US2615300A - Combustion chamber for gas turbines and having flame tube mounting means allowing radial and axial expansion - Google Patents

Combustion chamber for gas turbines and having flame tube mounting means allowing radial and axial expansion Download PDF

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Publication number
US2615300A
US2615300A US733911A US73391147A US2615300A US 2615300 A US2615300 A US 2615300A US 733911 A US733911 A US 733911A US 73391147 A US73391147 A US 73391147A US 2615300 A US2615300 A US 2615300A
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Prior art keywords
flame tube
casing
combustion chamber
air
flame
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Expired - Lifetime
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US733911A
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Lombard Adrian Albert
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Rolls Royce PLC
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Rolls Royce PLC
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    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means

Definitions

  • This invention relates to combustion chambers of the kind employed in aircraft gas turbine engines. More particularly this invention relates to combustion chambers of the kind comprising an elongated outer casing having an air inlet at one end, and a flame tube mounted within the outer casing.
  • the object of the pres-- '.ent invention is to provide improvedmeans for .supportingthe flame tubein the outer casing.
  • the flametube in a combustion chamber of the above-kind is supported at each end from the outer casing with freedom for axial movement and radial ex- "pansion and means is provided for restraining at :a. single point on the flame tube, relative axial 'movement of the'flame tube and the outercasing.
  • said'member also restrains relative "rotational movement of the flame tube.
  • the said means conveniently comprises a spigot and socket carried one by the outer casing and the other by the flame tube.
  • Figure 1 is a longitudinal sectional view of a combustion chamberin accordance withthis invention
  • Figure2' is a view in the direction of arrow 2 A01? Figure 1, and
  • Figure '3 is. a fragmentary view of a part of- Figure 1 to an enlarged scale for the sake of clar- 1 ity.
  • the combustion chamber as shown in Figure 1, comprises a tubular outer casing 5 having an air inlet 6 at one end and a flame tube I mounted co-axially within the casing 5.
  • the inlet 6 to the combustion chamber communicates with a compressor of the internal combustion turbine in known manner.
  • the discharge endvof the combustion "chamber is supported "as hereinafter more fully described, from a'nozzle box casing 8 which also serves to support the nozzle box 9 by which the combustion products are conveyed from the chamber to the turbine.
  • a burner assembly generally indicated by the reference numeral ID is mounted in the inlet end of the casing 5. Fuel is supplied to this burner from which it emerges as an atomised spray directed towards the discharge end of the combustion chamber.
  • the air entering the inlet 6 is divided into various streams, the primary air stream passing between vanes H to within the flame tube whilst the secondary air passes between the casing 5 and the flame tube and enters the latter through the holes 12. Tertiary radially withinthe outer casing.
  • the burner assembly I0 has a cylin'dricalportion' MLprojecting'into the inlet end of the flame tube 1. 1
  • The'latter carries the vanes l I which im part a swirling motion to the primary air.
  • vanes H carryan inner shroud'liwhich fits on the cylindrical portion M of the burner'assembly, being slid axially thereon. In this way the flame'tube issu'pporte'd on the burner.
  • the outlet end of the flame tube 1' is mounted in the outercasing 5 by means'of a-sheet metal band 16' which surrounds the outer surface' of the'flame tube and is secured thereto at one end.
  • the pin extends across the space between the casing 5 and the'flame tube 1 and fits'as. a spigot in a'soeket 20- secured tothe .flame'tube I.
  • the dowel pin l8 restrai'n's'the flame "tube. from both axial and rotary "movements relativelyto the casing! but imposesno restraint on expansion of the flame tube either radially or axially to each side, of the pin. 1"
  • the flame tube 1 is supported at ,each..end and is located at a point along its length, this construction'permitting the flame tubeto expand freely both ,zradially and axially whilst being correctly located in the outer casing.
  • a combustion chamber of the kind employed in an aircraft gas turbine engine comprising an air casing having an inlet end and outlet end, a cylindrical member secured to said air casing to lie within it at its inlet end, a flame tube having an internal cylindrical bore in axial sliding engagement with said cylindrical member, axial sliding means to support said flame tube within said air casing at the outlet end thereof, said axial sliding means being of the kind which permits radial expansion of said flame tube relative to said air casing, and locating means to locate said flame tube axially with respect to the air casing, said locating means permitting free 3 radial expansion of said flame tube with respect to said air casing.
  • a combustion chamber of the kind employed in an aircraft gas turbine engine comprising an air casing having an inlet end and an outlet end, a cylindrical member secured to said air casing to lie within it at its inlet end, a flame tube having an internal cylindrical bore in axial sliding engagement with said cylindrical member, axial sliding radially-deformable resilient means to support said flame tube within said air casing at the outlet end thereof, and locating means secured with respect to said air casing and engaging said flame tube to locate said flame tube axially with respect to the air casing, said locating means and said flame tube engaging each other in a manner to permit relative radial movement therebetween.
  • a combustion chamber of the kind employed in an aircraft gas turbine engine comprising in combination an elongated outer casing having an air inlet at one end and an exhaust" outlet at the other end, an elongated flame-tube within said outer casing, said flame tube having an inlet end adjacent said air inlet and an outlet end adjacent said exhaust outlet, a cylindrical member secured with respect to said outer casing to lie within it in said air inlet for supporting said flame tube, a sleeve formed on the inlet end of said flame tube having an internal cylindrical bore to receive said cylindrical member with freedom for relative axialmovement between said cylindrical member and said flame tube at said inlet end, second supporting means secured with respect to said outer casing for supporting said flame tube at said outlet end with freedom for relative axial movement between said second supporting means and said flame tube at said outlet end, said second supporting means being of the kind which permits radialexpansion of said flame tube relative to said air casing, and locating means secured with respect to said outer casing and engaging said flame tube at a single place between said first andsecond supporting means to prevent
  • a combustion chamber of the kind employed in an aircraft gas turbine engine comprising an air casing having an inlet and an out- -let end, a-- cylindrical member secured to said air casing to lie coaxially within it at its inlet end, ,aflame tube-having an internal cylindrical bore coaxial vwiththe flame tube and in axial sliding engagement with said cylindrical member, axial sliding means to support said flame tube within said air casing at the outlet end thereof, said axial sliding means being of the kind which permits radial expansion of said flame tube relative to said air casing and locating means to locate said flame tube axially with end, a cylindrical member secured to said air casing to lie within it at its inlet end, a flame tube, having an internal cylindrical bore in axial sliding engagement with said cylindrical member, axial sliding means to support said flame tube within said air casing at the outlet end thereof, said axial sliding means being of the kind which permits radial expansion of said flame tube relative to said casing, a radially-inwardly-extending dowel secured to said air casing
  • a combustion chamber of the kind employed in an aircraft gas turbine engine comprising an air casing having an inlet end and an outlet end, a cylindrical fuel injector secured to said air casing to lie within it at its inlet end, a flame tube having an internal cylindrical bore in axial sliding engagement with said fuel injector, axial sliding means to support said flame tube within said air casing at the outlet end thereof, and locating means to locate said flame tube axially with respect to said air casing, said axial sliding means and said locating means being of the kind which permit radial expansion of said flame tube relative to said air casing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Description

Oct. 28, A. BARD COMBUSTION CHAMBER FOR GAS TURBINES AND HAVING FLAME TUBE MOUNTING MEANS ALLOWING RADIAL AND AXIAL EXPANSION Filed March 11, 1947 2 SHEETS-SHEET l v d zomlaz'd 2,615,300 ES AND HAVING FLAME' TUBE" MOUNTING MEANS ALLOWING RADIAL AND AXIAL EXPANSION Filed March 11, 1947 2 SHEETS-SHEET 2 A. A.\LOMBARD COMBUSTION CHAMBER FOR GAS TURBIN w m MM z w m m Patented Oct. 28, 1952 UNITED js'rAr-s S E OFFICE.
COMBUSTION CHAMBER FOB GAS TUR- BINES AND HAVING FLAME TUBE MOUNT- .ING -MEANS ALLOWING 'RADIAL AND AXIAL EXPANSION Adrian Albert Lombard, Clitherce, England, as-
' signor to Rolls Royce Limited, Derby, England,
a British company Application March 11, 1947, Serial No. 733,911 In Great Britain April 8, 1946 '6 Claims.
This invention relates to combustion chambers of the kind employed in aircraft gas turbine engines. More particularly this invention relates to combustion chambers of the kind comprising an elongated outer casing having an air inlet at one end, and a flame tube mounted within the outer casing. The object of the pres-- '.ent invention is to provide improvedmeans for .supportingthe flame tubein the outer casing. Accordingto the present invention the flametube in a combustion chamber of the above-kind ,.is supported at each end from the outer casing with freedom for axial movement and radial ex- "pansion and means is provided for restraining at :a. single point on the flame tube, relative axial 'movement of the'flame tube and the outercasing. Preferably said'member also restrains relative "rotational movement of the flame tube. The said means conveniently comprises a spigot and socket carried one by the outer casing and the other by the flame tube.
A specific embodiment of the invention will now be described, by way of example, with reference to the accompanying drawings whereof,
Figure 1 is a longitudinal sectional view of a combustion chamberin accordance withthis invention,
.Figure2'is a view in the direction of arrow 2 A01? Figure 1, and
Figure '3 is. a fragmentary view of a part of- Figure 1 to an enlarged scale for the sake of clar- 1 ity.
'The combustion chamber, as shown in Figure 1, comprises a tubular outer casing 5 having an air inlet 6 at one end and a flame tube I mounted co-axially within the casing 5. The inlet 6 to the combustion chamber communicates with a compressor of the internal combustion turbine in known manner. ,The discharge endvof the combustion "chamber is supported "as hereinafter more fully described, from a'nozzle box casing 8 which also serves to support the nozzle box 9 by which the combustion products are conveyed from the chamber to the turbine.
A burner assembly generally indicated by the reference numeral ID is mounted in the inlet end of the casing 5. Fuel is supplied to this burner from which it emerges as an atomised spray directed towards the discharge end of the combustion chamber. The air entering the inlet 6 is divided into various streams, the primary air stream passing between vanes H to within the flame tube whilst the secondary air passes between the casing 5 and the flame tube and enters the latter through the holes 12. Tertiary radially withinthe outer casing.
a 2 airv flowing between the casing andthe'fla'me tube enters the latter through the openings I3.
The burner assembly I0 has a cylin'dricalportion' MLprojecting'into the inlet end of the flame tube 1. 1 The'lattercarries the vanes l I which im part a swirling motion to the primary air. The
"vanes H carryan inner shroud'liwhich fits on the cylindrical portion M of the burner'assembly, being slid axially thereon. In this way the flame'tube issu'pporte'd on the burner.
' The outlet end of the flame tube 1' is mounted in the outercasing 5 by means'of a-sheet metal band 16' which surrounds the outer surface' of the'flame tube and is secured thereto at one end.
The other endof the band I6 is bent outwardly to be clear of the flame tube and is provided with a number orslots [1 in a hitherto known manner 'to form resilient fingers which 'bear against aring secured to' the endof 'the'outer casing'B. In thisway the flame tube '1 is located radially i'n'the outer casingwith-freedom"for axial movementrelativelythereto. This: mountingalso' permits of theflame tube expanding A dowel pin, |8"is screwed 'nto 'a-"c'ollar H! which issecuredto the outer casing 5 towards the front end of it. :The pin extends across the space between the casing 5 and the'flame tube 1 and fits'as. a spigot in a'soeket 20- secured tothe .flame'tube I. The dowel pin l8 restrai'n's'the flame "tube. from both axial and rotary "movements relativelyto the casing! but imposesno restraint on expansion of the flame tube either radially or axially to each side, of the pin. 1"
It will be seen that with the presentinvention the flame tube 1 is supported at ,each..end and is located at a point along its length, this construction'permitting the flame tubeto expand freely both ,zradially and axially whilst being correctly located in the outer casing.
I claim:
1. A combustion chamber of the kind employed in an aircraft gas turbine engine comprising an air casing having an inlet end and outlet end, a cylindrical member secured to said air casing to lie within it at its inlet end, a flame tube having an internal cylindrical bore in axial sliding engagement with said cylindrical member, axial sliding means to support said flame tube within said air casing at the outlet end thereof, said axial sliding means being of the kind which permits radial expansion of said flame tube relative to said air casing, and locating means to locate said flame tube axially with respect to the air casing, said locating means permitting free 3 radial expansion of said flame tube with respect to said air casing.
2. A combustion chamber of the kind employed in an aircraft gas turbine engine comprising an air casing having an inlet end and an outlet end, a cylindrical member secured to said air casing to lie within it at its inlet end, a flame tube having an internal cylindrical bore in axial sliding engagement with said cylindrical member, axial sliding radially-deformable resilient means to support said flame tube within said air casing at the outlet end thereof, and locating means secured with respect to said air casing and engaging said flame tube to locate said flame tube axially with respect to the air casing, said locating means and said flame tube engaging each other in a manner to permit relative radial movement therebetween.
3. A combustion chamber of the kind employed in an aircraft gas turbine engine comprising in combination an elongated outer casing having an air inlet at one end and an exhaust" outlet at the other end, an elongated flame-tube within said outer casing, said flame tube having an inlet end adjacent said air inlet and an outlet end adjacent said exhaust outlet, a cylindrical member secured with respect to said outer casing to lie within it in said air inlet for supporting said flame tube, a sleeve formed on the inlet end of said flame tube having an internal cylindrical bore to receive said cylindrical member with freedom for relative axialmovement between said cylindrical member and said flame tube at said inlet end, second supporting means secured with respect to said outer casing for supporting said flame tube at said outlet end with freedom for relative axial movement between said second supporting means and said flame tube at said outlet end, said second supporting means being of the kind which permits radialexpansion of said flame tube relative to said air casing, and locating means secured with respect to said outer casing and engaging said flame tube at a single place between said first andsecond supporting means to prevent axial movement relative to said outer casing of said I flame tube at said single place.
4; A combustion chamber of the kind employed in an aircraft gas turbine engine comprising an air casing having an inlet and an out- -let end, a-- cylindrical member secured to said air casing to lie coaxially within it at its inlet end, ,aflame tube-having an internal cylindrical bore coaxial vwiththe flame tube and in axial sliding engagement with said cylindrical member, axial sliding means to support said flame tube within said air casing at the outlet end thereof, said axial sliding means being of the kind which permits radial expansion of said flame tube relative to said air casing and locating means to locate said flame tube axially with end, a cylindrical member secured to said air casing to lie within it at its inlet end, a flame tube, having an internal cylindrical bore in axial sliding engagement with said cylindrical member, axial sliding means to support said flame tube within said air casing at the outlet end thereof, said axial sliding means being of the kind which permits radial expansion of said flame tube relative to said casing, a radially-inwardly-extending dowel secured to said air casing, and a radially-outwardly-extending socket secured to said flame tube and receiving said dowel, whereby said dowel and socket locate said flame tube axially with respect to said air casing and permit relative radial expansion between said flame tube and said air casing by sliding of the dowel within the socket.
6. A combustion chamber of the kind employed in an aircraft gas turbine engine comprising an air casing having an inlet end and an outlet end, a cylindrical fuel injector secured to said air casing to lie within it at its inlet end, a flame tube having an internal cylindrical bore in axial sliding engagement with said fuel injector, axial sliding means to support said flame tube within said air casing at the outlet end thereof, and locating means to locate said flame tube axially with respect to said air casing, said axial sliding means and said locating means being of the kind which permit radial expansion of said flame tube relative to said air casing.
ADRIAN ALBERT LOMBARD.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Date OTHER REFERENCES Proceedings,Institute of Mech. Eng. (London), 1945, vol. 153,,pages 465 and 466.
US733911A 1946-04-08 1947-03-11 Combustion chamber for gas turbines and having flame tube mounting means allowing radial and axial expansion Expired - Lifetime US2615300A (en)

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GB10805/46A GB612532A (en) 1946-04-08 1946-04-08 Improvements in or relating to combustion chambers for internal combustion turbines

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Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2800767A (en) * 1952-12-31 1957-07-30 United Aircraft Corp Combustion section construction
US2828608A (en) * 1950-11-17 1958-04-01 Power Jets Res & Dev Ltd Improved construction of combustion chamber of the cyclone or vortex type
US2839894A (en) * 1952-12-31 1958-06-24 Gen Motors Corp Supporting arrangement for a gas turbine combustion chamber
US2851854A (en) * 1955-01-21 1958-09-16 United Aircraft Corp Afterburner liner
US3048015A (en) * 1959-07-08 1962-08-07 Gen Motors Corp Combustion chamber support and igniter
US3084907A (en) * 1960-10-31 1963-04-09 Gen Electric Gas turbine scroll mount
US5224825A (en) * 1991-12-26 1993-07-06 General Electric Company Locator pin retention device for floating joint
US5419114A (en) * 1992-07-18 1995-05-30 Man Gutehoffnungshutte Ag Thermoelastic connection of the injector tube and the flame tube of a gas turbine
US5572863A (en) * 1994-09-15 1996-11-12 Rolls-Royce Plc Resilient annular mounting member for a transition duct of a combustion chamber
US6116013A (en) * 1998-01-02 2000-09-12 Siemens Westinghouse Power Corporation Bolted gas turbine combustor transition coupling
US20050016182A1 (en) * 2003-07-08 2005-01-27 Oleg Morenko Combustor attachment with rotational joint
US20050050902A1 (en) * 2003-08-28 2005-03-10 Nuovo Pignone Holdings Spa Fixing system of a flame pipe or liner
US20080034759A1 (en) * 2006-08-08 2008-02-14 David Edward Bulman Methods and apparatus for radially compliant component mounting
US20090060636A1 (en) * 2005-02-22 2009-03-05 Lev Alexander Prociw Positioning arrangement for components of a pressure vessel and method
US20090064681A1 (en) * 2007-09-07 2009-03-12 The Boeing Company Scalloped Flexure Ring
US20100227698A1 (en) * 2007-09-07 2010-09-09 The Boeing Company Bipod Flexure Ring
US9416969B2 (en) * 2013-03-14 2016-08-16 Siemens Aktiengesellschaft Gas turbine transition inlet ring adapter

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1011066A (en) * 1948-11-30 1952-06-18 Combustion chamber
DE1060667B (en) * 1955-10-15 1959-07-02 Stroemungsmasch Anst Combustion device for gas turbines
US2852914A (en) * 1955-12-30 1958-09-23 United Aircraft Corp Combustion chamber support means
DE1047536B (en) * 1956-07-07 1958-12-24 Daimler Benz Ag Combustion chamber for gas turbines

Citations (9)

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Publication number Priority date Publication date Assignee Title
US2183313A (en) * 1938-07-07 1939-12-12 Robert H Goddard Combustion chamber for aircraft
US2195025A (en) * 1935-07-17 1940-03-26 Couzinet Rene Alexandre Arthur Gas turbine
US2225775A (en) * 1940-01-26 1940-12-24 David L Garrett Apparatus for deparaffining oil wells
US2268464A (en) * 1939-09-29 1941-12-30 Bbc Brown Boveri & Cie Combustion chamber
US2420135A (en) * 1944-06-07 1947-05-06 Elliott Co Support for expansible members
GB588086A (en) * 1943-04-01 1947-05-14 Power Jets Ltd Improvements relating to combustion apparatus
US2432359A (en) * 1947-12-09 Internal-combustion turbine power
US2458497A (en) * 1945-05-05 1949-01-11 Babcock & Wilcox Co Combustion chamber
US2500925A (en) * 1943-03-13 1950-03-21 Claude A Bonvillian Apparatus for the combustion of fuel

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2432359A (en) * 1947-12-09 Internal-combustion turbine power
US2195025A (en) * 1935-07-17 1940-03-26 Couzinet Rene Alexandre Arthur Gas turbine
US2183313A (en) * 1938-07-07 1939-12-12 Robert H Goddard Combustion chamber for aircraft
US2268464A (en) * 1939-09-29 1941-12-30 Bbc Brown Boveri & Cie Combustion chamber
US2225775A (en) * 1940-01-26 1940-12-24 David L Garrett Apparatus for deparaffining oil wells
US2500925A (en) * 1943-03-13 1950-03-21 Claude A Bonvillian Apparatus for the combustion of fuel
GB588086A (en) * 1943-04-01 1947-05-14 Power Jets Ltd Improvements relating to combustion apparatus
US2420135A (en) * 1944-06-07 1947-05-06 Elliott Co Support for expansible members
US2458497A (en) * 1945-05-05 1949-01-11 Babcock & Wilcox Co Combustion chamber

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2828608A (en) * 1950-11-17 1958-04-01 Power Jets Res & Dev Ltd Improved construction of combustion chamber of the cyclone or vortex type
US2800767A (en) * 1952-12-31 1957-07-30 United Aircraft Corp Combustion section construction
US2839894A (en) * 1952-12-31 1958-06-24 Gen Motors Corp Supporting arrangement for a gas turbine combustion chamber
US2851854A (en) * 1955-01-21 1958-09-16 United Aircraft Corp Afterburner liner
US3048015A (en) * 1959-07-08 1962-08-07 Gen Motors Corp Combustion chamber support and igniter
US3084907A (en) * 1960-10-31 1963-04-09 Gen Electric Gas turbine scroll mount
US5224825A (en) * 1991-12-26 1993-07-06 General Electric Company Locator pin retention device for floating joint
US5419114A (en) * 1992-07-18 1995-05-30 Man Gutehoffnungshutte Ag Thermoelastic connection of the injector tube and the flame tube of a gas turbine
US5572863A (en) * 1994-09-15 1996-11-12 Rolls-Royce Plc Resilient annular mounting member for a transition duct of a combustion chamber
US6116013A (en) * 1998-01-02 2000-09-12 Siemens Westinghouse Power Corporation Bolted gas turbine combustor transition coupling
US20050016182A1 (en) * 2003-07-08 2005-01-27 Oleg Morenko Combustor attachment with rotational joint
US7024863B2 (en) 2003-07-08 2006-04-11 Pratt & Whitney Canada Corp. Combustor attachment with rotational joint
EP1564494A2 (en) 2003-08-28 2005-08-17 Nuovo Pignone Holding S.P.A. Fixing system of a flame pipe or liner
US20050050902A1 (en) * 2003-08-28 2005-03-10 Nuovo Pignone Holdings Spa Fixing system of a flame pipe or liner
US7555906B2 (en) * 2003-08-28 2009-07-07 Nuovo Pignone Holding S.P.A. Mounting system for a flame pipe or liner
EP1564494A3 (en) * 2003-08-28 2013-01-16 Nuovo Pignone Holding S.P.A. Fixing system of a flame pipe or liner
US20090060636A1 (en) * 2005-02-22 2009-03-05 Lev Alexander Prociw Positioning arrangement for components of a pressure vessel and method
US20080034759A1 (en) * 2006-08-08 2008-02-14 David Edward Bulman Methods and apparatus for radially compliant component mounting
US8141370B2 (en) * 2006-08-08 2012-03-27 General Electric Company Methods and apparatus for radially compliant component mounting
US20090064681A1 (en) * 2007-09-07 2009-03-12 The Boeing Company Scalloped Flexure Ring
US20100227698A1 (en) * 2007-09-07 2010-09-09 The Boeing Company Bipod Flexure Ring
US8328453B2 (en) 2007-09-07 2012-12-11 The Boeing Company Bipod flexure ring
US8726675B2 (en) * 2007-09-07 2014-05-20 The Boeing Company Scalloped flexure ring
US8834056B2 (en) 2007-09-07 2014-09-16 The Boeing Company Bipod flexure ring
US9416969B2 (en) * 2013-03-14 2016-08-16 Siemens Aktiengesellschaft Gas turbine transition inlet ring adapter

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GB612532A (en) 1948-11-15
FR944168A (en) 1949-03-29
CH261728A (en) 1949-05-31

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