WO2005063564A2 - Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system including such an air guiding flap - Google Patents
Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system including such an air guiding flap Download PDFInfo
- Publication number
- WO2005063564A2 WO2005063564A2 PCT/EP2004/014856 EP2004014856W WO2005063564A2 WO 2005063564 A2 WO2005063564 A2 WO 2005063564A2 EP 2004014856 W EP2004014856 W EP 2004014856W WO 2005063564 A2 WO2005063564 A2 WO 2005063564A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- flap
- air
- ram air
- ram
- pressure
- Prior art date
Links
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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
Definitions
- Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system including such an air guiding flap
- the present invention relates to air guiding flaps of aircraft, particularly aeroplanes, and a ram air system including such an air guiding flap.
- the present invention relates to a ram air escape flap, however the basic principle of the present invention is applicable to any air guiding flap.
- Air guiding flaps on aircraft can be exposed to strong aerodynamic forces particularly in the event that they are disposed on the outside of an aircraft and exposed to the pressure of the relative wind flowing past the aeroplane.
- This relates for example to the ram air escape flap of a ram air system which is part of a fresh air generating system of an aircraft.
- the fresh air feeding to an aircraft cabin is normally generated by guiding hot engine air known as bleed air through an air conditioning unit for the purpose of cooling and afterwards feeding it to the aircraft cabin at the desired temperature and at the desired pressure.
- air conditioning unit As a cooling medium for the air conditioning unit outside air is employed which outside air flows during the flight through a ram air intake flap disposed on the aircraft into a ram air duct out of which the ram air then flows through the air conditioning unit and finally to a ram air escape flap through which the now warmer ram air leaves the aircraft again.
- By changing the position of the ram air escape flap the quantity of cooling air that flows through the air conditioning unit is controlled. In the event that more cooling air is required the ram air escape flap is forcibly opened accordingly.
- the enlargement of the intake opening of the ram air duct is brought about by means of a forcible opening of the ram air intake flap.
- the ram air escape flap is accordingly forcibly closed followed by forcibly closing the ram air duct intake flap.
- the object of the invention is to provide a solution to the problem cited above wherein by means of the use of an air guiding flap embodied as a ram air escape flap the advantages of the presence of a ram air escape flap, namely reduced air resistance of an aircraft and increased potential performance of an air conditioning unit, are obtained without negatively influencing the production and operating costs.
- an actuator for automatically opening and closing of the air guiding flap which actuator cooperates with an arrangement for controlling the position of the air guiding flap
- the object in accordance with the invention is achieved by the presence of a force detecting arrangement which detects the force impinging on the actuator based on a difference between the prevailing pressure in the air duct and the pressure of the relative wind flowing past the aircraft and wherein the controlling arrangement adjusts the position of the air guiding flap such that the force impinging on the actuator at any one time is at least approaching zero.
- the air guiding flap according to the invention is always adjusted such as to avoid excessive forces impinging thereon and further that the forces of pressure impinging on its two sides, i.e. the dynamic pressure brought about by the relative wind on the one hand and the dynamic pressure in the duct on the other substantially cancel one another out.
- the force impinging on the actuator is slight or not present at all.
- the actuator and the force impinging thereon are not significant and rather that only the measurement of the force impinging on the actuator serves as a directly correlated measurement of the stress of the air guiding flap.
- the position of the air guiding flap is controlled according to the principle of aerodynamically balanced forces.
- an air guiding flap thus embodied is used as a ram air escape flap of a fresh air generating system for an aircraft the problems outlined at the outset with reference to such a system are solved. Therefore, with a preferred embodiment of the invention the air guiding flap is a ram air escape flap and the pressure in the air duct is a dynamic pressure.
- the ram air escape flap is forcibly closed in the event that the force of pressure of the relative wind flowing past the aircraft impinging thereon is greater than the force of pressure of the dynamic pressure in the air duct impinging thereon until at least an approaching equilibrium of the said force of pressures has ensued.
- the air guiding flap is again a ram air escape flap and the pressure in the air duct is a dynamic pressure.
- the ram air escape flap is forcibly opened in the event that the force of pressure of the relative wind flowing past the aircraft impinging thereon is less than the force of pressure of the dynamic pressure in the air duct impinging thereon until at least an approaching equilibrium of the said force of pressures has ensued.
- a ram air system for the purpose of supplying an auxiliary assembly of an aircraft with ram air
- ram air system comprises a ram air duct having an intake opening and an escape opening and from which ram air duct is taken the required ram air for the auxiliary assembly and further comprises a ram air intake flap controlling the flow cross section of the intake opening and a ram air escape flap controlling the flow cross section of the escape opening, wherein in accordance with the invention the quantity of the required ram air for the auxiliary assembly is controlled by opening or closing the ram air intake flap and further that the ram air escape flap is an air guiding flap in accordance with one of the exemplified embodiments described above.
- the auxiliary assembly is in accordance with a preferred embodiment a fresh air generating device of an aircraft.
- a fresh air generating device serves to bring the air feeding into the cockpit and the cabin of the aircraft to cabin pressure and to a desired temperature and preferably in this case the control parameter for the position of the ram air intake flap is the temperature at the output of the compressor (also described as an air washbox or turbo cooler) of the fresh air generating device.
- the control is brought about in the case of a preferred embodiment such that the ram air intake flap is forcibly opened when the compressor output temperature exceeds a predetermined temperature value. Should the compressor output temperature fall short of a predetermined temperature value the ram air intake flap is forcibly closed.
- the aforementioned predetermined temperature value can be one and the same temperature value although a temperature value can also be determined the exceeding of which can cause the ram air intake flap to be forcibly opened and a further temperature value can be determined the falling short of which can cause the ram air intake flap to be forcibly closed.
- the quantity of required ram air is therefore adjusted and/or controlled by changing the flow cross section of the ram air duct intake opening.
- the flow cross section of the ram air duct intake opening is enlarged (by forcible opening of the ram air intake flap) this leads to an increase of the force of pressure exerted on the ram air duct-facing surface of the ram air escape flap.
- the ram air escape flap is forcibly opened in order to reduce the flow resistance for the air flowing through the ram air duct.
- the forcible opening of the ram air escape flap is realised until the ram air escape flap is equilibrated with respect to forces, i.e. until the dynamic pressure in the ram air duct complies at least substantially with the dynamic pressure exerted on the ram air escape flap by the relative wind from outside.
- the ram air intake flap is accordingly forcibly closed.
- the dynamic pressure thereby reduces and consequently the force exerted on the inside of the ram air escape flap.
- the ram air escape flap is forcibly closed until an equilibrium of the aerodynamic flow forces impinging on the ram air escape flap is achieved.
- the forcible closing of the ram air escape flap reduces the flow resistance of the aircraft and thereby contributes to the saving of fuel.
- the present invention thus relates to a process for controlling the position of an air guiding flap of an aircraft characterised in that the position of the air guiding flap is always controlled such that the aerodynamic forces impinging on an inner side and an outer side of the air guiding flap are at least approaching equilibrium.
- Figure 1 shows a perspective view of a fresh air generating system of an aircraft wherein an air guiding flap according to the invention is employed as an air escape flap which air guiding flap is position-controlled according to the process in accordance with the invention
- Figure 2 shows a schematic sectional view of the fresh air generating system from Figure 1.
- FIG. 1 is illustrated, designated in general with 10, a fresh air generating system for an aircraft.
- the fresh air generating system 10 serves for the preparation of air to be fed to an aircraft cabin.
- hot air from the engine or engines of the aircraft (or also from an auxiliary turbine of the aircraft) is bled off and guided through a bleed air intake 12 into the fresh air generating system 10.
- the bleed air has a temperature of around 200°C and is depressurized and cooled in the fresh air generating system 10.
- outside air is employed which outside air is available during the flight as ram air and which can be fed by means of a ram air system 14 to the fresh air generating system 10.
- the ram air system 14 comprises a ram air duct 16 with a ram air duct intake opening 18 and a ram air duct escape opening 20.
- a diffuser 22 which in the present case is laterally disposed on the ram air duct 16 distributes the ram air serving as cooling air over the surface of heat exchangers of the fresh air generating system 10 for the purpose of cooling the hot bleed air.
- the cooling air quantity flowing through the ram air duct 16 during the flight is always kept as low as possible.
- the controlling of the cooling air quantity is part of a temperature controller of the fresh air generating system 10.
- Control parameter is the temperature at the output of a compressor of the fresh air generating system 10 which compressor is controlled to a predetermined value during the flight, for example to 180°C. Should the compressor output temperature rise above this value the cooling air quantity flowing through the ram air duct 16 must be increased. Should the compressor output temperature fall below this value the cooling air quantity must be reduced.
- a ram air intake flap 24 and a ram air escape flap 26 are provided.
- the flow cross section of the ram air duct intake opening 18 can be changed from a value of zero (closed position of the ram air intake flap) up to a maximum value (open position of the ram air intake flap).
- the flow cross section of the ram air duct escape opening 20 can be adjusted.
- the ram air escape flap 26 is disposed in or near the outer skin of the aircraft body and has one surface 28 facing the ram air duct 16 and designated as an inner side, which inner side is exposed to the prevailing dynamic pressure in the ram air duct 16, and further an opposite surface 30 designated as an outer side which is exposed to the pressure of the relative wind flowing past the aircraft.
- An actuator 32 serves to change the position of the ram air intake flap 24 while the position of the ram air escape flap 26 is changeable by means of an actuator 34.
- the ram air intake flap 24 is forcibly opened slightly with the aid of the actuator 32 in order to enlarge the flow cross section of the ram air intake opening 18.
- the greater cooling air quantity flowing via the thus enlarged intake cross section into the ram air duct 16 increases the dynamic pressure in the ram air duct 16 and thereby the force acting on the inner side 28 of the ram air intake flap 26.
- the actuator 34 is provided with a force detecting device 36 which force detecting device 36 detects the force impinging on the actuator 34 due to a difference between the prevailing pressure in the ram air duct 16 and the pressure of the relative wind flowing past the aircraft.
- the force detecting device 36 is coupled to a control whose objective it is to always adjust the ram air escape flap 26 for the purpose of avoiding high stresses such that the aerodynamic flow forces impinging on the inner side 28 and the outer side 30 of the ram air escape flap 26 are at least approaching equilibrium. Should therefore the greater cooling air quantity obtained via the further opened ram air intake flap 24 lead to a dynamic pressure in ram air duct 16 which dynamic pressure exceeds the relative wind pressure impinging on the outer side 30 of the ram air escape flap 26 the ram air intake flap 26 shall be controllably forcibly opened until the force impinging on the actuator 34 is at least approaching zero, i.e. until the cited force equilibrium has at least substantially ensued.
- the forcible opening of the ram air escape flap 26 reduces namely the flow resistance of the ram air duct 16 and more precisely of its ram air escape flap 20 such that the dynamic pressure in ram air duct 16 lowers.
- the cooling air quantity flowing through the ram air duct 16 must be reduced. This occurs by means of a controlled closing of the ram air intake flap 24 whereby the flow cross section of the ram air duct intake opening 18 is reduced.
- the dynamic pressure in the ram air duct 16 also falls and consequently the force impinging on the inner side 28 of the ram air escape flap 26.
- the ram air escape flap 26 is thus forcibly closed until the force impinging on the actuator 34 is at least approaching zero, which is synonymous with an at least substantially present force equilibrium between the aerodynamic pressure forces impinging on the inner side 28 and the outer side 30 of the ram air escape flap 26.
- the required cooling air quantity for this system can be controlled within wide limits with minimised effect on the overall flow resistance of the aircraft.
- the ram air escape flap 26 that is controlled as described comprises due to low stresses a good operating reliability and a long service life.
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/582,567 US7543777B2 (en) | 2003-12-30 | 2004-12-30 | Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system including such an air guiding flap |
CA2551932A CA2551932C (en) | 2003-12-30 | 2004-12-30 | Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system includingsuch an air guiding flap |
JP2006546120A JP4635012B2 (en) | 2003-12-30 | 2004-12-30 | Aircraft air guide flap having a control device for controlling the pressure applied to the air guide flap, a method for adjusting the position of the air guide flap, and a ram air device including such an air guide flap |
BRPI0418197-2A BRPI0418197A (en) | 2003-12-30 | 2004-12-30 | aircraft air guide flap, dynamic air system, and process for controlling the position of an aircraft air guide flap |
EP04804441A EP1699697B1 (en) | 2003-12-30 | 2004-12-30 | Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system including such an air guiding flap |
DE602004009473T DE602004009473T2 (en) | 2003-12-30 | 2004-12-30 | AIRFLOW FLAP OF AN AIRCRAFT WITH CONTROLLING THE PRESSURIZED IMPACTING FORCEPS, METHOD FOR ADJUSTING THE POSITION OF AN AIRFLOW FLOW, AND LUBRICATION SYSTEM WITH SUCH AN AIRFLOW FLAP |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10361644.6 | 2003-12-30 | ||
DE10361644A DE10361644B4 (en) | 2003-12-30 | 2003-12-30 | Air deflector of an aircraft with regulation of the compressive forces acting on it, and ram air system with such a spoiler |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2005063564A2 true WO2005063564A2 (en) | 2005-07-14 |
WO2005063564A3 WO2005063564A3 (en) | 2005-09-22 |
Family
ID=34716237
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2004/014856 WO2005063564A2 (en) | 2003-12-30 | 2004-12-30 | Air guiding flap of an aircraft comprising control of the pressure forces impinging thereon, process for adjusting the position of an air guiding flap and ram air system including such an air guiding flap |
Country Status (9)
Country | Link |
---|---|
US (1) | US7543777B2 (en) |
EP (1) | EP1699697B1 (en) |
JP (1) | JP4635012B2 (en) |
CN (1) | CN100484836C (en) |
BR (1) | BRPI0418197A (en) |
CA (1) | CA2551932C (en) |
DE (2) | DE10361644B4 (en) |
RU (1) | RU2375261C2 (en) |
WO (1) | WO2005063564A2 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009064288A1 (en) | 2007-11-13 | 2009-05-22 | The Boeing Company | Cabin air and heat exchanger ram air inlets for aircraft environmental control systems, and associated method of use |
US8978628B2 (en) | 2013-06-06 | 2015-03-17 | The Boeing Company | Engine cooling system |
US9650147B2 (en) | 2008-05-30 | 2017-05-16 | Airbus Operations Gmbh | Device and method for cooling exhaust air of aircraft air-conditioning systems |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102005053696B4 (en) * | 2005-11-10 | 2009-05-14 | Airbus Deutschland Gmbh | Emergency ram air inlet flap of an aircraft |
DE102007019820B4 (en) * | 2007-04-26 | 2012-03-08 | Airbus Operations Gmbh | Cooling system through boundary layer extraction |
FR2928900B1 (en) * | 2008-03-20 | 2010-03-19 | Airbus France | DEVICE FOR REDUCING INFRARED EMISSIONS OF A TURBOPROPULSER. |
DE102008017962B4 (en) * | 2008-04-08 | 2012-09-06 | Eurocopter Deutschland Gmbh | Apparatus for supplying combustion air to an engine of an aircraft |
DE102009017040B4 (en) * | 2009-04-09 | 2017-02-09 | Airbus Operations Gmbh | Resistance-optimized ram air channel and method for controlling an ambient air mass flow through a ram air channel |
DE102009017039A1 (en) * | 2009-04-09 | 2010-10-21 | Airbus Deutschland Gmbh | ram air outlet |
DE102009043797A1 (en) * | 2009-09-30 | 2011-03-31 | Airbus Operations Gmbh | Ram air duct flap arrangement and ram air duct |
DE102011011879A1 (en) * | 2011-02-21 | 2012-08-23 | Airbus Operations Gmbh | Cooling air inlet, engine bleed air system and method for operating a cooling air inlet |
KR101525545B1 (en) * | 2013-06-28 | 2015-06-04 | 퍼스텍주식회사 | Environment Control Unit and Pod System for Airplane Electronic Device therewith |
DE102015113517B4 (en) * | 2015-08-17 | 2023-05-25 | Minebea Mitsumi Inc. | Method for controlling a motorized flap drive and flap drive for adjusting a fluid flow |
Citations (3)
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FR886438A (en) * | 1938-08-27 | 1943-10-14 | Versuchsanstalt Fu R Luftfahrt | Adjusting device for airplanes |
FR942092A (en) * | 1942-08-21 | 1949-01-28 | Constructions Aeronautiques Sudest | Arrangement of radiators on aircraft |
US6272838B1 (en) * | 1999-02-25 | 2001-08-14 | Alliedsignal, Inc. | Method and apparatus for controlling the inlet duct leading to an auxiliary power unit |
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GB945862A (en) * | 1961-08-18 | 1964-01-08 | Rolls Royce | Gas turbine by-pass engines |
FR1325056A (en) * | 1962-03-15 | 1963-04-26 | Nord Aviation | Improvements to turbojet-ramjet combinations |
US4064692A (en) * | 1975-06-02 | 1977-12-27 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable cycle gas turbine engines |
FR2630182B1 (en) | 1988-04-18 | 1990-09-07 | Abg Semca | VALVE WITH A VALVE AND A VALVE COMPRISING A VALVE AS WELL AS AN AIRCRAFT COMPRISING SUCH A VALVE |
US4991795A (en) * | 1989-01-17 | 1991-02-12 | The Boeing Company | Two-stage supersonic inlet |
DE10119433C1 (en) * | 2001-04-20 | 2002-08-22 | Liebherr Aerospace Gmbh | Ram air duct for an aircraft air conditioning system |
DE10201426B8 (en) * | 2002-01-16 | 2004-09-02 | Liebherr-Aerospace Lindenberg Gmbh | Cooling system |
-
2003
- 2003-12-30 DE DE10361644A patent/DE10361644B4/en not_active Expired - Fee Related
-
2004
- 2004-12-30 US US10/582,567 patent/US7543777B2/en not_active Expired - Fee Related
- 2004-12-30 CN CNB2004800395585A patent/CN100484836C/en not_active Expired - Fee Related
- 2004-12-30 JP JP2006546120A patent/JP4635012B2/en not_active Expired - Fee Related
- 2004-12-30 EP EP04804441A patent/EP1699697B1/en not_active Expired - Fee Related
- 2004-12-30 DE DE602004009473T patent/DE602004009473T2/en active Active
- 2004-12-30 BR BRPI0418197-2A patent/BRPI0418197A/en not_active IP Right Cessation
- 2004-12-30 RU RU2006122214/11A patent/RU2375261C2/en not_active IP Right Cessation
- 2004-12-30 WO PCT/EP2004/014856 patent/WO2005063564A2/en active IP Right Grant
- 2004-12-30 CA CA2551932A patent/CA2551932C/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR886438A (en) * | 1938-08-27 | 1943-10-14 | Versuchsanstalt Fu R Luftfahrt | Adjusting device for airplanes |
FR942092A (en) * | 1942-08-21 | 1949-01-28 | Constructions Aeronautiques Sudest | Arrangement of radiators on aircraft |
US6272838B1 (en) * | 1999-02-25 | 2001-08-14 | Alliedsignal, Inc. | Method and apparatus for controlling the inlet duct leading to an auxiliary power unit |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009064288A1 (en) | 2007-11-13 | 2009-05-22 | The Boeing Company | Cabin air and heat exchanger ram air inlets for aircraft environmental control systems, and associated method of use |
US9650147B2 (en) | 2008-05-30 | 2017-05-16 | Airbus Operations Gmbh | Device and method for cooling exhaust air of aircraft air-conditioning systems |
US8978628B2 (en) | 2013-06-06 | 2015-03-17 | The Boeing Company | Engine cooling system |
US9328650B2 (en) | 2013-06-06 | 2016-05-03 | The Boeing Company | Engine cooling system |
Also Published As
Publication number | Publication date |
---|---|
JP2007516892A (en) | 2007-06-28 |
DE602004009473D1 (en) | 2007-11-22 |
DE10361644B4 (en) | 2008-08-07 |
DE602004009473T2 (en) | 2008-02-07 |
CN100484836C (en) | 2009-05-06 |
RU2006122214A (en) | 2008-02-10 |
WO2005063564A3 (en) | 2005-09-22 |
CA2551932C (en) | 2010-09-21 |
JP4635012B2 (en) | 2011-02-16 |
RU2375261C2 (en) | 2009-12-10 |
CN1902093A (en) | 2007-01-24 |
DE10361644A1 (en) | 2005-08-11 |
CA2551932A1 (en) | 2005-07-14 |
US7543777B2 (en) | 2009-06-09 |
EP1699697B1 (en) | 2007-10-10 |
BRPI0418197A (en) | 2007-06-26 |
EP1699697A2 (en) | 2006-09-13 |
US20070145186A1 (en) | 2007-06-28 |
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