GB2340890A - Combined environmental control and power system for aircraft - Google Patents
Combined environmental control and power system for aircraft Download PDFInfo
- Publication number
- GB2340890A GB2340890A GB9918609A GB9918609A GB2340890A GB 2340890 A GB2340890 A GB 2340890A GB 9918609 A GB9918609 A GB 9918609A GB 9918609 A GB9918609 A GB 9918609A GB 2340890 A GB2340890 A GB 2340890A
- Authority
- GB
- United Kingdom
- Prior art keywords
- power
- power system
- environmental control
- aircraft
- turbine
- 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.)
- Withdrawn
Links
- 230000007613 environmental effect Effects 0.000 title claims abstract description 33
- 238000001816 cooling Methods 0.000 claims abstract description 33
- 239000000446 fuel Substances 0.000 claims abstract description 22
- 239000012530 fluid Substances 0.000 claims abstract description 9
- 239000000314 lubricant Substances 0.000 claims abstract description 5
- 238000000034 method Methods 0.000 claims description 5
- 230000004044 response Effects 0.000 claims description 2
- 238000010079 rubber tapping Methods 0.000 claims description 2
- 238000009835 boiling Methods 0.000 abstract description 2
- 230000009467 reduction Effects 0.000 description 5
- 230000008901 benefit Effects 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000005461 lubrication Methods 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000000740 bleeding effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- 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
- B64D41/00—Power installations for auxiliary purposes
-
- 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Control Of Turbines (AREA)
Abstract
In a combined environmental control and power system for an aircraft, bleed air bled from the engine 10 is cooled by a heat exchanger 12 and supplied to an expansion turbine 14 where it expands to generate mechanical power and cools to a temperature appropriate for cooling the cockpit and/or avionics equipment. The power generated by the turbine 14 is supplied to the aircraft gearbox 28 where it is combined with that obtained from a power take off 22 which takes mechanical power directly from the engine 10, and is then available to drive various pumps and generators. The turbine air outlet temperature is controlled by a variable ram air inlet 18 to the heat exchanger 12. Fuel may be used to cool hydraulic fluid 42 and a lubricant heat exchanger 44, boiling of the fuel being prevented by first passing through ram air coolers 46. The intercooler and compressor of a conventional cold air unit are not required.
Description
2340890 Combined Environmental Control and Power System For Aircraft This
invention relates to a combined environmental control and power system for an aircraft. The term,,aircraft" embraces aircraft of fixed or rotary wing design 5 and those of variable wing geometry.
Aircraft general systems, which include those for fuel, hydraulics, environmental control, and power generation, receive their power from the main engine powerplant or powerplants. In the case of the environmental control system (ECS), the vast majority of its power is extracted by means of air bled off the engine compressor, and in many typical arrangements most of the energy in the air is wasted after having fulfilled its function for ECS. In addition, the environmental control system and other aircraft general systems often require heat exchangers which utilise external boundary layer air as their heat sink and thus create additional air frame drag which also represents an equivalent engine power offtake.
The normal operation of a conventional environmental control system is achieved by bleeding air from the compression stage of an aircraft main gas turbine powerplant at high temperature and pressure. The pressure is then reduced to the required level (typically 65OkPag) via a pressure regulator and temperature is reduced to the required level (typically 100OC) via a heat exchanger known as a pre- cooler. From the pre-cooler, the air passes through a boot-strap cold air unit, which is a turbo- 2 compressor device with intercooling, to condition the air down to the required temperature and pressure. In such a device, all the power generated by the turbine is used to drive the compressor. System airf low control is achieved by 5 the turbine nozzles.
The power for the fuel, hydraulics and power generation systems is typically extracted from the powerplant or powerplants via a power offtake coupled by a gear assembly to a shaft or spool of the aircraft powerplant. The mechanical power from the power offtake shaft is normally passed by the engine gear box to the aircraft gear box which in turn provides a source of power for the systems, and is normally referred to as the secondary power system. it should be noted that the electrical power required by the is environmental control system, as well as the fuel and hydraulic systems, is provided by an integrated drive generator which receives power from the secondary power system.
In the past, the aircraft general systems have been designed individually to meet their own particular performance requirements. This approach has resulted in adequate individual systems performance without optimising the overall aircraft effectiveness.
We have investigated the design of an arrangement in which the environmental control system and the secondary power system are integrated and we have found that this approach provides several unexpected benefits.
Accordingly, in one aspect of this invention, there is 3 provided a combined environmental control and power system for co- operation with a main gas turbine powerplant on board an aircraft, said system comprising:powerplant bleed means operable in use to tap a supply of pressurised bleed air from said powerplant, a cooling turbine for receiving said pressurised bleed air and expanding it to generate mechanical power and to discharge a supply of relatively cool air for cooling purposes, and drive means coupled to said cooling turbine to transmit said generated mechanical power to a power system, said power system also being coupled to a power offtake means which in use draws mechanical power from said powerplant, said power system further being operable to supply power for is use by other aircraft components.
Relative to conventional arrangements, the above system uses power from the cooling turbine to augment the mechanical power input to the power system, thereby reducing the amount of mechanical power offtake from the powerplant.
Another particularly preferred feature relative to conventional boot-strap cold air units is removal of the compressor and intercooler stages of the cold air unit.
Preferably, said system includes pre-cooler means for cooling said pressurised bleed air prior to delivery to said cooling turbine. The pre-cooler means preferably comprises ram air cooler means adapted to receive ram air during aircraft flight.
Preferably, the ram air cooler means has means for 4 varying the effective inlet area thereof. In a particularly preferred arrangement, the inlet area control means is responsive to a sensed temperature elsewhere on the aircraft (for example at the outlet of the cooling turbine) to control said means for varying the effective inlet area of the ram air inlet cooler to suit a pre-determined temperature requirement. In this manner, the cooling turbine inlet temperature may be controlled to that required to achieve the necessary temperature drop across the turbine. In turn this means that only the required amount of boundary layer ram air cooling flow to pass through the ram air cooling means is captured by the variable area intake. This may result in a further overall drag reduction for the aircraft since the intake area of the pre- cooler means, which in conventional aircraft is fully open during the whole of the aircraft flight, will be partially closed for most, if not all of the flight. An additional advantage of this arrangement is that the variable inlet area means that overcooling of the engine bleed air can be avoided, thereby avoiding the need to provide a further portion of hot engine bleed air downstream of the turbine to restore the temperature level. This minimises the air bleed from the engine.
Preferably, said secondary power system comprises a 25 gear box having respective input shafts connected to said turbine drive means and to said power offtake means, and output means for supplying power to said other aircraft components. As noted above, the power contribution from the cooling turbine reduces that taken from the powerplant via the power offtake means. Another important advantage arising from this arrangement is that by connecting the turbine to a gearbox shared by the power offtake means, the turbine can be regulated to normal operating speeds, thus obviating the need for advanced turbine technology.
The other aircraft components powered by said power system may comprise one or more fuel pumps, hydraulic pumps and electrical generators. In this instance, the system may further include heat exchange means for transferring heat from the hydraulic fluid and/or other circulated fluids such as lubrication oil, to the aircraft fuel, to reduce the temperature of the hydraulic fluid and/or lubrication oil. Dependent on the particular operating regime, the quantity is of heat transferred into the aircraft fuel may be enough to cause the fuel to boil if no counter-measures are taken. Accordingly, the system may further include a ram air cooler means for cooling said fuel. Preferably, said ram air fuel cooler means comprises retractable inlets movable between a deployed position in which they receive boundary layer ram f low and a stowed position in which they do not protrude significantly beyond the aircraft surface.
In another aspect, the invention extends to a method for providing environmental control and power for an aircraft having a main gas turbine powerplant, said method comprising:- tapping a supply of pressurised bleed air fluid from said powerplant; 6 passing said bleed air through a cooling turbine thereby to generate mechanical power and a supply of expanded, cooled, air for cooling purposes; transmitting said generated mechanical power to a power 5 system, said power system also receiving mechanical power direct from said powerplant via a power offtake means, thereby to provide cooling and mechanical power.
Whilst the invention has been described above, it extends to any inventive combination of the features set out above or in the following description.
The invention may be performed in various ways, and an embodiment thereof will now be described by way of example only, reference being made to the accompanying drawing which is a schematic block diagram of a combined environmental control and power system in accordance with this invention.
The arrangement described below with reference to the drawing provides an integrated solution to the reduction of engine power offtake and the airframe drag associated with aircraft general systems. This is achieved by integration of the environmental control system and the secondary power system which centres around connecting the environmental control system cooling turbine to the aircraft gear box to use the turbine power to offset some of the power normally supplied by the powerplant via the power take off shaft. To achieve this requires a fundamental change in the way in which the environmental control system is configured and operated.
7 Referring more specifically to the Figure, engine bleed air is tapped f rom the compressor of the powerplant or engine 10, and supplied to the cooling pass of an environmental control system heat exchanger 12, acting as a pre-cooler. The pre-cooled engine bleed air is then passed to a cooling turbine 14 where it expands and drops in temperature to a level suitable for cooling the cockpit and/or avionics equipment, and generating rotational power via the turbine output shaft 16 at the same time.
In order to utilise the turbine power (typically up to kW), the compression stage of the cold air unit has been removed. To compensate for this, since the pressure ratio of the turbine 14 has to be maintained, the engine bleed air has to be controlled to a substantially higher pressure, is typically 110OkPag. However, because there is no longer a compressor being driven by the turbine 14, the need for intercooling has been removed. Since intercooling is normally via a heat exchanger utilising aircraft boundary layer as the heatsink, the removal of this heat exchanger represents a significant aircraft drag reduction and weight saving.
The turbine outlet temperature is controlled to the required level (typically a nominal SOC) by controlling the inlet temperature to that required to achieve the necessary temperature drop across the cooling turbine 14. This is achieved by providing the environmental control system heat exchanger 12 with a variable area ram air inlet 18 which includes a suitable mechanism, such as a movable scoop 19, to allow the effective ram air inlet area to be adjusted so that only the required amount of ram air cooling flow passes through the environmental control system heat exchanger 12. Downstream of the environmental control system heat exchanger 12 the heated ram air exhausts via a fixed geometry exhaust 20. A power take off 22 is connected in conventional manner to one of the drive shafts or drive spools of the powerplant and supplies power to the engine gearbox 24. The output shaft 26 of the engine gear box 24 is supplied as an input to the aircraft gear box 28 where the power input from the shaft 26 and that from the output shaft 16 of the cooling turbine 14 are combined in conventional manner and distributed between the fuel pump or pumps 30, the hydraulic pump 32, and the integrated drive generator 34. Also shown is the auxiliary power unit 36 which can also supply power to the aircraft gear box 28 as required in the case of main powerplant failure or to act as a starter motor.
It will be noted that the fuel feed on line 38 passes via a hydraulic heat exchanger 40 where it cools hydraulic fluid passing along hydraulic feed pipe 42, and then through a lubricant heat exchanger 44 where it cools lubricant for the engine. The fuel is then passed to the main powerplant.
Depending on the operating regime of the aircraft, the amount of heat dumped into the fuel from the hydraulic heat exchanger 40 and the lubricant heat exchanger 44 may be sufficient to bring the fuel near or beyond boiling point. In this case the fuel system may include one or more air 9 cooled fuel coolers 46 positioned adjacent the aircraft skin and which are cooled by boundary layer ram air but are deployed in response to the fuel temperature so that they are deployed only when necessary, thereby removing the 5 associated drag when they are not required.
The arrangement as described above provides many advantages and opportunities for design improvements. The mechanical power offtake from the engine is reduced due to recovering energy from the cooling turbine. The intercooler and the compressor of the conventional cold air unit are not required and this results in reductions in mass, drag, cost and waste energy. The drag associated with the environmental control system pre-cooler is likely to be lower due to the cooling air inlet only being sufficiently open to meet demand. Accordingly, the preferred embodiment provides an integrated solution to the reduction of engine power offtake and airframe drag associated with aircraft general systems.
Claims (12)
1. A combined environmental control and power system for co-operation with a main gas turbine powerplant on board an aircraft, said system comprising powerplant bleed means operable in use to tap a supply of pressurised bleed air from said powerplant, a cooling turbine for receiving said pressurised bleed air and expanding it to generate mechanical power and to discharge a supply of relatively cool air for cooling purposes, and drive means coupled to said cooling turbine to transmit said generated mechanical power to a power system, said power system also being coupled to a power offtake means which in use draws mechanical power from said powerplant, is said power system further being operable to supply power for use by other aircraft components.
2. A combined environmental control and power system according to Claim 1, including pre-cooler means for cooling said pressurised bleed air prior to delivery to said cooling turbine.
3. A combined environmental control and power system according to Claim 1, wherein said pre-cooler means includes ram air cooler means adapted to receive ram air during aircraft flight.
4. A combined environmental control and power system according to Claim 3, wherein said ram air cooler means has means for varying the effective inlet area thereof.
5. A combined environmental control and power system according to Claim 4, which includesinlet area control means responsive to a sensed temperature elsewhere on the aircraft to vary said means for varying the effective inlet area of said ram air cooler means.
6. A combined environmental control and power system according to any of the preceding Claims, wherein said secondary power system comprises a gearbox having respective input shafts connected to said turbine drive means and said power offtake means and output means for supplying power to said other aircraft components.
7. A combined environmental control and power system according to any of the preceding Claims, wherein said other aircraft components include one or more fuel pumps, a is hydraulic pump, and an electrical generator.
8. A combined environmental control and power system according to Claim 7, which includes heat exchange means for transferring heat from the hydraulic fluid andlor lubricant fluid to the aircraft fuel.
9. A combined environmental control and power system according to Claim 8, wherein said heat exchange means comprise deployable ram air means for being deployed in response to the temperature of the fuel.
10. A method for providing environmental control and power for an aircraft having a main gas turbine powerplant, said method comprising:- tapping a supply of pressurised bleed air fluid from said powerplant; passing said bleed air through a cooling 12 turbine there by to generate mechanical power and a supply of expanded, cooled, air for cooling purposes; transmitting said generated mechanical power to a power system, said power system also receiving mechanical power 5- direct from said powerplant via a power offtake means, thereby to provide cooling and mechanical power.
11. A combined environmental control and power system substantially as hereinbefore described with reference to, and as illustrated in, the accompanying drawing.
12. A method for providing environmental control and power for an aircraft substantially as hereinbefore described with reference to the accompanying drawing.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GBGB9817879.1A GB9817879D0 (en) | 1998-08-18 | 1998-08-18 | Combined environmental control and power system for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB9918609D0 GB9918609D0 (en) | 1999-10-13 |
| GB2340890A true GB2340890A (en) | 2000-03-01 |
Family
ID=10837370
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GBGB9817879.1A Ceased GB9817879D0 (en) | 1998-08-18 | 1998-08-18 | Combined environmental control and power system for aircraft |
| GB9918609A Withdrawn GB2340890A (en) | 1998-08-18 | 1999-08-09 | Combined environmental control and power system for aircraft |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GBGB9817879.1A Ceased GB9817879D0 (en) | 1998-08-18 | 1998-08-18 | Combined environmental control and power system for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (2) | GB9817879D0 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7690595B2 (en) | 2006-12-12 | 2010-04-06 | Lockheed Martin Corporation | System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines |
| RU2464204C2 (en) * | 2007-03-20 | 2012-10-20 | Эйрбас Оперейшнс Гмбх | Aircraft power controller |
| WO2014013201A1 (en) * | 2012-07-20 | 2014-01-23 | Snecma | Device for the transfer of heat between a lubrication pipe and a turbomachine blade pitch actuator control hydraulic pipe |
| US20170081040A1 (en) * | 2015-09-21 | 2017-03-23 | Hamilton Sundstrand Corporation | Heat exchanger and cooling system for generator electronics cooling |
| EP3564128A1 (en) * | 2018-05-02 | 2019-11-06 | Hamilton Sundstrand Corporation | Super-cooled heat exchanger of an air cycle machine |
| US10906663B2 (en) | 2018-07-23 | 2021-02-02 | Textron Innovations Inc. | Apparatus for boundary layer air inlet utilization |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4503666A (en) * | 1983-05-16 | 1985-03-12 | Rockwell International Corporation | Aircraft environmental control system with auxiliary power output |
| US4514976A (en) * | 1980-06-02 | 1985-05-07 | Rockwell International Corporation | Integrated auxiliary power and environmental control unit |
| US5440905A (en) * | 1993-02-12 | 1995-08-15 | Takigen Manufacturing Co. Ltd. | Door locking handle assembly of a pull-out and side-swinging lever-action type |
| US5600965A (en) * | 1996-03-14 | 1997-02-11 | Solar Turbines Incorporated | Air conditioning system |
-
1998
- 1998-08-18 GB GBGB9817879.1A patent/GB9817879D0/en not_active Ceased
-
1999
- 1999-08-09 GB GB9918609A patent/GB2340890A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4514976A (en) * | 1980-06-02 | 1985-05-07 | Rockwell International Corporation | Integrated auxiliary power and environmental control unit |
| US4503666A (en) * | 1983-05-16 | 1985-03-12 | Rockwell International Corporation | Aircraft environmental control system with auxiliary power output |
| US5440905A (en) * | 1993-02-12 | 1995-08-15 | Takigen Manufacturing Co. Ltd. | Door locking handle assembly of a pull-out and side-swinging lever-action type |
| US5600965A (en) * | 1996-03-14 | 1997-02-11 | Solar Turbines Incorporated | Air conditioning system |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7690595B2 (en) | 2006-12-12 | 2010-04-06 | Lockheed Martin Corporation | System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines |
| RU2464204C2 (en) * | 2007-03-20 | 2012-10-20 | Эйрбас Оперейшнс Гмбх | Aircraft power controller |
| US8403258B2 (en) | 2007-03-20 | 2013-03-26 | Airbus Operations Gmbh | Power regulating device for an aircraft |
| WO2014013201A1 (en) * | 2012-07-20 | 2014-01-23 | Snecma | Device for the transfer of heat between a lubrication pipe and a turbomachine blade pitch actuator control hydraulic pipe |
| FR2993607A1 (en) * | 2012-07-20 | 2014-01-24 | Snecma | THERMAL TRANSFER DEVICE BETWEEN A LUBRICATION CHANNEL AND A TURBOMACHINE BLADE SETTING CYLINDER CONTROL HYDRAULIC PIPE |
| GB2519478A (en) * | 2012-07-20 | 2015-04-22 | Snecma | Device for the transfer of heat between a lubrication pipe and a turbomachine blade pitch actuator control hydraulic pipe |
| US20170081040A1 (en) * | 2015-09-21 | 2017-03-23 | Hamilton Sundstrand Corporation | Heat exchanger and cooling system for generator electronics cooling |
| EP3564128A1 (en) * | 2018-05-02 | 2019-11-06 | Hamilton Sundstrand Corporation | Super-cooled heat exchanger of an air cycle machine |
| US10526971B2 (en) | 2018-05-02 | 2020-01-07 | Hamilton Sundstrand Corporation | Super-cooled heat exchanger of an air cycle machine |
| US10906663B2 (en) | 2018-07-23 | 2021-02-02 | Textron Innovations Inc. | Apparatus for boundary layer air inlet utilization |
Also Published As
| Publication number | Publication date |
|---|---|
| GB9918609D0 (en) | 1999-10-13 |
| GB9817879D0 (en) | 1998-10-14 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |