CN104566456B - 涡轮系统中具有改进的后缘的过渡管道组件 - Google Patents

涡轮系统中具有改进的后缘的过渡管道组件 Download PDF

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Publication number
CN104566456B
CN104566456B CN201410573921.7A CN201410573921A CN104566456B CN 104566456 B CN104566456 B CN 104566456B CN 201410573921 A CN201410573921 A CN 201410573921A CN 104566456 B CN104566456 B CN 104566456B
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CN
China
Prior art keywords
axis
transition
transition conduit
transition duct
turbine
Prior art date
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Application number
CN201410573921.7A
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English (en)
Chinese (zh)
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CN104566456A (zh
Inventor
K.W.麦克马汉
C.G.肖特
C.L.英格拉姆
G.L.赛登
S.皮埃尔
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General Electric Company PLC
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General Electric Co
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Publication of CN104566456A publication Critical patent/CN104566456A/zh
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Publication of CN104566456B publication Critical patent/CN104566456B/zh
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Classifications

    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
CN201410573921.7A 2013-10-25 2014-10-24 涡轮系统中具有改进的后缘的过渡管道组件 Active CN104566456B (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US14/063,358 US9458732B2 (en) 2013-10-25 2013-10-25 Transition duct assembly with modified trailing edge in turbine system
US14/063358 2013-10-25

Publications (2)

Publication Number Publication Date
CN104566456A CN104566456A (zh) 2015-04-29
CN104566456B true CN104566456B (zh) 2018-10-09

Family

ID=52811878

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201410573921.7A Active CN104566456B (zh) 2013-10-25 2014-10-24 涡轮系统中具有改进的后缘的过渡管道组件

Country Status (5)

Country Link
US (1) US9458732B2 (enExample)
JP (1) JP6537161B2 (enExample)
CN (1) CN104566456B (enExample)
CH (1) CH708780A8 (enExample)
DE (1) DE102014115402A1 (enExample)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016057020A1 (en) * 2014-10-07 2016-04-14 Siemens Energy, Inc. Arrangement for a gas turbine combustion engine
WO2017023327A1 (en) * 2015-08-06 2017-02-09 Siemens Aktiengesellschaft Trailing edge duct for combustors with cooling features
CN107923253A (zh) * 2015-08-06 2018-04-17 西门子公司 燃气涡轮机燃烧室的过渡管道
WO2017023330A1 (en) * 2015-08-06 2017-02-09 Siemens Aktiengesellschaft A ducting arrangement for directing combustion gas
WO2017023325A1 (en) * 2015-08-06 2017-02-09 Siemens Aktiengesellschaft Trailing edge duct for gas turbine combustors
WO2017082876A1 (en) * 2015-11-10 2017-05-18 Siemens Aktiengesellschaft Serrated trailing edge ducts for gas turbine combustors
FR3043428B1 (fr) * 2015-11-10 2020-05-29 Safran Aircraft Engines Aube de redresseur de turbomachine
US10605459B2 (en) * 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10465520B2 (en) 2016-07-22 2019-11-05 General Electric Company Blade with corrugated outer surface(s)
US10450868B2 (en) 2016-07-22 2019-10-22 General Electric Company Turbine rotor blade with coupon having corrugated surface(s)
US10436037B2 (en) 2016-07-22 2019-10-08 General Electric Company Blade with parallel corrugated surfaces on inner and outer surfaces
US10443399B2 (en) 2016-07-22 2019-10-15 General Electric Company Turbine vane with coupon having corrugated surface(s)
US10465525B2 (en) 2016-07-22 2019-11-05 General Electric Company Blade with internal rib having corrugated surface(s)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7721547B2 (en) * 2005-06-27 2010-05-25 Siemens Energy, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
CN102171413A (zh) * 2008-08-12 2011-08-31 西门子能源公司 用于燃气涡轮发动机中过渡的倾斜出口
CN102654287A (zh) * 2011-02-28 2012-09-05 通用电气公司 燃烧室混合接头

Family Cites Families (62)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2702454A (en) 1951-06-07 1955-02-22 United Aircraft Corp Transition piece providing a connection between the combustion chambers and the turbine nozzle in gas turbine power plants
US3578264A (en) 1968-07-09 1971-05-11 Battelle Development Corp Boundary layer control of flow separation and heat exchange
US3776363A (en) 1971-05-10 1973-12-04 A Kuethe Control of noise and instabilities in jet engines, compressors, turbines, heat exchangers and the like
US4149375A (en) 1976-11-29 1979-04-17 United Technologies Corporation Lobe mixer for gas turbine engine
US4422288A (en) 1981-03-02 1983-12-27 General Electric Company Aft mounting system for combustion transition duct members
US4830315A (en) 1986-04-30 1989-05-16 United Technologies Corporation Airfoil-shaped body
US4741667A (en) * 1986-05-28 1988-05-03 United Technologies Corporation Stator vane
US4826400A (en) 1986-12-29 1989-05-02 General Electric Company Curvilinear turbine airfoil
US5110560A (en) 1987-11-23 1992-05-05 United Technologies Corporation Convoluted diffuser
US5118120A (en) 1989-07-10 1992-06-02 General Electric Company Leaf seals
US5077967A (en) 1990-11-09 1992-01-07 General Electric Company Profile matched diffuser
US5149250A (en) 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
JP3070167B2 (ja) * 1991-07-18 2000-07-24 石川島播磨重工業株式会社 タービンノズル
US5249920A (en) 1992-07-09 1993-10-05 General Electric Company Turbine nozzle seal arrangement
FR2711771B1 (fr) 1993-10-27 1995-12-01 Snecma Diffuseur de chambre à alimentation circonférentielle variable.
US5414999A (en) 1993-11-05 1995-05-16 General Electric Company Integral aft frame mount for a gas turbine combustor transition piece
US5457954A (en) 1993-12-21 1995-10-17 Solar Turbines Inc Rolling contact mounting arrangement for a ceramic combustor
EP0718468B1 (en) 1994-12-20 2001-10-31 General Electric Company Transition piece frame support
DE19549143A1 (de) 1995-12-29 1997-07-03 Abb Research Ltd Gasturbinenringbrennkammer
US6006523A (en) 1997-04-30 1999-12-28 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor with angled tube section
US5983641A (en) 1997-04-30 1999-11-16 Mitsubishi Heavy Industries, Ltd. Tail pipe of gas turbine combustor and gas turbine combustor having the same tail pipe
US6076835A (en) 1997-05-21 2000-06-20 Allison Advanced Development Company Interstage van seal apparatus
US5934687A (en) 1997-07-07 1999-08-10 General Electric Company Gas-path leakage seal for a turbine
US6360528B1 (en) 1997-10-31 2002-03-26 General Electric Company Chevron exhaust nozzle for a gas turbine engine
EP0924470B1 (de) 1997-12-19 2003-06-18 MTU Aero Engines GmbH Vormischbrennkammer für eine Gasturbine
GB2335470B (en) 1998-03-18 2002-02-13 Rolls Royce Plc A seal
US6471475B1 (en) 2000-07-14 2002-10-29 Pratt & Whitney Canada Corp. Integrated duct diffuser
US6431825B1 (en) 2000-07-28 2002-08-13 Alstom (Switzerland) Ltd Seal between static turbine parts
EP2090769A1 (en) 2000-10-02 2009-08-19 Rohr, Inc. Apparatus, method and system for gas turbine engine noise reduction
US6442946B1 (en) 2000-11-14 2002-09-03 Power Systems Mfg., Llc Three degrees of freedom aft mounting system for gas turbine transition duct
US6431555B1 (en) 2001-03-14 2002-08-13 General Electric Company Leaf seal for inner and outer casings of a turbine
US6564555B2 (en) 2001-05-24 2003-05-20 Allison Advanced Development Company Apparatus for forming a combustion mixture in a gas turbine engine
US6537023B1 (en) 2001-12-28 2003-03-25 General Electric Company Supplemental seal for the chordal hinge seal in a gas turbine
US6652229B2 (en) 2002-02-27 2003-11-25 General Electric Company Leaf seal support for inner band of a turbine nozzle in a gas turbine engine
GB2390890B (en) 2002-07-17 2005-07-06 Rolls Royce Plc Diffuser for gas turbine engine
US6662567B1 (en) 2002-08-14 2003-12-16 Power Systems Mfg, Llc Transition duct mounting system
US6907724B2 (en) 2002-09-13 2005-06-21 The Boeing Company Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance
US6840048B2 (en) 2002-09-26 2005-01-11 General Electric Company Dynamically uncoupled can combustor
US7234304B2 (en) 2002-10-23 2007-06-26 Pratt & Whitney Canada Corp Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine
US7007480B2 (en) 2003-04-09 2006-03-07 Honeywell International, Inc. Multi-axial pivoting combustor liner in gas turbine engine
US7024863B2 (en) 2003-07-08 2006-04-11 Pratt & Whitney Canada Corp. Combustor attachment with rotational joint
US7305817B2 (en) * 2004-02-09 2007-12-11 General Electric Company Sinuous chevron exhaust nozzle
JP2006090219A (ja) * 2004-09-24 2006-04-06 Toshiba Corp 軸流タービン
US7637110B2 (en) 2005-11-30 2009-12-29 General Electric Company Methods and apparatuses for assembling a gas turbine engine
US7571611B2 (en) 2006-04-24 2009-08-11 General Electric Company Methods and system for reducing pressure losses in gas turbine engines
US7966826B2 (en) 2007-02-14 2011-06-28 The Boeing Company Systems and methods for reducing noise from jet engine exhaust
US20090145132A1 (en) 2007-12-07 2009-06-11 General Electric Company Methods and system for reducing pressure losses in gas turbine engines
US8322146B2 (en) 2007-12-10 2012-12-04 Alstom Technology Ltd Transition duct assembly
JP2009197650A (ja) 2008-02-20 2009-09-03 Mitsubishi Heavy Ind Ltd ガスタービン
GB0810500D0 (en) 2008-06-09 2008-07-09 Airbus Uk Ltd Aircraft wing
RU2536709C2 (ru) 2008-07-31 2014-12-27 Коммонвелт Сайентифик Энд Индастриал Рисерч Оранайзейшн Способ получения металла карботермическим восстановлением оксида металла и реактор для осуществления способа
US8065881B2 (en) 2008-08-12 2011-11-29 Siemens Energy, Inc. Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
US8113003B2 (en) 2008-08-12 2012-02-14 Siemens Energy, Inc. Transition with a linear flow path for use in a gas turbine engine
US8276389B2 (en) * 2008-09-29 2012-10-02 Siemens Energy, Inc. Assembly for directing combustion gas
US9822649B2 (en) 2008-11-12 2017-11-21 General Electric Company Integrated combustor and stage 1 nozzle in a gas turbine and method
US8087253B2 (en) 2008-11-20 2012-01-03 General Electric Company Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath
US8616007B2 (en) 2009-01-22 2013-12-31 Siemens Energy, Inc. Structural attachment system for transition duct outlet
US20110259015A1 (en) * 2010-04-27 2011-10-27 David Richard Johns Tangential Combustor
US8632478B2 (en) 2010-05-04 2014-01-21 Solaiman B. Alkhattaf Pillow with mechanism for simulated respiration
US20120304665A1 (en) 2011-06-03 2012-12-06 General Electric Company Mount device for transition duct in turbine system
US8978388B2 (en) 2011-06-03 2015-03-17 General Electric Company Load member for transition duct in turbine system
US8915706B2 (en) 2011-10-18 2014-12-23 General Electric Company Transition nozzle

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7721547B2 (en) * 2005-06-27 2010-05-25 Siemens Energy, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
CN102171413A (zh) * 2008-08-12 2011-08-31 西门子能源公司 用于燃气涡轮发动机中过渡的倾斜出口
CN102654287A (zh) * 2011-02-28 2012-09-05 通用电气公司 燃烧室混合接头

Also Published As

Publication number Publication date
JP2015083916A (ja) 2015-04-30
CH708780A2 (de) 2015-04-30
US9458732B2 (en) 2016-10-04
CN104566456A (zh) 2015-04-29
US20150114003A1 (en) 2015-04-30
DE102014115402A1 (de) 2015-04-30
CH708780A8 (de) 2015-06-30
JP6537161B2 (ja) 2019-07-03

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Effective date of registration: 20240105

Address after: Swiss Baden

Patentee after: GENERAL ELECTRIC CO. LTD.

Address before: New York, United States

Patentee before: General Electric Co.