EP2809994B1 - Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion - Google Patents

Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion Download PDF

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Publication number
EP2809994B1
EP2809994B1 EP13712711.4A EP13712711A EP2809994B1 EP 2809994 B1 EP2809994 B1 EP 2809994B1 EP 13712711 A EP13712711 A EP 13712711A EP 2809994 B1 EP2809994 B1 EP 2809994B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
wall
heat
shield element
height
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
EP13712711.4A
Other languages
German (de)
English (en)
Other versions
EP2809994A2 (fr
Inventor
Francois Benkler
Thomas Brandenburg
Olga Deiss
Thomas Grieb
Marco Link
Nicolas Savilius
Daniel Vogtmann
Jan Wilkes
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP2809994A2 publication Critical patent/EP2809994A2/fr
Application granted granted Critical
Publication of EP2809994B1 publication Critical patent/EP2809994B1/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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • 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
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F23R2900/03042—Film 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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R3/02—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
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections

Definitions

  • the invention relates to a heat shield element of a combustion chamber, in particular an annular combustion chamber of a gas turbine plant, and refers to the bypass of compressor air around the combustion chamber at partial load.
  • the invention further relates to a combustion chamber and a corresponding gas turbine plant.
  • the increased temperature in the combustion chamber leads to the demand for better cooling of the heat shield elements facing the combustion chamber.
  • the EP 1 486 7630 A1 proposes for this purpose to provide the outwardly facing cold side of the heat shield elements with turbulators to improve the cooling by the cooling air.
  • the object of the present invention is to expand by specifying a bypass the carbon monoxide compliant driving range of the gas turbine as far as possible in the direction of low power.
  • Another object of the present invention is to provide an improved combustor. Finally, it is an object of the present invention to provide an improved gas turbine.
  • the first object is achieved by a heat shield element according to claim 1, the second object by a combustion chamber according to claim 6 and the third object by a gas turbine according to claim 10.
  • a heat shield element in particular for lining a combustion chamber wall, comprising a first wall with a hot side to be acted upon by a hot medium, a cold side facing the hot side and a peripheral edge located at a first, extending a second and a third narrow side of the first wall beyond the cold side substantially to a first height, the peripheral edge extends on a fourth narrow side to a second height which is smaller than the first height, and that substantially the second height is opposite to a second wall of the cold side and extends across the width of the fourth narrow side from the fourth narrow side over a portion of the length of the narrow side adjacent the fourth narrow side, wherein the second wall has an edge at its end facing away from the fourth narrow side, which he himself up to the first height treckt.
  • the invention is based on the idea that in an annular combustion chamber, which is largely lined with ceramic heat shield elements and only the inlet into the turbine is lined with metallic heat shield elements, the supply of the bypass air in the metallic heat shield elements of the combustion chamber wall should be done because the supply as possible far behind the combustion to prevent the flame from cooling but before the turbine to maximize gas turbine efficiency should.
  • a new design of the metallic heat shield elements is needed. This design is the subject of this invention.
  • the heat shield element is subdivided into two superimposed areas, which are sealed against each other and which in the installed state, i. with the combustion chamber wall, forming chambers.
  • a first chamber extends over the entire surface of the heat shield element and is used for normal cooling of the metallic heat shield.
  • a second chamber is located in the turbine facing portion of the heat shield element above the first chamber.
  • the heat shield element consists of a high-temperature-resistant metal or a high-temperature-resistant metal alloy, since these materials have a lower brittleness than, for example, ceramics and a comparatively good thermal and thermal conductivity behavior.
  • a plurality of cooling air openings arranged in the peripheral edge are provided, from which the compressor end air provided for cooling the heat shield element can escape into the combustion chamber.
  • cooling air openings are arranged at least in the region of the second wall between the first and the second wall.
  • the cooling holes are in the region of the first chamber for the cooling of the heat shield element.
  • the heat shield element further comprises a mounting opening, the enclosure of which extends from the first wall to the first height.
  • the heat shield element is used for protection against overheating of a component carrying hot gas, in particular a combustion chamber, preferably an annular combustion chamber of a gas turbine having a combustion chamber wall, with a burner side and a turbine side end, wherein the combustion chamber wall has a circumferential direction.
  • a number of heat shield elements is preferably arranged at the turbine-side end of the combustion chamber wall with the formation of two chambers in the circumferential direction, wherein the fourth narrow side is aligned towards the turbine end.
  • the heat shield elements are preferably fastened with fastening bolts on the combustion chamber wall.
  • bores are introduced in the combustion chamber wall so that coolant can be supplied to the heat shield elements.
  • At least one supply channel per heat shield element is arranged in the region of the respective second wall in the combustion chamber wall, which opens into a plenum which at least partially surrounds the combustion chamber.
  • the combustion chamber to which heat shield elements are attached is preferably part of a gas turbine.
  • This gas turbine comprises at least one discharge for compressor air, which opens via at least one line with a valve in the plenum.
  • the invention enables the supply of bypass air in the hot gas path without far-reaching modifications to hot gas components.
  • the implementation will therefore probably be relatively inexpensive. It ensures that no hot gas is drawn in even when the bypass is switched off, since the second chamber is constantly purged and its outlet streamlined between heat shield element and turbine vane 1 is located.
  • FIG. 1 shows schematically and by way of example the combustion system of an annular combustion chamber 1 according to the prior art in a housing 2.
  • the annular combustion chamber 1 consists of a closed ring which is arranged around a rotor axis 3. Burner 4 are arranged in the upper region of the combustion chamber 1 in inlet openings 5. There, the mixing of the fuel 6 with the compressor air 7 takes place. In the combustion chamber 1, the actual combustion takes place. Through the outlet at the turbine end 8 of the annular combustion chamber 1, the hot combustion gases enter the turbine 9, where they meet the first stationary vane 10.
  • the annular combustion chamber 1 is lined with ceramic heat shield elements 11 and metallic heat shield elements 12, which are fastened to the combustion chamber wall 13.
  • the supply of the bypass air in the area of the metallic heat shield elements 12 should take place, since the supply should be as far as possible behind the combustion and thus a cooling of the flame is avoided, but even before the turbine 9 in order to achieve the highest possible gas turbine efficiency.
  • FIG. 2 shows a metallic heat shield element 14 according to the invention, which is to be fastened to the combustion chamber wall 13 and forms with this a first 15 and a turbine open to the second chamber 16 which are sealed against each other.
  • the metallic heat shield element 14 itself comprises a first wall 17 with a hot side 18 which can be acted upon by a hot medium, a cold side 19 opposite the hot side 18 and four narrow sides 20, 21, 22, 23 located between them.
  • a peripheral edge 24 extends from each narrow side 20, 21, 22, 23 beyond the cold side 19 addition.
  • the edge 24 extends substantially up to a first height 25 relative to the cold side 19 of the first wall 17 and on the fourth narrow side 23 only to a smaller second height 26th
  • the installed metallic heat shield element 14 rests on the edges of three narrow sides 20, 21, 22 on the combustion chamber wall 13.
  • a second wall 27 is located substantially opposite to the second height 26 of the cold side 19. It extends over the width of the fourth narrow side 23 and from the fourth narrow side 23 over part of the length of the fourth narrow side 23 adjacent narrow sides 20, 22. Furthermore, the second wall 27 at its fourth narrow side 23 facing away from the end 28 has an edge 29, which extends from the second height 26 to the first height 25.
  • a plurality of cooling air openings 30 are provided in the peripheral edge 24 in the region of the first chamber 15.
  • the first chamber 15 is supplied, as in prior art heat shield elements 12, through holes through the combustor wall 13 with compressor discharge air for cooling, which escapes from the metallic heat shield element 14 via these cooling air openings 30.
  • the metallic heat shield element 14 has a mounting aperture 31, the skirt 32 of which extends from the first wall 17 to the first height 25. Through this attachment opening 31, the heat shield element 14 is fastened to the combustion chamber wall 13 by means of fastening bolts.
  • the supply of open in the direction of the turbine 9 second chamber 16 with compressor air consists of two components.
  • the second chamber 16 is permanently supplied with some compressor air for flushing via a few holes through the combustion chamber wall 13, so that no hot gas can penetrate into the second chamber 16 when the bypass is off.
  • the second chamber 16 can be engaged in a switchable manner with a bypass mass flow. This is done over comparatively large holes, i. compared to the holes for the flushing, fed in the combustion chamber wall 13.
  • the bypass mass flow then escapes via the opening at the trailing edge, i. the combustion chamber facing side of the heat shield element 14, on which the peripheral edge 24 extends only to the second height 26, in the gap between the metallic heat shield element 14 and the first stationary vane 10th
  • FIG. 3 shows how compressor air is initially led out of the gas turbine via a removal 33 for the bypass. Outside the gas turbine, the circuit via a valve 34. Thereafter, the air is returned via a line 35 into the gas turbine and entered into a circulating around the annular combustion chamber 1 plenum 36. From there, stub lines 37 or tap holes lead to the respective second chamber 16 of the respective metallic heat shield element 14.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Elément (14) de bouclier thermique, notamment pour revêtir une paroi (13) d'une chambre de combustion, comprenant une première paroi (17) ayant une face (18) chaude pouvant être alimentée en un fluide chaud, une face (19) froide opposée à la face (18) chaude et un bord (24), faisant le tour, qui s'étend sur un premier (20), un deuxième (21) et un troisième (22) petits côtés de la première paroi (17) au-delà de la face (19) froide sensiblement jusqu'à un premier niveau (25), caractérisé en ce que le bord (24) faisant le tour s'étend sur un quatrième petit côté (23) jusqu'à un deuxième niveau (26) qui est plus bas que le premier niveau (25) et en ce que sensiblement au deuxième niveau (26) une deuxième paroi (27) de la face (19) froide est en opposition et s'étend sur la largeur du quatrième petit côté (23) à partir du quatrième petit côté (23), sur une partie de la longueur des petits côtés (20, 22) voisins du quatrième petit côté (23), la deuxième partie (27) ayant à son extrémité (28) éloignée du quatrième petit côté (23) un bord (29) qui s'étend jusqu'au premier niveau (25).
  2. Elément (14) de bouclier thermique suivant la revendication 1, dans lequel l'élément (14) de bouclier thermique est en un métal résistant aux températures hautes ou en un alliage métallique résistant aux températures hautes.
  3. Elément (14) de bouclier thermique suivant l'une des revendications 1 ou 2, dans lequel il est prévu une pluralité d'ouïes (30) pour de l'air de refroidissement dans le bord (24) faisant le tour.
  4. Elément (14) de bouclier thermique suivant la revendication 3, dans lequel les ouïes (30) pour de l'air de refroidissement sont disposées au moins dans la partie de la deuxième paroi (27) comprise entre la première (26) et la deuxième parois (27).
  5. Elément (14) de bouclier thermique suivant l'une des revendications précédentes, comprenant en outre une ouverture (31) de fixation, dont la bordure (32) s'étend de la première paroi (17) jusqu'au premier niveau (25).
  6. Chambre de combustion (1) comprenant une paroi ayant une extrémité (8) du côté du foyer et une extrémité (8) du côté de la turbine, la paroi (13) de la chambre de combustion ayant une direction périphérique comprenant un certain nombre d'éléments (14) de bouclier thermique suivant l'une des revendications précédentes, qui sont disposés dans la direction périphérique à l'extrémité (8), du côté de la turbine, de la paroi (13) de la chambre de combustion en formant respectivement deux chambres (15, 16), le quatrième petit côté (23) étant tourné vers l'extrémité (8) du côté de la turbine.
  7. Chambre de combustion (1) suivant la revendication 6, dans laquelle les éléments (14) de bouclier thermique sont fixés par des boulons de fixation sur la paroi (13) de la chambre de combustion.
  8. Chambre de combustion (1) suivant l'une des revendications 6 ou 7, dans laquelle il est ménagé dans la paroi (13) de la chambre de combustion des trous de manière à pouvoir apporter du fluide de refroidissement aux éléments (14) de bouclier thermique.
  9. Chambre de combustion (1) suivant l'une des revendications 6 à 8, dans laquelle il est disposé dans la paroi (13) de la chambre de combustion au moins un canal d'apport, pour chaque élément (14) de bouclier thermique dans la région de sa deuxième paroi (27), canal, qui débouche dans une chambre (26) d'accumulation entourant au moins en partie la chambre de combustion (1).
  10. Turbine à gaz ayant une chambre de combustion (1) suivant l'une des revendications 6 à 9, la turbine à gaz comprenant au moins un prélèvement (33) d'air de compresseur, qui débouche dans la chambre (36) d'accumulation par au moins un conduit (35) ayant une soupape (34).
EP13712711.4A 2012-03-15 2013-03-12 Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion Not-in-force EP2809994B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012204103A DE102012204103A1 (de) 2012-03-15 2012-03-15 Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer
PCT/EP2013/055007 WO2013135702A2 (fr) 2012-03-15 2013-03-12 Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion

Publications (2)

Publication Number Publication Date
EP2809994A2 EP2809994A2 (fr) 2014-12-10
EP2809994B1 true EP2809994B1 (fr) 2016-05-04

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13712711.4A Not-in-force EP2809994B1 (fr) 2012-03-15 2013-03-12 Élément écran thermique pour une dérivation d'air de compresseur autour de la chambre de combustion

Country Status (6)

Country Link
US (1) US20150027128A1 (fr)
EP (1) EP2809994B1 (fr)
CN (1) CN104169648B (fr)
DE (1) DE102012204103A1 (fr)
RU (1) RU2622590C2 (fr)
WO (1) WO2013135702A2 (fr)

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Also Published As

Publication number Publication date
WO2013135702A3 (fr) 2013-11-14
RU2014141355A (ru) 2016-05-10
WO2013135702A2 (fr) 2013-09-19
US20150027128A1 (en) 2015-01-29
CN104169648A (zh) 2014-11-26
DE102012204103A1 (de) 2013-09-19
EP2809994A2 (fr) 2014-12-10
RU2622590C2 (ru) 2017-06-16
CN104169648B (zh) 2016-03-02

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