WO2009144345A1 - Configuración de la instalación neumática en la zona de cola de un avión - Google Patents
Configuración de la instalación neumática en la zona de cola de un avión Download PDFInfo
- Publication number
- WO2009144345A1 WO2009144345A1 PCT/ES2009/070109 ES2009070109W WO2009144345A1 WO 2009144345 A1 WO2009144345 A1 WO 2009144345A1 ES 2009070109 W ES2009070109 W ES 2009070109W WO 2009144345 A1 WO2009144345 A1 WO 2009144345A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- conduction
- apu
- pneumatic
- area
- plane
- Prior art date
Links
- 238000009434 installation Methods 0.000 claims description 16
- 239000003381 stabilizer Substances 0.000 claims description 10
- 238000004378 air conditioning Methods 0.000 claims description 9
- 230000003014 reinforcing effect Effects 0.000 claims 1
- 206010016256 fatigue Diseases 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000001010 compromised effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000001052 transient effect Effects 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
Definitions
- the present invention refers to the structure of the pneumatic air conditioning installation in the tail area of an airplane; which aims to provide a new structure that allows to reduce the length of the pneumatic installation conduction and eliminate the elbows that said conduction presents in the tail area of an airplane, so that the installation has a lower cost, a lower weight , and lower pressure losses in driving.
- the invention is applicable in any type of passenger aircraft, and more specifically it is part of the development of the new generation of double-aisle and long-range aircraft that are increasingly equipped with more and in turn more complex systems, so that demand increasing energy for its operation.
- airplanes include a pneumatic air conditioning installation comprising an auxiliary power unit (APU) that is determined by an auxiliary engine that is responsible for starting the main engines of the aircraft, as well as supplying electrical and pneumatic power to the airplane systems while the main engines are off.
- APU auxiliary power unit
- the joint use of the APU with the main engines is also contemplated when an extra power input is required.
- This engine is traditionally located in the rear tail cone of the plane, or also known as section 19.1. Its operation is that of a jet engine, although smaller than the main ones.
- the electrical energy is obtained by a generator driven by the motor shaft itself, and the mechanical energy is obtained by means of an air bleed of the first compression stages that circulates through it and that is absorbed from the outside of the aircraft.
- pneumatic driving incorporates elements of movement compensation that may have driving, movement that is more critical the closer we are to the APU, since being a motor the vibrations are transmitted to the driving, especially in transient regimes or malfunction. Therefore it is necessary to compensate the movements of the APU so that they are not transmitted to the conduction, which could result in failures or fatigue breakages. Therefore, the design of the pneumatic installation in the area of the tail of the plane is especially delicate, since the APU is located there.
- the invention has developed a new structure of the pneumatic air conditioning installation in the tail area of an aircraft, which, like conventional ones, is equipped with an auxiliary power unit ( APU) of pneumatic and electrical power supply, whose pneumatic power output is connected to a conduction that before reaching the area of the pressurized passenger cabin is located at the bottom of the plane; counting the conduction with thermal expansion compensation and vibration compensation elements that the APU produces in its operation.
- APU auxiliary power unit
- the novelty of the invention is that the output of the power of the APU is arranged in its front part in which the conduit which is constituted by a straight tube inclined and descending towards the front part of the plane is connected.
- the thermal expansion and vibration compensation elements produced by the APU are interposed in said tube, so that by means of this new structure the length of the pneumatic conduction is considerably reduced and the elbows that are conventionally incorporated into the same.
- This new configuration has the great advantage that pressure losses are considerably reduced, by avoiding elbows in such a critical area and reducing the length of the conduction, and therefore friction. It also has a lower complexity by reducing the number of necessary elements in the installation, while reducing the weight and cost of the installation.
- Figure 1. Shows a schematic side view of an airplane in which a conventional structure of the pneumatic air conditioning installation has been included.
- Figure 2. Shows a plan view of the previous figure.
- Figure 3. Shows a conventional schematic view of the area of the conduit leaving the APU.
- Figure 4. Shows a schematic side representation of a possible embodiment of the structure of the invention. DESCRIPTION OF THE PREFERRED EMBODIMENT
- the facilities pneumatic air conditioning in the area of the tail of the plane comprise an APU 1, whose upper part has an air outlet in which a conduit 2 is connected that initially runs through the top of the plane, and that has to be located in the lowest part of the plane before reaching the area of the pressurized passenger cabin 3.
- APU 1 whose upper part has an air outlet in which a conduit 2 is connected that initially runs through the top of the plane, and that has to be located in the lowest part of the plane before reaching the area of the pressurized passenger cabin 3.
- a reinforcement frame 4 that has to support the weight of the vertical plane 9 , so that its upper section 4a is much larger than its lower section 4b.
- conduit 2 has a considerable diameter, so there is little space to allow the conduction 2 to be lowered to the lower area of the plane, which determines that in the majority of the state of the art the conduction 2 runs along the part top of the plane passing over the tail stabilizer 5. For this it is necessary to practice some trades in the upper section 4a of the frame 4 so that the passage of the conduit 2 is allowed.
- the invention has developed a new structure in which it is envisaged that the power output of the APU 1 is arranged in its front part for which it is necessary to redesign the APU 1, so that the conduction is connected over the same, which allows the conduction to be constituted by a straight and inclined downward tube 2a towards the front part of the plane, so that it reaches the frame 4 by its lower part, which determines that the conduit 2 can pass through the lower part of the opening of the frames 4, that is, on the upper edge of the lower section 4b of the frame 4, the lower section 4b being much smaller than the upper section 4a of the frame 4, as already It was noted, so that the new arrangement of the invention does not affect the structure of the frame 4 and allows the passage through the bottom of the horizontal stabilizer 5 without having to incorporate tion of elbows 7.
- the thermal expansion compensation and compensation elements 6 are interleaved to preserve the tube 2a from being able to suffer fatigue breakage.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
- Duct Arrangements (AREA)
- Air-Conditioning For Vehicles (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BRPI0910553A BRPI0910553B1 (pt) | 2008-05-30 | 2009-04-22 | configuração de instalação pneumática na zona de cauda de aeronave |
EP09753999.3A EP2279946A4 (en) | 2008-05-30 | 2009-04-22 | CONFIGURING A PNEUMATIC INSTALLATION IN THE AIRCRAFT ZONE OF A PLANE |
CA2720891A CA2720891C (en) | 2008-05-30 | 2009-04-22 | Structure of a pneumatic installation in a tail zone of an aircraft |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ESP200801625 | 2008-05-30 | ||
ES200801625A ES2358650B1 (es) | 2008-05-30 | 2008-05-30 | Configuración de la instalación neum�?tica en la zona de cola de un avión. |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009144345A1 true WO2009144345A1 (es) | 2009-12-03 |
Family
ID=41376627
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/ES2009/070109 WO2009144345A1 (es) | 2008-05-30 | 2009-04-22 | Configuración de la instalación neumática en la zona de cola de un avión |
Country Status (6)
Country | Link |
---|---|
US (1) | US8128024B2 (es) |
EP (1) | EP2279946A4 (es) |
BR (1) | BRPI0910553B1 (es) |
CA (1) | CA2720891C (es) |
ES (1) | ES2358650B1 (es) |
WO (1) | WO2009144345A1 (es) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2946955B1 (fr) * | 2009-06-17 | 2012-09-21 | Airbus | Aeronef pourvu d'un systeme de pile a combustible. |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU1462678C (ru) * | 1987-06-29 | 1995-01-20 | Авиационный комплекс им.С.В.Ильюшина | Вспомогательная силовая установка летательного аппарата |
RU1228409C (ru) * | 1984-04-21 | 1995-06-27 | Авиационный комплекс им.С.В.Ильюшина | Вспомогательная силовая установка летательного аппарата |
US20070063098A1 (en) * | 2001-10-29 | 2007-03-22 | Luc Dionne | Passive cooling system for auxiliary power unit installation |
US20080057848A1 (en) * | 2006-08-31 | 2008-03-06 | Honeywell International, Inc. | Venturi gate valve assembly for an auxiliary power unit |
EP1918203A1 (en) * | 2006-10-31 | 2008-05-07 | Airbus Espana, S.L. | Tail cone for aircraft with movable fairing and support structure for auxiliary power unit and the ancillary elements thereof |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4706908A (en) * | 1984-10-10 | 1987-11-17 | Duncan Aviation, Inc. | Lightweight auxiliary power and forced air supply unit |
US5265408A (en) * | 1992-02-13 | 1993-11-30 | Allied-Signal Inc. | Exhaust eductor cooling system |
DE19821952C2 (de) * | 1998-05-15 | 2000-07-27 | Dbb Fuel Cell Engines Gmbh | Energieversorgungseinheit an Bord eines Luftfahrzeugs |
DE10301374B4 (de) * | 2003-01-16 | 2005-07-07 | Airbus Deutschland Gmbh | Faltenbalg zur mechanischen Verbindung von zwei, in einem vorgegebenen Abstand angeordneten Rohren |
US7975465B2 (en) * | 2003-10-27 | 2011-07-12 | United Technologies Corporation | Hybrid engine accessory power system |
US7380749B2 (en) * | 2005-04-21 | 2008-06-03 | The Boeing Company | Combined fuel cell aircraft auxiliary power unit and environmental control system |
-
2008
- 2008-05-30 ES ES200801625A patent/ES2358650B1/es active Active
- 2008-09-23 US US12/232,731 patent/US8128024B2/en not_active Expired - Fee Related
-
2009
- 2009-04-22 EP EP09753999.3A patent/EP2279946A4/en not_active Withdrawn
- 2009-04-22 CA CA2720891A patent/CA2720891C/en active Active
- 2009-04-22 BR BRPI0910553A patent/BRPI0910553B1/pt active IP Right Grant
- 2009-04-22 WO PCT/ES2009/070109 patent/WO2009144345A1/es active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU1228409C (ru) * | 1984-04-21 | 1995-06-27 | Авиационный комплекс им.С.В.Ильюшина | Вспомогательная силовая установка летательного аппарата |
RU1462678C (ru) * | 1987-06-29 | 1995-01-20 | Авиационный комплекс им.С.В.Ильюшина | Вспомогательная силовая установка летательного аппарата |
US20070063098A1 (en) * | 2001-10-29 | 2007-03-22 | Luc Dionne | Passive cooling system for auxiliary power unit installation |
US20080057848A1 (en) * | 2006-08-31 | 2008-03-06 | Honeywell International, Inc. | Venturi gate valve assembly for an auxiliary power unit |
EP1918203A1 (en) * | 2006-10-31 | 2008-05-07 | Airbus Espana, S.L. | Tail cone for aircraft with movable fairing and support structure for auxiliary power unit and the ancillary elements thereof |
Also Published As
Publication number | Publication date |
---|---|
CA2720891C (en) | 2016-07-05 |
BRPI0910553B1 (pt) | 2019-12-24 |
ES2358650A1 (es) | 2011-05-12 |
CA2720891A1 (en) | 2009-12-03 |
EP2279946A4 (en) | 2013-08-21 |
BRPI0910553A2 (pt) | 2015-09-29 |
EP2279946A1 (en) | 2011-02-02 |
ES2358650B1 (es) | 2012-03-23 |
US8128024B2 (en) | 2012-03-06 |
US20090294581A1 (en) | 2009-12-03 |
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