WO2009109712A1 - Entree d'air pour nacelle d'aeronef, et ensemble propulsif comprenant une telle entree d'air - Google Patents
Entree d'air pour nacelle d'aeronef, et ensemble propulsif comprenant une telle entree d'air Download PDFInfo
- Publication number
- WO2009109712A1 WO2009109712A1 PCT/FR2009/000061 FR2009000061W WO2009109712A1 WO 2009109712 A1 WO2009109712 A1 WO 2009109712A1 FR 2009000061 W FR2009000061 W FR 2009000061W WO 2009109712 A1 WO2009109712 A1 WO 2009109712A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- ferrule
- housing
- air intake
- assembly
- shell
- Prior art date
Links
Classifications
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
-
- 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
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- 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
- B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
-
- 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
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
-
- 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
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
Definitions
- Air intake for aircraft nacelle, and propulsion assembly comprising such an air intake
- the present invention relates in particular to an air intake for aircraft nacelle.
- An aircraft is propelled by one or more propulsion units each comprising a turbojet engine housing 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 comprises 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 fan casing.
- the inner face of the downstream structure of the air intake is formed by a tubular member frequently referred to as a "ferrule", generally having an acoustic function (structure formed by a honeycomb panel assembly).
- connection of this ferrule with the fan casing is carried out by an "L" section flange, comprising on the one hand a tubular portion fixed on the shell, and on the other hand an annular return fixed on the fan case: the documents FR2847304 and FR286936O show such fixing examples.
- the turbojet In the event of deformation or rupture of the blade of the fan (commonly referred to as "FBO” for “Fan Blade Out”), the turbojet generates vibrations and / or very significant shocks which have repercussions on the fan. whole of the nacelle, and in particular on the air inlet. The latter, which has a significant overhang compared to the rest of the nacelle, is vulnerable to such vibrations / shocks that can cause local deformation or the ruin of this air intake.
- the present invention is intended to provide means for limiting the risk of deformation or ruin of the air inlet in case of deformation or blade rupture of the turbojet fan.
- an air intake for aircraft nacelle comprising a ferrule adapted to be mounted on the fan casing of a turbojet engine, said ferrule being dimensioned to define a circumferential clearance with respect to said casing, and point connection means of said ferrule to said casing being discretely distributed at the periphery of said ferrule.
- This discrete connection of the ferrule of the air intake with the fan casing allows elastic and / or plastic displacements of the ferrule with respect to the fan casing in the event of vibrations or shocks generated in particular by a loss of dawn: these relative movements absorb some of the energy associated with these vibrations or shocks, and thus reduce the impact of these vibrations or shocks on the entire air intake.
- said connecting means comprise a plurality of brackets fixed equidistantly on said shell, and lugs mounted hinged to these brackets and adapted to be fixed on said housing;
- said tabs are adapted to be mounted on a flange integrated in said casing
- said connecting means comprise a plurality of brackets fixed equidistantly to said ferrule and adapted to be mounted directly on a flange integral with said blower housing; said connecting means comprise a plurality of orifices formed on the downstream edge of said shell, able to be traversed by fastening means mounted on the upstream edge of said casing;
- said ferrule comprises an annular groove into which said openings open;
- said ferrule comprises an annular recess into which said openings open, a flap being provided to close this recess;
- said connecting means comprise a plurality of studs distributed on the external face of said ferrule, able to come into engagement with fixing means mounted on the upstream edge of said casing;
- said ferrule is an acoustic ferrule: such a ferrule makes it possible to absorb a portion of the energy of the acoustic waves emitted by the blower and the turbojet engine; said ferrule is adapted to extend in part under the upstream edge of said casing: this arrangement makes it possible to bring the acoustic ferrule closer to the sound emission zones of the blower and the turbojet, and thus to improve the acoustic attenuation.
- the present invention also relates to an assembly comprising an air inlet comprising a ferrule according to the foregoing and a turbojet engine comprising a fan casing on which said ferrule is mounted.
- the upstream edge of said housing comprises a flange on which are fixed said tabs;
- the upstream edge of said casing comprises orifices receiving said fixing means
- the internal face of said casing comprises a step defining the clearance between said shell and said casing; said step has a ramp;
- said casing comprises a tubular tongue closing the recess formed in said ferrule
- the upstream edge of said housing is shaped to define a game with said ferrule upstream and downstream of said pads.
- the present invention also relates to an aircraft propulsion unit comprising an assembly in accordance with the foregoing.
- FIG. 1 is a partial diagrammatic view in axial section of a propulsion assembly according to the invention, on which it is possible to see in particular the acoustic ferrule of the air intake and the turbojet engine;
- FIG. 2 is a view of detail of the zone of cooperation of the ferrule of the air inlet with the turbojet fan casing, corresponding to zone II shown in FIG. 1,
- FIGS. 3 and 4 are views of a variant of the embodiment shown in FIG. 1, and FIGS. 5 to 8 show four variants of another embodiment according to the invention.
- FIG. 1 there is shown diagrammatically an aircraft turbojet, comprising in its upstream part a fan 3 provided with vanes 5, and in its downstream part the engine 7 itself, comprising as this is known per se its compression stages 9, combustion 11 and propulsion 13.
- a tubular member 19 Upstream of this casing 15, and situated in the extension thereof, is a tubular member 19, frequently referred to as a "ferrule", forming part of the nacelle intended to surround the turbojet engine 1.
- this shell 19 constitutes the inner face of the air inlet of the nacelle, as indicated in the preamble of the present description.
- this ferrule 19 is represented in the form of a structure having acoustic absorption properties, such as a honeycomb structure: in fact, such a structure is in fact general used to reduce the energy of the acoustic waves emitted by the turbojet engine 1 and the fan 3.
- the present invention is not limited to a shell 19 having such acoustic properties.
- brackets extend up to the flange 25, and have at their downstream end an articulated lug 29 fixed (for example by screwing) to the flange 25.
- brackets 27 are preferably distributed equidistantly around the circumference of the shell 19, and the geometry of the assembly is determined so that there is a slight clearance J between the outer face of the shell 19 and the inner face of the upstream edge of the housing 15.
- Bracket 27 is substantially lying along the outer face of the casing 15, and in that this bracket is connected directly to the casing via a fitting 31 .
- FIG. 4 illustrates another possible geometry of the stem 27, in this case directly connected to the flange 25, while keeping the games J and J 'similar to those of FIG.
- the ferrule 19 is connected to the inner face of the upstream edge of the housing 15 through a plurality of fastening means 33 of the screw-nut type.
- these fixing means 33 pass through orifices formed in the upstream edge of the casing 15 and in the downstream edge of the ferrule 19.
- the orifices formed in the downstream edge of the ferrule 19 open into an annular groove 35 formed in the downstream edge of the ferrule 19.
- the annular groove 35 may be defined by a compact (so-called monolithic) zone of the honeycomb structure.
- a clearance J is provided between the outer face of the shell 19 and the inner face of the upstream edge of the housing 15, such a game can be obtained by means of a step 43 provided on the inner face of the upstream part of the fan casing 15.
- downstream edge of ferrule 19 no longer defines an annular groove as in the preceding variant, but a simple annular recess 45, that is to say an open zone facing the axis.
- a turbojet This open annular zone allows the setting of nuts
- a substantially tubular flap 47 is then attached to the inner face of the shell 19 is fixed by appropriate means 49 so as to close the recess 45 and thus to allow the aerodynamic continuity between the shell 19 and the fan casing 15. Note that, in this variant as in the previous, a march 43 household clearance J between the outer face of the shell 19 and the inner face of the fan casing 15.
- step 43 has a ramp shape, as shown in FIG. 7, making it easier to insert the ferrule 19 inside the fan casing 15.
- pads 51 are fixed on the outer face of the acoustic shroud 19, preferably equidistantly on the circumference of this ferrule.
- the upstream edge of the fan casing 15 has a geometry defining a second housing 53 for positioning the pads 51.
- Screws 39 pass through the upstream edge of the fan casing 15 and engage with these pads 51.
- the geometry of the assembly is defined so as to allow a clearance J downstream of the pads 51 and a set J "upstream of these pads.
- the point common to all of the embodiments and variants set out above lies in the fact that the shell 19 is connected to the fan casing 15 by point means, it is that is, by means discretely distributed around the circumference of these elements.
- the geometry of the assembly is studied so that there is a clearance between the shell 19 and the fan casing 15. Thanks to all of these features, in case of deformation or rupture of one or more blades 5 of the blower 3, resulting in vibrations or shocks of the turbojet engine 1, the shell 19 can move elastically or plastically with respect to the fan casing 15, thus causing dissipation of the energy transmitted by the turbojet engine 1 and making it possible to avoid the ruin of the air intake and the nacelle. It will be noted in particular that, in the case of the variants shown in FIGS. 5 and 8, it is in particular the own elasticity of the ferrule 19 (in particular when it is an acoustic ferrule) which allows the dissipation of 'energy.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BRPI0906953-4A BRPI0906953A2 (pt) | 2008-01-29 | 2009-01-21 | Entrada de ar para nacela de aeronave, conjunto compreendendo entrada de ar, conjunto de propulsão para aeronave |
US12/864,901 US8985506B2 (en) | 2008-01-29 | 2009-01-21 | Air intake for aircraft nacelle, and propulsion assembly including such air intake |
EP09716599A EP2238031A1 (fr) | 2008-01-29 | 2009-01-21 | Entree d'air pour nacelle d'aeronef, et ensemble propulsif comprenant une telle entree d'air |
CN200980102533.8A CN101918276B (zh) | 2008-01-29 | 2009-01-21 | 用于飞行器机舱的进气口以及包括该进气口的推进组件 |
CA2708106A CA2708106A1 (fr) | 2008-01-29 | 2009-01-21 | Entree d'air pour nacelle d'aeronef, et ensemble propulsif comprenant une telle entree d'air |
RU2010134976/11A RU2494015C2 (ru) | 2008-01-29 | 2009-01-21 | Воздухозаборник для гондолы летательного аппарата и двигательная установка, содержащая данный воздухозаборник |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0800471A FR2926791B1 (fr) | 2008-01-29 | 2008-01-29 | Entree d'air pour nacelle d'aeronef, et ensemble propulsif comprenant une telle entree d'air |
FR0800471 | 2008-01-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009109712A1 true WO2009109712A1 (fr) | 2009-09-11 |
Family
ID=39707981
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2009/000061 WO2009109712A1 (fr) | 2008-01-29 | 2009-01-21 | Entree d'air pour nacelle d'aeronef, et ensemble propulsif comprenant une telle entree d'air |
Country Status (8)
Country | Link |
---|---|
US (1) | US8985506B2 (fr) |
EP (1) | EP2238031A1 (fr) |
CN (1) | CN101918276B (fr) |
BR (1) | BRPI0906953A2 (fr) |
CA (1) | CA2708106A1 (fr) |
FR (1) | FR2926791B1 (fr) |
RU (1) | RU2494015C2 (fr) |
WO (1) | WO2009109712A1 (fr) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7941993B2 (en) * | 2003-10-14 | 2011-05-17 | Rolls-Royce Plc | Engine cooling |
FR2963469B1 (fr) * | 2010-07-27 | 2012-07-27 | Aircelle Sa | Panneau acoustique |
GB201120996D0 (en) * | 2011-12-07 | 2012-01-18 | Airbus Operations Ltd | Apparatus for attachment of wing panels |
FR2997725B1 (fr) * | 2012-11-05 | 2018-03-02 | Safran Aircraft Engines | Carter de turbomachine |
FR2997726B1 (fr) | 2012-11-05 | 2018-03-02 | Safran Aircraft Engines | Carter de turbomachine |
FR2998545B1 (fr) | 2012-11-23 | 2016-10-28 | Airbus Operations Sas | Nacelle d'aeronef comprenant une liaison renforcee entre une entree d'air et une motorisation |
FR2998547B1 (fr) * | 2012-11-23 | 2016-01-29 | Airbus Operations Sas | Nacelle d'aeronef comprenant une liaison deformable entre une entree d'air et une motorisation |
US10180082B2 (en) | 2014-06-05 | 2019-01-15 | Rolls-Royce Corporation | Fan case |
FR3057545A1 (fr) * | 2016-10-13 | 2018-04-20 | Airbus Operations | Nacelle d'aeronef comprenant une liaison entre un conduit d'une entree d'air et un conduit d'une motorisation |
US11325717B2 (en) * | 2016-10-13 | 2022-05-10 | Airbus Operations Sas | Aircraft nacelle including a link between a conduit of an air inlet and a conduit of an engine |
GB201816989D0 (en) * | 2018-10-18 | 2018-12-05 | Rolls Royce Plc | Debris retention |
GB201816990D0 (en) * | 2018-10-18 | 2018-12-05 | Rolls Royce Plc | Debris retention |
FR3092611B1 (fr) * | 2019-02-07 | 2021-02-26 | Safran Aircraft Engines | Soufflante de turbomachine |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6123170A (en) * | 1997-08-19 | 2000-09-26 | Aerospatiale Societe Nationale Industrielle | Noise reducing connection assembly for aircraft turbine housings |
GB2407134A (en) * | 2003-10-16 | 2005-04-20 | Rolls Royce Plc | Aircraft engine mounting assembly |
FR2869360A1 (fr) * | 2004-04-27 | 2005-10-28 | Airbus France Sas | Ensemble reducteur de bruit pour turboreacteur d'aeronef |
FR2898870A1 (fr) * | 2006-03-24 | 2007-09-28 | Aircelle Sa | Structure de virole d'entree d'air |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4293053A (en) * | 1979-12-18 | 1981-10-06 | United Technologies Corporation | Sound absorbing structure |
SU1793650A1 (ru) * | 1991-01-28 | 1995-03-27 | Машиностроительный завод им.П.О.Сухого | Входное устройство силовой установки самолета |
US5336044A (en) * | 1993-08-06 | 1994-08-09 | General Electric Company | Blade containment system and method |
FR2757823B1 (fr) * | 1996-12-26 | 1999-03-12 | Aerospatiale | Nacelle de turboreacteur a ecoulement laminaire |
GB9820226D0 (en) * | 1998-09-18 | 1998-11-11 | Rolls Royce Plc | Gas turbine engine casing |
US6382905B1 (en) * | 2000-04-28 | 2002-05-07 | General Electric Company | Fan casing liner support |
FR2812911B1 (fr) * | 2000-08-11 | 2002-09-20 | Aircelle Sa | Entree d'air pour nacelle de grandes dimensions a transportabilite amelioree |
FR2840647B1 (fr) * | 2002-06-05 | 2004-10-29 | Airbus France | Dispositif pour le raccordement de deux pieces tubulaires de turboreacteur d'aeronef |
FR2856379B1 (fr) * | 2003-06-18 | 2006-11-24 | Airbus France | Moteur d'avion dont les capots de soufflante et d'inverseurs de poussee sont separes par un jeu reduit |
GB0408825D0 (en) * | 2004-04-20 | 2004-05-26 | Rolls Royce Plc | A rotor blade containment assembly for a gas turbine engine |
GB2429043B (en) * | 2005-08-13 | 2008-02-13 | Rolls Royce Plc | Clip |
US7866440B2 (en) * | 2006-07-21 | 2011-01-11 | Rohr, Inc. | System for joining acoustic cellular panel sections in edge-to-edge relation |
US7762086B2 (en) * | 2008-03-12 | 2010-07-27 | United Technologies Corporation | Nozzle extension assembly for ground and flight testing |
US8092169B2 (en) * | 2008-09-16 | 2012-01-10 | United Technologies Corporation | Integrated inlet fan case |
-
2008
- 2008-01-29 FR FR0800471A patent/FR2926791B1/fr not_active Expired - Fee Related
-
2009
- 2009-01-21 US US12/864,901 patent/US8985506B2/en not_active Expired - Fee Related
- 2009-01-21 CA CA2708106A patent/CA2708106A1/fr not_active Abandoned
- 2009-01-21 CN CN200980102533.8A patent/CN101918276B/zh not_active Expired - Fee Related
- 2009-01-21 BR BRPI0906953-4A patent/BRPI0906953A2/pt not_active IP Right Cessation
- 2009-01-21 WO PCT/FR2009/000061 patent/WO2009109712A1/fr active Application Filing
- 2009-01-21 EP EP09716599A patent/EP2238031A1/fr not_active Withdrawn
- 2009-01-21 RU RU2010134976/11A patent/RU2494015C2/ru not_active IP Right Cessation
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6123170A (en) * | 1997-08-19 | 2000-09-26 | Aerospatiale Societe Nationale Industrielle | Noise reducing connection assembly for aircraft turbine housings |
GB2407134A (en) * | 2003-10-16 | 2005-04-20 | Rolls Royce Plc | Aircraft engine mounting assembly |
FR2869360A1 (fr) * | 2004-04-27 | 2005-10-28 | Airbus France Sas | Ensemble reducteur de bruit pour turboreacteur d'aeronef |
FR2898870A1 (fr) * | 2006-03-24 | 2007-09-28 | Aircelle Sa | Structure de virole d'entree d'air |
Also Published As
Publication number | Publication date |
---|---|
CA2708106A1 (fr) | 2009-09-11 |
CN101918276A (zh) | 2010-12-15 |
RU2494015C2 (ru) | 2013-09-27 |
EP2238031A1 (fr) | 2010-10-13 |
RU2010134976A (ru) | 2012-03-10 |
US8985506B2 (en) | 2015-03-24 |
FR2926791B1 (fr) | 2010-05-28 |
FR2926791A1 (fr) | 2009-07-31 |
US20100320316A1 (en) | 2010-12-23 |
BRPI0906953A2 (pt) | 2015-07-14 |
CN101918276B (zh) | 2013-10-09 |
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