EP1443182A3 - Cooling device - Google Patents

Cooling device Download PDF

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Publication number
EP1443182A3
EP1443182A3 EP04100222A EP04100222A EP1443182A3 EP 1443182 A3 EP1443182 A3 EP 1443182A3 EP 04100222 A EP04100222 A EP 04100222A EP 04100222 A EP04100222 A EP 04100222A EP 1443182 A3 EP1443182 A3 EP 1443182A3
Authority
EP
European Patent Office
Prior art keywords
cavity
component
cooling
cooling gas
section
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Withdrawn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
EP04100222A
Other languages
German (de)
French (fr)
Other versions
EP1443182A2 (en
Inventor
Christoph Nagler
André Schwind
Ralf Walz
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1443182A2 publication Critical patent/EP1443182A2/en
Publication of EP1443182A3 publication Critical patent/EP1443182A3/en
Withdrawn legal-status Critical Current

Links

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Die vorliegende Erfindung betrifft eine Kühleinrichtung (17) zum Versorgen eines ersten Hohlraums (9) mit einem Kühlgas, insbesondere in einer Gasturbine einer Kraftwerksanlage, umfassend einen Kühlgaskanal (19), der in einem ersten Bauteil (6) ausgebildet ist und den ersten Hohlraum (9) mit einem zweiten Hohlraum (10) verbindet. An einer vom zweiten Hohlraum (10) abgewandten Anlageseite (15) liegt ein zweites Bauteil (16) an und trennt den ersten Hohlraum (9) vom einem dritten Hohlraum (12). Das zweite Bauteil (16) ist in einem Verstellbereich verstellbar.The present invention relates to a cooling device (17) for supplying a first cavity (9) with a cooling gas, in particular in a gas turbine of a power plant, comprising a cooling gas channel (19) which is formed in a first component (6) and the first cavity ( 9) connects to a second cavity (10). On a side facing away from the second cavity (10) plant side (15) is located on a second component (16) and separates the first cavity (9) from a third cavity (12). The second component (16) is adjustable in an adjustment range.

Zur Verbesserung der Kühlwirkung ist ein Mündungsbereich (20) des Kühlgaskanals (19) so dimensioniert und positioniert, dass sein Mündungsquerschnitt (21) aus dem Verstellbereich herausragt, derart, dass er in jeder Stellung des zweiten Bauteils (16) zumindest mit einem vorgegebenen Mindestquerschnitt offen ist.

Figure imgaf001
To improve the cooling effect, an opening region (20) of the cooling gas channel (19) is dimensioned and positioned such that its mouth cross-section (21) protrudes from the adjustment region such that it opens in any position of the second component (16) at least with a predetermined minimum cross-section is.
Figure imgaf001
EP04100222A 2003-01-29 2004-01-22 Cooling device Withdrawn EP1443182A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10303340A DE10303340A1 (en) 2003-01-29 2003-01-29 cooling device
DE10303340 2003-01-29

Publications (2)

Publication Number Publication Date
EP1443182A2 EP1443182A2 (en) 2004-08-04
EP1443182A3 true EP1443182A3 (en) 2006-12-20

Family

ID=32603010

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04100222A Withdrawn EP1443182A3 (en) 2003-01-29 2004-01-22 Cooling device

Country Status (3)

Country Link
US (1) US7131814B2 (en)
EP (1) EP1443182A3 (en)
DE (1) DE10303340A1 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009103636A1 (en) * 2008-02-20 2009-08-27 Alstom Technology Ltd. Thermal machine
US8128344B2 (en) * 2008-11-05 2012-03-06 General Electric Company Methods and apparatus involving shroud cooling
US8186933B2 (en) * 2009-03-24 2012-05-29 General Electric Company Systems, methods, and apparatus for passive purge flow control in a turbine
US8371814B2 (en) * 2009-06-24 2013-02-12 Honeywell International Inc. Turbine engine components
US8529193B2 (en) * 2009-11-25 2013-09-10 Honeywell International Inc. Gas turbine engine components with improved film cooling
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US20130028704A1 (en) * 2011-07-26 2013-01-31 Thibodeau Anne-Marie B Blade outer air seal with passage joined cavities
US9650900B2 (en) 2012-05-07 2017-05-16 Honeywell International Inc. Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
US10113433B2 (en) 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
US10233776B2 (en) 2013-05-21 2019-03-19 Siemens Energy, Inc. Gas turbine ring segment cooling apparatus
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US10428689B2 (en) * 2017-05-17 2019-10-01 Rolls-Royce Deutschland Ltd & Co Kg Heat shield for a gas turbine engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0709550A1 (en) * 1994-10-31 1996-05-01 General Electric Company Cooled shroud
US5641267A (en) * 1995-06-06 1997-06-24 General Electric Company Controlled leakage shroud panel
WO1999030009A1 (en) * 1997-12-05 1999-06-17 Pratt & Whitney Canada Corp. Seal assembly for a gas turbine engine
US5988975A (en) * 1996-05-20 1999-11-23 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
FR2832178A1 (en) * 2001-11-15 2003-05-16 Snecma Moteurs Gas turbine fixed ring cooler has cavities fitted with particle impact covers pierced with holes for passage of cooling air

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1126469A (en) * 1964-09-24 1968-09-05 English Electric Co Ltd Improvements in or relating to gas turbines
US4199151A (en) * 1978-08-14 1980-04-22 General Electric Company Method and apparatus for retaining seals
FR2548733B1 (en) * 1983-07-07 1987-07-10 Snecma DEVICE FOR SEALING MOBILE BLADES OF A TURBOMACHINE
US5165847A (en) * 1991-05-20 1992-11-24 General Electric Company Tapered enlargement metering inlet channel for a shroud cooling assembly of gas turbine engines
DE19756734A1 (en) * 1997-12-19 1999-06-24 Bmw Rolls Royce Gmbh Passive gap system of a gas turbine
DE19963371A1 (en) * 1999-12-28 2001-07-12 Alstom Power Schweiz Ag Baden Chilled heat shield
US6340285B1 (en) * 2000-06-08 2002-01-22 General Electric Company End rail cooling for combined high and low pressure turbine shroud

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0709550A1 (en) * 1994-10-31 1996-05-01 General Electric Company Cooled shroud
US5641267A (en) * 1995-06-06 1997-06-24 General Electric Company Controlled leakage shroud panel
US5988975A (en) * 1996-05-20 1999-11-23 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
WO1999030009A1 (en) * 1997-12-05 1999-06-17 Pratt & Whitney Canada Corp. Seal assembly for a gas turbine engine
FR2832178A1 (en) * 2001-11-15 2003-05-16 Snecma Moteurs Gas turbine fixed ring cooler has cavities fitted with particle impact covers pierced with holes for passage of cooling air

Also Published As

Publication number Publication date
DE10303340A1 (en) 2004-08-26
US20050089396A1 (en) 2005-04-28
US7131814B2 (en) 2006-11-07
EP1443182A2 (en) 2004-08-04

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