EP0848210B1 - Brennkammer mit integrierten Leitschaufeln - Google Patents

Brennkammer mit integrierten Leitschaufeln Download PDF

Info

Publication number
EP0848210B1
EP0848210B1 EP97810854A EP97810854A EP0848210B1 EP 0848210 B1 EP0848210 B1 EP 0848210B1 EP 97810854 A EP97810854 A EP 97810854A EP 97810854 A EP97810854 A EP 97810854A EP 0848210 B1 EP0848210 B1 EP 0848210B1
Authority
EP
European Patent Office
Prior art keywords
cooling
guide
air
combustion
gas turbine
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.)
Expired - Lifetime
Application number
EP97810854A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0848210A2 (de
EP0848210A3 (de
Inventor
Pierre Meylan
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.)
Alstom SA
Original Assignee
Alstom Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0848210A2 publication Critical patent/EP0848210A2/de
Publication of EP0848210A3 publication Critical patent/EP0848210A3/de
Application granted granted Critical
Publication of EP0848210B1 publication Critical patent/EP0848210B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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

Definitions

  • the invention relates to a gas turbine with between the combustion chamber and turbine impeller arranged after the guide vanes Preamble of claim 1.
  • a gas turbine has one between the combustion chamber and the turbine impeller guide vane group forming an independent unit, which are essentially functional and constructive from the neighboring ones Assemblies, such as combustion chamber and turbine impeller, is separated and also separate anchorings in the turbine housing having.
  • Assemblies such as combustion chamber and turbine impeller, is separated and also separate anchorings in the turbine housing having.
  • This has the disadvantage that each of these assemblies made separately and assembled separately and above all must also be adjusted to each other, which is very expensive caused.
  • such a design requires one very large number of components with all the complex disadvantages, of the manufacturing and assembly processes, the transport weight up to in particular thermal operating behavior.
  • DE 1 245 644 describes a gas turbine with a monolithic combustion chamber guide vane unit known.
  • the combustor vane assembly is in a cold Support structure attached.
  • the combustion chamber wall is in the flow direction from Air flows around the compressor to the turbine, which is guided into the guide vanes, and thence through mixed air openings into the hot gas flowing out of the combustion chamber flows.
  • Monolithic combustor guide vane units with analog Air ducts around the combustion chamber and through the guide vanes are also from US 3,608,310, DE 11 08 516, DE 14 76 887, DE 14 76 892, US 3,353,351, and DE 12 40 706 became known. Airflow becomes primary according to the teachings disclosed as mixed air to dilute the hot gas flow before entering the turbine impeller used. Cooling problems are not the focus; in particular, the thermally highly stressed power blades are already on the Combustion chamber wall of heated air flows through.
  • the present invention is based on the task of having a gas turbine between To specify the guide vanes arranged in the combustion chamber and turbine impeller, which the mentioned disadvantages of the prior art can avoid.
  • the solution to this problem is with the characteristics of the license plate circumscribed by claim 1. Details of the embodiments Such a gas turbine are characterized by the characteristics of dependent claims.
  • guide vanes 1.1 In a gas turbine with between each combustion chamber 1.2 and the turbine impeller 2 are arranged guide vanes 1.1 this integrated into the combustion chamber wall 1.2.1 according to the invention and formed as parts of the same. You put one in essential monolithic combustion chamber guide vane unit 1 The combustion chamber wall 1.2.1 goes into the wall of each associated one Guide vane 1.1 over, without being separated from it. This combustion chamber guide vane unit 1 is in a so-called cold support structure 3.1 of the gas turbine system used and is carried by this.
  • This combustor guide vane unit 1 is a gas turbine system split formed, creating a radially outer and a radially inner segment 1.B or 1.A arises, in each Segment the guide vane halves through corresponding boundary walls 1.1.i are separated from each other, i.e. each Guide vane 1.1 a radially closed to the outside inner and radially outer part, each in a corresponding Segment 1.A or 1.B has.
  • Each of these segments sits in an associated cold support structure 3.1 of the gas turbine system. Between each of these cold support structures 3.1 and their assigned segments 1.A and 1.B are cooling air ducts 4 is provided, which partially in the interior of the guide vanes 1.1 run.
  • the inflow openings 4.1 are the Cooling air channels 4 in the cold support structure 3.1 in the area the guide vanes 1.1 arranged, whereby a counterflow cooling the combustion chamber wall 1.2.1 is realized.
  • To the thermal conditions have to be met in the cooling air ducts 4 of the guide vanes 1.1 guide devices 4.2, e.g. Baffle plates or baffles, intended for the cooling air.
  • the dividing the guide vane 1.1 in the radial direction and adjacent boundary walls 1.1.i each thus formed guide vane half of corresponding segments at least one with the adjacent boundary wall 1.1.i corresponding paragraph 1.1.k as a sealing element for reduction of leakage losses.
  • segment 1.A or 1.B i.e. with optimal production [casting technology] and the cooling conditions between radially inside or radially are completely outside (0% and 100% of the channel height).
  • the dividing the guide vanes 1.1 and adjacent to each other Boundary walls 1.1.i corresponding to each guide vane half Segments can be arranged at any inclination to the rotor axis.
  • the cooling air is almost completely again Combustion cycle supplied, passing through the counterflow is already very well preheated.
  • the integrated Design can greatly reduce the cooling air loss become.
  • the countercurrent Cooling air ensures that the thermal loads are very high
  • the fresh and colder cooling air is guided by guide vanes preserved, thus be cooled better.
  • the Length of the combustion chamber with integrated guide vane by approx the axial extent of the first row of guide vanes has been shortened become.
  • there is the advantage that the Cooling air for the first row of blades of the first turbine no longer through the guide vane row, but directly from Compressors coming into the row of blades can.
  • the cooling air flows essentially in Series connected arise compared to the parallel connection the cooling air flows according to the prior art also significant advantages in terms of cooling efficiency.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP97810854A 1996-12-13 1997-11-11 Brennkammer mit integrierten Leitschaufeln Expired - Lifetime EP0848210B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19651881 1996-12-13
DE19651881A DE19651881A1 (de) 1996-12-13 1996-12-13 Brennkammer mit integrierten Leitschaufeln

Publications (3)

Publication Number Publication Date
EP0848210A2 EP0848210A2 (de) 1998-06-17
EP0848210A3 EP0848210A3 (de) 1999-11-17
EP0848210B1 true EP0848210B1 (de) 2003-04-16

Family

ID=7814598

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810854A Expired - Lifetime EP0848210B1 (de) 1996-12-13 1997-11-11 Brennkammer mit integrierten Leitschaufeln

Country Status (7)

Country Link
US (1) US5953919A (ja)
EP (1) EP0848210B1 (ja)
JP (1) JPH10184387A (ja)
CN (1) CN1130522C (ja)
CA (1) CA2219421C (ja)
DE (2) DE19651881A1 (ja)
TW (1) TW374821B (ja)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19737997A1 (de) * 1997-08-30 1999-03-04 Asea Brown Boveri Plenum
US20030074264A1 (en) * 2001-03-23 2003-04-17 Hoffman George Herry System, method and computer program product for low-cost fulfillment in a supply chain management framework
US7930891B1 (en) 2007-05-10 2011-04-26 Florida Turbine Technologies, Inc. Transition duct with integral guide vanes
DE602007007333D1 (de) * 2007-09-24 2010-08-05 Alstom Technology Ltd Dichtung in Gasturbine
US8276389B2 (en) * 2008-09-29 2012-10-02 Siemens Energy, Inc. Assembly for directing combustion gas
US8230688B2 (en) * 2008-09-29 2012-07-31 Siemens Energy, Inc. Modular transvane assembly
US9822649B2 (en) 2008-11-12 2017-11-21 General Electric Company Integrated combustor and stage 1 nozzle in a gas turbine and method
EP2405103B1 (en) 2009-08-24 2016-05-04 Mitsubishi Heavy Industries, Ltd. Split ring cooling structure
EP2587021A1 (en) 2011-10-24 2013-05-01 Siemens Aktiengesellschaft Gas turbine and method for guiding compressed fluid in a gas turbine
EP2613080A1 (en) * 2012-01-05 2013-07-10 Siemens Aktiengesellschaft Combustion chamber of an annular combustor for a gas turbine
US20140127008A1 (en) * 2012-11-08 2014-05-08 General Electric Company Transition duct having airfoil and hot gas path assembly for turbomachine
US9322335B2 (en) 2013-03-15 2016-04-26 Siemens Energy, Inc. Gas turbine combustor exit piece with hinged connections
US10024180B2 (en) * 2014-11-20 2018-07-17 Siemens Energy, Inc. Transition duct arrangement in a gas turbine engine
US20170370583A1 (en) * 2016-06-22 2017-12-28 General Electric Company Ceramic Matrix Composite Component for a Gas Turbine Engine
US11067277B2 (en) * 2016-10-07 2021-07-20 General Electric Company Component assembly for a gas turbine engine
US10816199B2 (en) * 2017-01-27 2020-10-27 General Electric Company Combustor heat shield and attachment features
US11248789B2 (en) 2018-12-07 2022-02-15 Raytheon Technologies Corporation Gas turbine engine with integral combustion liner and turbine nozzle
CN112484072B (zh) * 2020-11-24 2022-06-17 湖南省农友机械集团有限公司 一种热风炉进风装置及热风炉
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
CN112855617B (zh) * 2021-01-27 2022-07-08 山东亚通科技集团有限公司 一种风机

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2477683A (en) * 1942-09-30 1949-08-02 Turbo Engineering Corp Compressed air and combustion gas flow in turbine power plant
US2630679A (en) * 1947-02-27 1953-03-10 Rateau Soc Combustion chambers for gas turbines with diverse combustion and diluent air paths
FR1104644A (fr) * 1954-02-15 1955-11-22 Thomson Houston Comp Francaise Perfectionnements aux systèmes de commande de l'écoulement d'un fluide
US3088281A (en) * 1956-04-03 1963-05-07 Bristol Siddeley Engines Ltd Combustion chambers for use with swirling combustion supporting medium
US3316714A (en) * 1963-06-20 1967-05-02 Rolls Royce Gas turbine engine combustion equipment
GB1048968A (en) * 1964-05-08 1966-11-23 Rolls Royce Combustion chamber for a gas turbine engine
GB1034260A (en) * 1964-12-02 1966-06-29 Rolls Royce Aerofoil-shaped blade for use in a fluid flow machine
US3608310A (en) * 1966-06-27 1971-09-28 Gen Motors Corp Turbine stator-combustor structure
GB2189553B (en) * 1986-04-25 1990-05-23 Rolls Royce Cooled vane
US5239818A (en) * 1992-03-30 1993-08-31 General Electric Company Dilution pole combustor and method

Also Published As

Publication number Publication date
DE19651881A1 (de) 1998-06-18
CA2219421A1 (en) 1998-06-13
DE59709849D1 (de) 2003-05-22
CN1188210A (zh) 1998-07-22
CN1130522C (zh) 2003-12-10
TW374821B (en) 1999-11-21
EP0848210A2 (de) 1998-06-17
JPH10184387A (ja) 1998-07-14
US5953919A (en) 1999-09-21
EP0848210A3 (de) 1999-11-17
CA2219421C (en) 2007-04-24

Similar Documents

Publication Publication Date Title
EP0848210B1 (de) Brennkammer mit integrierten Leitschaufeln
DE3810600C2 (de) Rahmenanordnung für ein Gasturbinentriebwerk
DE60132864T2 (de) Scheidungswand für den Zwischenstufenraum einer Gasturbine
EP0447886B1 (de) Axialdurchströmte Gasturbine
DE69932966T2 (de) Leitschaufelanordnung für eine Turbomaschine
EP0313826B1 (de) Axialdurchströmte Gasturbine
DE69829892T2 (de) Gasturbine mit Rückführung des Kühlmediums
DE60016505T2 (de) Gehäuse für einen Hochdruckkompressor
DE102012015449A1 (de) Gasturbinenbrennkammer mit Mischluftöffnungen und Luftleitelementen in modularer Bauweise
EP2179143B1 (de) Spaltkühlung zwischen brennkammerwand und turbinenwand einer gasturbinenanlage
EP1451450B1 (de) Gasturbogruppe
EP1201879B1 (de) Gekühltes Bauteil, Gusskern für die Herstellung eines solchen Bauteils, sowie Verfahren zum Herstellen eines solchen Bauteils
EP1276972B1 (de) Turbine
EP1111189B1 (de) Kühlluftführung für den Turbinenrotor eines Gasturbinen-Triebwerkes
EP1048822A2 (de) Hitzeschild für eine Gasturbine
DE102011054388A1 (de) Inducer für ein Gasturbinensystem
EP1614863A1 (de) Strömungsstruktur für einen Turboverdichter
EP1413831A1 (de) Ringbrennkammern für eine Gasturbine und Gasturbine
DE102015219556A1 (de) Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
EP2543865A2 (de) Turbofan-Triebwerk mit Wärmetauscher im Kerntriebwerksgehäuse
DE19859787A1 (de) Gekühlte Turbinenschaufel
DE102016207057A1 (de) Gasturbinenbrennkammer
DE102017202177A1 (de) Wandbauteil einer Gasturbine mit verbesserter Kühlung
EP0636764A1 (de) Gasturbine mit gekühltem Rotor
DE102014102778A1 (de) Strömungshülse zur thermischen Steuerung eines doppelwandigen Turbinengehäuses und zugehöriges Verfahren

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: A2

Designated state(s): DE FR GB IT NL

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE CH DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

RIC1 Information provided on ipc code assigned before grant

Free format text: 6F 23R 3/16 A, 6F 01D 9/02 B, 6F 01D 9/04 B

17P Request for examination filed

Effective date: 20000502

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

Owner name: ABB ALSTOM POWER (SCHWEIZ) AG

AKX Designation fees paid

Free format text: DE FR GB IT NL

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

Owner name: ALSTOM

17Q First examination report despatched

Effective date: 20020128

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

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

Owner name: ALSTOM (SWITZERLAND) LTD

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

Designated state(s): DE FR GB IT NL

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 59709849

Country of ref document: DE

Date of ref document: 20030522

Kind code of ref document: P

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

Effective date: 20030715

ET Fr: translation filed
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

Effective date: 20040119

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

Ref country code: NL

Payment date: 20081113

Year of fee payment: 12

Ref country code: DE

Payment date: 20081121

Year of fee payment: 12

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

Ref country code: IT

Payment date: 20081125

Year of fee payment: 12

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

Ref country code: FR

Payment date: 20081113

Year of fee payment: 12

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

Ref country code: GB

Payment date: 20081117

Year of fee payment: 12

REG Reference to a national code

Ref country code: NL

Ref legal event code: V1

Effective date: 20100601

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20091111

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20100730

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

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100601

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20091130

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 NON-PAYMENT OF DUE FEES

Effective date: 20100601

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 NON-PAYMENT OF DUE FEES

Effective date: 20091111

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

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20091111