DE102014115402A1 - Übergangskanalanordnung mit modifizierter Hinterkante in einem Turbinensystem - Google Patents

Übergangskanalanordnung mit modifizierter Hinterkante in einem Turbinensystem Download PDF

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Publication number
DE102014115402A1
DE102014115402A1 DE102014115402.9A DE102014115402A DE102014115402A1 DE 102014115402 A1 DE102014115402 A1 DE 102014115402A1 DE 102014115402 A DE102014115402 A DE 102014115402A DE 102014115402 A1 DE102014115402 A1 DE 102014115402A1
Authority
DE
Germany
Prior art keywords
axis
transition
trailing edge
outlet
channels
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.)
Pending
Application number
DE102014115402.9A
Other languages
German (de)
English (en)
Inventor
Kevin Weston McMahan
Carl Gerard Schott
Clint Luigie Ingram
Gunnar L. Siden
Sylvain Pierre
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.)
GE Vernova GmbH
Original Assignee
General Electric Co
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
Application filed by General Electric Co filed Critical General Electric Co
Publication of DE102014115402A1 publication Critical patent/DE102014115402A1/de
Pending legal-status Critical Current

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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)
DE102014115402.9A 2013-10-25 2014-10-22 Übergangskanalanordnung mit modifizierter Hinterkante in einem Turbinensystem Pending DE102014115402A1 (de)

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
US14/063,358 2013-10-25

Publications (1)

Publication Number Publication Date
DE102014115402A1 true DE102014115402A1 (de) 2015-04-30

Family

ID=52811878

Family Applications (1)

Application Number Title Priority Date Filing Date
DE102014115402.9A Pending DE102014115402A1 (de) 2013-10-25 2014-10-22 Übergangskanalanordnung mit modifizierter Hinterkante in einem Turbinensystem

Country Status (5)

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017023326A1 (en) * 2015-08-06 2017-02-09 Siemens Aktiengesellschaft Transition ducts of a gas turbine combustor
WO2017023327A1 (en) * 2015-08-06 2017-02-09 Siemens Aktiengesellschaft Trailing edge duct for combustors with cooling features
FR3043428A1 (fr) * 2015-11-10 2017-05-12 Snecma Aube de redresseur de turbomachine

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10132175B2 (en) * 2014-10-07 2018-11-20 Siemens Energy, Inc. Arrangement for a gas turbine combustion engine
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
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)
US10443399B2 (en) 2016-07-22 2019-10-15 General Electric Company Turbine vane with coupon having corrugated 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
US10465525B2 (en) 2016-07-22 2019-11-05 General Electric Company Blade with internal rib having corrugated surface(s)

Family Cites Families (65)

* 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
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
US6006523A (en) 1997-04-30 1999-12-28 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor with angled tube section
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
EP1322854A4 (en) 2000-10-02 2004-08-04 Rohr Inc APPARATUS, METHOD AND SYSTEM FOR REDUCING THE NOISE OF A GAS TURBINE
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
US7721547B2 (en) * 2005-06-27 2010-05-25 Siemens Energy, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
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
CA2731670C (en) 2008-07-31 2016-08-23 Commonwealth Scientific And Industrial Research Organisation Production process
US8091365B2 (en) 2008-08-12 2012-01-10 Siemens Energy, Inc. Canted outlet for transition 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
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
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
US10030872B2 (en) * 2011-02-28 2018-07-24 General Electric Company Combustor mixing joint with flow disruption surface
US8978388B2 (en) 2011-06-03 2015-03-17 General Electric Company Load member for transition duct in turbine system
US20120304665A1 (en) 2011-06-03 2012-12-06 General Electric Company Mount device for transition duct in turbine system
US8915706B2 (en) 2011-10-18 2014-12-23 General Electric Company Transition nozzle

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017023326A1 (en) * 2015-08-06 2017-02-09 Siemens Aktiengesellschaft Transition ducts of a gas turbine combustor
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
FR3043428A1 (fr) * 2015-11-10 2017-05-12 Snecma Aube de redresseur de turbomachine

Also Published As

Publication number Publication date
CH708780A2 (de) 2015-04-30
US20150114003A1 (en) 2015-04-30
CN104566456B (zh) 2018-10-09
US9458732B2 (en) 2016-10-04
JP6537161B2 (ja) 2019-07-03
CN104566456A (zh) 2015-04-29
CH708780A8 (de) 2015-06-30
JP2015083916A (ja) 2015-04-30

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R012 Request for examination validly filed
R081 Change of applicant/patentee

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: GENERAL ELECTRIC COMPANY, SCHENECTADY, N.Y., US