GB2076897A - Integrated auxiliary power and environmental control unit - Google Patents

Integrated auxiliary power and environmental control unit Download PDF

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Publication number
GB2076897A
GB2076897A GB8110055A GB8110055A GB2076897A GB 2076897 A GB2076897 A GB 2076897A GB 8110055 A GB8110055 A GB 8110055A GB 8110055 A GB8110055 A GB 8110055A GB 2076897 A GB2076897 A GB 2076897A
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GB
United Kingdom
Prior art keywords
compressor
turbine
environmental control
air
prime mover
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.)
Granted
Application number
GB8110055A
Other versions
GB2076897B (en
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing North American Inc
Original Assignee
Rockwell International Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Rockwell International Corp filed Critical Rockwell International Corp
Publication of GB2076897A publication Critical patent/GB2076897A/en
Application granted granted Critical
Publication of GB2076897B publication Critical patent/GB2076897B/en
Expired legal-status Critical Current

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Classifications

    • 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
    • F02C7/26—Starting; Ignition
    • 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
    • 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
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0611—Environmental Control Systems combined with auxiliary power units (APU's)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/50—Application for auxiliary power units (APU's)
    • 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

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  • 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 Positive-Displacement Air Blowers (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Compressors, Vaccum Pumps And Other Relevant Systems (AREA)

Abstract

The unit comprises a prime mover 4 (auxiliary engine), a variable geometry compressor 22, and controlled emission turbine 24 which is shaft-coupled to the compressor and cooperating with the compressor to form an environmental control unit. In a first operating mode, the prime mover 4 drives the compressor through a gearbox 6 and overrunning clutch 18 and air from the compressor passes through heat exchanger circuits to the turbine and thence to the cabin of a vehicle. In a second mode, when the prime mover 4 is not running, a valve 28 is opened and bleed air from a propulsion engine of the vehicle and cabin recirculation air pass through respective heat exchanger circuits to the turbine and cabin. In a third operating mode, the prime mover drives the compressor and the compressed air therefrom is fed solely to the other aircraft pneumatic equipment, specifically the starters for the main engine. <IMAGE>

Description

SPECIFICATION Integrated auxiliary power and environmental control unit This invention relates to integrated auxiliary power and environmental control units for aircraft and other vehicles.
In large aircraft, it has been the custom to provide an auxiliary power unit, comprising a prime mover driving a compressor, which serves to provide compressed air for powering the recirculating air environmental control unit, or for powering the airplane engine air starters. In passenger planes, it has been customary to also provide an environmental control unit for cooling, heating and pressurization of the passenger compartment. This unit has comprised a turbine which may be driven either by bleed air from the airplane's propulsion engines or by compressed air provided by a separate prime mover (auxiliary power unit). The prime mover mechanically drives a compressor for providing additional air flow to the environmental control unit turbine, to provide both the proper aircraft ventilation rate and contribute a low energy absorption method for the environmental control cycle.Air flow from the environmental control unitturbin is also provided to the aircraft cabin at the desired temperature and pressure. It has been conventional, heretofore, to drive the compressor of the environmental control unit at maximum outputs to provide a maximum flow rate for the limiting heating or cooling condition and adjust the output flow temperature by flow mixing through a temperature control valve. In large passenger planes, it has been customary to provide a plurality of independent environmental control units.
It will be apparent that, where a plurality of independent environmental control units are provided, it is also necessary to provide a corresponding plurality of sensor and control system. It should also be noted that, with the systems of the prior art, it has been necessary to operate each of these environmental control unit compressors at maximum output at all times, regardless of the actual demand, in order to be able to accommodate a range of potential demands. Obviously, this is not energy efficient.
These disadvantages of the prior art are overcome with the present invention which is defined in claim 1. The invention enables the functions of an auxiliary power unit plus a plurality of environmental control units, of the prior art, to be accomplished with substantially improved energy efficiency, reduced complexity, lower operating and maintenance costs and lighter, less expensive equipment.
The preferred embodiment of the present invention comprises an auxiliary power unit comprising a prime mover and a variable geometry compressor shaft-coupled to a controlled emission turbine and which can be driven by bleed air from the plane's propulsion engines or can be connected through an overruning clutch to be driven by the auxiliary engine, the compressor and turbine forming an environmental control unit. When this unit is directly driven by the auxiliary engine, it can serve the needs of both the auxiliary power unit and the environmental control unit. Alternatively, when the plane is in flight, the compressor can be decoupled from the power unit by means of the overruning clutch, and can be driven by bleed air from the plane's propulsion engines to serve the environmental control unit.
It will be seen that a single compressor employed in the present invention replaces two compressors in prior art equipment. This provides substantial reductions in weight and size, which can be translated into greater financial return or reduced requirements for a given payload. In addition, the variable geometry compressor has variable exit vanes which can be adjusted to regulate flow to the turbine to substantially constant pressure, and thereby maintain near peak operating efficiencies. The turbine emission can be controlled by partitioning the flow supply to achieve flow matching with the compressor, to minimize pressure throttling to the turbine and, hence, to maintain near constant pressure over a wide flow operating range. This also permits a portion of the compressor discharge air to be diverted from the turbine for other purposes, such as driving an engine starter motor.In addition, this arrangement enables the environmental control unit to operate at constant speed, near peak design efficiency, throughout most of the operating range.
Consequently, the unit of the present invention is highly energy efficient. The unit can also be compact, light-weight and economical to install and maintain. Moreover, the unit can operate at constant speed, near peak design efficiency, over a wide operating range.
The invention will be described in more detail by way of example, with reference to the accompanying drawing, in which the figure is a diagrammatic representation of an integrated auxiliary power and environmental control unit embodying the present invention.
The figure shows an integrated auxiliary power unit and environmental control unit having an auxiliary engine indicated as a prime mover 4 which drives a gearbox 6 and through the gearbox 6, drives a variety of equipment, such as generator 8, cooling fan 10, fuel pump 12, lubrication pump 14 and overrunning clutch 18. Another overrunning clutch 16 is engageable for the starter 20 to rotate the prime mover 4through the gearbox 6, for starting the prime mover. The clutch 18 is engageable to drive a variable geometry compressor 22 and a controlled emission turbine 24 which are mounted on a common drive shaft 26.
The variable geometry compressor 22 is formed with variable exit diffuser vanes which are adjustable to control the flow area and pressure of air passing into or out of the compressor 22. This permits operation of the compressor 22 at nearly constant pressure and near peak efficiency with low energy utilization, with the prime mover 4 providing minimal drive power or, if the prime mover 4 is inactive, the compressor 22 is driven by a minimal amount of engine bleed air (engine power loss), by opening a valve. If desired, a variable set of com pressor inlet guide vanes can also be added to further reduce the energy utilization of the environmental control unit.Such compressors are components of the Lycoming T55-L1 1 aircraft engine, manufactured by AVCO Lycoming Corporation, Stratford, Connecticut, and as components of engines developed by the National Aeronautics and Space Administration. The controlled emission turbine 24 uses controllable inlet ducting to partition the amount of air flow input to the turbine, while maintaining substantially constant pressure so as to assure operation of the turbine 24 at near peak efficiency. This permits adjustment of the emission from the turbine 24 to match the flow from compressor 22 which minimizes pressure throttling to the turbine and permits maintenance of near constant pressure over a wide flow operating range.
The illustrated valves allow various operating modes to be established. In a first mode the primer mover 4 is running to drive the compressor/turbine for cabin pressurization, cabin recircuiation air and outside air being drawn into the compressor and passed vai the heat exchanges and turbine to the cabin. In a second mode, when the prime mover is not running, the valve 28 is opened and main engine bleed air and cabin recirculation air are passed through the respective heat exchanger circuits and to the cabin. In a third mode, the prime mover 4 drives the compressor which simply comprises outside airforfeeding to other aircraft pneumatic equipment, specifically the main engine starters. The inlet valves to the turbine are closed to prevent air then being taken off via the heat exchanger circuits.
The integrated unit described combines the energy saving features of an energy-efficient, recirculating, environmental control unit and a loadcompressor, auxiliary power unit into a single integrated unit, which can be controlled to expend less energy than a separate environmental control unit and a separate auxiliary power unit, throughout the aircraft mission. Obviously, combining the environmental control unit and auxiliary power unit permits elimination of one compressor, with attendant savings in weight, space, installation and operating costs. Furthermore, shaft coupling of the compressor and turbine is about 98% efficient, while conventional air coupling is only about 80% efficient.

Claims (8)

1. An integrated environmental control and auxiliary power unit for a vehicle having a propulsion engine, the unit comprising an auxiliary engine coupled to a compressor through an overrunning clutch, a turbine, a common drive shaft coupling the compressor and turbine for simultaneous rotation and, means for supplying bleed air from the propulsion engine to drive the coupled compressor and turbine when the auxiliary engine is not running, and means for independently utilizing the output flows from the compressor and the turbine.
2. A unit according to claim 1, wherein the utilizing means include means for feeding air from the compressor to a penumaticstarterforthe propulsion engine.
3. A unit according to claim 1 or 2, wherein the utilizing means include means for feeding air from the turbine to a cabin of the vehicle.
4. A unit according to claim 1,2 or 3, wherein the utilizing means include meansforfeeding airfrom the compressor through at least one heat exchanger circuit to the turbine.
5. A unit according to any of claims 1 to 4, wherein the means for supplying bleed air comprise a heat exchanger circuit for supplying the bleed air to the turbine.
6. A unit according to any of claims 1 to 5, wherein the compressor is a variable geometry compressor.
7. A unit according to claim 6, wherein the turbine is a controlled emission turbine.
8. An integrated environmental control and auxiliary power unit for a vehicle having a propulsion engine substantially as hereinbefore described with reference to and as illustrated in the accompanying drawings.
GB8110055A 1980-06-02 1981-03-31 Integrated auxiliary and environmental control unit Expired GB2076897B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15536980A 1980-06-02 1980-06-02

Publications (2)

Publication Number Publication Date
GB2076897A true GB2076897A (en) 1981-12-09
GB2076897B GB2076897B (en) 1983-06-29

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Family Applications (1)

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GB8110055A Expired GB2076897B (en) 1980-06-02 1981-03-31 Integrated auxiliary and environmental control unit

Country Status (4)

Country Link
JP (1) JPS5758598A (en)
DE (1) DE3121909A1 (en)
FR (1) FR2483356A1 (en)
GB (1) GB2076897B (en)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2127492A (en) * 1982-09-23 1984-04-11 Rockwell International Corp Integrated auxiliary power and environmental control unit
US4665973A (en) * 1984-12-21 1987-05-19 The Garrett Corporation Environmental control system
US4706908A (en) * 1984-10-10 1987-11-17 Duncan Aviation, Inc. Lightweight auxiliary power and forced air supply unit
US4869071A (en) * 1988-03-24 1989-09-26 Sundstrand Corporation Cooling system for an aircraft pod
GB2243408A (en) * 1990-04-02 1991-10-30 Gen Electric Turbine driven compressor for supplying refrigerated air.
GB2243407A (en) * 1990-03-30 1991-10-30 Gen Electric Turbine driven compressor for supplying refrigerated air.
WO1992005351A1 (en) * 1990-09-24 1992-04-02 Allied-Signal Inc. Multifunction integrated power unit and power transfer apparatus therefor
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
US5490645A (en) * 1993-12-09 1996-02-13 Allied-Signal Inc. Fully integrated environmental and secondary power system
US5967461A (en) * 1997-07-02 1999-10-19 Mcdonnell Douglas Corp. High efficiency environmental control systems and methods
US6750557B2 (en) * 2001-09-06 2004-06-15 Energy Transfer Group, L.L.C. Redundant prime mover system
US6776002B1 (en) 2003-04-25 2004-08-17 Northrop Grumman Corporation Magnetically coupled integrated power and cooling unit
US6912451B2 (en) 2001-09-06 2005-06-28 Energy Transfer Group, Llc Control system for a redundant prime mover system
US7305842B1 (en) * 2005-05-23 2007-12-11 Peter Schiff Environmental control system and method for an aircraft
EP2347956A2 (en) * 2008-10-24 2011-07-27 Airbus Operations S.L. Auxiliary power unit (apu) of an aircraft
US20110220759A1 (en) * 2008-09-26 2011-09-15 Airbus Operations Gmbh Power distribution system
FR2976975A1 (en) * 2011-06-22 2012-12-28 Snecma RELAY VENT OF ACCESSORIES, TURBOJET ENGINE COMPRISING SUCH RELAY
EP2772438A1 (en) * 2013-02-28 2014-09-03 Honeywell International Inc. Auxiliary power units (APUs) and methods and systems for activation and deactivation of a load compressor therein
US9605591B2 (en) 2000-10-09 2017-03-28 Energy Transfer Group, L.L.C. Arbitrage control system for two or more available power sources
US10808618B2 (en) 2014-07-03 2020-10-20 General Electric Company Jet engine cold air cooling system
EP3961013A1 (en) * 2020-08-28 2022-03-02 Rolls-Royce plc Modular cabin blower system for aircraft

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3546716C2 (en) * 1984-03-31 1992-10-15 Deutsche Airbus Gmbh, 8000 Muenchen, De Air conditioning power unit for aircraft
DE3509767A1 (en) 1984-03-31 1986-01-02 Deutsche Airbus GmbH, 8000 München Method and device for energy production and air-conditioning fresh-air production in aircraft
DE4320302C2 (en) * 1993-06-18 1996-09-12 Daimler Benz Aerospace Airbus Arrangement for energy generation on board an aircraft, in particular a passenger aircraft
DE19542843C1 (en) * 1995-11-17 1996-12-19 Daimler Benz Aerospace Airbus Reduction of structure heating in supersonic aircraft during flight
US10954865B2 (en) * 2018-06-19 2021-03-23 The Boeing Company Pressurized air systems for aircraft and related methods

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3965673A (en) * 1973-05-19 1976-06-29 Vereinigte Flugtechnische Werke-Fokker Gesellschaft Mit Beschrankter Haftung Apparatus for starting aircraft engines and for operating auxiliary on-board power generating equipment
US4091613A (en) * 1976-07-30 1978-05-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Independent power generator

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2127492A (en) * 1982-09-23 1984-04-11 Rockwell International Corp Integrated auxiliary power and environmental control unit
US4706908A (en) * 1984-10-10 1987-11-17 Duncan Aviation, Inc. Lightweight auxiliary power and forced air supply unit
US4665973A (en) * 1984-12-21 1987-05-19 The Garrett Corporation Environmental control system
US4869071A (en) * 1988-03-24 1989-09-26 Sundstrand Corporation Cooling system for an aircraft pod
GB2243407A (en) * 1990-03-30 1991-10-30 Gen Electric Turbine driven compressor for supplying refrigerated air.
GB2243408A (en) * 1990-04-02 1991-10-30 Gen Electric Turbine driven compressor for supplying refrigerated air.
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
US5201798A (en) * 1990-09-24 1993-04-13 Allied-Signal Inc. Multifunction integrated power unit and power transfer apparatus therefor
WO1992005351A1 (en) * 1990-09-24 1992-04-02 Allied-Signal Inc. Multifunction integrated power unit and power transfer apparatus therefor
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
US5490645A (en) * 1993-12-09 1996-02-13 Allied-Signal Inc. Fully integrated environmental and secondary power system
US5967461A (en) * 1997-07-02 1999-10-19 Mcdonnell Douglas Corp. High efficiency environmental control systems and methods
US9605591B2 (en) 2000-10-09 2017-03-28 Energy Transfer Group, L.L.C. Arbitrage control system for two or more available power sources
US6750557B2 (en) * 2001-09-06 2004-06-15 Energy Transfer Group, L.L.C. Redundant prime mover system
US6912451B2 (en) 2001-09-06 2005-06-28 Energy Transfer Group, Llc Control system for a redundant prime mover system
US7042111B2 (en) 2001-09-06 2006-05-09 Enevsy Transfer Group, Llc System, method and apparatus for a redundant prime mover system
US6776002B1 (en) 2003-04-25 2004-08-17 Northrop Grumman Corporation Magnetically coupled integrated power and cooling unit
US7305842B1 (en) * 2005-05-23 2007-12-11 Peter Schiff Environmental control system and method for an aircraft
US20110220759A1 (en) * 2008-09-26 2011-09-15 Airbus Operations Gmbh Power distribution system
US8672263B2 (en) * 2008-09-26 2014-03-18 Airbus Operations Gmbh Power distribution system
EP2347956A2 (en) * 2008-10-24 2011-07-27 Airbus Operations S.L. Auxiliary power unit (apu) of an aircraft
EP2347956A4 (en) * 2008-10-24 2013-10-23 Airbus Operations Sl Auxiliary power unit (apu) of an aircraft
FR2976975A1 (en) * 2011-06-22 2012-12-28 Snecma RELAY VENT OF ACCESSORIES, TURBOJET ENGINE COMPRISING SUCH RELAY
EP2772438A1 (en) * 2013-02-28 2014-09-03 Honeywell International Inc. Auxiliary power units (APUs) and methods and systems for activation and deactivation of a load compressor therein
US9382910B2 (en) 2013-02-28 2016-07-05 Honeywell International Inc. Auxiliary power units (APUs) and methods and systems for activation and deactivation of a load compressor therein
US10808618B2 (en) 2014-07-03 2020-10-20 General Electric Company Jet engine cold air cooling system
US10815890B2 (en) 2014-07-03 2020-10-27 General Electric Company Jet engine cold air cooling system
EP3961013A1 (en) * 2020-08-28 2022-03-02 Rolls-Royce plc Modular cabin blower system for aircraft

Also Published As

Publication number Publication date
FR2483356B1 (en) 1985-03-22
GB2076897B (en) 1983-06-29
FR2483356A1 (en) 1981-12-04
JPS5758598A (en) 1982-04-08
DE3121909A1 (en) 1982-04-08

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PCNP Patent ceased through non-payment of renewal fee