EP3333484B1 - Bardeau de chambre de combustion d'une turbine à gaz - Google Patents

Bardeau de chambre de combustion d'une turbine à gaz Download PDF

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Publication number
EP3333484B1
EP3333484B1 EP17205686.3A EP17205686A EP3333484B1 EP 3333484 B1 EP3333484 B1 EP 3333484B1 EP 17205686 A EP17205686 A EP 17205686A EP 3333484 B1 EP3333484 B1 EP 3333484B1
Authority
EP
European Patent Office
Prior art keywords
cooling air
edge strip
combustion chamber
recess
main body
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.)
Active
Application number
EP17205686.3A
Other languages
German (de)
English (en)
Other versions
EP3333484A1 (fr
Inventor
Dr. Kay HEINZE
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 Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3333484A1 publication Critical patent/EP3333484A1/fr
Application granted granted Critical
Publication of EP3333484B1 publication Critical patent/EP3333484B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • 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

Definitions

  • the combustion chamber shingle has a base body on which at least one edge area is provided.
  • This edge area is designed in the form of an edge strip which extends essentially to the surface of the base body.
  • the edge strip has a thickness which differs from the thickness of the base body.
  • the edge strip is usually designed with a greater thickness than the base body itself.
  • the plate-shaped component according to the invention can be optimized with regard to cooling.
  • the additive manufacturing process makes it possible to design the cooling holes differently over their length, for example to change the cross section. All of this means that a sufficient volume of cooling air can be directed to the rear side of the base body of the plate-shaped component opposite the edge strip.
  • the possibility of making the cooling holes variable in their longitudinal extent also makes it possible to implement curved or coiled or meandering shapes of cooling air holes. This leads to more effective cooling.
  • the recess is formed symmetrically to the central plane of the cooling air hole. This results in uniform stress distributions in the area of the recess and the adjacent areas of the support body. Furthermore, the supply of the cooling air into the cooling air hole is optimized.
  • An edge strip 2 which has a thickness d2, is formed in one piece with it on the edge region of the base body 1.
  • the thickness d1 is measured from the surface 6 of the base body 1 to its rear side.
  • the thickness d2 of the edge strip 2 is defined in the same direction.
  • Both the straight-line wall courses 7 with the lengths l1 and l2 and the rounded wall courses 8 with the radii r1 and r2 are not absolutely necessary for the invention; other wall courses can also be realized in order to form the recess 4.
  • the lengths l1 and l2 as well as the radii r1 and r2 can differ from one another in the specified intervals. It is also not absolutely necessary for the recess 4 to be arranged symmetrically with respect to a central plane of the cooling air hole 5.
  • the component according to the invention is usually produced by an additive method with the base body 1 being aligned vertically. If this is provided with an edge strip on all sides, an edge strip with the thickness d2 is first built up. The transition to the base body 1 with a thickness d1 takes place continuously through the respective support body 3, which is provided with the recesses 4.

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)

Claims (11)

  1. Bardeau de chambre de combustion d'une turbine à gaz comprenant un corps de base (1), qui est pourvu d'un seul tenant, au niveau d'au moins une zone de bord, d'un rebord (2) configuré sensiblement perpendiculaire par rapport à la surface du corps de base (1), le corps de base (1) présentant une épaisseur (d1) différente de celle du rebord (2), un corps d'appui (3) ayant une section transversale sensiblement triangulaire et relié d'un seul tenant avec le corps de base (1) et le rebord (2) étant disposé entre le rebord (2) et le corps de base (1), caractérisé en ce que le corps d'appui (3) est pourvu de plusieurs cavités (4) en forme de fentes, la cavité (4) présentant des deux côtés un tracé de paroi rectiligne (7) adjacent à la surface (6) du corps de base (1), lequel se transforme en un tracé de paroi arrondi (8) en vue de former une structure de type ogive.
  2. Bardeau de chambre de combustion selon la revendication 1, caractérisé en ce qu'un trou à air de refroidissement (5) qui traverse le corps de base est respectivement disposé dans les cavités (4) en forme de fentes.
  3. Bardeau de chambre de combustion selon l'une des revendications précédentes, comprenant en outre des trous à air de refroidissement supplémentaires (15) qui suivent un tracé depuis la cavité (4) à travers le rebord (2).
  4. Bardeau de chambre de combustion selon la revendication 3, caractérisé en ce que les trous à air de refroidissement supplémentaires (15) possèdent une section transversale qui s'élargit dans le sens de l'écoulement à travers les trous à air de refroidissement supplémentaires (15), notamment qui s'élargit de manière conique.
  5. Bardeau de chambre de combustion selon la revendication 4, la section transversale la plus petite des trous à air de refroidissement supplémentaires (15) se trouvant à l'entrée dans le rebord (2) ou voisine de l'entrée dans le rebord (2).
  6. Bardeau de chambre de combustion selon l'une des revendications précédentes, caractérisé en ce que la cavité (4) est de configuration asymétrique par rapport au plan central du trou à air de refroidissement (5).
  7. Bardeau de chambre de combustion selon l'une des revendications précédentes, caractérisé en ce que l'écart (a) entre les cavités (4) voisines dans le sens longitudinal du rebord (2) est a ≥ l3 x 0,5, l3 étant la largeur de la cavité (4).
  8. Bardeau de chambre de combustion selon l'une des revendications 1 et 7, caractérisé en ce que le tracé de paroi arrondi (8) présente un rayon (r1, r2) qui est compris entre 0,1 et 2 fois, notamment entre 1 et 2 fois la largeur (l3) de la cavité (4).
  9. Bardeau de chambre de combustion selon l'une des revendications précédentes, caractérisé en ce que les tracés de paroi arrondis (8) forment un angle (a) entre 45° et 120°.
  10. Bardeau de chambre de combustion selon l'une des revendications précédentes, caractérisé en ce que le corps d'appui (3) présente un angle (β) entre 30° et 60°, de préférence de 45°, par rapport à la surface (6) du corps de base (1).
  11. Bardeau de chambre de combustion selon l'une des revendications 2 à 10, caractérisé en ce que l'axe central (9) du trou à air de refroidissement (5) est configuré perpendiculaire ou avec un angle obtus par rapport à la surface (6) du corps de base (1).
EP17205686.3A 2016-12-09 2017-12-06 Bardeau de chambre de combustion d'une turbine à gaz Active EP3333484B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016224632.1A DE102016224632A1 (de) 2016-12-09 2016-12-09 Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung

Publications (2)

Publication Number Publication Date
EP3333484A1 EP3333484A1 (fr) 2018-06-13
EP3333484B1 true EP3333484B1 (fr) 2020-07-22

Family

ID=60654704

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17205686.3A Active EP3333484B1 (fr) 2016-12-09 2017-12-06 Bardeau de chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US10753612B2 (fr)
EP (1) EP3333484B1 (fr)
DE (1) DE102016224632A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3980692B1 (fr) * 2019-06-07 2024-10-23 Safran Helicopter Engines Procédé de fabrication d'un tube à flamme pour une turbomachine
FR3097029B1 (fr) * 2019-06-07 2021-05-21 Safran Helicopter Engines Procédé de fabrication d’un tube à flamme pour une turbomachine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4622821A (en) * 1985-01-07 1986-11-18 United Technologies Corporation Combustion liner for a gas turbine engine
FR2668246B1 (fr) * 1990-10-17 1994-12-09 Snecma Chambre de combustion munie d'un dispositif de refroidissement de sa paroi.
US6032457A (en) * 1996-06-27 2000-03-07 United Technologies Corporation Fuel nozzle guide
EP1022437A1 (fr) 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Elément de construction à l'usage d'une machine thermique
US6609891B2 (en) * 2001-08-30 2003-08-26 General Electric Company Turbine airfoil for gas turbine engine
US6792757B2 (en) * 2002-11-05 2004-09-21 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle
US7270514B2 (en) * 2004-10-21 2007-09-18 General Electric Company Turbine blade tip squealer and rebuild method
EP1672281A1 (fr) 2004-12-16 2006-06-21 Siemens Aktiengesellschaft Elément de protection thermique
US7681398B2 (en) * 2006-11-17 2010-03-23 Pratt & Whitney Canada Corp. Combustor liner and heat shield assembly
DE102007018061A1 (de) * 2007-04-17 2008-10-23 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand
US7665306B2 (en) * 2007-06-22 2010-02-23 Honeywell International Inc. Heat shields for use in combustors
EP2182285A1 (fr) * 2008-10-29 2010-05-05 Siemens Aktiengesellschaft Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
US7980821B1 (en) * 2008-12-15 2011-07-19 Florida Turbine Technologies, Inc. Turbine blade with trailing edge cooling
US20130333388A1 (en) * 2012-06-13 2013-12-19 General Electric Company Combustor liner cooling assembly for a gas turbine system
DE102012022259A1 (de) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine sowie Verfahren zu deren Herstellung
EP2941543B1 (fr) * 2013-03-13 2017-03-22 Rolls-Royce Corporation Agencement de trou de refroidissement à tranchée pour une ailette composite à matrice céramique
WO2015112220A2 (fr) * 2013-11-04 2015-07-30 United Technologies Corporation Bouclier thermique pour chambre de combustion de moteur à turbine doté d'un ou de plusieurs éléments de refroidissement
US10190773B2 (en) 2013-11-05 2019-01-29 United Technologies Corporation Attachment stud on a combustor floatwall panel with internal cooling holes
DE102013223258A1 (de) * 2013-11-14 2015-06-03 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerhitzeabschirmelement einer Gasturbine
DE102014204472A1 (de) * 2014-03-11 2015-09-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine
EP2927592A1 (fr) * 2014-03-31 2015-10-07 Siemens Aktiengesellschaft Élément de bouclier thermique, bouclier thermique et turbomachine
US10041675B2 (en) * 2014-06-04 2018-08-07 Pratt & Whitney Canada Corp. Multiple ventilated rails for sealing of combustor heat shields
DE102014214981B3 (de) * 2014-07-30 2015-12-24 Siemens Aktiengesellschaft Seitenbeschichtetes Hitzeschildelement mit Prallkühlung an Freiflächen
DE102014221225A1 (de) * 2014-10-20 2016-04-21 Siemens Aktiengesellschaft Hitzeschildelement und Verfahren zu seiner Herstellung
DE102015202570A1 (de) * 2015-02-12 2016-08-18 Rolls-Royce Deutschland Ltd & Co Kg Abdichtung eines Randspalts zwischen Effusionsschindeln einer Gasturbinenbrennkammer

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Title
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Also Published As

Publication number Publication date
EP3333484A1 (fr) 2018-06-13
US20180163964A1 (en) 2018-06-14
US10753612B2 (en) 2020-08-25
DE102016224632A1 (de) 2018-06-14

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