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EP2770260B1 - Chambre de combustion de turbine à gaz avec bardeau à refroidissement par impact effusion - Google Patents

Chambre de combustion de turbine à gaz avec bardeau à refroidissement par impact effusion Download PDF

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Publication number
EP2770260B1
EP2770260B1 EP14156300.7A EP14156300A EP2770260B1 EP 2770260 B1 EP2770260 B1 EP 2770260B1 EP 14156300 A EP14156300 A EP 14156300A EP 2770260 B1 EP2770260 B1 EP 2770260B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
shingle
turbine combustion
gas
effusion
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.)
Not-in-force
Application number
EP14156300.7A
Other languages
German (de)
English (en)
Other versions
EP2770260A3 (fr
EP2770260A2 (fr
Inventor
Dr.-Ing. Miklós Gerendas
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 EP2770260A2 publication Critical patent/EP2770260A2/fr
Publication of EP2770260A3 publication Critical patent/EP2770260A3/fr
Application granted granted Critical
Publication of EP2770260B1 publication Critical patent/EP2770260B1/fr
Not-in-force 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
    • 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
    • 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
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling

Definitions

  • the invention relates to a gas turbine combustor according to the preamble of claim 1.
  • the invention relates to a gas turbine combustor having a combustor wall.
  • a gas turbine combustor having a combustor wall.
  • impingement cooling holes through which cooling air is passed, which impinges on the arranged at a distance from the shingle support wall or surface of the shingle. The air is then passed through effusion holes of the shingle to effect cooling of the surface of the shingle.
  • the GB 2 087 065 A discloses an impingement cooling configuration with a clipped shingle, wherein each individual impingement cooling jet is protected from upstream flow by an upstream fin on the shingle. Furthermore, the pins or ribs increase the area available for heat transfer.
  • the GB 2 360 086 A shows a baffle cooling configuration with hexagonal ribs and partly additional prisms centrally located within the hexagonal ribs to increase the heat transfer.
  • the WO 95/25932 A1 discloses a combustion chamber wall in which ribs are provided on the cooling air side into which the effusion bores are introduced at a shallow angle.
  • the US 6,408,620 A describes a combustion chamber wall, which is equipped with donated shingles, in the additional effusion holes are introduced at a low angle to the surface.
  • the US 5,000,005 A shows a heat shield for a combustion chamber, which identifies cooling holes, which are designed at a shallow angle to the surface and expanding in the flow direction.
  • the WO 92/16798 A1 uses only a flat surface as the target of impingement cooling. An attachment of ribs would bring little except the simple increase in the area, since the ribs, such as in GB 2 360 086 A are shown to require an overflow to take effect. Due to the congruence of impingement cooling air supply and removal of the air through the effusion bores, however, there is no appreciable speed in the upper flow of the ribs. In part, the pressure difference across the shingle is reduced by the torch swirl so that no effective flow through the effusion holes takes place more or even threatens hot gas burglary in the impingement cooling chamber of the shingle.
  • GB 2 087 065 A and GB 360 086 A contain no technical teaching on the renewal of the cooling film on the hot gas side within the Extension of the shingle.
  • the shingle must be made so short in the flow direction that the cooling film generated by the upstream shingle over the entire length of the shingle carries. This forces a multitude of shingles along the combustion chamber wall and does not allow to cover this distance with a single shingle.
  • the WO 95/25932 A1 describes a single-walled combustion chamber construction in which no impingement cooling takes place on the cooling air side, but only convection cooling.
  • the US 6,408,628 A shows a combustion chamber wall in which the pressure difference across the shingle can be fully optimized neither for convective cooling, since they prefer a large pressure difference, nor for the Effusionkühlung, as they prefer a small pressure difference to improve the film cooling.
  • the US 5,000,005 A relates to a heat shield for a combustion chamber, which is provided with expanding in the flow direction cooling holes, without going into the geometric relationship of impingement cooling holes and diffusive effusion holes.
  • Effusion cooling holes arranged at an angle are also available from the EP 1 983 265 A2 previously known.
  • the arrangement of these effusion cooling holes is separated from the areas of the combustion chamber wall in which impingement cooling holes are provided.
  • the JP S58 72822 A discloses a double-walled combustion chamber in which impingement cooling holes and effusion cooling holes are provided alternately.
  • the invention has for its object to provide a gas turbine combustor, which allows a simple design and simple, cost manufacturability highly efficient cooling.
  • a construction in which shingles are mounted at a distance on a shingle support.
  • the shingles can be fixed, for example by means of threaded bolts or the like.
  • the shingle support has impingement cooling holes, through which the cooling air is passed, in order to impinge on the side of the shingle facing away from the combustion chamber and facing the shingle support. This will cool the shingle.
  • the shingles have effusion holes, through which the air can escape from the gap between the shingle support and the shingle (baffle cooling gap). The exiting through the effusion holes air is the film cooling of the shingle.
  • the inlet openings of the effusion holes are formed on raised portions of a surface structure of the shingle.
  • the raised areas are designed as ribs. It is important in the context of the invention that the inlet openings of the effusion holes have a distance from the surface of the shingle and are thus arranged closer to the surface of the shingle support. This leads to more favorable flow conditions and better heat transfer.
  • the inlet opening has a distance from the surface of the shingle support, which is 0.5 to 1.5 of the diameter of the inlet opening. This leads to a particularly efficient air flow and inflow into the inlet opening of the respective effusion hole.
  • the central axis of the inlet openings and thus the central axis of the at least first region of the effusion hole is arranged substantially perpendicular to the surface of the shingle carrier and parallel oriented to the central axis of the baffle hole. This leads to an improved flow guidance.
  • Another measure to ensure the inflow into the inlet openings during operation with thermally induced distortion is to provide at least one spacer adjacent to the inlet opening. This prevents thermal distortion that the effusion hole can be closed by the shingle support. This spacer can also partially enclose the inlet opening. It can also be designed so that it is designed to form a twist of the air flowing into the inlet opening.
  • the effusion hole may be straight or curved or partly straight and partly curved. It can be provided with a constant or with an expanding cross-section.
  • the surface structure in the form of cells which are triangular, quadrangular or polygonal.
  • the surface structure may also be provided in the form of a circular depression.
  • the impingement cooling jets of the air jets emerging from the impingement cooling holes can be directed to the center of these cells or recesses to improve the flow conditions.
  • it may also be provided to provide a prism or similar configuration within these cells in order to distribute the air evenly.
  • 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 solidifies a circumferentially extending arrangement stationary stator vanes 20, which are generally referred to as stator blades and which project radially inwardly from the engine housing 21 in an annular flow channel through the compressors 13, 14.
  • 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 vanes 22 disposed 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 schematic representation of a cross section of a gas turbine combustor according to the prior art.
  • compressor outlet blades 101 and a combustion chamber outer housing 102 and a combustion chamber inner housing 103 are shown schematically.
  • the reference numeral 104 denotes a burner with arm and head
  • the reference numeral 105 denotes a combustion chamber head, which is followed by a combustion chamber wall 106, through which the flow to turbine inlet blades 107 is passed.
  • the Fig. 3 shows the construction of a known from the prior art construction.
  • a shingle support 109 is shown in sectional view, which may be identical to the combustion chamber wall 106 or may be formed as a separate component.
  • the shingle support 109 is provided with a plurality of impingement cooling holes 108, the axes 133 of which are arranged perpendicular to the center plane or to the surfaces of the plate-shaped shingle support 109. Cooling air flows into an impingement cooling gap 114 through the impingement cooling holes 108. This is formed by the spaced arrangement of a shingle 110.
  • the shingle 110 is by means of threaded bolts 115 and nuts 131 attached.
  • the shingle 110 further has effusion holes 111, through which the cooling air for cooling the surface flows out by means of a cooling film.
  • the reference numeral 112 denotes the cooling air flow, while the reference numeral 113 shows the hot gas flow.
  • the Fig. 4 shows a further illustration of a shingle according to the prior art.
  • this has on its the shingle support side facing a surface structure 116 and 117, which may be in the form of ribs or singular elevations.
  • prisms 119 are formed to distribute the exiting cooling air.
  • the surface structure may also be formed by depressions 118.
  • the Fig. 5 shows a schematic plan view, analog Fig. 4 , It follows that the effusion holes 111 have an inlet opening 120 through which the cooling air flows. From the Fig. 5 It can be seen that the inlet openings are arranged in the prior art on the flanks of the prism 119 or in the region of the recess 118.
  • the Fig. 6 shows an embodiment of the invention.
  • the shingle support 109 has, as in the prior art, a plurality of impingement cooling holes 108. These are arranged so that they preferably impinge on the tips 121 of the prisms 119.
  • the inlet openings 120 of the effusion holes 111 are formed on the raised areas of the surface structure 116, 117. These raised portions are formed in the form of ribs as known in the art.
  • the Fig. 6 further shows that the effusion holes 111 may be formed straight or angled.
  • the cross section can remain constant or expand. It is also possible to form the effusion holes 111 bent.
  • the right half of the picture Fig. 6 shows an enlarged curved cross section 129, next to a constant curved cross section 128.
  • the cross section 127 is formed in sections straight and enlarged.
  • the cross section 126 is straight trained and expanded in the second section.
  • the cross section 125 is angled and each has a constant cross section.
  • the cross section 124 is straight and has a constant cross section.
  • the reference numeral 132 shows the central axis of the entrance opening 120 and the adjacent area of the effusion hole 111, respectively.
  • FIGS. 7 and 8 each show plan views of variants not according to the invention. It follows that the inlet openings 120 are respectively arranged on the raised areas of the surface structures 116, 117 or adjacent depressions 118.
  • the reference numeral 122 shows a hexagonal structure or cell, the reference numeral 123 shows a prism.
  • Fig. 9 and 10 each show enlarged side views of further embodiments, in which adjacent to the inlet opening 120 spacers 130 are provided. These can, as in particular in Fig. 10 shown to be provided for the formation of a twist.
  • the effusion holes 111 may have a constant 124, 125, 128, or a flow-increasing cross-section 126, 127, 129.
  • the effusion holes may have a continuous straight axis 124, 126, a sectionally straight axis 125, 127 or an arcuate axis 28, 29.
  • the extended outlet cross section is performed at a smaller angle than 90 ° to the surface.
  • the spacers 130 are due to tolerances usually not in contact with the shingle support, otherwise they could be longer depending on the tolerance position than the shingle edge high, and thus they could provide an increase in edge leakage.
  • the spacers 130 may be configured to swirl the air flowing into the effusion hole 111 in front of the entrance port 120.
  • the surface structure 116, 117 is in the form of (hexagonal) ribs, these can be filled with a prism 119, 123, so that the tip 121 of the prism 119, 123 is at the level of the ribs or above or below.
  • On the hot gas side facing the shingle 110 may have a thermal barrier coating of ceramic material.
  • the impingement cooling holes 108 may vary in diameter in the axial and / or circumferential direction, as well as the effusion holes 111 and the dimensions of the surface structure 116, 117.
  • the impingement cooling holes 108 are aligned substantially perpendicular to the impingement cooling surface and the main flow directions of cooling air 112 and hot gas 113.
  • the placement of the inlet opening 120 of the effusion holes 111 on the raised areas of the surface structure 116, 117 increases the length of the effusion holes 111 and thus their total surface area and also the amount of heat transferred.
  • the wall normal velocity of the outflowing air can be reduced by the curvature of the axis 132 or by the widening of the flow channel (or both) and, despite the small entrance surface 120 of the effusion hole 111 good film cooling effect.

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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)

Claims (8)

  1. Chambre de combustion de turbine à gaz avec une paroi de chambre de combustion (106) comprenant un support de bardeaux (109) sur laquelle sont logés à une certaine distance des bardeaux (110) afin de former une fente de refroidissement par impact (114), sachant que le support de bardeaux (109) présente des trous de refroidissement par impact (108) et que le bardeau (110) est muni de trous d'effusion (111), que sur sa face orientée vers le support de bardeaux (109), le bardeau (110) est doté d'une structure superficielle (116, 117) qui s'étend en relief sur la surface du bardeau (110) en direction du support de bardeaux (109), que les ouvertures d'entrée (120) des trous d'effusion (111) se trouvent sur des zones en relief de la structure superficielle (116, 117), caractérisée en ce qu'un axe centrique (132) de l'ouverture d'entrée (120) est sensiblement perpendiculaire à la surface du support de bardeaux (109) et qu'un axe centrique (132) de l'ouverture d'entrée (120) est sensiblement parallèle à l'axe centrique (133) du trou de refroidissement par impact (108), et que les zones en relief sont conçues sous forme de nervures.
  2. Chambre de combustion de turbine à gaz selon la revendication n° 1, caractérisée en ce que la distance des ouvertures d'entrée (120) à la surface du support de bardeaux (109) a une valeur comprise entre 0,5 et 1,5 fois la valeur du diamètre de l'ouverture d'entrée (120).
  3. Chambre de combustion de turbine à gaz selon une des revendications n° 1 ou n° 2, caractérisée en ce qu'une entretoise (130) est disposée autour de l'ouverture d'entrée (120) en entourant partiellement cette dernière.
  4. Chambre de combustion de turbine à gaz selon une des revendications n° 1 à n° 3, caractérisée en ce qu'une entretoise (130) est disposée au voisinage de l'ouverture d'entrée (120).
  5. Chambre de combustion de turbine à gaz selon une des revendications n° 1 à n° 4, caractérisée en ce que le trou d'effusion (111) est formé de manière rectiligne ou curviligne ou partiellement rectiligne ou partiellement curviligne.
  6. Chambre de combustion de turbine à gaz selon une des revendications n° 1 à n° 5, caractérisée en ce que le trou d'effusion (111) présente un diamètre constant ou s'évasant.
  7. Chambre de combustion de turbine à gaz selon une des revendications n° 3 à n° 6, caractérisée en ce que l'entretoise (130) est conçue pour former un tourbillonnement de l'air affluant dans l'ouverture d'entrée (120).
  8. Chambre de combustion de turbine à gaz selon une des revendications n° 1 à n° 7, caractérisée en ce que la structure superficielle (116, 117) est en outre conçue avec formation de cellules polygonales (122), en particulier avec disposition d'un prisme (119, 123) à l'intérieur de la cellule (122).
EP14156300.7A 2013-02-26 2014-02-24 Chambre de combustion de turbine à gaz avec bardeau à refroidissement par impact effusion Not-in-force EP2770260B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013003444.2A DE102013003444A1 (de) 2013-02-26 2013-02-26 Prall-effusionsgekühlte Schindel einer Gasturbinenbrennkammer mit verlängerten Effusionsbohrungen

Publications (3)

Publication Number Publication Date
EP2770260A2 EP2770260A2 (fr) 2014-08-27
EP2770260A3 EP2770260A3 (fr) 2015-09-30
EP2770260B1 true EP2770260B1 (fr) 2016-05-18

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EP14156300.7A Not-in-force EP2770260B1 (fr) 2013-02-26 2014-02-24 Chambre de combustion de turbine à gaz avec bardeau à refroidissement par impact effusion

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Country Link
US (1) US9518738B2 (fr)
EP (1) EP2770260B1 (fr)
DE (1) DE102013003444A1 (fr)

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CN118361754A (zh) 2023-01-19 2024-07-19 通用电气公司 用于燃气涡轮的燃烧器的圆顶-导流器组件

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Also Published As

Publication number Publication date
DE102013003444A1 (de) 2014-09-11
US20140238030A1 (en) 2014-08-28
EP2770260A3 (fr) 2015-09-30
US9518738B2 (en) 2016-12-13
EP2770260A2 (fr) 2014-08-27

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