US3899882A - Gas turbine combustor basket cooling - Google Patents

Gas turbine combustor basket cooling Download PDF

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Publication number
US3899882A
US3899882A US455161A US45516174A US3899882A US 3899882 A US3899882 A US 3899882A US 455161 A US455161 A US 455161A US 45516174 A US45516174 A US 45516174A US 3899882 A US3899882 A US 3899882A
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United States
Prior art keywords
combustor
air
generally
combustor basket
disposed
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.)
Expired - Lifetime
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US455161A
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English (en)
Inventor
Stephen R Parker
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Westinghouse Electric Corp
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Westinghouse Electric Corp
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Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Priority to US455161A priority Critical patent/US3899882A/en
Priority to CA221,030A priority patent/CA983730A/en
Priority to IT21651/75A priority patent/IT1034535B/it
Priority to JP50035667A priority patent/JPS5235806B2/ja
Application granted granted Critical
Publication of US3899882A publication Critical patent/US3899882A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/045—Air inlet arrangements using pipes

Definitions

  • a step-liner type combustion chamber for a gas turbine has a combustor basket cooling arrangement as part of the combustion air orifice structure.
  • the combustion air orifices include a flanged tubular arrangement for ducting combustion air into the combustion chamber while causing air adjacent to the orifice to flow along the combustor basket wall for cooling purposes.
  • the flange is disposed outwardly of the combustor basket and has a spacer member disposed between the flange and the gasket.
  • the tubular portion extends into the basket.
  • the spacer has a gap disposed on its downstream side.
  • An arrangement for air supply orifices is similar, whereby a disc is raised radially outwardly from the combustor basket surface by a spacer member.
  • Each spacer member has a gap across its downstream side to cause air to flow therethrough between the basket wall and the disc member or flange portion on the tubular arrangements, permitting air currents to pass close to the combustor basket wall. This flow of air next to the basket wall increases heat transfer by convection thereby reducing distortion and weld failure in the combustor basket wall.
  • a gas turbine power plant has a compressor section, in which there is disposed at least one combustor or combustion chamber, and a turbine section.
  • the combustion chamber is of the step-liner type and is comprised of wall portions having a step configuration, each of the portions being of greater diameter than the preceding portion from the upstream end to the downstream end of the combustor.
  • Disposed in annular arrays within the liner portions are several types of combustion air inlet orifices.
  • One type of combustion air inlet orifice is comprised ofa generally tubular member extending inwardly into the combustor basket through a hole in the wall of the combustor.
  • the tubular member has an annular flange on its radially outer end.
  • An intermediate spacer is fixedly attached around each hole, to the combustor basket, and the flange is attached radially outwardly of the spacer.
  • the spacer has an arcuate gap on its downstream side to permit air to flow between the flange and the wall of the combustor basket.
  • the air flowing next to the combustor basket wall aids in convective heat transfer with the hot combustor basket walls. This air also prevents combustion flame from attaching to the downstream side of the tubular portion of the air inlet orifice, reducing the incidence of inlet orifice burning common in the prior art.
  • a similar type combustor basket wall cooling arrangement is used for combustion air holes, wherein a disc member having a hole therein is disposed over an intermediate spacer having a hole.
  • the spacer being disposed about an air entrance hole in the combustor basket wall.
  • An arcuate gap is disposed on the downstream side of the spacer member to permit air to flow between the disc member and the wall of the combustor basket.
  • the air passing adjacent to the combustor basket wall due to the above described configuration increases the convective heat transfer from the conbustor wall and therefore reduces distortion and spot weld failures common to the prior art.
  • the air entering the combustor basket close to the main entrance passageway reduces the entrainment of any cooling film caused by the ejector effect of the air jet entering into the combustor basket through the main air entrance passageways.
  • FIG. 1 is an axial sectional view of a portion of the upper half of a gas turbine power plant provided with combustion apparatus constructed in accordance with the principles of this invention
  • FIG. 2 is an enlarged sectional view of the combus tion apparatus illustrated in FIG. 1;
  • FIG. 3 is a view taken along lines III-III of FIG. 2;
  • FIG. 4 is a view taken along lines IV-IV of FIG. 3;
  • FIG. 5 is a view taken along lines VV of FIG. 2;
  • FIG. 6 is a view taken along lines VIVI of FIG. 5.
  • FIG. I there is shown a portion of a gas turbine power plant 10 having combustion apparatus 12.
  • the combustion apparatus 12 may be employed with any suitable type of gas turbine power plant.
  • the power plant 10 includes an axial flow air compressor 14, for directing air to the combustion apparatus 12, and a gas turbine 16 connected to the combustion apparatus 10, which receives hot products of combustion therefrom for motivating the power plant.
  • the air compressor 14 includes, as well known in the art, a multistage bladed rotor structure 18 cooperatively associated with a stator structure having equal number of multistage stationary blades 20 for compressing the air directed therethrough to a suitable pressure value for combustion in the combustion apparatus 12.
  • the outlet of the compressor 14 is directed through an annular diffusion member 22 forming an intake for a plenum chamber 24, partially defined by a housing structure 26.
  • the housing 26 includes a shell member of circular cross section 25, and as shown, of cylindrical shape, coaxial with the axis of rotation R R of the power plant 10, a forward dome-shaped wall member 28 connected to the external casing of the compressor 14 and a rearward annular wall member 30 connected to the outer casing of the turbine I6.
  • the turbine 16 is of the axial flow type and includes a plurality of expansion stages formed by a plurality of rows of stationary blades 32 cooperatively associated with an equal plurality of rotating blades 34 mounted on a turbine rotor 36.
  • the turbine rotor 36 is drivingly connected to the compressor rotor by a tubular connecting shaft member 27, and a tubular liner or fairing member 29 is suitably supported in encompassing stationary relation with the connecting shaft portion 27 to provide a smooth air flow surface for the air entering the plenum chamber 24 from the compressor diffuser 22.
  • combustion chambers 38 Disposed within the housing 26 are a plurality of tubular elongated combustion chambers or combustors 38 only one being shown, of the telescopic step-liner type.
  • the combustion chambers 38 are disposed in an annular mutually spaced array concentric with the center line of the power plant and are equally spaced from each other in the housing 26.
  • the chambers 38 are arranged in such a manner that their axes are substantially parallel to the outer casing 26 and with the center line R R of the power plant 10. It is pointed out that this invention is applicable to other types of combustors such as the single annular basket type or the can annular type having composite features of the canister and annular types.
  • each combustor 38 is comprised of three sections: an upstream primary portion 40, an intermediate secondary portion 42 and a downstream transition portion 44.
  • the forward wall 28 of the combustion apparatus 12 is provided with a central opening 35 through which a fuel injector 37 extends.
  • the fuel injector 37 is supplied with fuel by a suitable conduit 39 connected to any suitable fuel supply, not shown, and may be of the well known atomizing type formed in a manner to provide a substantially conical spray of fuel within the primary portion 40 of the combustion chamber 38.
  • a suitable electrical ignitor 41 is provided for igniting the fuel and air mixture in the combustor 38.
  • the primary portion 40 of the combustor 38 are a plurality of liner portions 47 of circular cross section and in the example shown, the liner portions are cylindrical.
  • the primary portion 40 is of stepped liner construction, each of the liner portions 47 having a circular section of greater circumference or diameter than the preceding portions from the upstream to the downstream end of the combustor to permit telescopic insertion of the portions.
  • Some portions 47 have an annular array of apertures, 50 and 52, for admitting primary or secondary air from within the plenum chamber 24 into the primary portion 40 of the combustor to support combustion of the fuel ejected therein by the fuel injector 37.
  • the combustor 38 further includes the intermediate portion 42 which is provided with additional arrays of annular rows of apertures 50 and 52 for admitting secondary air from the plenum chamber 24 into the combustor 38 during operation, to cool the hot gaseous products and make it adaptable to the turbine blades 32 and 34.
  • the transition portion 44 is provided with a forward portion 45 of cylindrical shape disposed in encompassing and slightly overlapping relationship with the intermediate portion 42.
  • the transition protion 44 is also provided with a rearward tubular portion 49 that purposely changes in contour from a circular cross section at the juncture with the cylindrical portion 45 to an arcuate cross section at its outlet end portion 51.
  • the arcuate extent of the outlet 51 is such that jointly with the outlets of the other combustors 38, not shown, a complete annulus is provided for admitting the hot products of combustion from each of the combustors 38 to the blades 32 and 34 of the turbine 16, thereby to provide full peripheral admission of the motivating gasses into the turbine 16.
  • the combustor 38 has a plurality of combustion air orifices or apertures 50 and 52 disposed in annular arrays thereon.
  • the combustion air orifices, 50 and 52 comprise a portion of the combustion air supply means, which cause air to enter the combustor 38 through a plurality of holes 49 in the combustor liner member 47 or basket walls.
  • Aperture 50 otherwise known as an air scoop, is shown in detail in FIGS. 3 and 4.
  • the aperture 50 is comprised of a tubular portion 60, a generally annular flange portion 62, and an intermediate spacer member 64.
  • Each tubular portion 60 is disposed through a hole 49 in the basket wall 47, and extends radially inwardly into the combustion chamber of combustor basket 38.
  • Disposed between the walls or liner 47 of the combustor basket 38 and the annular flange member 62 of the air scoop 50 is an intermediate spacer member 64.
  • the intermediate spacer member 64 may be generally C- shaped, however, the gap portion may be larger than the spacer member segment 64 itself.
  • An arcuate gap 66 defined by the dotted lines 65 and 67 is shown in FIG.
  • the gap 66 could be defined by dotted lines 65' and 67 or by a plurality of arcuate gaps spaced therebetween.
  • the arcuate gap 66 shown in FIG. 3 permits the flow of air therethrough, cooling the combustor basket wall 47.
  • the air flowing through the arcuate gap follows the path indicated by the letter E, shown in FIG. 4.
  • the tubular portion 60 of the aperture or air scoop 50 forces some of the air into the inner portion of the combustor 12 for combustion of the fuel and the mixing of the combustion products.
  • the air scoop 50 is shown in FIGS. I and 2, on both the primary combustor areas 40 and the secondary diluent areas 42 of the combustor 38.
  • Aperture 52 is shown in detail in FIGS. 5 and 6. Each aperture 52 is disposed radially outwardly of its respective hole 49 in the liner walls 47 of the combustor basket 38.
  • Each air orifice 52 is comprised of a disc member 70, and a generally C-shaped intermediate spacer member 72.
  • Each disc member 70 has a hole 73 disposed through its center portion. The diameter of the hole 73 in disc 70 may be dissimilar to the diameter of its respective hole 49 that is disposed in the wall 47 of the combustor basket 38. Disposed between the walls or liner 47 of the combustor basket and the disc member 70, is C-shaped intermediate spacer member 72.
  • An arcuate gap 74 defined by the dotted line 75 and 77, is shown in FIG. 5, disposed on the downstream side of the air orifice 52.
  • the gap 74 may be defined by a combination of the dotted lines 75, 75", 77 and 77".
  • the arcuate gap 74 in any case, permits the flow of air therethrough, cooling the combustor basket wall 47, by convection;
  • the air flowing through the arcuate gap 74 follows the path indicated by the letter G, shown in FIG. 6.
  • Both of the apertures 50 and 52 may be spot welded to their respective intermediate spacer members, 64 and 72, as indicated in FIGS. 3, 4, 5 and 6, by an array of spot weld marks 69.
  • the cooling permitted by the apertures 50 and 52, is caused by the forced convective cooling close to the combustor basket wall 47.
  • a combustor for a gas turbine comprising:
  • annular arrays of air inlets comprising:
  • annular arrays of air scoops disposed in said generally cylindrical combustor basket
  • annular arrays of air orifices disposed in said generally cylindrical combustor basket
  • said intermediate generally annular spacer member between said generally annular flange and said combustor basket having at least one arcuate gap disposed therein;
  • said air orifices being comprised of
  • a disc member having an air passage hole there through, said hole in said disc member being disposed generally radially outwardly of its respective adjacent hole in said combustor basket;
  • said disc members and said second intermediate annular spacer members being fixedly attached to each other and said combustor basket;
  • said second intermediate generally annular spacer member between said disc member and said combustor basket having at least one generally arcuate gap disposed therein.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US455161A 1974-03-27 1974-03-27 Gas turbine combustor basket cooling Expired - Lifetime US3899882A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US455161A US3899882A (en) 1974-03-27 1974-03-27 Gas turbine combustor basket cooling
CA221,030A CA983730A (en) 1974-03-27 1975-02-28 Gas turbine combustor basket cooling
IT21651/75A IT1034535B (it) 1974-03-27 1975-03-26 Raffreddamento del tubo di fiamma di una turbina a gas
JP50035667A JPS5235806B2 (enrdf_load_stackoverflow) 1974-03-27 1975-03-26

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US455161A US3899882A (en) 1974-03-27 1974-03-27 Gas turbine combustor basket cooling

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US (1) US3899882A (enrdf_load_stackoverflow)
JP (1) JPS5235806B2 (enrdf_load_stackoverflow)
CA (1) CA983730A (enrdf_load_stackoverflow)
IT (1) IT1034535B (enrdf_load_stackoverflow)

Cited By (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4050239A (en) * 1974-09-11 1977-09-27 Motoren- Und Turbinen-Union Munchen Gmbh Thermodynamic prime mover with heat exchanger
US4104874A (en) * 1976-02-06 1978-08-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Double-walled combustion chamber shell having combined convective wall cooling and film cooling
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
FR2422035A1 (fr) * 1978-04-04 1979-11-02 Gen Electric Dispositif de combustion refroidi par film d'air
US4192138A (en) * 1977-08-29 1980-03-11 Westinghouse Electric Corp. Gas turbine combustor air inlet
US4226088A (en) * 1977-02-23 1980-10-07 Hitachi, Ltd. Gas turbine combustor
WO1988006257A1 (en) * 1987-02-11 1988-08-25 The Secretary Of State For Defence In Her Britanni Gas turbine engine combustion chambers
EP0318312A1 (en) * 1987-11-27 1989-05-31 General Electric Company Aperture insert for the combustion chamber of a gas turbine
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
US6101814A (en) * 1999-04-15 2000-08-15 United Technologies Corporation Low emissions can combustor with dilution hole arrangement for a turbine engine
US6494044B1 (en) 1999-11-19 2002-12-17 General Electric Company Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method
US20030046934A1 (en) * 2001-09-11 2003-03-13 Rolls-Royce Plc Gas turbine engine combustor
US6681578B1 (en) * 2002-11-22 2004-01-27 General Electric Company Combustor liner with ring turbulators and related method
US6681577B2 (en) * 2002-01-16 2004-01-27 General Electric Company Method and apparatus for relieving stress in a combustion case in a gas turbine engine
US6722134B2 (en) 2002-09-18 2004-04-20 General Electric Company Linear surface concavity enhancement
US20040079082A1 (en) * 2002-10-24 2004-04-29 Bunker Ronald Scott Combustor liner with inverted turbulators
US6761031B2 (en) 2002-09-18 2004-07-13 General Electric Company Double wall combustor liner segment with enhanced cooling
EP1457737A2 (en) 2003-03-14 2004-09-15 Rolls-Royce Plc Gas turbine engine combustor
US20040250549A1 (en) * 2001-11-15 2004-12-16 Roland Liebe Annular combustion chamber for a gas turbine
US20050106021A1 (en) * 2003-11-19 2005-05-19 General Electric Company Hot gas path component with mesh and dimpled cooling
US20050106020A1 (en) * 2003-11-19 2005-05-19 General Electric Company Hot gas path component with mesh and turbulated cooling
US20070193216A1 (en) * 2006-01-25 2007-08-23 Woolford James R Wall elements for gas turbine engine combustors
US20090145099A1 (en) * 2007-12-06 2009-06-11 Power Systems Mfg., Llc Transition duct cooling feed tubes
US20100050649A1 (en) * 2008-09-04 2010-03-04 Allen David B Combustor device and transition duct assembly
US20100064693A1 (en) * 2008-09-15 2010-03-18 Koenig Michael H Combustor assembly comprising a combustor device, a transition duct and a flow conditioner
US20100122537A1 (en) * 2008-11-20 2010-05-20 Honeywell International Inc. Combustors with inserts between dual wall liners
US20100251723A1 (en) * 2007-01-09 2010-10-07 Wei Chen Thimble, sleeve, and method for cooling a combustor assembly
US20100269513A1 (en) * 2009-04-23 2010-10-28 General Electric Company Thimble Fan for a Combustion System
US20100293957A1 (en) * 2009-05-19 2010-11-25 General Electric Company System and method for cooling a wall of a gas turbine combustor
US20120036859A1 (en) * 2010-08-12 2012-02-16 General Electric Company Combustor transition piece with dilution sleeves and related method
US20130008178A1 (en) * 2011-07-05 2013-01-10 General Electric Company Support assembly for transition duct in turbine system
US8627669B2 (en) 2008-07-18 2014-01-14 Siemens Energy, Inc. Elimination of plate fins in combustion baskets by CMC insulation installed by shrink fit
DE102012015449A1 (de) * 2012-08-03 2014-02-20 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit Mischluftöffnungen und Luftleitelementen in modularer Bauweise
DE102012015452A1 (de) * 2012-08-03 2014-04-24 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand mit Mischluftöffnungen und Luftleitelementen
EP2226562A3 (en) * 2009-03-06 2014-07-02 General Electric Company Injection device for a turbomachine
US9255526B2 (en) 2012-08-23 2016-02-09 Siemens Energy, Inc. System and method for on line monitoring within a gas turbine combustor section
US9255835B2 (en) 2012-08-22 2016-02-09 Siemens Energy, Inc. System for remote vibration detection on combustor basket and transition in gas turbines
US20160069568A1 (en) * 2014-09-08 2016-03-10 Alstom Technology Ltd Dilution gas or air mixer for a combustor of a gas turbine
US20160201511A1 (en) * 2013-09-13 2016-07-14 United Technologies Corporation Shielding pockets for case holes
US10359194B2 (en) 2014-08-26 2019-07-23 Siemens Energy, Inc. Film cooling hole arrangement for acoustic resonators in gas turbine engines
EP3702668A1 (en) * 2019-02-28 2020-09-02 Rolls-Royce plc Combustion liner and gas turbine engine comprising a combustion liner
US11085639B2 (en) * 2018-12-27 2021-08-10 Rolls-Royce North American Technologies Inc. Gas turbine combustor liner with integral chute made by additive manufacturing process
US11255543B2 (en) * 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5827264Y2 (ja) * 1978-07-07 1983-06-13 日産自動車株式会社 ガスタ−ビンの燃焼器ライナ
JPS5932862U (ja) * 1982-08-27 1984-02-29 三菱重工業株式会社 ガスタ−ビン燃焼器

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US3121996A (en) * 1961-10-02 1964-02-25 Lucas Industries Ltd Liquid fuel combustion apparatus
US3440818A (en) * 1966-07-08 1969-04-29 Nationale D Etude De Construct Combustion and cooling air control in turbojet engines
US3656297A (en) * 1968-05-13 1972-04-18 Rolls Royce Combustion chamber air inlet

Patent Citations (3)

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US3121996A (en) * 1961-10-02 1964-02-25 Lucas Industries Ltd Liquid fuel combustion apparatus
US3440818A (en) * 1966-07-08 1969-04-29 Nationale D Etude De Construct Combustion and cooling air control in turbojet engines
US3656297A (en) * 1968-05-13 1972-04-18 Rolls Royce Combustion chamber air inlet

Cited By (67)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4050239A (en) * 1974-09-11 1977-09-27 Motoren- Und Turbinen-Union Munchen Gmbh Thermodynamic prime mover with heat exchanger
US4104874A (en) * 1976-02-06 1978-08-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Double-walled combustion chamber shell having combined convective wall cooling and film cooling
US4226088A (en) * 1977-02-23 1980-10-07 Hitachi, Ltd. Gas turbine combustor
US4192138A (en) * 1977-08-29 1980-03-11 Westinghouse Electric Corp. Gas turbine combustor air inlet
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
FR2404110A1 (fr) * 1977-09-23 1979-04-20 United Technologies Corp Chemise de refroidissement pour la chambre de combustion d'un moteur a turbine a gaz
FR2422035A1 (fr) * 1978-04-04 1979-11-02 Gen Electric Dispositif de combustion refroidi par film d'air
WO1988006257A1 (en) * 1987-02-11 1988-08-25 The Secretary Of State For Defence In Her Britanni Gas turbine engine combustion chambers
EP0318312A1 (en) * 1987-11-27 1989-05-31 General Electric Company Aperture insert for the combustion chamber of a gas turbine
US4875339A (en) * 1987-11-27 1989-10-24 General Electric Company Combustion chamber liner insert
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
EP0363624A1 (en) * 1988-10-07 1990-04-18 Westinghouse Electric Corporation Gas turbine combustion chamber with air scoops
US6101814A (en) * 1999-04-15 2000-08-15 United Technologies Corporation Low emissions can combustor with dilution hole arrangement for a turbine engine
US6494044B1 (en) 1999-11-19 2002-12-17 General Electric Company Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method
US20030046934A1 (en) * 2001-09-11 2003-03-13 Rolls-Royce Plc Gas turbine engine combustor
US7395669B2 (en) 2001-09-11 2008-07-08 Rolls-Royce Plc Gas turbine engine combustor
US20040250549A1 (en) * 2001-11-15 2004-12-16 Roland Liebe Annular combustion chamber for a gas turbine
US6681577B2 (en) * 2002-01-16 2004-01-27 General Electric Company Method and apparatus for relieving stress in a combustion case in a gas turbine engine
US6761031B2 (en) 2002-09-18 2004-07-13 General Electric Company Double wall combustor liner segment with enhanced cooling
US6722134B2 (en) 2002-09-18 2004-04-20 General Electric Company Linear surface concavity enhancement
US20040079082A1 (en) * 2002-10-24 2004-04-29 Bunker Ronald Scott Combustor liner with inverted turbulators
US7104067B2 (en) 2002-10-24 2006-09-12 General Electric Company Combustor liner with inverted turbulators
US6681578B1 (en) * 2002-11-22 2004-01-27 General Electric Company Combustor liner with ring turbulators and related method
US7121096B2 (en) * 2003-03-14 2006-10-17 Rolls-Royce Plc Gas turbine engine combustor
EP1457737A2 (en) 2003-03-14 2004-09-15 Rolls-Royce Plc Gas turbine engine combustor
US20040231336A1 (en) * 2003-03-14 2004-11-25 Rolls-Royce Plc Gas turbine engine combustor
EP1457737B1 (en) * 2003-03-14 2015-04-01 Rolls-Royce Plc Gas turbine engine combustor
EP1457737A3 (en) * 2003-03-14 2009-08-12 Rolls-Royce Plc Gas turbine engine combustor
US6984102B2 (en) 2003-11-19 2006-01-10 General Electric Company Hot gas path component with mesh and turbulated cooling
US7182576B2 (en) 2003-11-19 2007-02-27 General Electric Company Hot gas path component with mesh and impingement cooling
US7186084B2 (en) 2003-11-19 2007-03-06 General Electric Company Hot gas path component with mesh and dimpled cooling
US20050118023A1 (en) * 2003-11-19 2005-06-02 General Electric Company Hot gas path component with mesh and impingement cooling
US20050106020A1 (en) * 2003-11-19 2005-05-19 General Electric Company Hot gas path component with mesh and turbulated cooling
US20050106021A1 (en) * 2003-11-19 2005-05-19 General Electric Company Hot gas path component with mesh and dimpled cooling
US20070193216A1 (en) * 2006-01-25 2007-08-23 Woolford James R Wall elements for gas turbine engine combustors
US8650882B2 (en) * 2006-01-25 2014-02-18 Rolls-Royce Plc Wall elements for gas turbine engine combustors
US8281600B2 (en) * 2007-01-09 2012-10-09 General Electric Company Thimble, sleeve, and method for cooling a combustor assembly
US20100251723A1 (en) * 2007-01-09 2010-10-07 Wei Chen Thimble, sleeve, and method for cooling a combustor assembly
US20090145099A1 (en) * 2007-12-06 2009-06-11 Power Systems Mfg., Llc Transition duct cooling feed tubes
US8151570B2 (en) * 2007-12-06 2012-04-10 Alstom Technology Ltd Transition duct cooling feed tubes
US8627669B2 (en) 2008-07-18 2014-01-14 Siemens Energy, Inc. Elimination of plate fins in combustion baskets by CMC insulation installed by shrink fit
US20100050649A1 (en) * 2008-09-04 2010-03-04 Allen David B Combustor device and transition duct assembly
US20100064693A1 (en) * 2008-09-15 2010-03-18 Koenig Michael H Combustor assembly comprising a combustor device, a transition duct and a flow conditioner
US8490400B2 (en) 2008-09-15 2013-07-23 Siemens Energy, Inc. Combustor assembly comprising a combustor device, a transition duct and a flow conditioner
US8161752B2 (en) * 2008-11-20 2012-04-24 Honeywell International Inc. Combustors with inserts between dual wall liners
US20100122537A1 (en) * 2008-11-20 2010-05-20 Honeywell International Inc. Combustors with inserts between dual wall liners
EP2226562A3 (en) * 2009-03-06 2014-07-02 General Electric Company Injection device for a turbomachine
US20100269513A1 (en) * 2009-04-23 2010-10-28 General Electric Company Thimble Fan for a Combustion System
US8397511B2 (en) * 2009-05-19 2013-03-19 General Electric Company System and method for cooling a wall of a gas turbine combustor
US20100293957A1 (en) * 2009-05-19 2010-11-25 General Electric Company System and method for cooling a wall of a gas turbine combustor
US20120036859A1 (en) * 2010-08-12 2012-02-16 General Electric Company Combustor transition piece with dilution sleeves and related method
US20130008178A1 (en) * 2011-07-05 2013-01-10 General Electric Company Support assembly for transition duct in turbine system
US8650852B2 (en) * 2011-07-05 2014-02-18 General Electric Company Support assembly for transition duct in turbine system
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JPS5235806B2 (enrdf_load_stackoverflow) 1977-09-12
IT1034535B (it) 1979-10-10
CA983730A (en) 1976-02-17
JPS50133313A (enrdf_load_stackoverflow) 1975-10-22

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