air with it, drives the turbo-compresser 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 high-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 high-pressure stage, then take out and infeed passenger cabin from the entrance of second stage 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 High Temperature High Pressure 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 air compressor.T wherein
1, T
2, C
aBe a turbo-compresser unit, T
3, C
bBe another turbo-compresser 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 entrance draw portion of air and infeed passenger cabin, the cold air duct of H Exch (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 CB in the accompanying drawing 2 is the low pressure stage bleed from engine compressor EC, then utilizes H Exch (5) and passenger cabin exhaust to carry out interchange of heat, 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 High Temperature High Pressure air of being drawn by engine compressor EC at first passed through H Exch (1), and the cold air of being discharged by H Exch (4) cools off, and then enters air compressor C
aThe intensification of boosting by H Exch (2), is cooled off by ram air then.The temperature of ram air is by turbine T
3Air compressor 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 H Exch (2), at last by air compressor C
bBoost outside the discharge machine of back.By the cooled air admission of H Exch (2) by turbine T
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 recirculated air that is driven by blower fan (6) and the fresh air that infeeds passenger cabin by H Exch (3); Cold air that another part cold air and H Exch (3) are discharged and passenger cabin exhaust mix then cools off by the liquid of H Exch (4) to the circulation cooling electronic machine of electronics bay.The cold air of being discharged by H Exch (4) is again by the cold air duct of H Exch (1), and bleed is cooled off to engine compressor EC high-pressure stage, discharges outside the machine then.
System is in service, and engine compressor high-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 the aux. controls effect 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 H Exch (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 air compressor C
b, the cold air duct of H Exch (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 air 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, C opens and regulates the valves
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.The E that meanwhile opens and regulate the valves, 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 control mechanisms 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 design calculation.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 design computational 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 turbo-compresser unit of ram air, by the turbine expansion acting, the temperature fall of ram air is got off, and makes it still can serve as radiator when high Mach number flight actv. 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 air compressor that the present invention adopts, H Exch, 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. an air circulating plane environmental control system that makes full use of the energy comprises turbine, air compressor, H Exch, pipeline, valve, the induction tract inlet sending and receiving motivation air compressor EC high-pressure stage bleed ports that it is characterized in that the High Temperature High Pressure air of system, the outlet of system connects ambient atmosphere, meets ram-air turbine T with the cold air duct import of the H Exch (2) of ram air Ra cooling down high-temperature high pressure air
3Outlet, ram-air turbine T
3Import connect ram air Ra admission port.
2. the air circulating plane environmental control system that makes full use of the energy according to claim 1 is characterized in that being provided with in the turbo-compresser unit two turbine T
1With T
2With an air compressor Ca, two turbine T
1With T
2All be connected in air compressor Ca by output shaft, their gas channel is connected mutually, and air compressor Ca is at first order turbine T
1Before, second stage turbine T
2At first order turbine T
1Afterwards, constitute the boost type system of an one-level air compressor increasing temperature and pressure two-stage turbine decrease temperature and pressure; And at first order turbine T
1Be provided with the H Exch (1) and (2) of cooling down high-temperature high pressure air in the High Temperature High Pressure airline before; After H Exch and first order turbine T
1Be provided with condenser CD, the High Temperature High Pressure air by-pass passage of CD is connected on first order turbine T before
1Import before, the cold air channel of CD is connected on first order turbine T
1After the outlet, the water separator WE after the CD moisture from coming out to spray into ram air channel; Two turbine T
1With T
2Be 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 is characterized in that ram-air turbine T
3Link to each other with air compressor Cb is coaxial, the cold air duct outlet with the H Exch (2) of ram air cooling down high-temperature high pressure air is connected in air compressor Cb import, and ram-air turbine T
3Adopt 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 is characterized in that, supplies with the steam line import of passenger cabin fresh air, for the less aircraft of air demand, is connected on the second stage turbine T of system
2Induction tract on, the passenger cabin exhaust is connected on cold air channel import to the H Exch (4) of electronics bay EL cooling with pipeline; For the big aircraft of air demand, be connected on the engine compressor EC low pressure stage, the passenger cabin exhaust is carried out interchange of heat by H Exch (5) and the fresh air of supplying with passenger cabin.
5. the air circulating plane environmental control system that makes full use of the energy according to claim 3 is characterized in that supplying with the steam line import of passenger cabin fresh air, for the less aircraft of air demand, is connected on the second stage turbine T of system
2Induction tract on, the passenger cabin exhaust is connected on cold air channel import to the H Exch (4) of electronics bay EL cooling with pipeline; For the big aircraft of air demand, be connected on the engine compressor EC low pressure stage, the passenger cabin exhaust is carried out interchange of heat by H Exch (5) and the fresh air of supplying with passenger cabin.
6. the air circulating plane environmental control system that makes full use of the energy according to claim 1 and 2 is characterized in that second stage turbine T
2The outlet connection and the cold air channel import of the passenger cabin recirculated air H Exch (3) that carries out interchange of heat, the cold air channel outlet of H Exch (3) is connected and the liquid of circulation cooling electronic machine carries out the cold air channel import of the H Exch (4) of interchange of heat, the outlet connection of the cold air channel of H Exch (4) and the High Temperature High Pressure air of system carry out the cold air channel import of the H Exch (1) of interchange of heat, and the cold air channel outlet of H Exch (1) connects ambient atmosphere.
7. the air circulating plane environmental control system that makes full use of the energy according to claim 3 is characterized in that, second stage turbine T
2The outlet connection and the cold air channel import of the passenger cabin recirculated air H Exch (3) that carries out interchange of heat, the cold air channel outlet of H Exch (3) is connected and the liquid of circulation cooling electronic machine carries out the cold air channel import of the H Exch (4) of interchange of heat, the outlet connection of the cold air channel of H Exch (4) and the High Temperature High Pressure air of system carry out the cold air channel import of the H Exch (1) of interchange of heat, and the cold air channel outlet of H Exch (1) connects ambient atmosphere.
8. the air circulating plane environmental control system that makes full use of the energy according to claim 4 is characterized in that, second stage turbine T
2The outlet connection and the cold air channel import of the passenger cabin recirculated air H Exch (3) that carries out interchange of heat, the cold air channel outlet of H Exch (3) is connected and the liquid of circulation cooling electronic machine carries out the cold air channel import of the H Exch (4) of interchange of heat, the outlet connection of the cold air channel of H Exch (4) and the High Temperature High Pressure air of system carry out the cold air channel import of the H Exch (1) of interchange of heat, and the cold air channel outlet of H Exch (1) connects ambient atmosphere.
9. the air circulating plane environmental control system that makes full use of the energy according to claim 5 is characterized in that, second stage turbine T
2The outlet connection and the cold air channel import of the passenger cabin recirculated air H Exch (3) that carries out interchange of heat, the cold air channel outlet of H Exch (3) is connected and the liquid of circulation cooling electronic machine carries out the cold air channel import of the H Exch (4) of interchange of heat, the outlet connection of the cold air channel of H Exch (4) and the High Temperature High Pressure air of system carry out the cold air channel import of the H Exch (1) of interchange of heat, and the cold air channel outlet of H Exch (1) connects ambient atmosphere.
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 CN1138685A (en) | 1996-12-25 |
| CN1078558C true 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) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006042584B4 (en) * | 2006-09-11 | 2008-11-20 | Airbus Deutschland Gmbh | Air supply system of an aircraft and method for mixing two air streams in an air supply system |
| 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 |
| 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 |
| 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 |
| CN104850153B (en) * | 2015-05-06 | 2017-01-11 | 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 |
| US20170305559A1 (en) * | 2016-04-22 | 2017-10-26 | Hamilton Sundstrand Corporation | Environmental control system utilizing enhanced compressor |
| US10239624B2 (en) | 2017-02-15 | 2019-03-26 | The Boeing Company | Reverse air cycle machine (RACM) thermal management systems and methods |
| FR3070967B1 (en) * | 2017-09-14 | 2019-08-30 | Airbus Operations | COMPACT THERMAL EXCHANGE DEVICE INCORPORATED IN AN AIRCRAFT MAT |
| 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 |
| 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 |
-
1995
- 1995-12-28 CN CN 95112822 patent/CN1078558C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN1138685A (en) | 1996-12-25 |
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