WO2008097247A2 - Engine exhaust system - Google Patents

Engine exhaust system Download PDF

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Publication number
WO2008097247A2
WO2008097247A2 PCT/US2007/013679 US2007013679W WO2008097247A2 WO 2008097247 A2 WO2008097247 A2 WO 2008097247A2 US 2007013679 W US2007013679 W US 2007013679W WO 2008097247 A2 WO2008097247 A2 WO 2008097247A2
Authority
WO
WIPO (PCT)
Prior art keywords
duct
exhaust
engine
primary
airframe
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.)
Ceased
Application number
PCT/US2007/013679
Other languages
French (fr)
Other versions
WO2008097247A3 (en
WO2008097247A8 (en
Inventor
Charles Hollimon
John Barber
John Sherrer
Robert Laramee
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Bell Helicopter Textron Inc
Original Assignee
Bell Helicopter Textron Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority to EA200802441A priority Critical patent/EA200802441A1/en
Priority to AU2007346730A priority patent/AU2007346730A1/en
Priority to CN2007800214973A priority patent/CN101466940B/en
Priority to MX2008015788A priority patent/MX2008015788A/en
Priority to US12/303,963 priority patent/US8123159B2/en
Priority to JP2009514422A priority patent/JP2009540195A/en
Priority to BRPI0712611-5A priority patent/BRPI0712611A2/en
Priority to EP07872523A priority patent/EP2032828A4/en
Application filed by Bell Helicopter Textron Inc filed Critical Bell Helicopter Textron Inc
Priority to DE07872523T priority patent/DE07872523T1/en
Priority to CA2654751A priority patent/CA2654751C/en
Publication of WO2008097247A2 publication Critical patent/WO2008097247A2/en
Publication of WO2008097247A3 publication Critical patent/WO2008097247A3/en
Anticipated expiration legal-status Critical
Publication of WO2008097247A8 publication Critical patent/WO2008097247A8/en
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL-COMBUSTION ENGINES
    • F01N1/00—Silencing apparatus characterised by method of silencing
    • F01N1/02—Silencing apparatus characterised by method of silencing by using resonance
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL-COMBUSTION ENGINES
    • F01N1/00—Silencing apparatus characterised by method of silencing
    • 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
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • 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
    • F02K1/52—Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line
    • 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 technical field is engine exhaust systems.
  • an exhaust ejector In conventional aircraft exhaust systems, an exhaust ejector has a primary exhaust gas duct attached to an engine flange for receiving exhaust gas from the engine and passing exhaust gas through the primary exhaust gas duct.
  • the conventional exhaust ejector also has a secondary engine exhaust gas duct attached to the airframe and initially concentric with the primary exhaust duct.
  • shifting, vibrating, or other relative movement of the engine with respect to the airframe often results in the primary exhaust gas duct becoming non-concentric with the secondary exhaust gas duct.
  • Figure 1 shows a prior-art engine exhaust system comprising a primary exhaust duct 13, a secondary exhaust duct 15.
  • Primary exhaust duct 13 is attached directly to engine 17 and moves with engine 17, whereas secondary exhaust duct 15 is attached to airframe 19 and remains in a generally fixed position relative to airframe 19.
  • secondary exhaust duct 15 is attached to airframe 19 and remains in a generally fixed position relative to airframe 19.
  • FIG. 13 and secondary duct 15 may become non-coaxial and non-concentric.
  • Figure 1 illustrates this, as axis 21 of primary duct 13 is not coaxial with axis 23 of secondary duct 15.
  • the exhaust gas flow in secondary duct 15 may be directionally biased, resulting in poor ejector performance.
  • the misalignment can cause several undesirable conditions, including turbulent exhaust gas flow within secondary duct 15 and/or direct impinging of portions of the flow of hot exhaust gas 25 on inner surface 27 of secondary duct 15. Both of these conditions can result in overheating of portions of secondary duct 15.
  • less than optimal exhaust gas ejection may include higher engine compartment temperatures, higher exhaust gas temperatures, and these effects may negatively impact other components of the aircraft.
  • Figure 1 is a cross-sectional side view of a prior-art engine exhaust system.
  • Figure 2 is an oblique view of an embodiment of an engine exhaust system.
  • Figure 3 is a top view of the engine exhaust system of Figure 1.
  • Figure 4 is a side view of the engine exhaust system of Figure 1.
  • Figure 5 is an end view of the engine exhaust system of Figure 1.
  • Figure 6 is a cross-sectional side view of the engine exhaust system of Figure 1.
  • an engine exhaust system provides a means for linking the two ducts together so that even with engine movement relative to the airframe, the two ducts remain concentric. Therefore, if engine movement occurs for any reason, the airframe mounted secondary duct is pushed or pulled into consistent alignment with the primary duct, maintaining maximum ejector performance.
  • Exhaust system 101 comprises a tubular primary exhaust duct 103 (only shown in Figure 6), a tubular secondary exhaust duct 105, and a slip joint 107 for allowing relative axial movement between ducts 103, 105.
  • Primary exhaust duct 103 and secondary exhaust duct 105 are also held in alignment by a drag link 109.
  • Secondary exhaust duct 105 is connected to an airframe 111 and is supported by vertical struts 113 and a lateral strut 115, which are preferably struts connected at each end with uni-ball connectors.
  • Vertical struts 113 carry vertical loads
  • lateral strut 115 carries side loads.
  • the strut attachments are located on or very close to the center of gravity to avoid any undesired moments.
  • Primary exhaust duct 103 is attached directly to engine 117 for allowing exhaust gas to flow from engine 117 through primary exhaust duct 103 and into secondary duct 105.
  • a forward end of secondary exhaust duct 105 is slipped concentrically into and sealably joined to an engine flange 119 through the use of o- ring type seal 121 in slip joint 107, and use of o-ring seal 121 allows for thermal expansion of ducts 103, 105.
  • O-ring seal 107 is preferably a high-temperature o-ring type seal.
  • Slip joint 107 also supports duct 105 in both vertical and horizontal directions, but not in an axial direction.
  • Axial control of duct 105 is accomplished with drag link 109, which connects flange 119 to secondary duct 105.
  • the mounts of drag link 109 are preferably uni-ball connectors, and this configuration allows for relative axial movement between engine 117 and secondary duct 105, but this does not allow for vertical or lateral movement.
  • the single degree of freedom associated with drag link 109 allows engine movement to push or pull secondary exhaust duct 105 consistently with primary duct 103 and keeps the system in the desired alignment.
  • the exhaust system provides for several advantages, including: (1) the ability to maintain primary and secondary exhaust ducts in a desired orientation; (2) low weight; (3) increased reliability and durability; and (4) easy installation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Exhaust Silencers (AREA)
  • Joints Allowing Movement (AREA)
  • Testing Of Engines (AREA)

Abstract

An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.

Description

ENGINE EXHAUST SYSTEM
Technical Field
The technical field is engine exhaust systems.
Description of the Prior Art
In conventional aircraft exhaust systems, an exhaust ejector has a primary exhaust gas duct attached to an engine flange for receiving exhaust gas from the engine and passing exhaust gas through the primary exhaust gas duct. The conventional exhaust ejector also has a secondary engine exhaust gas duct attached to the airframe and initially concentric with the primary exhaust duct. However, shifting, vibrating, or other relative movement of the engine with respect to the airframe often results in the primary exhaust gas duct becoming non-concentric with the secondary exhaust gas duct.
For example, Figure 1 shows a prior-art engine exhaust system comprising a primary exhaust duct 13, a secondary exhaust duct 15. Primary exhaust duct 13 is attached directly to engine 17 and moves with engine 17, whereas secondary exhaust duct 15 is attached to airframe 19 and remains in a generally fixed position relative to airframe 19. When engine 17 moves relative to airframe 19, primary duct
13 and secondary duct 15 may become non-coaxial and non-concentric. Figure 1 illustrates this, as axis 21 of primary duct 13 is not coaxial with axis 23 of secondary duct 15.
When primary duct 13 is not concentric with secondary duct 15, the exhaust gas flow in secondary duct 15 may be directionally biased, resulting in poor ejector performance. The misalignment can cause several undesirable conditions, including turbulent exhaust gas flow within secondary duct 15 and/or direct impinging of portions of the flow of hot exhaust gas 25 on inner surface 27 of secondary duct 15. Both of these conditions can result in overheating of portions of secondary duct 15. In addition, less than optimal exhaust gas ejection may include higher engine compartment temperatures, higher exhaust gas temperatures, and these effects may negatively impact other components of the aircraft. Brief Description of the Drawings
Figure 1 is a cross-sectional side view of a prior-art engine exhaust system.
Figure 2 is an oblique view of an embodiment of an engine exhaust system.
Figure 3 is a top view of the engine exhaust system of Figure 1.
Figure 4 is a side view of the engine exhaust system of Figure 1.
Figure 5 is an end view of the engine exhaust system of Figure 1.
Figure 6 is a cross-sectional side view of the engine exhaust system of Figure 1.
Description of the Preferred Embodiment
To resolve the issue of aircraft exhaust ducts undesirably becoming non- concentric due to relative movement between the engine and the airframe of an aircraft, an engine exhaust system provides a means for linking the two ducts together so that even with engine movement relative to the airframe, the two ducts remain concentric. Therefore, if engine movement occurs for any reason, the airframe mounted secondary duct is pushed or pulled into consistent alignment with the primary duct, maintaining maximum ejector performance.
Referring now to Figures 2 through 6 in the drawings, an embodiment of an engine exhaust system 101 is illustrated. Exhaust system 101 comprises a tubular primary exhaust duct 103 (only shown in Figure 6), a tubular secondary exhaust duct 105, and a slip joint 107 for allowing relative axial movement between ducts 103, 105. Primary exhaust duct 103 and secondary exhaust duct 105 are also held in alignment by a drag link 109. Secondary exhaust duct 105 is connected to an airframe 111 and is supported by vertical struts 113 and a lateral strut 115, which are preferably struts connected at each end with uni-ball connectors. Vertical struts 113 carry vertical loads, and lateral strut 115 carries side loads. Preferably, the strut attachments are located on or very close to the center of gravity to avoid any undesired moments. Primary exhaust duct 103 is attached directly to engine 117 for allowing exhaust gas to flow from engine 117 through primary exhaust duct 103 and into secondary duct 105. A forward end of secondary exhaust duct 105 is slipped concentrically into and sealably joined to an engine flange 119 through the use of o- ring type seal 121 in slip joint 107, and use of o-ring seal 121 allows for thermal expansion of ducts 103, 105. O-ring seal 107 is preferably a high-temperature o-ring type seal. Slip joint 107 also supports duct 105 in both vertical and horizontal directions, but not in an axial direction. Axial control of duct 105 is accomplished with drag link 109, which connects flange 119 to secondary duct 105. The mounts of drag link 109 are preferably uni-ball connectors, and this configuration allows for relative axial movement between engine 117 and secondary duct 105, but this does not allow for vertical or lateral movement. The single degree of freedom associated with drag link 109 allows engine movement to push or pull secondary exhaust duct 105 consistently with primary duct 103 and keeps the system in the desired alignment.
The exhaust system provides for several advantages, including: (1) the ability to maintain primary and secondary exhaust ducts in a desired orientation; (2) low weight; (3) increased reliability and durability; and (4) easy installation.
This description includes reference to illustrative embodiments, but it is not intended to be construed in a limiting sense. Various modifications and combinations of the illustrative embodiments, as well as other embodiments, will be apparent to persons skilled in the art upon reference to the description.

Claims

Claims
1. An exhaust system for an aircraft having an airframe and an engine with an exhaust exit, the exhaust system comprising: a primary exhaust duct adapted to communicate exhaust gas from the engine exhaust exit and configured for movement with the engine; a secondary exhaust duct in fluid communication with the primary exhaust duct and adapted to be movably mounted to the airframe; and means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.
2. The exhaust system according to Claim 1 , wherein the relative alignment is generally coaxial.
3. The exhaust system according to Claim 1 , wherein the means for maintaining a generally consistent relative alignment comprises a drag link adapted to connect an end portion of the secondary duct to the exhaust exit.
4. The exhaust system according to Claim 1 , wherein the means for maintaining a generally consistent relative alignment comprises: a drag link adapted to connect an end portion of the secondary duct to the exhaust exit; and at least one strut adapted to connect the secondary duct to an airframe.
5. An aircraft engine system, comprising: an engine having an exhaust exit; a primary exhaust duct in fluid communication with the exhaust exit and configured for movement with the engine; a secondary exhaust duct in fluid communication with the primary exhaust duct and adapted to be movably mounted to the airframe; and means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.
6. The engine system according to Claim 5, wherein the relative alignment is generally coaxial.
7. The engine system according to Claim 5, wherein the means for maintaining a generally consistent relative alignment comprises a drag link connecting the secondary duct to the exhaust exit.
8. The engine system according to Claim 5, wherein the means for maintaining a generally consistent relative alignment comprises: a drag link connecting the secondary duct to the engine exhaust exit; and at least one strut adapted to connect the secondary duct to an airframe.
9. An aircraft, comprising: an airframe; an engine having an exhaust exit; a primary exhaust duct in fluid communication with the exhaust exit and configured for movement with the engine; a secondary exhaust duct in fluid communication with the primary exhaust duct and movably mounted to the airframe; and means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.
10. The aircraft according to Claim 9, wherein the relative alignment is generally coaxial.
11. The aircraft according to Claim 9, wherein the means for maintaining a generally consistent relative alignment comprises a link connecting the secondary duct to the exhaust exit.
12. The aircraft according to Claim 9, wherein the means for maintaining a generally consistent relative alignment comprises: a link connecting the secondary duct to the engine exhaust exit; and at least one strut connecting the secondary duct to the airframe.
13. An aircraft, comprising: an airframe; an engine having an exhaust exit; a primary exhaust duct in fluid communication with the exhaust exit and configured for movement with the engine; a secondary exhaust duct in fluid communication with the primary exhaust duct and movably mounted to the airframe; a link connecting the secondary duct to the engine exhaust exit; and at least one strut connecting the secondary duct to the airframe; wherein the link and at least one strut cooperate to maintain a generally consistent relative alignment between the primary duct and the secondary duct.
PCT/US2007/013679 2006-06-09 2007-06-11 Engine exhaust system Ceased WO2008097247A2 (en)

Priority Applications (10)

Application Number Priority Date Filing Date Title
BRPI0712611-5A BRPI0712611A2 (en) 2006-06-09 2007-06-11 engine exhaust system
CN2007800214973A CN101466940B (en) 2006-06-09 2007-06-11 Engine exhaust system
MX2008015788A MX2008015788A (en) 2006-06-09 2007-06-11 Engine exhaust system.
US12/303,963 US8123159B2 (en) 2006-06-09 2007-06-11 Engine exhaust system
JP2009514422A JP2009540195A (en) 2006-06-09 2007-06-11 Engine exhaust system
EP07872523A EP2032828A4 (en) 2006-06-09 2007-06-11 Engine exhaust system
DE07872523T DE07872523T1 (en) 2006-06-09 2007-06-11 MOTOR EXHAUST SYSTEM
EA200802441A EA200802441A1 (en) 2006-06-09 2007-06-11 EXHAUST ENGINE DEVICE
AU2007346730A AU2007346730A1 (en) 2006-06-09 2007-06-11 Engine exhaust system
CA2654751A CA2654751C (en) 2006-06-09 2007-06-11 Engine exhaust system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US81239106P 2006-06-09 2006-06-09
US60/812,391 2006-06-09

Publications (3)

Publication Number Publication Date
WO2008097247A2 true WO2008097247A2 (en) 2008-08-14
WO2008097247A3 WO2008097247A3 (en) 2008-10-16
WO2008097247A8 WO2008097247A8 (en) 2008-12-31

Family

ID=39682229

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2007/013679 Ceased WO2008097247A2 (en) 2006-06-09 2007-06-11 Engine exhaust system

Country Status (12)

Country Link
US (1) US8123159B2 (en)
EP (1) EP2032828A4 (en)
JP (1) JP2009540195A (en)
KR (1) KR20090020658A (en)
CN (1) CN101466940B (en)
AU (1) AU2007346730A1 (en)
BR (1) BRPI0712611A2 (en)
CA (1) CA2654751C (en)
DE (1) DE07872523T1 (en)
EA (1) EA200802441A1 (en)
MX (1) MX2008015788A (en)
WO (1) WO2008097247A2 (en)

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US20110000222A1 (en) * 2007-08-31 2011-01-06 General Electric Company Gas turbine rotor-stator support system
US20130344790A1 (en) * 2012-06-20 2013-12-26 Hamilton Sundstrand Corporation Air cycle machine for an environmental control system
EP3052783B1 (en) * 2013-10-01 2018-08-08 United Technologies Corporation Alignment system for exhaust installation
US9605562B2 (en) * 2015-02-09 2017-03-28 United Techologies Corporation Turbomachine accessory gearbox alignment pin
DE102015113159A1 (en) * 2015-08-10 2017-02-16 Faurecia Emissions Control Technologies, Germany Gmbh Component of an exhaust system
GB2634911A (en) * 2023-10-24 2025-04-30 Gkn Aerospace Sweden Ab Rear engine mounting structure

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US4772033A (en) 1983-09-28 1988-09-20 General Electric Company Flexible duct joint utilizing lip in recess in a flange
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JPH10252503A (en) 1997-03-13 1998-09-22 Tech Res & Dev Inst Of Japan Def Agency Connection and support structure of the engine and nozzle of the jet engine
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US2604339A (en) 1948-03-29 1952-07-22 Northrop Aircraft Inc Flexible tail pipe connection
US2579619A (en) 1949-12-14 1951-12-25 Ite Circuit Breaker Ltd Flexible tail pipe for jet engines
US3367108A (en) 1965-06-14 1968-02-06 Snecma Articulated connections for ducts
GB1437030A (en) 1972-09-15 1976-05-26 Snecma Sealing devices
GB2069612A (en) 1980-02-15 1981-08-26 Rolls Royce Gas Turbine Power Plant
US4772033A (en) 1983-09-28 1988-09-20 General Electric Company Flexible duct joint utilizing lip in recess in a flange
DE4109100A1 (en) 1990-07-27 1992-01-30 Gen Electric SEALING RING
JPH10252503A (en) 1997-03-13 1998-09-22 Tech Res & Dev Inst Of Japan Def Agency Connection and support structure of the engine and nozzle of the jet engine
WO2006041463A1 (en) 2004-10-01 2006-04-20 Bell Helicopter Textron Inc. Free floating bellows

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Title
See also references of EP2032828A4

Also Published As

Publication number Publication date
CA2654751A1 (en) 2008-08-14
US8123159B2 (en) 2012-02-28
EA200802441A1 (en) 2009-06-30
US20100229569A1 (en) 2010-09-16
CN101466940A (en) 2009-06-24
WO2008097247A3 (en) 2008-10-16
MX2008015788A (en) 2009-03-06
DE07872523T1 (en) 2009-07-30
EP2032828A4 (en) 2012-10-10
CN101466940B (en) 2012-03-21
KR20090020658A (en) 2009-02-26
WO2008097247A8 (en) 2008-12-31
BRPI0712611A2 (en) 2012-10-23
JP2009540195A (en) 2009-11-19
EP2032828A2 (en) 2009-03-11
CA2654751C (en) 2012-12-18
AU2007346730A1 (en) 2008-08-14

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