EP2093487B1 - Arrangement avec une chambre de combustion de turbine à gaz avec un tube de flamme céramique pour un moteur - Google Patents

Arrangement avec une chambre de combustion de turbine à gaz avec un tube de flamme céramique pour un moteur Download PDF

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Publication number
EP2093487B1
EP2093487B1 EP09002226.0A EP09002226A EP2093487B1 EP 2093487 B1 EP2093487 B1 EP 2093487B1 EP 09002226 A EP09002226 A EP 09002226A EP 2093487 B1 EP2093487 B1 EP 2093487B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
flame tube
arrangement
engine
supported
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
EP09002226.0A
Other languages
German (de)
English (en)
Other versions
EP2093487A2 (fr
EP2093487A3 (fr
Inventor
Miklos Dr. Gerendás
Sermed Sadig
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 EP2093487A2 publication Critical patent/EP2093487A2/fr
Publication of EP2093487A3 publication Critical patent/EP2093487A3/fr
Application granted granted Critical
Publication of EP2093487B1 publication Critical patent/EP2093487B1/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
    • F23R3/007—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
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/04—Supports for linings
    • 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
    • F23D—BURNERS
    • F23D2212/00—Burner material specifications
    • F23D2212/10—Burner material specifications ceramic

Definitions

  • the present invention relates to an arrangement with an annular gas turbine combustion chamber for a drive with a substantially cylindrical flame tube.
  • the GB-A 1 450 894 describes the construction of a gas turbine combustor with monolithic ceramic shingles.
  • the shingles are used for thermal insulation and are attached to a structural metal housing component. Since ceramic and metal have different thermal expansions, attention must be paid to their connection.
  • the bearing surface between metallic and ceramic component is in a special angle, which is characterized in that the clamping force remains constant even at elevated temperatures.
  • a disadvantage of the gas turbine combustor is the direct connection of the shingles to the housing, which is not suitable for axial combustion chambers with a high mass flow rate, since the radial cross section is not sufficient to bring the pressure loss in the annulus to a sufficiently low level. Due to the segmented structure of the flame tube, there is the additional problem of keeping the gap between the individual shingles, which leave the support structure unprotected, from hot gas.
  • the US-A 6,397,603 describes a gas turbine combustor whose flame tube is made entirely of CMC (ceramic matrix composite material).
  • the combustion chamber is held at the head with studs in their appropriate position.
  • the combustion chamber structure has the disadvantage that the connection of the flame tube with the combustion chamber head via a bolt that allows large radial movements. Due to the type of connection, however, a large radial clearance is required, its control within the operation as very is considered difficult.
  • the gap results from the resulting relative thermal expansions of the CMC tube relative to the metallic combustion chamber head and the housing. During pressure oscillations or impacts in the engine mount, the CMC component beats due to the necessary play on the metal fasteners. Furthermore, the production of the entire flame tube from one piece involves high costs, since the volume of an autoclave is not fully utilized due to the hollow cylinder shape.
  • the US 3,854,503 A describes a gas turbine combustor made of ceramic with circumferentially divided elements.
  • the elements each have radially outwardly directed axial flanges, which are rigidly connected by means of metallic clamping elements, wherein the clamping elements extend in the axial direction and at their ends support the combustion chamber or the flame tube.
  • the axial flanges lead to a static overdetermination of the bearing of the combustion chamber.
  • the US 5 333 443 A shows a seal assembly in which individual combustion chamber shingles are connected to each other by means of radially outwardly facing mounting legs and secured to the combustion chamber wall.
  • This type of storage is statically overdetermined and can not serve to take into account different thermal expansion coefficients.
  • the invention has for its object to provide an arrangement with a gas turbine combustor of the type mentioned, which allows the use of fiber-reinforced ceramic materials with a simple structure and simple, cost-effective manufacturability.
  • the flame tube is made of a ceramic material and divided in the circumferential direction into a plurality of peripheral elements.
  • the peripheral elements are connected to each other by axial flanges.
  • the axial flanges are connected or coupled by means of articulated, chain-link-like coupling elements with the associated components, so that, on the one hand, a statically unambiguous assignment is created and, on the other hand, thermal expansion can be absorbed without damaging the components.
  • the extended center lines of the coupling elements intersect with the engine axis.
  • a flame tube 2 of a combustion chamber of a fiber-reinforced ceramic ceramic material
  • the combustion chamber is composed of an outer flame tube 2, an inner flame tube 8, and the combustion chamber head 7. Outer and inner flame tubes are divided circumferentially into three or more parts.
  • the flame tube 2.8 is divided circumferentially into three or more parts.
  • the individual segments are connected to each other by axial flanges 1, 9 by means of fastening elements 106.
  • the holder of the outer flame tube 2 to a combustion chamber housing 3 is carried out with a hinged rigid support in the form of a chain link 104, which with the outer Axialflansch 1 am outer flame tube 2 and a projection 101 for attachment to the combustion chamber housing 3 is connected.
  • the imaginary extensions 304 of the chain links 104 intersect on an engine axis 301 at an angle that is greater than 0 ° and less than 180 °.
  • the outer flame tube 2 is guided on an angled bearing surface 208 and positioned. Depending on the design, the outer flame tube 2 can rest on the bearing surface 208, so that the holder allows a constant clamping force during operation, or it can be set to a desired cooling gap, which is held constant during operation by the holder.
  • a flexible high temperature resistant sealing element 209 may additionally be positioned.
  • connection between the flame tube 2,8 and combustion chamber head 7 is also via an articulated bracket 4, 204, which attaches both to the axial flange 1, 9 of the flame tube 2 and to a projection 103, 203 for attachment to the Brennschkopt 7.
  • the extensions 302, 303 of the chain links 4, 204 intersect on the engine axis 301 at an angle which is greater than 0 ° and less than 180 °.
  • the projections 103, 203 may be integrally formed or joined to the combustion chamber head 7.
  • the projection 101 may be integrally formed or joined to the combustion chamber housing 3.
  • hinged supports 4, 204 and the projections 103, 203 are independent of their shape.
  • the connecting elements may be made of metallic or ceramic materials.
  • the holder according to the invention makes it possible to move the ceramic housing at high temperatures stress-free relative to the combustion chamber housing and the combustion chamber head.
  • the relative movements are intercepted by the articulated mounting of the flame tube.
  • the segmentation of the flame tube makes it possible to keep the manufacturing costs low compared to a full-ring design, since the volume of an autoclave is better utilized by stacking the individual segments. Nevertheless, the introduction of the Axialflanschs no leaks, as in shingles after GB-A 1 450 894 are common, up.
  • Fig. 6 shows a schematic overall view of a combustion chamber according to the invention in a gas turbine.
  • a combustion chamber 401 a burner 402 with arm and head, bypass 403, fan 404, compressor 405, inner and outer combustion chamber housing 407 and 408, Turbinenleitrad 409, turbine runner 410, drive shaft 411 and 412 combustion chamber head are provided.

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)

Claims (5)

  1. Arrangement avec une chambre de combustion annulaire de turbine à gaz pour un moteur, comprenant un tube à flamme (2, 8) pour l'essentiel cylindrique qui est fabriqué en un matériau céramique et subdivisé dans le sens circonférentiel en plusieurs éléments circonférentiels (10, 11, 12), les éléments circonférentiels (10, 11, 12) étant respectivement reliés par des brides axiales (1, 9), caractérisé en ce que les brides axiales (1, 9) sont respectivement logées au moyen d'éléments de couplage (4, 104, 204) articulés en forme de chaînon, et que des prolongements des lignes médianes (302, 303, 304) des éléments de couplage (4, 104, 204) coupent un axe du moteur (301).
  2. Arrangement selon la revendication n° 1, caractérisé en ce qu'une bride axiale (1) extérieure dans le sens radial du tube à flamme (2) extérieur est logée au moyen d'un élément de couplage (104) sur un carter extérieur (3) de la chambre de combustion.
  3. Arrangement selon la revendication n° 1, caractérisé en ce qu'une bride axiale (9) intérieure dans le sens radial du tube à flamme (8) intérieur est logée au moyen d'un élément de couplage sur un carter intérieur (205) de la chambre de combustion.
  4. Arrangement selon une des revendications n° 1 à n° 3, caractérisé en ce qu'une bride axiale (9) intérieure dans le sens radial du tube à flamme (8) intérieur est logée au moyen d'un élément de couplage (204) sur une tête (7) de la chambre de combustion.
  5. Arrangement selon une des revendications n° 1 à n° 4, caractérisé en ce qu'une bride axiale (1) extérieure dans le sens radial du tube à flamme (2) extérieur est logée au moyen de l'élément de couplage (4) sur une tête (7) de la chambre de combustion.
EP09002226.0A 2008-02-21 2009-02-17 Arrangement avec une chambre de combustion de turbine à gaz avec un tube de flamme céramique pour un moteur Not-in-force EP2093487B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102008010294A DE102008010294A1 (de) 2008-02-21 2008-02-21 Gasturbinenbrennkammer mit keramischem Flammenrohr

Publications (3)

Publication Number Publication Date
EP2093487A2 EP2093487A2 (fr) 2009-08-26
EP2093487A3 EP2093487A3 (fr) 2013-11-27
EP2093487B1 true EP2093487B1 (fr) 2016-08-17

Family

ID=40512449

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09002226.0A Not-in-force EP2093487B1 (fr) 2008-02-21 2009-02-17 Arrangement avec une chambre de combustion de turbine à gaz avec un tube de flamme céramique pour un moteur

Country Status (3)

Country Link
US (1) US8281598B2 (fr)
EP (1) EP2093487B1 (fr)
DE (1) DE102008010294A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015226079A1 (de) * 2015-12-18 2017-06-22 Dürr Systems Ag Brennkammervorrichtung und Gasturbinenvorrichtung

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014149108A1 (fr) 2013-03-15 2014-09-25 Graves Charles B Agencement d'enceinte et de chemisage à dalles pour une chambre de combustion
US10100737B2 (en) 2013-05-16 2018-10-16 Siemens Energy, Inc. Impingement cooling arrangement having a snap-in plate
RU2598964C2 (ru) * 2014-12-12 2016-10-10 Федеральное агентство научных организаций Федеральное Государственное Бюджетное Научное Учреждение Всероссийский научно-исследовательский институт электрификации сельского хозяйства (ФГБНУ ВИЭСХ) Устройство камеры сгорания с регулируемым зазором подачи охлаждающего воздуха для микрогазотурбинного двигателя
US10533740B2 (en) 2015-07-09 2020-01-14 Carrier Corporation Inward fired ultra low NOX insulating burner flange
CN205016725U (zh) * 2015-09-10 2016-02-03 欧品电子(昆山)有限公司 电源插座端子
US11015812B2 (en) * 2018-05-07 2021-05-25 Rolls-Royce North American Technologies Inc. Combustor bolted segmented architecture
CN110107402B (zh) * 2019-04-29 2021-06-08 中国航空工业集团公司金城南京机电液压工程研究中心 一种陶瓷涡轮发动机
CN114484505B (zh) * 2022-01-27 2023-05-16 西安鑫垚陶瓷复合材料有限公司 陶瓷基复合材料全环型火焰筒、定型模具及其制备方法

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Publication number Priority date Publication date Assignee Title
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Also Published As

Publication number Publication date
US8281598B2 (en) 2012-10-09
DE102008010294A1 (de) 2009-08-27
EP2093487A2 (fr) 2009-08-26
EP2093487A3 (fr) 2013-11-27
US20090235667A1 (en) 2009-09-24

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