EP2749816A2 - Procédé d'agencement de trous de refroidissement par impact et d'orifices d'effusion dans une paroi de chambre de combustion d'une turbine à gaz - Google Patents

Procédé d'agencement de trous de refroidissement par impact et d'orifices d'effusion dans une paroi de chambre de combustion d'une turbine à gaz Download PDF

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Publication number
EP2749816A2
EP2749816A2 EP13196228.4A EP13196228A EP2749816A2 EP 2749816 A2 EP2749816 A2 EP 2749816A2 EP 13196228 A EP13196228 A EP 13196228A EP 2749816 A2 EP2749816 A2 EP 2749816A2
Authority
EP
European Patent Office
Prior art keywords
holes
effusion
impingement cooling
combustion chamber
cooling holes
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Withdrawn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
EP13196228.4A
Other languages
German (de)
English (en)
Other versions
EP2749816A3 (fr
Inventor
Dr.-Ing. Miklós Gerendas
Maren Fanter
Volker Herzog
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 EP2749816A2 publication Critical patent/EP2749816A2/fr
Publication of EP2749816A3 publication Critical patent/EP2749816A3/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/02—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
    • 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
    • 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
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49231—I.C. [internal combustion] engine making

Definitions

  • the invention relates to a method for the arrangement of effusion holes and impingement cooling holes in a combustion chamber wall of a gas turbine according to the preamble of claim 1. More particularly, the invention relates to the arrangement and mutual association of the effusion holes and the impingement cooling holes in the combustion chamber wall and in this attached combustion chamber shingle. The invention also relates to a combustion chamber wall produced by the method.
  • cooling air flows through the combustion chamber shingle and lays as a film on the hot surface of the combustion chamber shingle to cool it and shield it from the hot combustion gases.
  • the WO 92/16798 A1 describes the construction of a gas turbine combustor by stud bolts attached metallic shingles, which leads by the combination of impingement and effusion cooling to an effective cooling effect and thus allows the reduction of the cooling air consumption.
  • the geometric relationship of the baffle to the effusion holes is not defined, each baffle hole is associated with an effusion hole.
  • the US Pat. No. 6,237,344 B1 describes a two-layer baffle effusion cooling using two sheets which are pushed in by on the cold side Bulges are kept at a defined distance.
  • a 1: 1 relationship of protrusions and impingement cooling holes is established because the protrusions are intended to protect the impingement cooling jets from the crossflow in the impingement cooling cavity.
  • a geometric relationship between baffle and effusion holes is not described.
  • the EP 1 104 871 B1 describes the relationship of a large impingement cooling hole to a group of effusion holes, for example 6 effusion holes, evenly spaced from a central seventh effusion hole, with the impingement cooling jet within the group impinging on the effusion wall.
  • the impingement cooling holes are arranged in staggered rows so as to form a uniform distance from the surrounding impingement cooling holes, thus forming an equilateral triangle therebetween, one side of the triangle being circumferentially aligned.
  • the US 5 758 504 A describes an impingement effusion pattern in which the impingement cooling holes are arranged in equilateral quadrilaterals on the combustion chamber wall with one diagonal of the square aligned circumferentially.
  • the effusion holes are arranged relative to the impingement cooling holes according to different principles (eg relative to the vertices of the square, but not in the middle).
  • the prior art shows design principles of cooling hole patterns, which may be arranged in different types and configurations.
  • hopping patterns are known, which may comprise two or more recesses.
  • the prior art also shows n-sided basic cells, for example triangular or square or square basic cells, one side or diagonal of the basic cell usually in the circumferential direction or in the axial direction of the combustion chamber (relative to a center axis of the combustion chamber) is aligned.
  • baffle jets directly hit an effusion hole and therefore do not actually bounce on the combustion chamber wall, but immediately flow away through the effusion hole. Then no stagnation point is formed on the combustion chamber wall. A high heat transfer at this point and thus the superior cooling effect thus remain.
  • the invention has for its object to provide a method for the arrangement of effusion holes and impingement cooling holes, which ensures a reliable design and reliable cooling of the combustion chamber shingles with a simple design and ease of use.
  • an n-hopping pattern is used on the effusion side so that the pattern repeats after n rows or columns
  • an m-side basic cell is used on the baffle cooling side for distributing the baffle cooling holes in such a way that the probability of a baffle hole directly to be placed over an effusion hole is minimized taking into account all construction and assembly tolerances.
  • a basic cell is defined here so that there is a cooling air hole in each corner of the basic cell.
  • the selected ground cell is then rotated in edge length and orientation with respect to the axial direction and the circumferential direction so that the likelihood of the overlap is minimized despite the component and assembly tolerances. If the number of overlaps for the selected basic cell is still too high, or if the hits are too close to each other, a basic cell with a higher or lower number of corners is selected and the optimization is repeated.
  • the same method according to the invention can also be used with an arrangement of the effusion holes on an n-corner basic pattern.
  • An advantageous robust arrangement according to the method of the invention is also characterized in that the number of effusion holes is not an even multiple of the number of impingement cooling holes.
  • the inventive method for selecting a non-related pattern between impact and effusion holes can be applied to impact-cooled shingles, but also to other two-walled cooling schemes, for example, two layers of sheet metal.
  • the impact cooling effect is utilized to a great extent even with wide component and assembly tolerances and thus ensures a high cooling effect and thus a long component service life. Due to the wide tolerances, the component costs are reduced and it nevertheless creates a robust product.
  • the impingement cooling holes are distributed according to another rule than the effusion holes, wherein a fixed geometric relationship of impingement cooling holes and effusion holes is avoided.
  • the invention also relates to a combustion chamber wall, which is formed according to the method according to the invention. It should be noted in particular that at least on a part of the combustion chamber wall, the impingement cooling holes, while avoiding a fixed geometric relationship between the impingement cooling holes and the effusion cooling holes, are distributed according to another rule than the effusion holes.
  • the gas turbine engine 10 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and a Exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate pressure compressor 13 and the high pressure compressor 14 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, that radially inwardly from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the blades 22 arranged thereon and the turbine rotor hub 27 and the Turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 shows a simplified sectional view according to the prior art, which shows a combustion chamber wall 29, which is provided with a plurality of impingement cooling holes 31.
  • combustion chamber shingles 30 are arranged, which are provided with effusion holes 32.
  • the combustion chamber shingles 30 are fastened in a conventional manner by means of bolts 33 to the combustion chamber wall 29 (shingle carrier) so that a gap 34 results, through which the cooling air in the manner shown can flow from the impingement cooling holes 31 to the effusion holes 32.
  • the 3 and 4 each show the assignment of impingement cooling holes 31 to effusion holes 32.
  • the impingement cooling holes 31 are shown as asterisks, while the effusion holes are shown as an ellipse. This embodiment does not have to correspond to the realized hole formation, it has been selected only to clarify the figures.
  • the Fig. 3 shows a structurally provided arrangement according to a construction drawing. It can be seen that the impingement cooling holes 31 and the effusion holes 32 are arranged on a line grid and each, with respect to their centers, evenly spaced from each other.
  • the Fig. 4 shows the arrangement according to Fig. 3 in the real design with component tolerances and mounting tolerances. It can be seen that the impingement cooling holes 31 are shifted from the arrangement of the effusion holes 32 so that the impingement cooling holes 31 partially overlap the effusion holes 32, so that sufficient impingement cooling can not take place. Furthermore, the flow through the effusion holes 32 is changed by the direct cooling air.
  • the Fig. 5 shows an inventive embodiment according to the inventive method. It follows that the impingement cooling holes 31 are provided in a different arrangement to the uniform arrangement of the effusion holes 32. According to the invention, the assignment takes place in such a way that in the case of Fig. 6 shown real arrangement, taking into account the component tolerance and the mounting tolerance all or almost all impingement cooling holes 31 are placed so that the air flow does not or only insignificantly hits the effusion holes 32. This results in the advantages described in the invention, so that a reliable and reliable cooling is guaranteed.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13196228.4A 2012-12-27 2013-12-09 Procédé d'agencement de trous de refroidissement par impact et d'orifices d'effusion dans une paroi de chambre de combustion d'une turbine à gaz Withdrawn EP2749816A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102012025375.3A DE102012025375A1 (de) 2012-12-27 2012-12-27 Verfahren zur Anordnung von Prallkühllöchern und Effusionslöchern in einer Brennkammerwand einer Gasturbine

Publications (2)

Publication Number Publication Date
EP2749816A2 true EP2749816A2 (fr) 2014-07-02
EP2749816A3 EP2749816A3 (fr) 2017-07-26

Family

ID=49726617

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13196228.4A Withdrawn EP2749816A3 (fr) 2012-12-27 2013-12-09 Procédé d'agencement de trous de refroidissement par impact et d'orifices d'effusion dans une paroi de chambre de combustion d'une turbine à gaz

Country Status (3)

Country Link
US (1) US20140290258A1 (fr)
EP (1) EP2749816A3 (fr)
DE (1) DE102012025375A1 (fr)

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* Cited by examiner, † Cited by third party
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EP3015770B1 (fr) * 2014-11-03 2020-07-01 Ansaldo Energia Switzerland AG Chambre de combustion de caisson
US10386067B2 (en) * 2016-09-15 2019-08-20 United Technologies Corporation Wall panel assembly for a gas turbine engine
US10295190B2 (en) 2016-11-04 2019-05-21 General Electric Company Centerbody injector mini mixer fuel nozzle assembly
US10724740B2 (en) 2016-11-04 2020-07-28 General Electric Company Fuel nozzle assembly with impingement purge
US10393382B2 (en) 2016-11-04 2019-08-27 General Electric Company Multi-point injection mini mixing fuel nozzle assembly
US10352569B2 (en) 2016-11-04 2019-07-16 General Electric Company Multi-point centerbody injector mini mixing fuel nozzle assembly
US10465909B2 (en) 2016-11-04 2019-11-05 General Electric Company Mini mixing fuel nozzle assembly with mixing sleeve
DE102016222099A1 (de) * 2016-11-10 2018-05-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine
US10634353B2 (en) 2017-01-12 2020-04-28 General Electric Company Fuel nozzle assembly with micro channel cooling
US20180299126A1 (en) * 2017-04-18 2018-10-18 United Technologies Corporation Combustor liner panel end rail
US20180306113A1 (en) * 2017-04-19 2018-10-25 United Technologies Corporation Combustor liner panel end rail matching heat transfer features
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel
US10830435B2 (en) 2018-02-06 2020-11-10 Raytheon Technologies Corporation Diffusing hole for rail effusion
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
US11022307B2 (en) 2018-02-22 2021-06-01 Raytheon Technology Corporation Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
US10935245B2 (en) 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
US11286884B2 (en) 2018-12-12 2022-03-29 General Electric Company Combustion section and fuel injector assembly for a heat engine
US11073114B2 (en) 2018-12-12 2021-07-27 General Electric Company Fuel injector assembly for a heat engine
US11156360B2 (en) 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly
DE102019105442A1 (de) * 2019-03-04 2020-09-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung eines Triebwerksbauteils mit einer Kühlkanalanordnung und Triebwerksbauteil
US11959641B2 (en) 2020-01-31 2024-04-16 Rtx Corporation Combustor shell with shaped impingement holes
CN112963862A (zh) * 2021-04-07 2021-06-15 西北工业大学 一种双层菱形交叉冷却结构

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992016798A1 (fr) 1991-03-22 1992-10-01 Rolls-Royce Plc Bruleur de turbine a gaz
US5758504A (en) 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner
US6237344B1 (en) 1998-07-20 2001-05-29 General Electric Company Dimpled impingement baffle
EP1104871B1 (fr) 1999-12-01 2004-07-21 Alstom Power UK Ltd. Chambre de combustion pour une turbine à gaz

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4004056A (en) * 1975-07-24 1977-01-18 General Motors Corporation Porous laminated sheet
GB2049152B (en) * 1979-05-01 1983-05-18 Rolls Royce Perforate laminated material
US4302940A (en) * 1979-06-13 1981-12-01 General Motors Corporation Patterned porous laminated material
US6964170B2 (en) * 2003-04-28 2005-11-15 Pratt & Whitney Canada Corp. Noise reducing combustor
DE102007018061A1 (de) * 2007-04-17 2008-10-23 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand
US9145779B2 (en) * 2009-03-12 2015-09-29 United Technologies Corporation Cooling arrangement for a turbine engine component
GB0912715D0 (en) * 2009-07-22 2009-08-26 Rolls Royce Plc Cooling arrangement
GB201105790D0 (en) * 2011-04-06 2011-05-18 Rolls Royce Plc A cooled double walled article

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992016798A1 (fr) 1991-03-22 1992-10-01 Rolls-Royce Plc Bruleur de turbine a gaz
US5758504A (en) 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner
US6237344B1 (en) 1998-07-20 2001-05-29 General Electric Company Dimpled impingement baffle
EP1104871B1 (fr) 1999-12-01 2004-07-21 Alstom Power UK Ltd. Chambre de combustion pour une turbine à gaz

Also Published As

Publication number Publication date
EP2749816A3 (fr) 2017-07-26
DE102012025375A1 (de) 2014-07-17
US20140290258A1 (en) 2014-10-02

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