WO2013024218A1 - Cône d'éjection pour turboréacteur d'aéronef - Google Patents
Cône d'éjection pour turboréacteur d'aéronef Download PDFInfo
- Publication number
- WO2013024218A1 WO2013024218A1 PCT/FR2012/051583 FR2012051583W WO2013024218A1 WO 2013024218 A1 WO2013024218 A1 WO 2013024218A1 FR 2012051583 W FR2012051583 W FR 2012051583W WO 2013024218 A1 WO2013024218 A1 WO 2013024218A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- flange
- ejection cone
- cone
- outer skin
- connecting flange
- Prior art date
Links
Classifications
-
- 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
-
- 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
- F02K1/04—Mounting of an exhaust cone in the jet pipe
-
- 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
- F02K1/44—Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
-
- 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
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
-
- 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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- 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 an ejection cone for an aircraft turbojet engine.
- FIG. 1 Such a conventional ejection cone 1 is shown in Figure 1 appended hereto, in which the front and the rear of the structure along a motor axis are respectively located on the left and right of the figure.
- This ejection cone is intended to be positioned downstream of the turbine of the turbojet, over which the primary nozzle is placed concentrically.
- the ejection cone and the primary nozzle are both attached to a turbojet casing by a flange fastening system.
- the ejection cone 1 comprises, strictly speaking, a front portion 5 (commonly referred to as “front plug”), of substantially cylindrical shape, and a rear portion 7 (commonly referred to as “rear”). plug "), of conical shape.
- the front portion 5 may be especially acoustic or monolithic stiffened.
- the front part 5 is acoustic, it means that it comprises at least one peripheral acoustic attenuation structure of the sandwich type comprising at least one resonator, in particular of honeycomb type, covered with a perforated outer skin and a full inner skin.
- the outer skin also constitutes an outer surface (sheet) of the front portion 5 of the ejection cone.
- the structure consists of a single sheet reinforced by stiffeners.
- the rear portion 7 is monolithic stiffened by 9d stiffeners.
- the front part 5 and the rear part 7 of the ejection cone may in particular be made from Inconel 625 type metal alloy sheets and be assembled by a flange connection system denoted 9b for the front flange part and 9c for the front flange part. rear flange part.
- the front portion 5 further comprises an upstream connecting flange 9a to allow its attachment to the rear of the turbojet engine.
- the flange 9b of the front portion 5 has on the one hand a portion 1 1 of diameter substantially equal to that of the outer skin of this front portion 5, and on the other hand a portion 13 of smaller diameter than that of the flange 9c of the rear portion 7 to which it is intended to be bonded, so that this portion 13 of the flange 9b can be inserted inside the flange 9c of the rear part 7.
- Housing 15 formed in the thickness of the flange 9c can accommodate bolts 17 passing through the flange 9c and the flange 9b, fixed by means of nuts 18 attached by the interior of the ejection cone 1 thus assembled.
- the housings 15 prevent the heads 19 of the bolts 17 are protruding outwardly of the cone 1, and thus cause aerodynamic losses.
- an ejection cone of the prior art (FIG. 2) is a complex, multi-piece structure, and the cost of manufacturing is high and impacts the mass of the whole, which is undesirable.
- the acoustic panel is closed at its front and rear ends respectively by peripheral flanges having a section C and commonly called closure C.
- closure C's are bonded, in particular by brazing, with the corresponding front and rear flanges respectively providing the connection with the turbojet engine and the rear cone portion and ensures a large part of the maintenance of the acoustic attenuation structure.
- These closing C are expensive parts made by machining and above all they represent a significant mass relative to the complete mass of the ejection cone.
- the present invention aims to simplify the design of the acoustic attenuation structure and the ejection cone by overcoming these C closures.
- an ejection cone for an aircraft turbojet engine comprising a front part having a front end equipped with a connecting flange at an output of a turbojet engine and / or a rear end equipped with a connecting flange at a rear portion of the ejection cone, said front portion being further provided with at least one acoustic attenuation structure comprising a corresponding outer skin, characterized in that the outer skin overlaps with at least one a part of the flange of the ia ison upstream or downstream corresponding and is assembled to the latter.
- this type of direct connection between the acoustic attenuation structure and the front / rear flanges of the front part may concern only one or both closure Cs.
- the outer skin and the front / rear flange are assembled by riveting.
- the outer skin and the flange are assembled by brazing.
- the rear link flange also constitutes a connecting flange before a rear portion of the ejection cone.
- the outer skin is made from a metal alloy, such as Inconel 625.
- FIG. 1 is a perspective view in axial section of an ejection cone of the prior art, mentioned in the preamble of the present description
- FIG. 2 is a widened view of a junction zone between the acoustic panel and a rear flange connecting to a rear part of the ejection cone and showing the use of a closure C of the acoustic panel according to FIG. prior art
- FIG. 3 is a widened view of a junction zone between the acoustic panel and a flange before binding to a rboreactor and showing the use of a closure C of the acoustic panel according to FIG. prior art
- FIG. 4 is a view in longitudinal section of an ejection cone according to the invention.
- FIGS. 5 and 6 are partial diagrammatic views in sections of the zones of attachment of the acoustic panel to an upstream flange according to two modes of assembly of the acoustic panel with the front flange,
- FIG. 7 is a schematic partial sectional view of the rear zone of the acoustic panel attached to the rear flange of the front portion of the cone.
- the front part 5 of the ejection cone 1 is equipped with an acoustic attenuation structure comprising a honeycomb core 51, for example a structure in honeycombs. covered with an outer skin 52 perforated and a full inner skin 53.
- the cellular core is closed by a closing C 54, this closing C is also covered by the long run 55 of the pe r ex e 52, extension 55 not perforated, and by an extension of the inner skin 53.
- connection between the acoustic attenuation structure and the rear link flange 9b is provided by the closing C 54, as previously explained, in particular by brazing between these elements.
- the flange 9b has a thickness ensuring the absence of shift ("step", step) with the outer skin 52, and its extension 55 so as to best ensure the external aerodynamic continuity of the front portion 5 cone.
- the junction shown in FIG. 3 between the acoustic attenuation structure and the flange 9a of the house is effected by means of a closing C by means of rows of rivets 56.
- the present invention relates to an ejection cone 101 for an aircraft turbojet engine comprising a front portion of cone 105 of substantially cylindrical shape and equipped with at least one acoustic attenuation structure, said front portion 1 05 having, on the one hand, an upstream end eq ued with a flange lia ison 9a to an output of a turbojet, and secondly, a downstream end equipped with a connecting flange 9b to a rear portion of cone 7 substantially conical.
- the front portion 105 of the cone is as previously described made from an acoustic attenuation structure comprising a cellular core 51 covered with an outer skin 52 perforated and a full inner skin 53.
- the outer skin 52 is in extension of the cellular core (non-perforated extension) and overlaps with at least a portion of the corresponding connecting flange 9a and / or rear 9b and is assembled to the latter.
- the outer skin 55 and the flange 9a are assembled at their connection zone by rivets 56.
- the outer skin 55 and the flange 9a are joined together at the level of their bonding zone by welding.
- the assembly by welding ensures an optimal continuity of the aerodynamic profile by avoiding any shifts ("step") between the front flange 9a and the outer skin 55.
- the same principle is applicable to the rear end of the front part 105 with the flange of the section 9b, itself attached to the front flange 9c of the rear part 7.
- the rear link flange 9b also constitutes a front connecting flange 9c of a rear portion 7 of the ejection cone 101.
- the outer skin is made from a metal alloy such as Inconel 625. This same material can be used for all or part of the flanges.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Exhaust Silencers (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BR112014001679A BR112014001679A2 (pt) | 2011-08-12 | 2012-07-05 | cone de escape para motor turbojato de aeronave |
CN201280039233.1A CN103717870A (zh) | 2011-08-12 | 2012-07-05 | 涡轮喷气发动机的排气锥 |
EP12744051.9A EP2742230A1 (fr) | 2011-08-12 | 2012-07-05 | Cône d'éjection pour turboréacteur d'aéronef |
RU2014108721/06A RU2014108721A (ru) | 2011-08-12 | 2012-07-05 | Конус сопла для турбореактивного двигателя летательного аппарата |
CA2842874A CA2842874A1 (fr) | 2011-08-12 | 2012-07-05 | Cone d'ejection pour turboreacteur d'aeronef |
US14/177,494 US9051899B2 (en) | 2011-08-12 | 2014-02-11 | Exhaust cone for aircraft turbojet engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR11/57321 | 2011-08-12 | ||
FR1157321A FR2978989B1 (fr) | 2011-08-12 | 2011-08-12 | Cone d'ejection pour turboreacteur d'aeronef |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/177,494 Continuation US9051899B2 (en) | 2011-08-12 | 2014-02-11 | Exhaust cone for aircraft turbojet engine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2013024218A1 true WO2013024218A1 (fr) | 2013-02-21 |
Family
ID=46639577
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/051583 WO2013024218A1 (fr) | 2011-08-12 | 2012-07-05 | Cône d'éjection pour turboréacteur d'aéronef |
Country Status (8)
Country | Link |
---|---|
US (1) | US9051899B2 (fr) |
EP (1) | EP2742230A1 (fr) |
CN (1) | CN103717870A (fr) |
BR (1) | BR112014001679A2 (fr) |
CA (1) | CA2842874A1 (fr) |
FR (1) | FR2978989B1 (fr) |
RU (1) | RU2014108721A (fr) |
WO (1) | WO2013024218A1 (fr) |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3026786B1 (fr) * | 2014-10-07 | 2019-07-26 | Safran Aircraft Engines | Flasque de fermeture d'un carter d'echappement |
US10337453B2 (en) * | 2015-04-21 | 2019-07-02 | Rohr, Inc. | Attachment feature for a core panel |
FR3037358B1 (fr) * | 2015-06-11 | 2017-05-19 | Snecma | Ensemble a carter d'echappement et piece aval de revolution |
CN105298684B (zh) * | 2015-09-18 | 2017-11-03 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种航空发动机用尾椎连接结构 |
FR3043138B1 (fr) * | 2015-11-04 | 2019-09-13 | Safran Aircraft Engines | Tube de degazage et cone d'ejection pour une turbomachine, ainsi que leur outillage de montage |
US10907508B2 (en) * | 2015-11-12 | 2021-02-02 | Rohr, Inc. | Turbine engine and exhaust system connection |
FR3082238A1 (fr) * | 2018-06-11 | 2019-12-13 | Airbus Operations | Tuyere primaire d'un conduit d'ejection primaire d'une turbomachine |
FR3084917B1 (fr) * | 2018-08-09 | 2021-04-16 | Safran Ceram | Ensemble pour une tuyere d'ejection de turbomachine |
FR3084916B1 (fr) * | 2018-08-10 | 2020-07-17 | Safran Ceramics | Cone d'ejection a fixation flexible |
CN109372653A (zh) * | 2018-12-13 | 2019-02-22 | 中国航发沈阳发动机研究所 | 一种涡扇发动机降噪排气组件 |
FR3098552B1 (fr) * | 2019-07-08 | 2022-07-15 | Airbus Operations Sas | Turbomachine comportant une structure et une structure interne d’un conduit d’ejection primaire fixee a ladite structure |
FR3100575B1 (fr) * | 2019-09-05 | 2022-04-08 | Safran Ceram | Cone d’ejection a fixation flexible aerodynamique |
FR3100845B1 (fr) * | 2019-09-13 | 2022-07-08 | Safran Nacelles | Organe de tuyère extérieur pour turbomachine |
FR3115830B1 (fr) * | 2020-11-05 | 2022-09-30 | Safran Nacelles | Ensemble pour une turbomachine |
FR3115832B1 (fr) * | 2020-11-05 | 2023-04-21 | Safran Nacelles | Ensemble pour une turbomachine |
US11867077B2 (en) | 2021-06-07 | 2024-01-09 | Rohr, Inc. | Acoustic structure with floating interior skin |
US11976597B2 (en) | 2021-09-13 | 2024-05-07 | Rohr, Inc. | Low-frequency acoustic center body |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1543312A (en) * | 1976-07-21 | 1979-04-04 | Rolls Royce | Honeycomb linings |
EP0316233A1 (fr) * | 1987-11-12 | 1989-05-17 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Méthode d'assemblage de deux pièces en matériaux ayant des coefficients de dilatation thermique différents |
GB2259954A (en) * | 1991-09-27 | 1993-03-31 | Short Brothers Plc | Ducted fan turbine engine nozzle assembly |
EP0540193A1 (fr) * | 1991-10-30 | 1993-05-05 | General Electric Company | Capot pour inverseur de poussée avec parois de bifurcation et capot intérieur intégrés |
US6358590B1 (en) * | 1996-06-28 | 2002-03-19 | Short Brothers Plc | Noise attenuation panel |
FR2949820A1 (fr) * | 2009-09-04 | 2011-03-11 | Aircelle Sa | Ensemble structurant pour une tuyere d'ejection. |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US7870722B2 (en) * | 2006-12-06 | 2011-01-18 | The Boeing Company | Systems and methods for passively directing aircraft engine nozzle flows |
FR2920146B1 (fr) * | 2007-08-20 | 2009-10-30 | Aircelle Sa | Nacelle a section de sortie adaptable |
FR2935753B1 (fr) * | 2008-09-08 | 2011-07-01 | Snecma Propulsion Solide | Liaisons souples a butee pour fixation de piece en cmc |
DE102008051241B4 (de) * | 2008-10-10 | 2011-06-16 | Airbus Operations Gmbh | Schalldämpfer für ein Hilfstriebwerk eines Flugzeugs |
US8579584B2 (en) * | 2010-10-06 | 2013-11-12 | Dewain Ray Brown | Turbofan jet engine |
US9279386B2 (en) * | 2012-03-09 | 2016-03-08 | Hamilton Sundstrand Corporation | Jet noise reduction using eduction effect |
FR2988777B1 (fr) * | 2012-03-29 | 2014-04-25 | Snecma Propulsion Solide | Integration de pieces d'arriere-corps de moteur aeronautique |
US8985942B2 (en) * | 2012-07-02 | 2015-03-24 | United Technologies Corporation | Turbine exhaust case duct |
-
2011
- 2011-08-12 FR FR1157321A patent/FR2978989B1/fr active Active
-
2012
- 2012-07-05 BR BR112014001679A patent/BR112014001679A2/pt not_active IP Right Cessation
- 2012-07-05 RU RU2014108721/06A patent/RU2014108721A/ru not_active Application Discontinuation
- 2012-07-05 EP EP12744051.9A patent/EP2742230A1/fr not_active Withdrawn
- 2012-07-05 CA CA2842874A patent/CA2842874A1/fr not_active Abandoned
- 2012-07-05 CN CN201280039233.1A patent/CN103717870A/zh active Pending
- 2012-07-05 WO PCT/FR2012/051583 patent/WO2013024218A1/fr active Application Filing
-
2014
- 2014-02-11 US US14/177,494 patent/US9051899B2/en active Active
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1543312A (en) * | 1976-07-21 | 1979-04-04 | Rolls Royce | Honeycomb linings |
EP0316233A1 (fr) * | 1987-11-12 | 1989-05-17 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Méthode d'assemblage de deux pièces en matériaux ayant des coefficients de dilatation thermique différents |
GB2259954A (en) * | 1991-09-27 | 1993-03-31 | Short Brothers Plc | Ducted fan turbine engine nozzle assembly |
EP0540193A1 (fr) * | 1991-10-30 | 1993-05-05 | General Electric Company | Capot pour inverseur de poussée avec parois de bifurcation et capot intérieur intégrés |
US6358590B1 (en) * | 1996-06-28 | 2002-03-19 | Short Brothers Plc | Noise attenuation panel |
FR2949820A1 (fr) * | 2009-09-04 | 2011-03-11 | Aircelle Sa | Ensemble structurant pour une tuyere d'ejection. |
Also Published As
Publication number | Publication date |
---|---|
BR112014001679A2 (pt) | 2017-03-07 |
CN103717870A (zh) | 2014-04-09 |
US9051899B2 (en) | 2015-06-09 |
CA2842874A1 (fr) | 2013-02-21 |
RU2014108721A (ru) | 2015-09-20 |
FR2978989A1 (fr) | 2013-02-15 |
FR2978989B1 (fr) | 2013-07-26 |
US20140158458A1 (en) | 2014-06-12 |
EP2742230A1 (fr) | 2014-06-18 |
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