EP2966352A1 - Chambre de combustion d'une turbine a gaz dotee de tete de chambre de combustion vissee - Google Patents

Chambre de combustion d'une turbine a gaz dotee de tete de chambre de combustion vissee Download PDF

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Publication number
EP2966352A1
EP2966352A1 EP15175908.1A EP15175908A EP2966352A1 EP 2966352 A1 EP2966352 A1 EP 2966352A1 EP 15175908 A EP15175908 A EP 15175908A EP 2966352 A1 EP2966352 A1 EP 2966352A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
head
top plate
chamber head
heat shield
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Withdrawn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
EP15175908.1A
Other languages
German (de)
English (en)
Inventor
Dr.-Ing. Sebastian BAKE
Dr.-Ing. Carsten Clemen
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 EP2966352A1 publication Critical patent/EP2966352A1/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Withdrawn legal-status Critical Current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
    • F23R3/42—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
    • 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
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • 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
    • 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
    • F23M2700/00—Constructional details of combustion chambers
    • F23M2700/005—Structures of combustion chambers or smoke ducts
    • F23M2700/0053—Bricks for combustion chamber walls
    • 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

Definitions

  • the invention relates to a combustion chamber of a gas turbine according to the preamble of claim 1.
  • the invention relates to a combustion chamber of a gas turbine, which has a top plate, to which on the inside of heat shields are connected by means of screw. Furthermore, the combustion chamber has a combustion chamber head.
  • the combustion chamber head is welded to the combustion chamber wall.
  • the combustion chamber head is either manufactured as a solid ring by means of a casting process or manufactured in segments, which are then welded to form a solid ring and subsequently also joined to the combustion chamber wall by means of a welded connection. It is also known to form the combustion chamber head from sheet metal and bolt it to the combustion chamber outer wall.
  • Such constructions are from the US 6,672,067 B2 . US 2004/0045301 A1 . JP 2004101174 A . US 5,924,288 and EP 0 550 953 A1 known.
  • the invention has for its object to provide a combustion chamber of a gas turbine of the type mentioned, which has a simple structure and simple, inexpensive to manufacture a cost-effective and technically advantageous embodiment of the combustion chamber head.
  • each heat shield and the combustion chamber head are fastened by means of common screw connections to the top plate.
  • the top plates are screwed to the heat shield.
  • threaded bolts are provided on the heat shields, which are usually designed as cast parts, which are guided through recesses of the top plate and screwed from outside the combustion chamber interior.
  • individual of these screw connections are used to secure the combustion chamber head. It is thus not necessary according to the invention to take additional fastening measures. Rather, the existing screw for attaching the heat shield with the top plate for storage and mounting of the combustion chamber head can be shared. It is particularly advantageous if each heat shield is connected by means of several screw with the top plate and only a few of these screw connections are used for the attachment of the combustion chamber head.
  • combustion chamber head is provided with access recesses for accessing the screw connection.
  • the combustor head thus preferably has a plurality of access recesses to gain access to the threaded studs of the top plate and to unscrew them on these nuts.
  • the combustion chamber head has in the region of the access recesses in the interior of the combustion chamber head protruding mounting sleeves. These also serve as spacers to be applied against the top plate. This results in a precise alignment and assembly of the combustion chamber head.
  • the fastening sleeves are formed so that they are provided with air passage openings. Thus, a uniform flushing of the interior of the combustion chamber head can be done with cooling air.
  • the combustion chamber head can either be designed as a solid ring or be manufactured segmented.
  • the individual segments can be screwed in the manner described above with the heat shield or the top plate.
  • the combustion chamber head is produced by means of an additive manufacturing method, for example by means of a DLD method (direct laser depositioning).
  • a DLD method direct laser depositioning
  • the inventive design offers the possibility of screwing the combustion chamber head with the top plate and the heat shield without additional parts are required. This results in a significant weight reduction. Furthermore, the assembly is simplified. The total manufacturing costs can be reduced.
  • the gas turbine engine 110 is a generalized example of a turbomachine, in which the invention can be applied.
  • the engine 110 is formed in a conventional manner and comprises in succession an air inlet 111, a fan 112 circulating in a housing, a medium pressure compressor 113, a high pressure compressor 114, a combustion chamber 115, a high pressure turbine 116, a medium pressure turbine 117 and a low pressure turbine 118 and a Exhaust nozzle 119, which are all arranged around a central engine center axis 101.
  • the intermediate pressure compressor 113 and the high pressure compressor 114 each include a plurality of stages, each of which includes a circumferentially extending array of fixed stationary vanes 120, commonly referred to as stator vanes, that radially inwardly from the engine casing 121 into an annular flow passage through the compressors 113, 114 protrude.
  • the compressors further include an array of compressor blades 122 projecting radially outward from a rotatable drum or disc 125 coupled to hubs 126 of high pressure turbine 116 and intermediate pressure turbine 117, respectively.
  • the turbine sections 116, 117, 118 have similar stages, comprising an array of fixed vanes 123 projecting radially inward from the housing 121 into the annular flow passage through the turbines 116, 117, 118, and a downstream array of turbine blades 124 projecting outwardly from a rotatable hub 126.
  • the compressor drum or compressor disk 125 and the vanes 122 disposed thereon and the turbine rotor hub 126 and the Turbine blades 124 disposed thereon rotate about the engine centerline 101 during operation.
  • the Fig. 2 shows a simplified sectional view of a combustion chamber outer wall 1 and a combustion chamber inner wall 2. These are interconnected. With the combustion chamber outer wall 1, a combustion chamber head 3 is connected, for example by means of a welding process. In the interior of the combustion chamber, a heat shield 4 is provided, which is provided with four heat shield bolts 5, which are provided with an external thread to unscrew a nut 10.
  • the Fig. 2 further shows a combustion chamber head 3, which is shown in more detail in the following figures.
  • the combustion chamber head 3 is designed so that it can be inserted with its edge region 12 in a precise fit in a groove 13 of the top plate 6 and thus can be centered.
  • the mounting sleeves 7 are formed so that they rest against mounting lugs 14 of the top plate 6 in the mounted state. Subsequently, by means of nuts 10 a screwing done.
  • the combustion chamber head 3 is provided with access recesses 8 to allow the screwing of the combustion chamber head 3 with the heat shield 4. Furthermore, the combustion chamber head access recesses 9, through which access to the Verschraubungsstellen is provided by means of which the heat shield 4 is bolted to the top plate 6.
  • the Fig. 3 shows a perspective view of in Fig. 2 shown view. It can be seen in particular that only some of the heat shield bolts 5 are used for fastening the combustion chamber head 3.
  • the 4 to 6 show perspective partial views of the combustion chamber head with a view towards the inside of the combustion chamber head 3. It can be seen that a plurality of burner passage openings 15 are provided on the combustion chamber head 3. Each of these burner passage openings 15 is a heat shield 4 assigned, which is screwed by means of four heat shield bolts 5. While two of these attachment points are used for direct connection of the heat shield 4 with the top plate 6, 3 mounting sleeves are provided at two of these attachment points on the combustion chamber head, by means of which, as in the Fig. 2 and 3 shown, the combustion chamber head 3 is attached.
  • Fig. 4 and 5 in particular also show the air passage openings 11 of the fastening sleeves 7.
  • the Fig. 6 shows an overall view of the combustion chamber head 3, which is composed of four segments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
EP15175908.1A 2014-07-09 2015-07-08 Chambre de combustion d'une turbine a gaz dotee de tete de chambre de combustion vissee Withdrawn EP2966352A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014213302.5A DE102014213302A1 (de) 2014-07-09 2014-07-09 Brennkammer einer Gasturbine mit verschraubtem Brennkammerkopf

Publications (1)

Publication Number Publication Date
EP2966352A1 true EP2966352A1 (fr) 2016-01-13

Family

ID=53723997

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15175908.1A Withdrawn EP2966352A1 (fr) 2014-07-09 2015-07-08 Chambre de combustion d'une turbine a gaz dotee de tete de chambre de combustion vissee

Country Status (3)

Country Link
US (1) US10012390B2 (fr)
EP (1) EP2966352A1 (fr)
DE (1) DE102014213302A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10378775B2 (en) * 2012-03-23 2019-08-13 Pratt & Whitney Canada Corp. Combustor heat shield
US10267521B2 (en) 2015-04-13 2019-04-23 Pratt & Whitney Canada Corp. Combustor heat shield
GB201613299D0 (en) 2016-08-02 2016-09-14 Rolls Royce Plc A method of assembling an annular combustion chamber assembly
DE102017201349A1 (de) 2017-01-27 2018-08-02 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung einer Gasturbine
DE102017203244A1 (de) 2017-02-28 2018-08-30 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung mit Brennkammerwand aus Blech
DE102018112540A1 (de) * 2018-05-25 2019-11-28 Kueppers Solutions Gmbh Brennstoffdüsensystem

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0550953A1 (fr) 1992-01-02 1993-07-14 General Electric Company Plaque de capot et dispositif de fixation d'embout intégrées pour une chambre de combustion
EP0837286A2 (fr) * 1996-10-18 1998-04-22 BMW Rolls-Royce GmbH Chambre de combustion de turbine à gaz avec section de dÔme annulaire
US5924288A (en) 1994-12-22 1999-07-20 General Electric Company One-piece combustor cowl
EP1193451A2 (fr) * 2000-10-02 2002-04-03 Rolls-Royce Deutschland Ltd & Co KG Tête de chambre de combustion d'une turbine à gaz
WO2003044433A1 (fr) * 2001-11-20 2003-05-30 Volvo Aero Corporation Dispositif pour la chambre a combustion d'une turbine a gaz
US6672067B2 (en) 2002-02-27 2004-01-06 General Electric Company Corrugated cowl for combustor of a gas turbine engine and method for configuring same
US20040045301A1 (en) 2002-09-10 2004-03-11 Gilbert Farmer Fabricated cowl for double annular combustor of a gas turbine engine and method of making same
US20130247575A1 (en) * 2012-03-23 2013-09-26 Bhawan B. Patel Combustor heat shield

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4870818A (en) * 1986-04-18 1989-10-03 United Technologies Corporation Fuel nozzle guide structure and retainer for a gas turbine engine
FR2914399B1 (fr) * 2007-03-27 2009-10-02 Snecma Sa Carenage pour fond de chambre de combustion.
JP4815513B2 (ja) * 2009-07-06 2011-11-16 川崎重工業株式会社 ガスタービン燃焼器
US9765968B2 (en) * 2013-01-23 2017-09-19 Honeywell International Inc. Combustors with complex shaped effusion holes

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0550953A1 (fr) 1992-01-02 1993-07-14 General Electric Company Plaque de capot et dispositif de fixation d'embout intégrées pour une chambre de combustion
US5924288A (en) 1994-12-22 1999-07-20 General Electric Company One-piece combustor cowl
EP0837286A2 (fr) * 1996-10-18 1998-04-22 BMW Rolls-Royce GmbH Chambre de combustion de turbine à gaz avec section de dÔme annulaire
EP1193451A2 (fr) * 2000-10-02 2002-04-03 Rolls-Royce Deutschland Ltd & Co KG Tête de chambre de combustion d'une turbine à gaz
WO2003044433A1 (fr) * 2001-11-20 2003-05-30 Volvo Aero Corporation Dispositif pour la chambre a combustion d'une turbine a gaz
US6672067B2 (en) 2002-02-27 2004-01-06 General Electric Company Corrugated cowl for combustor of a gas turbine engine and method for configuring same
US20040045301A1 (en) 2002-09-10 2004-03-11 Gilbert Farmer Fabricated cowl for double annular combustor of a gas turbine engine and method of making same
JP2004101174A (ja) 2002-09-10 2004-04-02 General Electric Co <Ge> ガスタービンエンジンの複式環状燃焼器用の組立てカウルとその製作方法
US20130247575A1 (en) * 2012-03-23 2013-09-26 Bhawan B. Patel Combustor heat shield

Also Published As

Publication number Publication date
US10012390B2 (en) 2018-07-03
US20160010869A1 (en) 2016-01-14
DE102014213302A1 (de) 2016-01-14

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