EP1999021A1 - Air inlet lip for a pod with electric defrosting - Google Patents
Air inlet lip for a pod with electric defrostingInfo
- Publication number
- EP1999021A1 EP1999021A1 EP07731155A EP07731155A EP1999021A1 EP 1999021 A1 EP1999021 A1 EP 1999021A1 EP 07731155 A EP07731155 A EP 07731155A EP 07731155 A EP07731155 A EP 07731155A EP 1999021 A1 EP1999021 A1 EP 1999021A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- connector
- lip
- electrical
- downstream structure
- air intake
- 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- Withdrawn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
- 238000010257 thawing Methods 0.000 title claims abstract description 6
- 238000005485 electric heating Methods 0.000 claims abstract description 23
- 238000005192 partition Methods 0.000 claims description 6
- 230000005611 electricity Effects 0.000 abstract description 2
- 238000011144 upstream manufacturing Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000005465 channeling Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000006116 polymerization reaction Methods 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 230000035939 shock 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
- 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; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric 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
- 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
- F02C7/047—Heating to prevent icing
-
- 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
- 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
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
-
- 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
Definitions
- the present invention relates to a lip of an air intake of a turbojet engine nacelle intended to be attached to a downstream air intake structure and comprising at least one electric defrost heating element, as well as to a corresponding downstream structure and a turbojet nacelle comprising an air inlet according to the invention.
- An aircraft is propelled by one or more propulsion units comprising a turbojet engine housed in a tubular nacelle.
- Each propulsion unit is attached to the aircraft by a mast located generally under a wing or at the fuselage.
- a nacelle generally has a structure comprising an air inlet upstream of the engine, a median section intended to surround a fan of the turbojet, a downstream section housing thrust reverser means and intended to surround the combustion chamber of the turbojet engine, and is generally terminated by an ejection nozzle whose outlet is located downstream of the turbojet engine.
- the air intake comprises, on the one hand, an inlet lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet engine, and other on the other hand, a downstream structure to which the lip is attached and intended to properly channel the air towards the blades of the fan.
- the assembly is attached upstream of a blower housing belonging to the upstream section of the nacelle.
- ice may form on the nacelle at the air intake lip.
- the presence of ice or frost changes the aerodynamic properties of the air intake and disturbs the flow of air to the blower.
- pieces of ice may eventually become detached from the air inlet lip and collide with components of the turbojet such as the blades of the fan.
- the air inlet lip is a part subjected to many shocks with external elements such as gravel, birds, hail and others, from undermining the aerodynamic integrity of the outer surface and causing premature wear. Since the performance of the turbojet engine is related to the quantity and quality of the air intake achieved by the air inlet, it is necessary to replace this defective lip as soon as possible. Such a replacement is a long and expensive maintenance operation because only a portion of the lip may have been damaged.
- a first solution for deicing an air intake lip is to take hot air from the compressor of the turbojet engine and bring it to the level of the air intake lip which it warms the walls by flowing through an inner channel of the air inlet lip.
- a device requires a system of hot air supply ducts between the turbojet engine and the air inlet, as well as a system for evacuating hot air at the inlet lip of the engine. 'air. This increases the mass of the propulsion unit, which is not desired.
- An additional consequence of such a system is that to avoid multiplying the hot air inflow and outflow, the air intake lip is made in one piece having a continuous peripheral inner duct for the circulation of the air. hot air, which must be completely changed in case of alteration of its external profile.
- a second solution, described in patent EP 1 495 963 consists in applying a heating resistor on an outer wall of the air intake lip fed from a source of electricity of the nacelle.
- This technology makes it possible to create a modular air inlet lip from several basic structures. Although less complex, a change of one or more structures remains long, due to the reconnection of the power supply means of the structure.
- the replacement of the lip can be facilitated by producing a lip of an air inlet intended to be attached to a downstream air inlet structure and comprising at least an electric heating element defrosting, characterized in that said electric heating element is equipped with at least one electrical connector adapted to be connected to at least one corresponding power supply connector of the downstream structure.
- the present invention aims to further improve the ease of replacement of such an air intake lip and consists for this purpose in a lip of an air inlet of a turbojet engine nacelle intended to be attached to a structure downstream air inlet and comprising at least one electric defrost heating element, said electric heating element being equipped with at least one electrical connector adapted to be connected to at least one corresponding power supply connector of the downstream structure, characterized in that the lip is decomposed into at least two identical structures placed end to end on a periphery of the air inlet.
- the lip is made from identical modules, it is possible to replace a damaged portion of the lip without changing the undamaged structures. Moreover, by providing that these structures are identical, the replacement is further facilitated since it avoids the multiplication of spare parts.
- the lip is broken down into four identical structures placed end to end.
- At least one electrical connector is located substantially in the middle of each structure.
- At least one electrical connector is situated substantially at one end of each structure.
- At least one electrical connector is located at each end of the structure, each connector being able to receive a conductive plug capable of ensuring the electrical continuity of the connector which is not intended to be connected to the corresponding power supply connector.
- the present invention also relates to a downstream structure for an air intake of a turbojet engine nacelle for receiving a lip according to the invention, characterized in that it comprises at least one power supply connector adapted to cooperate with a corresponding electrical connector of the air intake lip, said electrical connector being fixed in a front wall of the downstream structure.
- the front partition comprises at least one aperture adapted to allow access to the power supply connector.
- the power supply connector is mounted in a removable plate forming part of the front partition.
- the downstream structure comprises at least one hatch formed in an outer wall and adapted to allow access to the power supply connector.
- the hatch is located at a junction between two structures according to the invention.
- the downstream structure has an outer wall at least partially associated with movable covers equipping a central section of the nacelle. In this way, it is no longer necessary to provide traps in the structure, the access being done by opening the movable covers of the middle structure.
- the present invention relates to a nacelle for a turbojet, characterized in that it comprises an air inlet comprising a downstream structure according to the invention on which is reported an air intake lip according to the invention.
- FIG. 1 is a schematic perspective representation of a nacelle according to the invention .
- Figure 2 is an enlarged cross-sectional view of a structure of the air intake lip according to the invention.
- FIG. 3 is an enlarged schematic view in cross section of an air inlet of the nacelle shown in FIG.
- FIG. 4 is an enlarged partial exploded perspective representation of the air intake lip made from structures according to FIG.
- Figure 5 is a schematic front view of the air intake lip according to Figure 4.
- Figure 6 is an enlarged cross-sectional view of another air inlet comprising a downstream structure provided with traps.
- FIGS. 7 to 11 show various alternative embodiments of the electrical circuit of the structures according to FIG.
- a nacelle 1 according to the invention as shown in Figure 1 is a tubular housing for a turbojet (not visible) which it serves to channel the air flow it generates.
- the nacelle 1 is located under a wing 2 to which it is attached by a mast 3. It also houses various components necessary for the operation of the turbojet engine.
- the nacelle 1 has a structure comprising a front section forming an air inlet 4, a median section 5 surrounding a blower (not visible) of the turbojet engine, and a rear section 6 surrounding the turbojet engine and housing an inversion system thrust (not visible).
- the air intake 4 is divided into two parts, namely on the one hand, an inlet lip 4a adapted to allow optimal capture to the turbojet of the air necessary to supply the fan and compressors internal turbojet, and secondly, a downstream structure 4b on which is reported the lip 4a and for properly channeling air to the vanes of the fan.
- the assembly is attached upstream of a fan casing belonging to the median section 5 of the nacelle 1.
- the air intake lip 4a 4 is made using structures 7 according to the invention reported on the downstream structure 4b over the entire periphery of the nacelle 1.
- Each structure 7 is separated from the adjacent structure 7 by a separating element 8 integral with the downstream structure 4b.
- the air intake lip 4a 4 is here made from four structures 7. It could of course be made using two structures 7, in one piece or from more than four structures 7.
- Each structure 7 comprises a wall 10 shaped so as to give the lip 4a the desired profile and an acoustic attenuation structure 30, of the honeycomb type, the latter being located in contact with a zone the wall 10 overlooking the inlet of the fan and provided with a plurality of perforations 11 regularly spaced.
- the wall 10 of the structure 7 comprises an outer skin 12 intended to be oriented towards the outside of the lip 4a, an inner skin 13 intended to be oriented towards the inside of the lip 4a and an electric heating element 14 situated between the internal skin 13 and the outer skin 12.
- the electric heating element 14 is intended to be connected to a power supply socket 16 of the downstream structure 4b via a connector 15 connected to a power cable 15 ' Electrical:
- This cable 15 ' has been omitted in Figure 3 so as not to overload the drawing. It should be noted that clipping holding means (not shown) of the cable 15 'can be provided.
- the outer skin 12 provides the aerodynamic outer line of the lip 4a. It may be metallic or made of composite material, be preformed or made at the same time as the introduction of the electric heating element 14.
- the outer skin 12 has a relatively small thickness so as to ensure good heat transfer to the outside of the lip 4a. For example, this thickness will be a few tenths of a millimeter.
- the inner skin 13 covers the electric heating element 14 and finalize the wall 10.
- the outer skin 12 may be metallic or made of composite material, be preformed or made at the same time as the installation of the Electric heating element 14. It should be noted that the thicknesses of the outer skin 12 and the inner skin 13 may not be identical.
- the various layers constituting the wall 10 of the structure 7 are bonded to each other by a bonding material of glue or resin type (not shown).
- the electric heating element 14 is of the cut metal resistance type.
- a particularly advantageous form of the electric heating element 14 is a serpentine shape. Of course, it should be ensured that the surface of the electric heating element 14 achieves the desired defrosting temperature.
- the power supply of the electric heating element 14 is effected by a cable 15 'connected to an electrical source.
- This cable 15 passeses through the inner skin 13 of the structure 7 close to the center of the latter and is then connected to the electrical source of the downstream structure 4b of the air inlet 4 via its connector 15.
- This electric cable 15 will take care to protect this electric cable 15 'during the manufacture of the wall 10 and in particular during the polymerization of the inner skin 13 and the outer skin 12 and resins in the case of organic skin composite material.
- FIGS 7 to 11 show various configurations for the electric heating element 14. It should also be understood that several electric heating elements 14 can be connected in parallel. Thus, in the event of failure of an electric heating element 14, the other electric heating elements 14 can continue to perform their defrosting function. It may also have several layers of electric heating elements 14 arranged in possibly different configurations.
- downstream structure 4b comprises a front partition 18 in which is mounted a connector 19 by lip structure 4a 4a, each connector 19 being connected to a source of electrical power (not shown) of the nacelle 1 via a 19 'power supply cable. Each connector 19 is then intended to cooperate with the connector 15 of the corresponding structure 7 via the power plug 16.
- the connectors 19 can be mounted on removable plates 20 belonging to the front partition 18, as shown more specifically in FIG. 6, which shows an alternative embodiment. of a nacelle 1 according to the invention. By removing the one or more removable plate (s), an operator has access to the inside of the lip structure 4a.
- the access to the electrical elements can be done via openings (not shown) formed in the bulkhead before 18 in the vicinity of each connector 19.
- the outer wall 22 may be partly associated with movable covers of the middle section 5 to access the housing of the fan. The opening of these movable covers will then open the outer wall 22 of the downstream structure 4b, thus allowing access to the front partition 18 and the connectors 19.
- FIG. 5 A particular arrangement is shown by way of example in FIG. 5.
- the power outlets 16 of the downstream structure 4b are arranged to be located at least at one end of each structure 7.
- the structure 7 has a connector 15 in the vicinity of each end.
- Each connector 15 is covered by a conductive plug 24. Once in place, simply remove the conductive plug 24 of the connector 15 located opposite the connector 19, and leave in place the conductive plug 24 located on the other connector 15 to keep the electrical continuity of the corresponding electric heating element 14.
- the electric heating element may, unlike those described above, be housed in the volume delimited respectively by the lip 4a or by each structure 7, and no longer be sandwiched between two skins 12, 13 of the structure 7.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0602548A FR2898869B1 (en) | 2006-03-24 | 2006-03-24 | ELECTRIC DEGIVER NACELLE AIR INLET LAUNDRY |
PCT/FR2007/000463 WO2007122307A1 (en) | 2006-03-24 | 2007-03-19 | Air inlet lip for a pod with electric defrosting |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1999021A1 true EP1999021A1 (en) | 2008-12-10 |
Family
ID=37451466
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07731155A Withdrawn EP1999021A1 (en) | 2006-03-24 | 2007-03-19 | Air inlet lip for a pod with electric defrosting |
Country Status (7)
Country | Link |
---|---|
US (1) | US8540185B2 (en) |
EP (1) | EP1999021A1 (en) |
CN (1) | CN101415607B (en) |
CA (1) | CA2643023C (en) |
FR (1) | FR2898869B1 (en) |
RU (1) | RU2445237C2 (en) |
WO (1) | WO2007122307A1 (en) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2898868B1 (en) * | 2006-03-24 | 2008-12-12 | Aircelle Sa | STRUCTURE FOR AIR ENTRANCE LAUNCHER WITH ELECTRIC DEFROSTING |
FR2922522B1 (en) * | 2007-10-22 | 2010-04-16 | Aircelle Sa | PIEZOELECTRIC DEFROSTING OF AN AIR INPUT |
US7837150B2 (en) * | 2007-12-21 | 2010-11-23 | Rohr, Inc. | Ice protection system for a multi-segment aircraft component |
US8769924B2 (en) * | 2008-05-30 | 2014-07-08 | United Technologies Corporation | Gas turbine engine assembly including accessory components within the nacelle |
US8522522B2 (en) * | 2010-07-30 | 2013-09-03 | Hamilton Sundstrand Corporation | Fan embedded power generator |
GB2498006B (en) * | 2011-12-22 | 2014-07-09 | Rolls Royce Plc | Gas turbine engine systems |
GB2497807B (en) | 2011-12-22 | 2014-09-10 | Rolls Royce Plc | Electrical harness |
GB201306674D0 (en) * | 2013-04-12 | 2013-05-29 | Rolls Royce Plc | Rigid Raft for a Gas Turbine Engine |
US9663238B2 (en) * | 2013-11-11 | 2017-05-30 | The Boeing Company | Nacelle inlet lip skin with pad-up defining a developable surface having parallel ruling lines |
CN105447437B (en) | 2015-02-13 | 2017-05-03 | 比亚迪股份有限公司 | fingerprint identification method and device |
US10823060B2 (en) * | 2015-12-18 | 2020-11-03 | Raytheon Technologies Corporation | Gas turbine engine with short inlet, acoustic treatment and anti-icing features |
US10662877B2 (en) * | 2016-10-03 | 2020-05-26 | Rohr, Inc. | Embedded aircraft heater repair |
CN108688824B (en) * | 2017-04-10 | 2020-07-14 | 清华大学 | Engine air inlet deicing system, internal combustion engine and aircraft |
RU180269U1 (en) * | 2017-08-29 | 2018-06-07 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | Gas turbine engine intake duct |
US10960983B2 (en) * | 2017-09-01 | 2021-03-30 | Textron Innovations Inc. | Tailored rotor-blade ice-protection system |
US11053849B2 (en) * | 2019-08-23 | 2021-07-06 | Mitsubishi Power Americas, Inc. | Anti icing method and apparatus |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1190933A (en) * | 1966-05-26 | 1970-05-06 | Teddington Aircraft Controls L | Improvements in or relating to Air Intake Cowls for Aero Engines |
GB1247071A (en) * | 1969-01-24 | 1971-09-22 | Rolls Royce | An aircraft engine nose cowl |
GB1314162A (en) * | 1969-05-08 | 1973-04-18 | Secr Defence | Intake anti-icing system for gas turbine engines |
US4688757A (en) | 1986-08-11 | 1987-08-25 | Dresser Industries, Inc. | Soft seat Y pattern globe valve |
RU2234781C2 (en) * | 1998-12-01 | 2004-08-20 | Трастиз Оф Дартмут Колледж | Method and device for removing ice from surfaces |
FR2787509B1 (en) * | 1998-12-21 | 2001-03-30 | Aerospatiale | AIR INTAKE STRUCTURE FOR AIRCRAFT ENGINE |
RU21423U1 (en) * | 2001-08-27 | 2002-01-20 | Открытое акционерное общество Омское моторостроительное конструкторское бюро | GAS-TURBINE ENGINE DISCONTINUOUS SYSTEM |
US7588212B2 (en) * | 2003-07-08 | 2009-09-15 | Rohr Inc. | Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip |
CA2515276A1 (en) * | 2004-08-23 | 2006-02-23 | Goodrich Corporation | Aircraft wing |
US7469862B2 (en) * | 2005-04-22 | 2008-12-30 | Goodrich Corporation | Aircraft engine nacelle inlet having access opening for electrical ice protection system |
US7513458B2 (en) * | 2005-04-22 | 2009-04-07 | Rohr, Inc. | Aircraft engine nacelle inlet having electrical ice protection system |
-
2006
- 2006-03-24 FR FR0602548A patent/FR2898869B1/en active Active
-
2007
- 2007-03-19 US US12/279,735 patent/US8540185B2/en not_active Expired - Fee Related
- 2007-03-19 CN CN2007800101034A patent/CN101415607B/en not_active Expired - Fee Related
- 2007-03-19 WO PCT/FR2007/000463 patent/WO2007122307A1/en active Application Filing
- 2007-03-19 RU RU2008141472/11A patent/RU2445237C2/en not_active IP Right Cessation
- 2007-03-19 CA CA2643023A patent/CA2643023C/en not_active Expired - Fee Related
- 2007-03-19 EP EP07731155A patent/EP1999021A1/en not_active Withdrawn
Non-Patent Citations (1)
Title |
---|
See references of WO2007122307A1 * |
Also Published As
Publication number | Publication date |
---|---|
CN101415607B (en) | 2012-05-23 |
FR2898869B1 (en) | 2008-12-12 |
CA2643023A1 (en) | 2007-11-01 |
US8540185B2 (en) | 2013-09-24 |
WO2007122307A1 (en) | 2007-11-01 |
RU2445237C2 (en) | 2012-03-20 |
US20090134272A1 (en) | 2009-05-28 |
CN101415607A (en) | 2009-04-22 |
FR2898869A1 (en) | 2007-09-28 |
CA2643023C (en) | 2015-01-06 |
RU2008141472A (en) | 2010-04-27 |
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Inventor name: VAUCHEL, GUY, BERNARD Inventor name: BLIN, LAURENT, ALBERT Inventor name: PORTAL, JEAN-FABRICE, MARCEL Inventor name: THOREL, CHRISTOPHE |
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Effective date: 20160609 |