EP2028344A1 - Überleitkanal - Google Patents

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Publication number
EP2028344A1
EP2028344A1 EP07016387A EP07016387A EP2028344A1 EP 2028344 A1 EP2028344 A1 EP 2028344A1 EP 07016387 A EP07016387 A EP 07016387A EP 07016387 A EP07016387 A EP 07016387A EP 2028344 A1 EP2028344 A1 EP 2028344A1
Authority
EP
European Patent Office
Prior art keywords
transition duct
low pressure
pressure region
vane
generating element
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.)
Withdrawn
Application number
EP07016387A
Other languages
English (en)
French (fr)
Inventor
Nigel Wilbraham
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP07016387A priority Critical patent/EP2028344A1/de
Publication of EP2028344A1 publication Critical patent/EP2028344A1/de
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R3/002—Wall structures
    • 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
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • 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
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the low pressure region generating element may extend from an upper wall or from a bottom wall of the transition duct, preferably at the outlet of the transition duct.
  • the low pressure region generating element may extend from the upper wall to the bottom wall. This allows a stable mounting of the low pressure region generating element inside of the transition duct especially if the low pressure region generating element is fixed to the upper wall as well as to the bottom wall of the transition duct.
  • the used low pressure region generating element can be located in the transition duct such that the centreline of the low pressure region generating element is perpendicular to the centreline of the transition duct.
  • the transition duct 1 as it is shown in Figure 3 , comprises an upper wall 10 and a bottom wall 11.
  • the vane 7 is mounted at the centre of the outlet 5 of the transition duct 1 and is, in the present embodiment, fixed to the upper wall 10 and also to the bottom wall 11. If the vane 7 is at both its ends fixed (perpendicular) to the transition duct 1 it should have sufficient strength not to experience a condition of collapse due to the heating of the centre part of the vane 7. Whether this happens depends on the strength of the vane 7 itself relative to the structural strength of the walls in the transition duct 1.
  • FIG 4 the vane 7 is shown in a perspective view.
  • the figure shows the vane 7 with its internal hollow space 8 and the opening 14.
  • the centreline 3 of the vane 7 may be perpendicular to the centreline 2 of the transition duct 1 when the vane 7 is mounted in the transition duct 1.
  • a suitable bond coat would be a so-called MCrAlX coating, where M stand for iron (Fe), cobalt (Co) or nickel (Ni) and X for yttrium (Y) and/or silicon (Si) and/or at least one rare earth element and/or hafnium (Hf).
  • M stand for iron (Fe), cobalt (Co) or nickel (Ni)
  • X for yttrium (Y) and/or silicon (Si) and/or at least one rare earth element and/or hafnium (Hf).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07016387A 2007-08-21 2007-08-21 Überleitkanal Withdrawn EP2028344A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07016387A EP2028344A1 (de) 2007-08-21 2007-08-21 Überleitkanal

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07016387A EP2028344A1 (de) 2007-08-21 2007-08-21 Überleitkanal

Publications (1)

Publication Number Publication Date
EP2028344A1 true EP2028344A1 (de) 2009-02-25

Family

ID=39135224

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07016387A Withdrawn EP2028344A1 (de) 2007-08-21 2007-08-21 Überleitkanal

Country Status (1)

Country Link
EP (1) EP2028344A1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2738355A1 (de) * 2012-11-30 2014-06-04 General Electric Company Gasturbinentriebwerk und zugehöriges Verfahren
WO2014099074A3 (en) * 2012-09-26 2014-08-21 United Technologies Corporation Gas turbine engine combustor with integrated combustor vane
CN104235879A (zh) * 2014-08-08 2014-12-24 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机燃烧室过渡段结构
US9783309B2 (en) 2013-07-16 2017-10-10 The Boeing Company Methods and device for mixing airflows in environmental control systems
WO2018167913A1 (ja) * 2017-03-16 2018-09-20 株式会社 東芝 トランジションピース

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3652181A (en) * 1970-11-23 1972-03-28 Carl F Wilhelm Jr Cooling sleeve for gas turbine combustor transition member
US3930748A (en) * 1972-08-02 1976-01-06 Rolls-Royce (1971) Limited Hollow cooled vane or blade for a gas turbine engine
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
JPH01155120A (ja) * 1987-12-11 1989-06-19 Hitachi Ltd ガスタービン燃焼器の尾筒
US5397216A (en) * 1992-10-26 1995-03-14 Asea Brown Boveri Ltd. Flow divider for radial-axial inlet housings
US20050084657A1 (en) * 2002-08-02 2005-04-21 Minoru Ohara Method for forming heat shielding film, masking pin and tail pipe of combustor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3652181A (en) * 1970-11-23 1972-03-28 Carl F Wilhelm Jr Cooling sleeve for gas turbine combustor transition member
US3930748A (en) * 1972-08-02 1976-01-06 Rolls-Royce (1971) Limited Hollow cooled vane or blade for a gas turbine engine
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
JPH01155120A (ja) * 1987-12-11 1989-06-19 Hitachi Ltd ガスタービン燃焼器の尾筒
US5397216A (en) * 1992-10-26 1995-03-14 Asea Brown Boveri Ltd. Flow divider for radial-axial inlet housings
US20050084657A1 (en) * 2002-08-02 2005-04-21 Minoru Ohara Method for forming heat shielding film, masking pin and tail pipe of combustor

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014099074A3 (en) * 2012-09-26 2014-08-21 United Technologies Corporation Gas turbine engine combustor with integrated combustor vane
US9482432B2 (en) 2012-09-26 2016-11-01 United Technologies Corporation Gas turbine engine combustor with integrated combustor vane having swirler
EP2738355A1 (de) * 2012-11-30 2014-06-04 General Electric Company Gasturbinentriebwerk und zugehöriges Verfahren
CN103850796A (zh) * 2012-11-30 2014-06-11 通用电气公司 燃气涡轮发动机系统及其相关方法
US9551492B2 (en) 2012-11-30 2017-01-24 General Electric Company Gas turbine engine system and an associated method thereof
US9783309B2 (en) 2013-07-16 2017-10-10 The Boeing Company Methods and device for mixing airflows in environmental control systems
CN104235879A (zh) * 2014-08-08 2014-12-24 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机燃烧室过渡段结构
WO2018167913A1 (ja) * 2017-03-16 2018-09-20 株式会社 東芝 トランジションピース
US11098600B2 (en) 2017-03-16 2021-08-24 Toshiba Energy Systems & Solutions Corporation Transition piece

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