EP0578048B1 - Chambre à combustion cylindrique pour turbine à gaz - Google Patents

Chambre à combustion cylindrique pour turbine à gaz Download PDF

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Publication number
EP0578048B1
EP0578048B1 EP93109972A EP93109972A EP0578048B1 EP 0578048 B1 EP0578048 B1 EP 0578048B1 EP 93109972 A EP93109972 A EP 93109972A EP 93109972 A EP93109972 A EP 93109972A EP 0578048 B1 EP0578048 B1 EP 0578048B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
perforated cone
chamber casing
cone
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
EP93109972A
Other languages
German (de)
English (en)
Other versions
EP0578048A1 (fr
Inventor
Achim Dipl.-Ing. Zimmermann
Karl-Erhard Dr.-Ing. Beck
Klaus Dieter Dipl.-Ing. Mohr
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.)
MAN Gutehoffnungshutte GmbH
Original Assignee
MAN Gutehoffnungshutte GmbH
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 MAN Gutehoffnungshutte GmbH filed Critical MAN Gutehoffnungshutte GmbH
Publication of EP0578048A1 publication Critical patent/EP0578048A1/fr
Application granted granted Critical
Publication of EP0578048B1 publication Critical patent/EP0578048B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D9/023—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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • 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

Definitions

  • the invention relates to a cylindrical combustion chamber housing of a gas turbine with an unbladed inlet manifold with a narrowing annular channel arranged around the combustion chamber housing for introducing compressor air through openings into the interior of a combustion chamber.
  • a cylindrical combustion chamber housing of a gas turbine is known from document FR-A-2 439 362.
  • the compressor air flows from an unshielded rectangular manifold into a narrowing annular duct and from there through three rectangular openings distributed unevenly around the circumference into the interior of the combustion chamber housing and impinges there on the flame tube.
  • the object of the invention is to achieve a uniform air distribution and sufficient cooling of the inner cone, the mixer tube, by converting a tangential flow into an axial flow in the combustion chamber housing, to minimize the pressure loss in the feed area and to further improve the efficiency of the gas turbine.
  • the compressor air is supplied through a lateral inlet bend in the shape of an arc to the lower conical part of the combustion chamber housing, the perforated cone.
  • the inlet heart connects directly to the intake manifold, in which the compressor air is guided around the perforated cone on both sides.
  • the conversion of this tangential flow around a cone into an axial flow through the holes in the perforated cone is achieved in that the cross section of the inlet heart, i.e. the cross-sectional area between the perforated cone and the circumferential inlet heart, in the area between the inlet manifold and the flow divider, is reduced.
  • the reduction in cross-section is such that the air speed always remains approximately the same.
  • the holes in the hole cone are arranged and designed that the open cross section of the holes increases both from the front to the rear and from top to bottom.
  • the conversion of the tangential flow into an axial flow and the resulting uniform cooling of the mixing tube is supported by the six radially arranged ribs. This arrangement prevents the compressor air flowing obliquely upward and backward through the inlet manifold from cooling only a limited area of the mixing tube and from the rear lower area of the mixing tube not being cooled or being cooled insufficiently.
  • This arrangement according to the invention achieves optimal cooling of the mixing tube while minimizing the pressure loss in the air supply area.
  • Fig. 1 shows a cross section of the lower part of the combustion chamber housing with the inventive design of the air supply area with air inlet manifold (2), inlet heart (1) and perforated cone (5), whereby a uniform air distribution by converting a tangential flow into an axial flow in the combustion chamber housing and a sufficient Cooling of the mixing tube (6) is reached.
  • the compressor air represented by arrows is fed through a side inlet elbow (2) in an arc shape to the lower conical part of the combustion chamber housing (perforated cone 5).
  • the inlet heart (1) connects to the intake manifold (2), in which the compressor air is guided around the perforated cone (5) on both sides.
  • the holes (7) in the perforated cone (5) are arranged and designed so that the open cross section of the holes (7) from front to back and also from enlarged from top to bottom.
  • the bores (7) are arranged in the perforated cone (5) on five parallel circumferential lines (8) so that they are each gap.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Air Bags (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Control Of Turbines (AREA)

Claims (4)

  1. Carter cylindrique de la chambre de combustion d'une turbine à gaz, avec un coude d'entrée sans aubes avec, disposé autour du carter de la chambre de combustion, un canal annulaire allant en se rétrécissant pour introduire de l'air comprimé par des orifices dans l'intérieur d'une chambre de combustion, caractérisé en ce qu'un coude d'entrée (2), rapporté latéralement sous forme d'arc, est fixé sur la partie conique inférieure du carter (5) de la chambre de combustion, en ce que le coude d'entrée (2) se transforme en un coeur d'entrée (1) de préférence de forme circulaire, qui s'étend des deux côtés autour de la partie conique inférieure du carter (5) de la chambre de combustion, et en ce que la partie conique inférieure du carter (5) de la chambre de combustion revêt la forme d'un cône perforé, qui est disposé en forme de cercle autour du tube mélangeur conique (6).
  2. Carter cylindrique de la chambre de combustion d'une turbine à gaz selon la revendication 1, caractérisé en ce qu'entre le cône perforé (5) et le tube mélangeur (6) il est prévu des nervures de guidage (3) disposées radialement.
  3. Carter cylindrique de la chambre de combustion d'une turbine à gaz selon les revendications 1 et 2, caractérisé en ce que les perçages (7) dans le cône perforé (5) sont disposés et dimensionnés de façon que la section transversale ouverte des perçages (7) s'agrandisse du haut vers le bas, aussi bien au voisinage de coude d'entrée vers le diviseur de courant (4), qu'également sur le cône perforé (5).
  4. Carter cylindrique de la chambre de combustion d'une turbine à gaz selon les revendications 1 à 3, caractérisé en ce que les perçages (7) sur le cône perforé (5) sont rapportés sur plusieurs lignes périphériques et que ces perçages (7) sont décalés les uns par rapport aux autres.
EP93109972A 1992-07-08 1993-06-23 Chambre à combustion cylindrique pour turbine à gaz Expired - Lifetime EP0578048B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4222391 1992-07-08
DE4222391A DE4222391C2 (de) 1992-07-08 1992-07-08 Zylindrisches Brennkammergehäuse einer Gasturbine

Publications (2)

Publication Number Publication Date
EP0578048A1 EP0578048A1 (fr) 1994-01-12
EP0578048B1 true EP0578048B1 (fr) 1995-08-30

Family

ID=6462741

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93109972A Expired - Lifetime EP0578048B1 (fr) 1992-07-08 1993-06-23 Chambre à combustion cylindrique pour turbine à gaz

Country Status (6)

Country Link
US (1) US5363653A (fr)
EP (1) EP0578048B1 (fr)
AT (1) ATE127209T1 (fr)
CA (1) CA2099926C (fr)
DE (2) DE4222391C2 (fr)
DK (1) DK0578048T3 (fr)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4238602C2 (de) * 1992-11-16 1996-01-25 Gutehoffnungshuette Man Brennkammergehäuse einer Gasturbine
DE4328294A1 (de) * 1993-08-23 1995-03-02 Abb Management Ag Verfahren zur Kühlung eines Bauteils sowie Vorrichtung zur Durchführung des Verfahrens
EP1001224B1 (fr) * 1998-11-12 2006-03-22 Mitsubishi Heavy Industries, Ltd. Chambre de combustion pour une turbine à gaz
US6412268B1 (en) * 2000-04-06 2002-07-02 General Electric Company Cooling air recycling for gas turbine transition duct end frame and related method
DE10064264B4 (de) * 2000-12-22 2017-03-23 General Electric Technology Gmbh Anordnung zur Kühlung eines Bauteils
US7192244B2 (en) * 2004-02-23 2007-03-20 Grande Iii Salvatore F Bladeless conical radial turbine and method
US20060010874A1 (en) * 2004-07-15 2006-01-19 Intile John C Cooling aft end of a combustion liner
US7685823B2 (en) * 2005-10-28 2010-03-30 Power Systems Mfg., Llc Airflow distribution to a low emissions combustor
FR2893389B1 (fr) * 2005-11-15 2008-02-08 Snecma Sa Paroi transversale de chambre de combustion munie de trous de multiperforation
US7870739B2 (en) * 2006-02-02 2011-01-18 Siemens Energy, Inc. Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions
US9097117B2 (en) * 2010-11-15 2015-08-04 Siemens Energy, Inc Turbine transition component formed from an air-cooled multi-layer outer panel for use in a gas turbine engine
US9133721B2 (en) * 2010-11-15 2015-09-15 Siemens Energy, Inc. Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine
US20140208756A1 (en) * 2013-01-30 2014-07-31 Alstom Technology Ltd. System For Reducing Combustion Noise And Improving Cooling
US9163837B2 (en) 2013-02-27 2015-10-20 Siemens Aktiengesellschaft Flow conditioner in a combustor of a gas turbine engine
CN104296160A (zh) * 2014-09-22 2015-01-21 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种具有冷却功能的燃气轮机燃烧室的导流衬套
US10139109B2 (en) * 2016-01-07 2018-11-27 Siemens Energy, Inc. Can-annular combustor burner with non-uniform airflow mitigation flow conditioner
US20180087443A1 (en) * 2016-09-01 2018-03-29 Additive Rocket Corporation Additive manufactured combustion engine
US10774664B2 (en) * 2017-06-08 2020-09-15 General Electric Company Plenum for cooling turbine flowpath components and blades

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB637223A (en) * 1946-01-29 1950-05-17 Gen Electric Improvements in and relating to combustion units particularly for use in gas turbinesystems
US2541170A (en) * 1946-07-08 1951-02-13 Kellogg M W Co Air intake arrangement for air jacketed combustion chambers
US2669090A (en) * 1951-01-13 1954-02-16 Lanova Corp Combustion chamber
US2692478A (en) * 1951-02-24 1954-10-26 Boeing Co Turbine burner incorporating removable burner liner
US2745250A (en) * 1952-09-26 1956-05-15 Gen Electric Reverse vortex combustion chamber
GB736635A (en) * 1953-06-25 1955-09-14 Lucas Industries Ltd Liquid fuel combustion apparatus
DE1123868B (de) * 1958-08-26 1962-02-15 Schweizerische Lokomotiv Brennkammer, insbesondere fuer Gasturbinen
DE1224095B (de) * 1962-07-24 1966-09-01 Prvni Brnenska Strojirna Zd Y Gasturbinen-Brennkammer
US3485442A (en) * 1965-09-13 1969-12-23 Caterpillar Tractor Co Gas turbine engines
US3368604A (en) * 1966-06-14 1968-02-13 American Air Filter Co Combustion apparatus
DE2845588A1 (de) * 1978-10-19 1980-04-24 Motoren Turbinen Union Brennkammer fuer gasturbinentriebwerke
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
JPH0752014B2 (ja) * 1986-03-20 1995-06-05 株式会社日立製作所 ガスタ−ビン燃焼器
DE3640894C2 (de) * 1986-11-29 1997-05-28 Klein Schanzlin & Becker Ag Einlaufgehäuse für Kreiselpumpe
CA1309873C (fr) * 1987-04-01 1992-11-10 Graham P. Butt Methode de refroidissement par connection forcee du conduit de transition d'uneturbine a gaz

Also Published As

Publication number Publication date
DE59300530D1 (de) 1995-10-05
DE4222391C2 (de) 1995-04-20
DK0578048T3 (da) 1995-12-04
CA2099926A1 (fr) 1994-01-09
DE4222391A1 (de) 1994-01-20
EP0578048A1 (fr) 1994-01-12
ATE127209T1 (de) 1995-09-15
CA2099926C (fr) 2001-02-20
US5363653A (en) 1994-11-15

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