GB201105105D0 - Gas turbine engine component - Google Patents

Gas turbine engine component

Info

Publication number
GB201105105D0
GB201105105D0 GBGB1105105.9A GB201105105A GB201105105D0 GB 201105105 D0 GB201105105 D0 GB 201105105D0 GB 201105105 A GB201105105 A GB 201105105A GB 201105105 D0 GB201105105 D0 GB 201105105D0
Authority
GB
United Kingdom
Prior art keywords
cooling
turbine engine
gas turbine
component
external wall
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.)
Ceased
Application number
GBGB1105105.9A
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GBGB1105105.9A priority Critical patent/GB201105105D0/en
Publication of GB201105105D0 publication Critical patent/GB201105105D0/en
Priority to EP12157214A priority patent/EP2505787A1/en
Priority to US13/408,251 priority patent/US20120251295A1/en
Ceased legal-status Critical Current

Links

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
    • F23R3/002—Wall structures
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • 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
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Abstract

A component of a gas turbine engine is provided. The component includes an external wall (40) which, in use, is exposed on one surface (41) thereof to working gas flowing through the engine. The component further includes effusion cooling holes formed in the external wall (42). In use, cooling air blows through the cooling holes to form a cooling film on the surface of the external wall exposed to the working gas (41). The component further includes an air inlet arrangement (43) which receives the cooling air for distribution to the cooling holes (42). The component further includes a plurality of metering feeds (47) and a plurality of supply plena (45). The metering feeds (47) meter the cooling air from the air inlet arrangement (43) to respective of the supply plena (45), which in turn supply the metered cooling air to respective portions of the cooling holes (42).
GBGB1105105.9A 2011-03-28 2011-03-28 Gas turbine engine component Ceased GB201105105D0 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GBGB1105105.9A GB201105105D0 (en) 2011-03-28 2011-03-28 Gas turbine engine component
EP12157214A EP2505787A1 (en) 2011-03-28 2012-02-28 Component of a gas turbine engine and corresponding gas turbine engine
US13/408,251 US20120251295A1 (en) 2011-03-28 2012-02-29 Gas turbine engine component

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1105105.9A GB201105105D0 (en) 2011-03-28 2011-03-28 Gas turbine engine component

Publications (1)

Publication Number Publication Date
GB201105105D0 true GB201105105D0 (en) 2011-05-11

Family

ID=44067422

Family Applications (1)

Application Number Title Priority Date Filing Date
GBGB1105105.9A Ceased GB201105105D0 (en) 2011-03-28 2011-03-28 Gas turbine engine component

Country Status (3)

Country Link
US (1) US20120251295A1 (en)
EP (1) EP2505787A1 (en)
GB (1) GB201105105D0 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150198063A1 (en) 2014-01-14 2015-07-16 Alstom Technology Ltd Cooled stator heat shield
EP2894301A1 (en) 2014-01-14 2015-07-15 Alstom Technology Ltd Stator heat shield segment
US10422235B2 (en) 2014-05-29 2019-09-24 General Electric Company Angled impingement inserts with cooling features
CA2949539A1 (en) 2014-05-29 2016-02-18 General Electric Company Engine components with impingement cooling features
US9957816B2 (en) 2014-05-29 2018-05-01 General Electric Company Angled impingement insert
WO2016099662A2 (en) * 2014-10-31 2016-06-23 General Electric Company Engine component assembly
RU2706210C2 (en) 2016-01-25 2019-11-14 Ансалдо Энерджиа Свитзерлэнд Аг Stator thermal shield for gas turbine, gas turbine with such stator thermal shield and stator thermal shield cooling method
US10513943B2 (en) 2016-03-16 2019-12-24 United Technologies Corporation Boas enhanced heat transfer surface
CN111207412A (en) * 2020-01-17 2020-05-29 西北工业大学 Combustor flame tube adopting floating tile
GB202212532D0 (en) * 2022-08-30 2022-10-12 Rolls Royce Plc Turbine shroud segment and its manufacture

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE755567A (en) * 1969-12-01 1971-02-15 Gen Electric FIXED VANE STRUCTURE, FOR GAS TURBINE ENGINE AND ASSOCIATED TEMPERATURE ADJUSTMENT ARRANGEMENT
US4013376A (en) * 1975-06-02 1977-03-22 United Technologies Corporation Coolable blade tip shroud
US5048288A (en) * 1988-12-20 1991-09-17 United Technologies Corporation Combined turbine stator cooling and turbine tip clearance control
US5435139A (en) * 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5344283A (en) * 1993-01-21 1994-09-06 United Technologies Corporation Turbine vane having dedicated inner platform cooling
US5975851A (en) * 1997-12-17 1999-11-02 United Technologies Corporation Turbine blade with trailing edge root section cooling
US5993150A (en) * 1998-01-16 1999-11-30 General Electric Company Dual cooled shroud
EP1124039A1 (en) * 2000-02-09 2001-08-16 General Electric Company Impingement cooling apparatus for a gas turbine shroud system
FR2832178B1 (en) * 2001-11-15 2004-07-09 Snecma Moteurs COOLING DEVICE FOR GAS TURBINE RINGS
US7063503B2 (en) * 2004-04-15 2006-06-20 Pratt & Whitney Canada Corp. Turbine shroud cooling system
US20060056968A1 (en) * 2004-09-15 2006-03-16 General Electric Company Apparatus and methods for cooling turbine bucket platforms
DE102006011247A1 (en) * 2006-03-10 2007-09-13 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber wall has damping recesses for inner wall, with respective center axis arranged perpendicularly to inner wall, and cooling recesses, with respective center axis inclined at angle to inner wall
US7740444B2 (en) * 2006-11-30 2010-06-22 General Electric Company Methods and system for cooling integral turbine shround assemblies
US7665962B1 (en) * 2007-01-26 2010-02-23 Florida Turbine Technologies, Inc. Segmented ring for an industrial gas turbine
US7704039B1 (en) * 2007-03-21 2010-04-27 Florida Turbine Technologies, Inc. BOAS with multiple trenched film cooling slots
US8146364B2 (en) * 2007-09-14 2012-04-03 Siemens Energy, Inc. Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber
US20100095679A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine
CH700687A1 (en) * 2009-03-30 2010-09-30 Alstom Technology Ltd Chilled component for a gas turbine.
US8800298B2 (en) * 2009-07-17 2014-08-12 United Technologies Corporation Washer with cooling passage for a turbine engine combustor

Also Published As

Publication number Publication date
US20120251295A1 (en) 2012-10-04
EP2505787A1 (en) 2012-10-03

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Legal Events

Date Code Title Description
AT Applications terminated before publication under section 16(1)