WO2008006961A1 - Turbomoteur pour aéronef - Google Patents
Turbomoteur pour aéronef Download PDFInfo
- Publication number
- WO2008006961A1 WO2008006961A1 PCT/FR2007/001134 FR2007001134W WO2008006961A1 WO 2008006961 A1 WO2008006961 A1 WO 2008006961A1 FR 2007001134 W FR2007001134 W FR 2007001134W WO 2008006961 A1 WO2008006961 A1 WO 2008006961A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- tubular
- air inlet
- flange
- rear end
- turbine engine
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]
Definitions
- the present invention relates to turbine engines for aircraft and, more specifically, to the air intake and the fan casing of such a turbine engine.
- the inner wall of the air inlet and the blower housing are metallic and the rear end of said inner wall of the air inlet and the front end of said blower housing bear cooperating protruding peripheral flanges for securing them by means of fastening elements (screws, bolts, etc.) passing through said flanges.
- fastening elements screws, bolts, etc.
- the tests carried out in this direction have not proved to be of interest since, in use, there is a delamination of the fibers at the 90 ° connection elbow between said peripheral flanges and the remainder of the membrane. said inner wall and said casing delamination which causes a significant decrease in the mechanical strength of said parts and even the breaking thereof.
- the present invention aims to overcome this disadvantage.
- the aircraft turbine engine having a longitudinal axis and comprising:
- a blower supplied with air by said air inlet and enclosed in a casing, also tubular, is remarkable in that said inner wall of the air inlet and the fan casing form a single tubular part, made of a fiber / resin composite material.
- the flanges respectively disposed at the rear end of the inner wall of the air inlet and at the front end of the blower housing are eliminated.
- the disadvantages related to the presence of these flanges and mentioned above, are therefore completely eliminated.
- an integrated inner air inlet / fan casing assembly particularly advantageous in terms of weight and cost.
- Said composite tubular single piece can be made using carbon fibers, boron, glass, silicon carbide, etc., carbon fibers being however preferred.
- This piece can be obtained by any known method (filament winding, winding, removal of impregnated fibers or impregnated fabrics, etc ).
- said composite tubular member may be connected, by a flange and bolts, to the outer cover of the fan duct of said turbine engine.
- FIG. 1 shows, in partial schematic partial section, the front part of a known turbine engine.
- FIG. 2 shows, also in partial schematic partial section, an example of connection between the rear end of the air intake and the front end of the fan casing, in the known turbine engine of Figure 1.
- FIG. 3 shows, in a view similar to FIG. 1, the front part of a turbine engine according to the present invention.
- FIG. 4 shows, in partial enlarged section comparable to FIG. 2, the single tubular composite part forming the internal wall of the air inlet and the hood of the fan of the turbine engine of FIG.
- Figure 5 illustrates, in partial enlarged section, the connection between said single tubular composite part and the outer cover of the suffix channel.
- the known type of turbine engine 1 whose front part is schematically and partially shown in FIG. 1, comprises a longitudinal axis L-L.
- This front portion essentially comprises a tubular air inlet 2 and a blower 3.
- the tubular air inlet 2 has a leading edge 4 and is provided with a tubular metal inner wall 5, for example made of aluminum, internally carrying a tubular acoustic attenuation coating 6.
- An outer cover 7 surrounds said air inlet and delimits with said inner wall 5 a chamber 8 with an annular section, closed by an annular rear wall 9 on the opposite side to said leading edge 4.
- the fan 3 comprises blades 10 and is surrounded by a fan casing 11 constituted by a metal tubular piece 12, for example made of aluminum, and internally carrying a tubular acoustic attenuation coating 13.
- the rear end 2R of the air inlet 2 and the front end 1 1A of the fan casing 1 1 are assembled to one another along a joint plane J1.
- the assembly of the rear ends 2R and before 1 1A is obtained by two cooperating annular flanges 14 and 15 protruding outwardly from the inner wall 5 and the tubular part 12 and pressed against each other by bolts 16 passing through bores 17 and 18 facing each other, formed in said flanges 14 and 15.
- the annular flange 14 is attached to the inner wall 5 and is secured thereto by bolts 19 and 20.
- the flange 1 5 is machined in one piece with the tubular part 12.
- each bolt 16 is associated with a ring 21 traversed by said bolt 16 and secured thereto by the flange 15.
- the rings 21 are made so that they can be axially compressed plastically.
- the fan casing January 1 is assembled at the front end 22A of the outer cover 22 of the blower channel 23, along a joint plane J2.
- Such an assembly is obtained by means of a system of flanges 24, 25 similar to the flange system 14, 15, the flange 24 carried by the tubular piece 12 being for example identical to the flange 15 and the flange 25 of the flange.
- outer cover 22 can have any suitable shape (see Figure 5). Of course, bolts (not shown) are provided to assemble said flanges 24 and 25.
- the outer blower cover 22 internally carries a tubular acoustic attenuation coating 26.
- FIG 3 which schematically shows the front portion of the engine according to the present invention
- elements 2 to 4, 7 to 10, 22, 22A, 23, 25, 26 and J2 described above.
- the inner wall 5 of the air inlet 2 and the fan casing 11 have been replaced by a single tubular piece 30 of fiber / resin composite material internally bearing a tubular acoustic attenuation coating 31, replacing the coatings 6 and 13 (see also Figure 4).
- the flanges 14, 15, the bolts 16, 19, 20 and the joint plane J1 have been eliminated.
- a flange 32 intended to cooperate with the flange 25 of the outer cover 22 of the fan duct 23, to secure said part 30 of said cover.
- the flange 32 is constituted by a ring attached to the uniform rear end 3OR of said part 30 and fastened thereto by bolts 33, 34.
- Bolts 35 ensure the fastening of the flanges 25 and 32, and therefore that of the tubular part 30 and the hood 22 of the fan duct.
- tubular lining 31 may comprise different zones adapted to their location relative to the engine.
- tubular coating 31 may be of nature:
- the air intake according to the present invention has no impedance break, which improves the overall attenuation of the acoustic treatment.
Abstract
Description
Claims
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200760002824 DE602007002824D1 (de) | 2006-07-12 | 2007-07-04 | Triebwerk für ein flugzeug |
US12/307,886 US9261021B2 (en) | 2006-07-12 | 2007-07-04 | Turbine engine for aircraft |
CA 2656137 CA2656137C (fr) | 2006-07-12 | 2007-07-04 | Turbomoteur pour aeronef |
CN2007800261226A CN101490390B (zh) | 2006-07-12 | 2007-07-04 | 用于飞行器的涡轮发动机 |
JP2009518920A JP5097773B2 (ja) | 2006-07-12 | 2007-07-04 | 航空機のタービン・エンジン |
AT07803840T ATE445771T1 (de) | 2006-07-12 | 2007-07-04 | Triebwerk für ein flugzeug |
BRPI0713164-0A BRPI0713164A2 (pt) | 2006-07-12 | 2007-07-04 | motor a jato para aeronave |
EP20070803840 EP2038534B1 (fr) | 2006-07-12 | 2007-07-04 | Turbomoteur pour aéronef |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0606337 | 2006-07-12 | ||
FR0606337A FR2903734B1 (fr) | 2006-07-12 | 2006-07-12 | Turbomoteur pour aeronef. |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2008006961A1 true WO2008006961A1 (fr) | 2008-01-17 |
Family
ID=37759967
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2007/001134 WO2008006961A1 (fr) | 2006-07-12 | 2007-07-04 | Turbomoteur pour aéronef |
Country Status (11)
Country | Link |
---|---|
US (1) | US9261021B2 (fr) |
EP (1) | EP2038534B1 (fr) |
JP (1) | JP5097773B2 (fr) |
CN (1) | CN101490390B (fr) |
AT (1) | ATE445771T1 (fr) |
BR (1) | BRPI0713164A2 (fr) |
CA (1) | CA2656137C (fr) |
DE (1) | DE602007002824D1 (fr) |
FR (1) | FR2903734B1 (fr) |
RU (1) | RU2382218C1 (fr) |
WO (1) | WO2008006961A1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2116728A1 (fr) * | 2008-05-07 | 2009-11-11 | Siemens Aktiengesellschaft | Ensemble d'entrée de fluides |
EP2163748A1 (fr) * | 2008-09-16 | 2010-03-17 | United Technologies Corporation | Carter d'admission et de soufflante intégré |
RU2471681C2 (ru) * | 2008-01-29 | 2013-01-10 | Эрсель | Гондола турбореактивного двигателя |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2903734B1 (fr) * | 2006-07-12 | 2008-09-12 | Airbus France Sas | Turbomoteur pour aeronef. |
FR2931205B1 (fr) | 2008-05-16 | 2010-05-14 | Aircelle Sa | Ensemble propulsif pour aeronef, et structure d'entree d'air pour un tel ensemble |
US9140135B2 (en) * | 2010-09-28 | 2015-09-22 | United Technologies Corporation | Metallic radius block for composite flange |
US9249082B2 (en) | 2010-02-09 | 2016-02-02 | King Abdulaziz City for Science and Technology (KACST) | Synthesis of dimethyl carbonate from carbon dioxide and methanol |
CN103975142B (zh) * | 2011-12-07 | 2016-09-28 | 株式会社Ihi | 安装用凸台以及风扇壳 |
US9534505B2 (en) | 2012-07-23 | 2017-01-03 | United Technologies Corporation | Integrated nacelle inlet and metallic fan containment case |
JP5945209B2 (ja) * | 2012-10-25 | 2016-07-05 | 株式会社Ihi | 円筒状ケース及び円筒状ケースの製造方法 |
FR3015593B1 (fr) * | 2013-12-20 | 2018-09-07 | Safran Aircraft Engines | Carter en materiau composite a matrice organique favorisant l'evacuation des fumees |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3542152A (en) * | 1968-04-08 | 1970-11-24 | Gen Electric | Sound suppression panel |
EP1591643A1 (fr) * | 2004-04-27 | 2005-11-02 | Airbus France | Ensemble réducteur de bruit pour turboréacteur d'aéronef |
EP1621752A2 (fr) * | 2004-07-27 | 2006-02-01 | United Technologies Corporation | Atténuation de bruit d'une éclisse du revêtement d'une virole d'une soufflante |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4235303A (en) * | 1978-11-20 | 1980-11-25 | The Boeing Company | Combination bulk absorber-honeycomb acoustic panels |
GB2061389B (en) * | 1979-10-23 | 1983-05-18 | Rolls Royce | Rod installation for a gas turbine engine |
US6003424A (en) * | 1990-03-08 | 1999-12-21 | Alliedsignal Inc. | Armor systems |
US5259724A (en) * | 1992-05-01 | 1993-11-09 | General Electric Company | Inlet fan blade fragment containment shield |
DE4340951A1 (de) * | 1992-12-04 | 1994-06-09 | Grumman Aerospace Corp | Einstückiges Triebwerkeinlaß-Schallrohr |
US5431532A (en) * | 1994-05-20 | 1995-07-11 | General Electric Company | Blade containment system |
FR2734320B1 (fr) * | 1995-05-15 | 1997-07-18 | Aerospatiale | Dispositif pour prelever et refroidir de l'air chaud au niveau d'un moteur d'aeronef |
US6652222B1 (en) * | 2002-09-03 | 2003-11-25 | Pratt & Whitney Canada Corp. | Fan case design with metal foam between Kevlar |
DE10259943A1 (de) * | 2002-12-20 | 2004-07-01 | Rolls-Royce Deutschland Ltd & Co Kg | Schutzring für das Fan-Schutzgehäuse eines Gasturbinentriebswerks |
GB0403941D0 (en) * | 2004-02-21 | 2004-03-24 | Rolls Royce Plc | A gas turbine engine blade containment assembly |
US8191254B2 (en) * | 2004-09-23 | 2012-06-05 | Carlton Forge Works | Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine |
US7246990B2 (en) * | 2004-12-23 | 2007-07-24 | General Electric Company | Composite fan containment case for turbine engines |
FR2903734B1 (fr) * | 2006-07-12 | 2008-09-12 | Airbus France Sas | Turbomoteur pour aeronef. |
FR2903733B1 (fr) * | 2006-07-12 | 2011-03-04 | Airbus France | Turbomoteur pour aeronef. |
-
2006
- 2006-07-12 FR FR0606337A patent/FR2903734B1/fr not_active Expired - Fee Related
-
2007
- 2007-07-04 EP EP20070803840 patent/EP2038534B1/fr not_active Not-in-force
- 2007-07-04 DE DE200760002824 patent/DE602007002824D1/de active Active
- 2007-07-04 CA CA 2656137 patent/CA2656137C/fr not_active Expired - Fee Related
- 2007-07-04 JP JP2009518920A patent/JP5097773B2/ja not_active Expired - Fee Related
- 2007-07-04 BR BRPI0713164-0A patent/BRPI0713164A2/pt not_active IP Right Cessation
- 2007-07-04 US US12/307,886 patent/US9261021B2/en not_active Expired - Fee Related
- 2007-07-04 AT AT07803840T patent/ATE445771T1/de not_active IP Right Cessation
- 2007-07-04 CN CN2007800261226A patent/CN101490390B/zh not_active Expired - Fee Related
- 2007-07-04 WO PCT/FR2007/001134 patent/WO2008006961A1/fr active Application Filing
- 2007-07-04 RU RU2009104707A patent/RU2382218C1/ru not_active IP Right Cessation
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3542152A (en) * | 1968-04-08 | 1970-11-24 | Gen Electric | Sound suppression panel |
EP1591643A1 (fr) * | 2004-04-27 | 2005-11-02 | Airbus France | Ensemble réducteur de bruit pour turboréacteur d'aéronef |
EP1621752A2 (fr) * | 2004-07-27 | 2006-02-01 | United Technologies Corporation | Atténuation de bruit d'une éclisse du revêtement d'une virole d'une soufflante |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2471681C2 (ru) * | 2008-01-29 | 2013-01-10 | Эрсель | Гондола турбореактивного двигателя |
EP2116728A1 (fr) * | 2008-05-07 | 2009-11-11 | Siemens Aktiengesellschaft | Ensemble d'entrée de fluides |
WO2009135721A1 (fr) * | 2008-05-07 | 2009-11-12 | Siemens Aktiengesellschaft | Ensemble admission de fluide |
US8061982B2 (en) | 2008-05-07 | 2011-11-22 | Siemens Aktiengesellschaft | Fluid intake assembly |
EP2163748A1 (fr) * | 2008-09-16 | 2010-03-17 | United Technologies Corporation | Carter d'admission et de soufflante intégré |
US8092169B2 (en) | 2008-09-16 | 2012-01-10 | United Technologies Corporation | Integrated inlet fan case |
Also Published As
Publication number | Publication date |
---|---|
DE602007002824D1 (de) | 2009-11-26 |
US20090255589A1 (en) | 2009-10-15 |
CN101490390B (zh) | 2012-06-20 |
US9261021B2 (en) | 2016-02-16 |
BRPI0713164A2 (pt) | 2012-04-03 |
CA2656137A1 (fr) | 2008-01-17 |
ATE445771T1 (de) | 2009-10-15 |
CA2656137C (fr) | 2014-09-09 |
FR2903734B1 (fr) | 2008-09-12 |
RU2382218C1 (ru) | 2010-02-20 |
FR2903734A1 (fr) | 2008-01-18 |
EP2038534A1 (fr) | 2009-03-25 |
EP2038534B1 (fr) | 2009-10-14 |
CN101490390A (zh) | 2009-07-22 |
JP2009542974A (ja) | 2009-12-03 |
JP5097773B2 (ja) | 2012-12-12 |
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