EP0648979A1 - Méthode et moyens pour le refroidissement d'une chambre de combustion d'une turbine à gaz - Google Patents

Méthode et moyens pour le refroidissement d'une chambre de combustion d'une turbine à gaz Download PDF

Info

Publication number
EP0648979A1
EP0648979A1 EP94115334A EP94115334A EP0648979A1 EP 0648979 A1 EP0648979 A1 EP 0648979A1 EP 94115334 A EP94115334 A EP 94115334A EP 94115334 A EP94115334 A EP 94115334A EP 0648979 A1 EP0648979 A1 EP 0648979A1
Authority
EP
European Patent Office
Prior art keywords
cooling
combustion chamber
gas turbine
connecting openings
turbine combustion
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.)
Granted
Application number
EP94115334A
Other languages
German (de)
English (en)
Other versions
EP0648979B1 (fr
Inventor
Dr. Rolf Althaus
Dr. Jakob Keller
Dr. Burkhard Schulte-Werning
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 Switzerland GmbH
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0648979A1 publication Critical patent/EP0648979A1/fr
Application granted granted Critical
Publication of EP0648979B1 publication Critical patent/EP0648979B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the invention relates to a method and a device for cooling a gas turbine combustion chamber cooled by impact and convection cooling or pure convection cooling.
  • the invention tries to avoid all these disadvantages. It is the object of the invention to provide a method and a device for cooling in a gas turbine combustion chamber cooled by impact and convection cooling or pure convection cooling, with which it is possible to further increase this damage in the cooling duct when minor local damage occurs, for example holes to prevent.
  • this is achieved in a method for cooling the gas turbine combustion chamber in accordance with the preamble of the main claim in that a compensating flow of the cooling air is conducted between the cooling ducts in such a way that the flow velocity in the damaged cooling duct always exceeds a critical limit value after the point of damage and thus falls below a critical limit temperature .
  • this is achieved in a device for cooling the gas turbine combustion chamber in accordance with the preamble of the main claim in that connecting openings are arranged between adjacent cooling channels, the connecting openings being arranged offset on opposite sides of a cooling channel.
  • connection openings are advantageously made on the cooling fins.
  • the connecting openings between the cooling channels are dimensioned such that the product of the average opening width and the length of the cooling channel is between 2 and 8 in relation to the cross-sectional area of the cooling channel. Then the most effective cooling can be achieved.
  • a gas turbine combustion chamber is shown in simplified form in FIG. 1.
  • a convective cooling system is used to cool the combustion chamber wall 1.
  • the entire cooling air flows in cooling channels 2 between the outer wall 3 and the combustion chamber wall 1 before it is supplied to the combustion chamber as combustion air.
  • connection openings 5 between the cooling channels 2 is advantageously carried out according to the design rule 2 ⁇ sL / A ⁇ 8, that is, the product of the average opening width s between two cooling channels 2 and the cooling channel length L, based on the cross-sectional area A of the cooling channel 2, is in the range greater than 2 and less than 8. If the value falls below the lower limit of this interval, a very large hole can lead to overheating of the cooling channel 2 after the hole. Will the top If the value is significantly exceeded, then a very large hole or a longitudinal slot in one or more cooling channels can lead to such a high air loss that the burners overheat the primary zone of the combustion chamber at full load.
  • a local damage site 6 in the form of a small hole can form in the combustion chamber wall 1. Then there is the risk in conventional gas turbine combustion chambers, which are cooled by combined impingement and convection cooling systems or by pure convection cooling systems according to the prior art, that this small damage location 6 leads to major consequential damage because the cooling duct 2 no longer adequately contains cooling air after the hole is supplied.
  • connection openings 5 ensures that air can flow into the damaged cooling channel 2 from at least one adjacent channel at every axial position.
  • the compensating flow takes place on the outer wall 3 of the combustion chamber.
  • cooling film flows are formed on the outer wall 3, which intensely cool the cooling channel 2 and in particular the outer wall 3 in the area of the local damage site 6 (hole) and cool completely. This prevents the hole from growing further.
  • the damaged cooling channel is "self-healing".
  • the invention is particularly important in the case of thin combustion chamber walls with high thermal loads.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP94115334A 1993-10-18 1994-09-29 Méthode et moyens pour le refroidissement d'une chambre de combustion d'une turbine à gaz Expired - Lifetime EP0648979B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4335413A DE4335413A1 (de) 1993-10-18 1993-10-18 Verfahren und Vorrichtung zur Kühlung einer Gasturbinenbrennkammer
DE4335413 1993-10-18

Publications (2)

Publication Number Publication Date
EP0648979A1 true EP0648979A1 (fr) 1995-04-19
EP0648979B1 EP0648979B1 (fr) 1999-10-20

Family

ID=6500380

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94115334A Expired - Lifetime EP0648979B1 (fr) 1993-10-18 1994-09-29 Méthode et moyens pour le refroidissement d'une chambre de combustion d'une turbine à gaz

Country Status (4)

Country Link
US (2) US5615546A (fr)
EP (1) EP0648979B1 (fr)
JP (1) JP3863576B2 (fr)
DE (2) DE4335413A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016069599A1 (fr) * 2014-10-31 2016-05-06 General Electric Company Ensemble composant de moteur
US9957816B2 (en) 2014-05-29 2018-05-01 General Electric Company Angled impingement insert
US10422235B2 (en) 2014-05-29 2019-09-24 General Electric Company Angled impingement inserts with cooling features
US10690055B2 (en) 2014-05-29 2020-06-23 General Electric Company Engine components with impingement cooling features

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19812236C2 (de) 1998-03-20 2001-10-18 Daimler Chrysler Ag Verfahren zur Unterdrückung hochfrequenter Schwingungen an gelenkten Achsen eines Fahrzeugs
US8894363B2 (en) 2011-02-09 2014-11-25 Siemens Energy, Inc. Cooling module design and method for cooling components of a gas turbine system
US8959886B2 (en) * 2010-07-08 2015-02-24 Siemens Energy, Inc. Mesh cooled conduit for conveying combustion gases
EP2397653A1 (fr) 2010-06-17 2011-12-21 Siemens Aktiengesellschaft Segment de plateforme pour porter une aube de guidage pour turbine à gaz et procédé de refroidissement de ce segment
US9644511B2 (en) 2012-09-06 2017-05-09 Mitsubishi Hitachi Power Systems, Ltd. Combustion gas cooling apparatus, denitration apparatus including the combustion gas cooling apparatus, and combustion gas cooling method

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2077635A (en) * 1980-06-13 1981-12-23 Rolls Royce Manufacture of laminated material
EP0202050A1 (fr) * 1985-04-29 1986-11-20 Avco Corporation Structure d'une paroi de chambre de combustion
EP0225527A2 (fr) * 1985-12-02 1987-06-16 Siemens Aktiengesellschaft Paroi refroidie pour turbines à gaz
US4773227A (en) * 1982-04-07 1988-09-27 United Technologies Corporation Combustion chamber with improved liner construction
EP0489193A1 (fr) * 1990-12-05 1992-06-10 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
US5246341A (en) * 1992-07-06 1993-09-21 United Technologies Corporation Turbine blade trailing edge cooling construction

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2644302A (en) * 1948-06-17 1953-07-07 Gen Electric Combustion chamber having a flat wall liner with oppositely disposed apertures
US3408812A (en) * 1967-02-24 1968-11-05 Gen Electric Cooled joint construction for combustion wall means
SE314558B (fr) * 1968-10-28 1969-09-08 Stal Laval Turbin Ab
US3777484A (en) * 1971-12-08 1973-12-11 Gen Electric Shrouded combustion liner
US4071194A (en) * 1976-10-28 1978-01-31 The United States Of America As Represented By The Secretary Of The Navy Means for cooling exhaust nozzle sidewalls
US4236378A (en) * 1978-03-01 1980-12-02 General Electric Company Sectoral combustor for burning low-BTU fuel gas
CH633347A5 (de) * 1978-08-03 1982-11-30 Bbc Brown Boveri & Cie Gasturbine.
GB2033071B (en) * 1978-10-28 1982-07-21 Rolls Royce Sheet metal laminate
US4302941A (en) * 1980-04-02 1981-12-01 United Technologies Corporation Combuster liner construction for gas turbine engine
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
GB2118710B (en) * 1981-12-31 1985-05-22 Secr Defence Improvements in or relating to combustion chamber wall cooling
US4653279A (en) * 1985-01-07 1987-03-31 United Technologies Corporation Integral refilmer lip for floatwall panels
DE3615226A1 (de) * 1986-05-06 1987-11-12 Mtu Muenchen Gmbh Heissgasueberhitzungsschutzeinrichtung fuer gasturbinentriebwerke
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2077635A (en) * 1980-06-13 1981-12-23 Rolls Royce Manufacture of laminated material
US4773227A (en) * 1982-04-07 1988-09-27 United Technologies Corporation Combustion chamber with improved liner construction
EP0202050A1 (fr) * 1985-04-29 1986-11-20 Avco Corporation Structure d'une paroi de chambre de combustion
EP0225527A2 (fr) * 1985-12-02 1987-06-16 Siemens Aktiengesellschaft Paroi refroidie pour turbines à gaz
EP0489193A1 (fr) * 1990-12-05 1992-06-10 Asea Brown Boveri Ag Chambre de combustion pour turbine à gaz
US5246341A (en) * 1992-07-06 1993-09-21 United Technologies Corporation Turbine blade trailing edge cooling construction

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9957816B2 (en) 2014-05-29 2018-05-01 General Electric Company Angled impingement insert
US10422235B2 (en) 2014-05-29 2019-09-24 General Electric Company Angled impingement inserts with cooling features
US10690055B2 (en) 2014-05-29 2020-06-23 General Electric Company Engine components with impingement cooling features
WO2016069599A1 (fr) * 2014-10-31 2016-05-06 General Electric Company Ensemble composant de moteur
US10619488B2 (en) 2014-10-31 2020-04-14 General Electric Company Engine component assembly

Also Published As

Publication number Publication date
DE4335413A1 (de) 1995-04-20
US5615546A (en) 1997-04-01
EP0648979B1 (fr) 1999-10-20
DE59408840D1 (de) 1999-11-25
JPH07167436A (ja) 1995-07-04
JP3863576B2 (ja) 2006-12-27
US5651253A (en) 1997-07-29

Similar Documents

Publication Publication Date Title
DE10001109B4 (de) Gekühlte Schaufel für eine Gasturbine
DE60317920T2 (de) Effusionsgekühlter übergangskanal mit geformten kühllöchern
DE102005025823B4 (de) Verfahren und Vorrichtung zum Kühlen einer Brennkammerauskleidung und eines Übergangsteils einer Gasturbine
EP0745809B1 (fr) Générateur de tourbillons pour chambre de combustion
EP1701095B1 (fr) Ecran thermique
DE69528490T2 (de) Kühleinrichtung für das Umfangsgehäuse einer Turbine
EP2423599B1 (fr) Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à la mise en oeuvre du procédé
DE69816532T2 (de) Wärmeübergangsstruktur
DE69803069T2 (de) Gekühlte brennkammerwand für eine gasturbine
EP0599055B1 (fr) Chambre de combustion pour turbine à gaz
CH702172A2 (de) Brennkammer für eine Gasturbine ,mit verbesserter Kühlung.
DE2147135A1 (de) Brennkammermantel insbesondere für Gasturbinentriebwerke
CH697920A2 (de) Turbinentriebwerk mit einer Brennkammerauskleidung mit wirbelluftgekühltem hinterem Ende und Kühlverfahren.
DE3231689A1 (de) Mehrfach prallgekuehltes gebilde, insbesondere ummantelung eines gasstroemungsweges
DE10064264B4 (de) Anordnung zur Kühlung eines Bauteils
EP2154431A2 (fr) Machine thermique
DE2617999A1 (de) Kuehlring fuer brennkammern
DE4443864A1 (de) Gek}hltes Wandteil
EP0718561A2 (fr) Brûleur
EP0640745B1 (fr) Procédé de refroidissement d'un composant
EP0718558A2 (fr) Brûleur
EP0648979B1 (fr) Méthode et moyens pour le refroidissement d'une chambre de combustion d'une turbine à gaz
EP0892149A1 (fr) Système de refroidissement pour le bord d'attac d'une aube creuse pour turbine à gaz
EP0489193A1 (fr) Chambre de combustion pour turbine à gaz
DE60225411T2 (de) Flammrohr oder Bekleidung für die Brennkammer einer Gasturbine mit niedriger Schadstoffemission

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17P Request for examination filed

Effective date: 19950916

17Q First examination report despatched

Effective date: 19961030

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ASEA BROWN BOVERI AG

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REF Corresponds to:

Ref document number: 59408840

Country of ref document: DE

Date of ref document: 19991125

ET Fr: translation filed
RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ABB ALSTOM POWER (SCHWEIZ) AG

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20000223

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59408840

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Effective date: 20120621

Ref country code: DE

Ref legal event code: R081

Ref document number: 59408840

Country of ref document: DE

Owner name: ALSTOM TECHNOLOGY LTD., CH

Free format text: FORMER OWNER: ALSTOM, PARIS, FR

Effective date: 20120621

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20120802 AND 20120808

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Owner name: ALSTOM TECHNOLOGY LTD., CH

Effective date: 20120918

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20130827

Year of fee payment: 20

Ref country code: FR

Payment date: 20130826

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20130930

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 59408840

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20140928

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20140930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20140928