EP2154431B1 - Machine thermique - Google Patents

Machine thermique Download PDF

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Publication number
EP2154431B1
EP2154431B1 EP09167590.0A EP09167590A EP2154431B1 EP 2154431 B1 EP2154431 B1 EP 2154431B1 EP 09167590 A EP09167590 A EP 09167590A EP 2154431 B1 EP2154431 B1 EP 2154431B1
Authority
EP
European Patent Office
Prior art keywords
cooling
shells
parting plane
shroud segments
thermal machine
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
EP09167590.0A
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German (de)
English (en)
Other versions
EP2154431A3 (fr
EP2154431A2 (fr
Inventor
Remigi Tschuor
Hartmut Hähnle
Uwe Rüdel
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.)
General Electric Technology GmbH
Original Assignee
General Electric Technology GmbH
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Filing date
Publication date
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Publication of EP2154431A2 publication Critical patent/EP2154431A2/fr
Publication of EP2154431A3 publication Critical patent/EP2154431A3/fr
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Publication of EP2154431B1 publication Critical patent/EP2154431B1/fr
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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
    • F23R3/42—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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/00017—Assembling 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
    • F23R2900/00018—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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the present invention relates to the field of combustion technology. It relates to a thermal machine according to the preamble of claim 1.
  • IGT Modern industrial gas turbines
  • IGT are usually designed with annular combustion chambers.
  • Most smaller IGTs are designed as so-called "Can Annular Combustors".
  • An IGT with annular combustion chamber of the combustion chamber is limited by the side walls and the inlet and outlet plane of the hot gas.
  • Such a gas turbine is in the Fig. 1 and 2 shown.
  • the in the Fig. 1 and 2 Gas turbine 10 shown in the cutout has a turbine housing 11, in which a about an axis 27 rotating rotor 12th is housed.
  • the compressor 17 compresses air which flows into a plenum 14.
  • annular combustion chamber 15 is arranged, which is closed on the input side by a front plate cooling air 20 cooled front panel 19 and the output side is connected via a hot gas channel 25 with the input of the turbine 13 in connection.
  • EP599055 describes such a gas turbine.
  • burners 16 are arranged in a ring, which are designed for example as a double cone or EV burner and inject a fuel-air mixture into the combustion chamber 15.
  • the resulting during the combustion of the mixture hot air stream 26 passes through the hot gas channel 25 in the turbine 13 and is relaxed there under work.
  • the combustion chamber 15 with the hot gas channel 25 is outside with a distance surrounded by an outer and innerdehemd 21 and 31, which are fastened by means of fasteners 24 to the combustion chamber 15, 25 and between them and the combustion chamber 15, 25 each have a ring-shaped outer and inner Form cooling channel 22 and 32 respectively.
  • In the cooling channels 22, 32 flows in the opposite direction to the hot gas stream 26 cooling air on the walls of the combustion chamber 15, 25 along in a combustion chamber hood 18 and from there into the burner 16 and as a faceplate cooling air 20 directly into the combustion chamber 15th
  • the side walls of the combustion chamber 15, 25 are carried out either as shell elements or as solid shells (outer shell 23, inner shell 33).
  • a parting plane (29 in Fig. 2a ), which allows an upper half of the shell 23, 33 (upper half shell 33a in FIG Fig. 2a ) from the lower half (lower half-shell 33b in FIG Fig. 2a ), for example, to assemble or disassemble the gas turbine rotor 12.
  • the parting plane 29 has correspondingly two parting plane welding seams 30 (FIG. Fig.
  • the respective lower and upper half-shells 33a, 33b have to be cooled convectively.
  • the already mentioned cooling shirts (CoShirts) 21 and 31 are mounted on the half-shell cold side, which redirect ambient air and cause due to the combustion chamber pressure drop or burner pressure drop across the half-shells and thus cause a convective cooling.
  • the inner and outer shell 33 and 23 of a gas turbine such as the GT13E2 are thermally and mechanically stressed during operation.
  • the strength properties of the material of the shells 23, 33 are highly temperature dependent.
  • the shells 23, 33 are convectively cooled.
  • the shape and the high thermal load near the turbine inlet (hot gas channel 25) require, especially in this area a constant high heat transfer on the cooling air side. This is achieved in the outer shell 23 by impingement cooling.
  • space and flow conditions and a seal against a cross-flow for such an impingement cooling are not given. Therefore, a conventional convection cooling is resorted to, in which the intensity of the cooling is increased by reducing the channel height of the cooling channel 32.
  • the previously used configuration of the inner cooling sleeve 31 of 2 axial plates is on the one hand prone to distance tolerances and other irregularities, e.g. in the flow field before the cooling air inlet into the cooling channel, and on the other hand causes an undesirable reduction of the cooling air mass flow in the region of the smaller of the two axial plates.
  • the object is solved by the entirety of the features of claim 1.
  • Essential for the invention is that at least one of the cooling shirts on the Side on which the cooling air enters the cooling channel, to improve the Einström discipline has an outwardly curved, rounded leading edge.
  • the at least one cooling shirt in the region of the leading edge is flared bell-shaped or trumpet-like.
  • the inner cooling jacket on the side on which the cooling air emerges from the cooling channel to reduce the flow losses on an outwardly curved, rounded exit edge.
  • the cooling shirts are composed of individual, in the circumferential direction adjoiningdehemdsegmenten, wherein theharihemdsegmente are attached by means of distributed arranged fasteners to the associated shells.
  • a preferred development is characterized in that thedehemdsegmente overlap each other in pairs in the terminal areas, and that in each case adehemdsegment a pair is provided in the overlapping region with overlapping elements for a positive connection between the overlappingdehemdsegmenten.
  • the fastening elements are arranged in thedehemdsegmenten in the axial direction one behind the other, and that in the axial line with the fasteners additional holes are provided in thedehemdsegmenten, through which to improve the cooling cooling air in the rays from the outside flows into the respective cooling channel.
  • the combustion chamber is divided in a parting plane into an upper half with upper half shells and a lower half with lower half shells.
  • the half shells are interconnected in the parting plane by parting plane welds and have in the region of the parting plane welds deviating from the rotational symmetry shape.
  • the cooling shirts are adapted in the parting plane to the different shape of the shells.
  • the entirety of thedehemdsegmente in firstdehemdsegmente, which adjoin the parting plane, and seconddehemdsegmente, which are outside the parting plane, divided, wherein the firstdehemdsegmente to adapt to the different shape of the shells have a raised side edge.
  • Fig. 3 is shown in a side view of the part of an inner shell with segmented cooling shirt according to an embodiment of the invention.
  • an annular cooling channel 32 is formed on the outside of the inner shell 33 by a concentric inner cooling jacket 31 arranged concentrically therewith, in which on the in Fig. 3 Cooling air flows in on the left side, flows to the right and leaves the cooling channel 32 on the right side (see flow arrows in Fig. 3 ).
  • the innerdehemd 31 is composed of individual, extending in the axial directiondehemdsegmenten 34, which overlap each other. In the overlapping area, overlapping elements 36 protruding at the edges on the cooling-shirt segments are welded (see in particular FIG Fig. 7 ), which provide a positive fit between the overlapping segments in the overlap area.
  • Thedehemdsegmente 34 are distributed by means of fasteners 24 which pass through mounting holes 40 in the segments ( Fig. 5 . 6 and 8th ), attached to the associated inner shell 33.
  • the fastening elements 24 are arranged one behind the other in the axial direction.
  • additional holes 35 are provided in the cooling jacket segments 34 in the wake region of the fastening elements 24, flows through the air from the cooling air inlet. Due to its locally high velocity with respect to the incoming cooling air mass flow, the air jet entering the cooling channel 32 leads to an increase in the heat transfer coefficient and thus to a reduction in the wall temperature of the inner shell 33.
  • the inner cooling jacket 31 is flared bell-shaped or trumpet-like in the region of the leading edge 37.
  • This rounded "bellmouth-shaped" leading edge 37 of the axially one-piecede Kunststoffbleches allows on the one hand to minimize the pressure loss at the cooling air inlet and on the other an (unintended) variation of the heat transfer coefficient by detachment of the cooling air atdekanaleintritt (leading edge 37), as to Example of sharp-edged entries arise to prevent.
  • the achieved by the improved inflow conditions decreases the Verwirbelungsproe lead to a reduction of the required cooling air mass flow and thus to a more efficient operation of the combustion chamber.
  • the flow direction of the cooling air is opposite to the hot gas flow direction.
  • the inner shell cooling shirt or inner cooling shirt 31 is further designed so that at its outlet side (trailing edge 38) a new transition radius is selected, which causes a much more favorable, ie, lower, flow loss than the previous configuration.
  • the reduction in the flow loss at this point is compensated by a reduction in the cooling channel height, which in turn leads to an increase in the cooling air side heat transfer and thus leads to a reduction of the average material temperature of the inner shell 33.
  • the cooling jacket 31 recedes outward in the region of the parting plane weld seams 30 and creates space for a corresponding bulge of the combustion chamber shell 33 in the region of the parting plane weld seam 39.

Claims (7)

  1. Machine thermique, en particulier turbine à gaz (10), qui comprend une chambre de combustion annulaire (15, 25) délimitée vers l'extérieur par une coquille extérieure (23) et une coquille intérieure (33), à travers laquelle un courant de gaz chaud (26) s'écoule en direction axiale, dans laquelle la coquille extérieure (23) et la coquille intérieure (33) sont dotées sur leur côté extérieur, chaque fois en formant un canal de refroidissement (22 ou 32), d'une chemise de refroidissement concentrique (21 ou 31) posée à une certaine distance, canal de refroidissement (22 ou 32) par lequel de l'air de refroidissement peut s'écouler dans une direction opposée au courant de gaz chaud (26), dans laquelle au moins une des chemises de refroidissement (21 ou 31) présente, sur le côté sur lequel l'air de refroidissement peut entrer dans le canal de refroidissement (22 ou 32), une arête d'entrée incurvée vers l'extérieur, arrondie, (37) pour l'amélioration des conditions d'entrée, dans laquelle la chambre de combustion (15, 25) est divisée par un plan de séparation (29) en une moitié supérieure avec des demi-coquilles supérieures (33a) et une moitié inférieure avec des demi-coquilles inférieures (33b), caractérisée en ce que les demi-coquilles (33a, 33b) sont assemblées l'une à l'autre dans le plan de séparation (29) par des soudures du plan de séparation (30), en ce que les coquilles (23, 33) présentent dans la région des soudures du plan de séparation (30) une forme s'écartant de la symétrie de révolution, et en ce que les chemises de refroidissement (21, 31) sont adaptées dans le plan de séparation (29) à la forme déformée des coquilles (23, 33).
  2. Machine thermique selon la revendication 1, caractérisée en ce que ladite au moins une chemise de refroidissement (21 ou 31) est élargie en forme de cloche ou en forme de trompette dans la région de l'arête d'entrée (37).
  3. Machine thermique selon la revendication 2, caractérisée en ce que la chemise de refroidissement intérieure (31) présente, sur le côté sur lequel l'air de refroidissement sort du canal de refroidissement (32), une arête de sortie incurvée vers l'extérieur, arrondie (38), pour réduire les pertes de l'écoulement.
  4. Machine thermique selon l'une quelconque des revendications 1 à 3, caractérisée en ce que les chemises de refroidissement (21, 31) sont composées de segments individuels de chemise de refroidissement (34, 34a) se raccordant l'un à l'autre en direction périphérique, et en ce que les segments de chemise de refroidissement (34, 34a) sont fixés aux coquilles correspondantes (23 ou 33) au moyen d'éléments de fixation (24) disposés de façon répartie.
  5. Machine thermique selon la revendication 4, caractérisée en ce que les segments de chemise de refroidissement (34, 34a) se chevauchent mutuellement par paires dans les régions de raccordement, et en ce qu'un segment de chemise de refroidissement d'une paire est chaque fois équipé dans la zone de chevauchement d'éléments de chevauchement (36) pour une liaison par emboîtement entre les segments de chemise de refroidissement (34, 34a) qui se chevauchent.
  6. Machine thermique selon la revendication 4 ou 5, caractérisée en ce que les éléments de fixation (24) sont disposés respectivement en direction axiale l'un derrière l'autre dans les segments de chemise de refroidissement (34, 34a), et en ce qu'il est prévu en ligne axiale avec les éléments de fixation (24) des alésages supplémentaires (35) dans les segments de chemise de refroidissement (34, 34a), par lesquels de l'air de refroidissement pénètre sous forme de jets de l'extérieur dans le canal de refroidissement respectif (22 ou 32) pour l'amélioration du refroidissement.
  7. Machine thermique selon la revendication 4, caractérisée en ce que la totalité des segments de chemise de refroidissement (34, 34a) est divisée en premiers segments de chemise de refroidissement (34a), qui touchent au plan de séparation (29), et en seconds segments de chemise de refroidissement (34), qui sont situés à l'extérieur du plan de séparation (29), et en ce que les premiers segments de chemise de refroidissement (34a) présentent une arête latérale relevée (39) pour l'adaptation à la forme déformée des coquilles (23, 33).
EP09167590.0A 2008-08-14 2009-08-11 Machine thermique Active EP2154431B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH01277/08A CH699309A1 (de) 2008-08-14 2008-08-14 Thermische maschine mit luftgekühlter, ringförmiger brennkammer.

Publications (3)

Publication Number Publication Date
EP2154431A2 EP2154431A2 (fr) 2010-02-17
EP2154431A3 EP2154431A3 (fr) 2010-08-04
EP2154431B1 true EP2154431B1 (fr) 2017-07-26

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EP09167590.0A Active EP2154431B1 (fr) 2008-08-14 2009-08-11 Machine thermique

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US (1) US8434313B2 (fr)
EP (1) EP2154431B1 (fr)
AU (1) AU2009208110B2 (fr)
CH (1) CH699309A1 (fr)

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US9267687B2 (en) 2011-11-04 2016-02-23 General Electric Company Combustion system having a venturi for reducing wakes in an airflow
US9897317B2 (en) * 2012-10-01 2018-02-20 Ansaldo Energia Ip Uk Limited Thermally free liner retention mechanism
US20140208771A1 (en) * 2012-12-28 2014-07-31 United Technologies Corporation Gas turbine engine component cooling arrangement
US9739201B2 (en) 2013-05-08 2017-08-22 General Electric Company Wake reducing structure for a turbine system and method of reducing wake
US9322553B2 (en) 2013-05-08 2016-04-26 General Electric Company Wake manipulating structure for a turbine system
US9435221B2 (en) 2013-08-09 2016-09-06 General Electric Company Turbomachine airfoil positioning
EP2868898A1 (fr) * 2013-10-30 2015-05-06 Siemens Aktiengesellschaft Mode de fonctionnement en charge partielle amélioré d'une turbine à gaz comprenant un canal d'écoulement à dérivation réglable
GB201501817D0 (en) * 2015-02-04 2015-03-18 Rolls Royce Plc A combustion chamber and a combustion chamber segment
US10816212B2 (en) 2016-04-22 2020-10-27 Rolls-Royce Plc Combustion chamber having a hook and groove connection
US10641174B2 (en) 2017-01-18 2020-05-05 General Electric Company Rotor shaft cooling
US10801730B2 (en) * 2017-04-12 2020-10-13 Raytheon Technologies Corporation Combustor panel mounting systems and methods
US10697634B2 (en) 2018-03-07 2020-06-30 General Electric Company Inner cooling shroud for transition zone of annular combustor liner
CN113330190B (zh) * 2018-11-02 2023-05-23 克珞美瑞燃气涡轮有限责任公司 用于向燃气涡轮机燃烧室提供压缩空气的系统和方法
US11377970B2 (en) 2018-11-02 2022-07-05 Chromalloy Gas Turbine Llc System and method for providing compressed air to a gas turbine combustor
US11248797B2 (en) 2018-11-02 2022-02-15 Chromalloy Gas Turbine Llc Axial stop configuration for a combustion liner
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US11215367B2 (en) 2019-10-03 2022-01-04 Raytheon Technologies Corporation Mounting a ceramic component to a non-ceramic component in a gas turbine engine

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Also Published As

Publication number Publication date
EP2154431A3 (fr) 2010-08-04
US8434313B2 (en) 2013-05-07
AU2009208110A1 (en) 2010-03-04
US20100037621A1 (en) 2010-02-18
CH699309A1 (de) 2010-02-15
EP2154431A2 (fr) 2010-02-17
AU2009208110B2 (en) 2014-07-10

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