WO2011138571A1 - Ensemble pour système propulsif d'aéronef - Google Patents
Ensemble pour système propulsif d'aéronef Download PDFInfo
- Publication number
- WO2011138571A1 WO2011138571A1 PCT/FR2011/051042 FR2011051042W WO2011138571A1 WO 2011138571 A1 WO2011138571 A1 WO 2011138571A1 FR 2011051042 W FR2011051042 W FR 2011051042W WO 2011138571 A1 WO2011138571 A1 WO 2011138571A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- ferrule
- flange
- connecting flange
- plane
- connection
- Prior art date
Links
- 238000013016 damping Methods 0.000 claims abstract description 13
- 238000005452 bending Methods 0.000 claims abstract description 7
- 239000002131 composite material Substances 0.000 claims description 7
- 230000007704 transition Effects 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 5
- 241000251468 Actinopterygii Species 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 230000004907 flux Effects 0.000 abstract description 2
- 230000008901 benefit Effects 0.000 description 4
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 230000032798 delamination Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000004005 microsphere Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
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
-
- 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
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/827—Sound absorbing structures or liners
-
- 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
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
-
- 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
- Y10T403/00—Joints and connections
- Y10T403/45—Flexibly connected rigid members
Definitions
- the present invention avoids the appearance of delamination between the first ferrule and the connecting flange, insofar as at this particular distance, it avoids stressing the connection between the ferrule and the corresponding flange connection.
- FIG. 1 and 2 show partial sectional views of two assemblies of an air intake structure and a fan case of the state of the art
- It may include an air permeable inner skin, an outer breathable skin and a honeycomb honeycomb core.
- the middle section meanwhile, comprises on the one hand, an inner casing 20 surrounding the turbojet fan extending the inner shell 10 of the air intake structure and, on the other hand, an outer fairing structure of the casing extending the external hood of the air intake structure.
- the second connecting portion 32 of the flange 30 corresponding to the inner ferrule 10 of the air intake structure is intended to be fixed on said ferrule 10.
- this second connecting portion 32 forms a composite material part with the inner shell 10 of the air intake structure.
- connection between the inner ferrule 10 and the corresponding connection flange 30 is offset at a distance from the first portion 31 of the flange 30 corresponding to a characteristic quantity of a moment generated by the fluxes of through-forces said inner ferrule under predetermined conditions of use of the nacelle.
- connection bonded between the flange 30 and the acoustic panel of the inner shell 10 is biased by force flows in the shell 10, namely axial tension and compression denoted by t, tension and circumferential compression denoted by f and shear plane designated by Ti 2 and the two associated arrows, shear in the wall of ferrule 10.
- Such a damping length is defined by the following formula (1):
- v the fish coefficient of the material forming the ferrule at the first portion of the flange.
- the damping length of the aforementioned moment is the length at which the moment becomes negligible.
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)
- Details Of Aerials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Vibration Prevention Devices (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2012151435/11A RU2570181C2 (ru) | 2010-05-07 | 2011-05-09 | Узел авиационного двигателя |
BR112012026825A BR112012026825A2 (pt) | 2010-05-07 | 2011-05-09 | unidade para um propulsor de avião, comprrendendo uma primeira virola destinada a ser anexada a uma segunda virola e um primeiro flange de conexão destinado a ser fixado a um segundo flange de conexão correspondente fixo à segunda virola, tal flange de conexão compreendendo uma porção que forma uma superfície plana que se estende ao longo de uma direção radial com relação à primeira virola, nacela e método para fabricação de uma unidade |
CA2798005A CA2798005A1 (fr) | 2010-05-07 | 2011-05-09 | Ensemble pour systeme propulsif d'aeronef |
EP11725141A EP2566757A1 (fr) | 2010-05-07 | 2011-05-09 | Ensemble pour système propulsif d'aéronef |
CN201180020769.4A CN102858634B (zh) | 2010-05-07 | 2011-05-09 | 用于飞行器推进器的单元 |
US13/671,233 US9109509B2 (en) | 2010-05-07 | 2012-11-07 | Unit for an aircraft thruster |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1053578 | 2010-05-07 | ||
FR1053578A FR2959726B1 (fr) | 2010-05-07 | 2010-05-07 | Ensemble pour systeme propulsif d'aeronef |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/671,233 Continuation US9109509B2 (en) | 2010-05-07 | 2012-11-07 | Unit for an aircraft thruster |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011138571A1 true WO2011138571A1 (fr) | 2011-11-10 |
Family
ID=43301957
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2011/051042 WO2011138571A1 (fr) | 2010-05-07 | 2011-05-09 | Ensemble pour système propulsif d'aéronef |
Country Status (8)
Country | Link |
---|---|
US (1) | US9109509B2 (fr) |
EP (1) | EP2566757A1 (fr) |
CN (1) | CN102858634B (fr) |
BR (1) | BR112012026825A2 (fr) |
CA (1) | CA2798005A1 (fr) |
FR (1) | FR2959726B1 (fr) |
RU (1) | RU2570181C2 (fr) |
WO (1) | WO2011138571A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2434105A3 (fr) * | 2010-09-28 | 2014-05-14 | United Technologies Corporation | Cadre de renforcement métallique pour une bride composite d'un carter de rétention de soufflante |
WO2015022460A1 (fr) * | 2013-08-14 | 2015-02-19 | Aircelle | Ensemble comprenant une virole équipée d'une bride, disposant d'un espace annulaire rempli d'un matériau de liaison |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2975970B1 (fr) * | 2011-05-30 | 2013-05-17 | Aircelle Sa | Ensemble pour une nacelle d'aeronef |
FR3026134B1 (fr) | 2014-09-18 | 2019-07-19 | Safran Nacelles | Dispositif pour la fixation d’une entree d’air sur un carter de soufflante d’une nacelle de turboreacteur d’aeronef |
CN109606708B (zh) * | 2018-12-03 | 2022-04-08 | 江西洪都航空工业集团有限责任公司 | 一种小尺寸进气道结构制备方法 |
CN114790943A (zh) * | 2021-01-25 | 2022-07-26 | 中国航发商用航空发动机有限责任公司 | 航空发动机短舱的进气道和航空发动机短舱 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1357279A2 (fr) * | 1997-08-19 | 2003-10-29 | Airbus France | Ensemble réducteur de bruit pour turboréacteur d'aéronef |
EP1591643A1 (fr) * | 2004-04-27 | 2005-11-02 | Airbus France | Ensemble réducteur de bruit pour turboréacteur d'aéronef |
EP1927731A2 (fr) * | 2006-11-21 | 2008-06-04 | General Electric Company | Procédé de fabrication de structures dotées de brides de montage |
WO2010018314A1 (fr) * | 2008-08-13 | 2010-02-18 | Snecma | Paroi interne d'une nacelle de turbomachine |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4452565A (en) * | 1981-12-21 | 1984-06-05 | United Technologies Corporation | Containment structure |
DE4340951A1 (de) * | 1992-12-04 | 1994-06-09 | Grumman Aerospace Corp | Einstückiges Triebwerkeinlaß-Schallrohr |
FR2844303B1 (fr) * | 2002-09-10 | 2006-05-05 | Airbus France | Piece tubulaire d'attenuation acoustique pour entree d'air de reacteur d'aeronef |
FR2869874B1 (fr) * | 2004-05-04 | 2006-06-23 | Snecma Moteurs Sa | Moteur d'avion avec des moyens de suspension a la structure d'un avion |
FR2898870B1 (fr) * | 2006-03-24 | 2008-05-23 | Aircelle Sa | Structure de virole d'entree d'air |
FR2905990A1 (fr) * | 2006-09-20 | 2008-03-21 | Snecma Sa | Systeme propulsif a pylone integre pour avion. |
US7503425B2 (en) * | 2006-10-02 | 2009-03-17 | Spirit Aerosystems, Inc. | Integrated inlet attachment |
US8763753B2 (en) * | 2012-02-10 | 2014-07-01 | General Electric Company | Acoustic panel and method of forming |
-
2010
- 2010-05-07 FR FR1053578A patent/FR2959726B1/fr active Active
-
2011
- 2011-05-09 EP EP11725141A patent/EP2566757A1/fr not_active Withdrawn
- 2011-05-09 WO PCT/FR2011/051042 patent/WO2011138571A1/fr active Application Filing
- 2011-05-09 BR BR112012026825A patent/BR112012026825A2/pt not_active IP Right Cessation
- 2011-05-09 RU RU2012151435/11A patent/RU2570181C2/ru not_active IP Right Cessation
- 2011-05-09 CA CA2798005A patent/CA2798005A1/fr not_active Abandoned
- 2011-05-09 CN CN201180020769.4A patent/CN102858634B/zh not_active Expired - Fee Related
-
2012
- 2012-11-07 US US13/671,233 patent/US9109509B2/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1357279A2 (fr) * | 1997-08-19 | 2003-10-29 | Airbus France | Ensemble réducteur de bruit pour turboréacteur d'aéronef |
EP1591643A1 (fr) * | 2004-04-27 | 2005-11-02 | Airbus France | Ensemble réducteur de bruit pour turboréacteur d'aéronef |
EP1927731A2 (fr) * | 2006-11-21 | 2008-06-04 | General Electric Company | Procédé de fabrication de structures dotées de brides de montage |
WO2010018314A1 (fr) * | 2008-08-13 | 2010-02-18 | Snecma | Paroi interne d'une nacelle de turbomachine |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2434105A3 (fr) * | 2010-09-28 | 2014-05-14 | United Technologies Corporation | Cadre de renforcement métallique pour une bride composite d'un carter de rétention de soufflante |
US9140135B2 (en) | 2010-09-28 | 2015-09-22 | United Technologies Corporation | Metallic radius block for composite flange |
WO2015022460A1 (fr) * | 2013-08-14 | 2015-02-19 | Aircelle | Ensemble comprenant une virole équipée d'une bride, disposant d'un espace annulaire rempli d'un matériau de liaison |
FR3009744A1 (fr) * | 2013-08-14 | 2015-02-20 | Aircelle Sa | Ensemble comprenant une virole equipee d'une bride, disposant d’un espace annulaire rempli d'un materiau de liaison |
Also Published As
Publication number | Publication date |
---|---|
CA2798005A1 (fr) | 2011-11-10 |
US9109509B2 (en) | 2015-08-18 |
RU2570181C2 (ru) | 2015-12-10 |
US20130315657A1 (en) | 2013-11-28 |
FR2959726A1 (fr) | 2011-11-11 |
BR112012026825A2 (pt) | 2016-07-12 |
EP2566757A1 (fr) | 2013-03-13 |
CN102858634B (zh) | 2016-04-06 |
RU2012151435A (ru) | 2014-06-20 |
CN102858634A (zh) | 2013-01-02 |
FR2959726B1 (fr) | 2013-05-31 |
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