EP0618349A1 - Turbinengehäuse für eine Gasturbine - Google Patents

Turbinengehäuse für eine Gasturbine Download PDF

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Publication number
EP0618349A1
EP0618349A1 EP94301535A EP94301535A EP0618349A1 EP 0618349 A1 EP0618349 A1 EP 0618349A1 EP 94301535 A EP94301535 A EP 94301535A EP 94301535 A EP94301535 A EP 94301535A EP 0618349 A1 EP0618349 A1 EP 0618349A1
Authority
EP
European Patent Office
Prior art keywords
casing
stator vane
assembly
turbine
annular
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Withdrawn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
EP94301535A
Other languages
English (en)
French (fr)
Inventor
Keelin Theodore Lim
Roy Talbot Hirst
William Richards
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 PLC
Original Assignee
Rolls Royce PLC
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 PLC filed Critical Rolls Royce PLC
Publication of EP0618349A1 publication Critical patent/EP0618349A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor

Definitions

  • the present invention relates to a turbine assembly for a gas turbine engine and in particular to the mounting of stator vanes and a cooling duct in such a turbine.
  • a turbine for a gas turbine engine typically comprises a casing which encloses alternate arrays of radially extending rotor aerofoil blades and stator aerofoil vanes.
  • the stator vanes are connected at their radially outer extents to the turbine casing whilst the rotor blades of each annular array are attached at their radially inner extents to a rotor disc.
  • the stator vanes direct hot combustion gases onto the rotor blades which rotate to extract energy from the hot combustion gases.
  • Cooling air is used to control the temperature of the turbine casing and ensure a even temperature distribution.
  • the cooling air controls the thermal growth of the turbine casing which maintains blade tip clearance and hence improves the efficiency of the engine.
  • Compressor air is used to cool the turbine casing.
  • the compressor air passes through an annular cooling duct mounted on the turbine casing.
  • the cooling duct has conventionally been mounted by means of bolts which project radially from the turbine casing.
  • Special brackets are riveted onto the casing to hold the bolts in place. Riveting brackets onto the casing reduces the integrity of the turbine casing.
  • the present invention seeks to provide a turbine assembly in which the way in which the stator vanes and the cooling duct are mounted on the turbine casing is simplified.
  • the present invention reduces the weight of the turbine casing and eliminates the need for brackets riveted onto the turbine casing so improving the integrity of the turbine casing.
  • a turbine assembly for a gas turbine engine comprises alternate annular arrays of rotor blades and stator vanes enclosed in an annular casing, each stator vane being secured at its radially outer extent to the casing, location means being provided which extend through the radially outer extent of the stator vane to locate the stator vane relative to the casing and prevent circumferential movement of the stator vane, the location means extending radially through the casing to engage an annular cooling duct which encloses the casing to define a cavity through which in operation cooling air passes.
  • each stator vane is provided with a platform which engages the casing.
  • the platform of each stator vane may be provided with a flange having an axially extending portion which engages a recess in the casing to secure the stator vane to the casing.
  • each stator vane is provided with a further flange through which the location means extend to locate the stator vanes relative to the casing.
  • a member may be mounted on the turbine casing which abuts the further flange to prevent axial movement of the stator vane.
  • the location means is threaded so that retention means, such as a nut, can be attached to the location means to fasten the annular cooling duct securely to the casing.
  • retention means such as a nut
  • a removably annular member such as a washer, may be provided on the location means to accurately space the cooling duct from the casing.
  • the location means is a bolt.
  • Figure 1 is a diagrammatic view of a gas turbine engine in accordance with the present invention.
  • Figure 2 is an enlarged view of a portion of a turbine assembly in accordance with one embodiment of the present invention.
  • Figure 3 is a cross-sectional view of part of a turbine casing in accordance with the present invention.
  • a gas turbine engine generally indicated at 10, comprises in axial flow series a fan 12, a compressor 14, a combustor 16 and a turbine 20.
  • the engine operates in conventional manner so that the air is compressed by the fan 12 and the compressor 14 before being mixed with fuel and the mixture combusted in the combustor 16.
  • the hot combustion gases then expand through the turbine 20 which rotates to extract energy and so drive the fan and compressor before exhausting through an exhaust nozzle 18.
  • the turbine 20 has a casing 60 which encloses alternate annular arrays of stator vanes 40 and rotor blades 24.
  • the stator vanes 40 direct hot combustion gases onto the rotor blades 24 which rotate to extract energy from the hot combustion gases.
  • Each stator vane 40 has an aerofoil portion 41 which is cast integrally with a radially inner platform 42 and a radially outer platform 44.
  • the radially inner platform 42 is provided with a dog 43 which is cross keyed in conventional manner to a static portion 80 of the engine 10.
  • the radially outer platform 44 is connected to the turbine casing 60.
  • the upstream end 45 of the radially outer platform 44 has a flange 46 which has an axially extending portion 47 which engages an axial recess 62 in the turbine casing 60.
  • the downstream end 48 of the radially outer platform 44 has a radially extending flange 49 through which a bolt 50 extends.
  • the bolt 50 accurately locates the stator vanes 40 relative to the turbine casing 60 and prevents any circumferential movement of the stator vanes 40.
  • An L shaped member 38 is mounted in a recess 64 in the turbine casing 60 and abuts the flange 49 to prevent axial movement of the stator vanes 40.
  • the rotor blades 24 are connected at their radial inner extents 25 to rotor discs 26.
  • Platforms 28 are provided at the radial outer extents of the rotor blades 24.
  • shroud segments 30 are provided.
  • the shroud segments 30 have an abradable coating 36. If in operation the rotor blades 24 grow due to thermal expansion the platforms 28 of the rotor blades 24 interfere with the coating 36. The coating 36 is abraded preventing any damage to the platforms 28 of the rotor blades 24 or to the shroud segments 30.
  • Each shroud segment 30 is held in position by the radially outer platforms 44 of adjacent stator vanes 40.
  • the downstream end 32 of each shroud segment 30 is located between the flange 46 at the upstream end 45 of the radially outer platform 44 of an adjacent stator vane 40 and the axial recess 62 in the turbine casing 60.
  • the upstream end 34 of the shroud segment 30 has a curved portion 37 which abuts the flange 49 at the downstream end 48 of the radially outer platform 44 of an adjacent stator vane 40.
  • the curved portion 37 is located circumferentially by the L shaped member 38 mounted in the recess 64 in the turbine casing 60 and a portion of the radially outer platform 44 which overhangs the aerofoil portion 41 of the stator vane 40.
  • the curved portion 37 is further provided with a tang 37A which engages with the flange 49 to secure the shroud segment 30 in position.
  • the bolt 50 extends radially through the casing 60 so that the end of the bolt 50 protrudes therefrom.
  • a cooling duct 70 which encloses the casing 60 is mounted on the end of the bolt 50.
  • the end of the bolt 50 is threaded and a nut 52 is attached to the end of the bolt 50 to securely fasten the cooling duct 70 to the turbine casing 60.
  • a washer 54 is used to space the cooling duct 70 from the casing 60 to define a cavity 72 around the casing 60. In operation cooling air passes through the cavity 72 to cool the turbine casing 60.
  • the bolt 50 serves a dual purpose.
  • the bolt 50 locates the stator vane 30 relative to the casing 60 and is used to mount the cooling duct 70 from the casing 60.
  • the dual purpose of the bolt 50 simplifies the assembly of the turbine 20 and reduces the weight of the turbine 20.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP94301535A 1993-03-31 1994-03-03 Turbinengehäuse für eine Gasturbine Withdrawn EP0618349A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9306719 1993-03-31
GB939306719A GB9306719D0 (en) 1993-03-31 1993-03-31 A turbine assembly for a gas turbine engine

Publications (1)

Publication Number Publication Date
EP0618349A1 true EP0618349A1 (de) 1994-10-05

Family

ID=10733080

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94301535A Withdrawn EP0618349A1 (de) 1993-03-31 1994-03-03 Turbinengehäuse für eine Gasturbine

Country Status (2)

Country Link
EP (1) EP0618349A1 (de)
GB (1) GB9306719D0 (de)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0844369A1 (de) * 1996-11-23 1998-05-27 ROLLS-ROYCE plc Zusammenbau eines Schaufelrotors und dessen Gehäuses
EP1004759A2 (de) * 1998-11-24 2000-05-31 General Electric Company Gekühltes Turbinengehäuse
WO2002090724A1 (de) * 2001-05-09 2002-11-14 Mtu Aero Engines Gmbh Mantelring
EP1288444A1 (de) * 2001-08-30 2003-03-05 Snecma Moteurs Befestigung von Statorelementen in einem Turbomaschinengehäuse
FR2846997A1 (fr) * 2002-11-07 2004-05-14 Snecma Moteurs Agencement de montage de secteurs de redresseur
EP2518278A1 (de) 2011-04-28 2012-10-31 Siemens Aktiengesellschaft Kühlleitung eines Turbinengehäuses mit stromaufwärts fliessender Kühlflüssigkeit
EP2696037A1 (de) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Abdichtung des Strömungskanals einer Strömungsmaschine
EP2725203A1 (de) * 2012-10-23 2014-04-30 MTU Aero Engines GmbH Kühlluftführung in einer Gehäusestruktur einer Strömungsmaschine
EP3179053A1 (de) * 2015-12-07 2017-06-14 MTU Aero Engines GmbH Gehäusestruktur einer strömungsmaschine mit hitzeschutzschild
CN109339873A (zh) * 2018-09-30 2019-02-15 东方电气集团东方汽轮机有限公司 用于高背压供热的汽轮机末级叶片保护装置
EP3000990B1 (de) 2014-09-26 2019-05-29 Rolls-Royce plc Halter einer turbinenummantelung
US10975721B2 (en) 2016-01-12 2021-04-13 Pratt & Whitney Canada Corp. Cooled containment case using internal plenum

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB721453A (en) * 1951-10-19 1955-01-05 Vickers Electrical Co Ltd Improvements relating to gas turbines
GB856599A (en) * 1958-06-16 1960-12-21 Gen Motors Corp Improvements relating to axial-flow compressors
US3335483A (en) * 1961-12-19 1967-08-15 Gen Electric Method of manufacturing a stator assembly for turbomachines
GB2239678A (en) * 1989-12-08 1991-07-10 Rolls Royce Plc Gas turbine engine shroud assembly
WO1992017686A1 (en) * 1991-04-02 1992-10-15 Rolls-Royce Plc Turbine casing
US5167488A (en) * 1991-07-03 1992-12-01 General Electric Company Clearance control assembly having a thermally-controlled one-piece cylindrical housing for radially positioning shroud segments

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB721453A (en) * 1951-10-19 1955-01-05 Vickers Electrical Co Ltd Improvements relating to gas turbines
GB856599A (en) * 1958-06-16 1960-12-21 Gen Motors Corp Improvements relating to axial-flow compressors
US3335483A (en) * 1961-12-19 1967-08-15 Gen Electric Method of manufacturing a stator assembly for turbomachines
GB2239678A (en) * 1989-12-08 1991-07-10 Rolls Royce Plc Gas turbine engine shroud assembly
WO1992017686A1 (en) * 1991-04-02 1992-10-15 Rolls-Royce Plc Turbine casing
US5167488A (en) * 1991-07-03 1992-12-01 General Electric Company Clearance control assembly having a thermally-controlled one-piece cylindrical housing for radially positioning shroud segments

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0844369A1 (de) * 1996-11-23 1998-05-27 ROLLS-ROYCE plc Zusammenbau eines Schaufelrotors und dessen Gehäuses
US6062813A (en) * 1996-11-23 2000-05-16 Rolls-Royce Plc Bladed rotor and surround assembly
EP1004759A2 (de) * 1998-11-24 2000-05-31 General Electric Company Gekühltes Turbinengehäuse
EP1004759A3 (de) * 1998-11-24 2002-07-17 General Electric Company Gekühltes Turbinengehäuse
WO2002090724A1 (de) * 2001-05-09 2002-11-14 Mtu Aero Engines Gmbh Mantelring
US6966752B2 (en) 2001-05-09 2005-11-22 Mtu Aero Engines Gmbh Casing ring
EP1288444A1 (de) * 2001-08-30 2003-03-05 Snecma Moteurs Befestigung von Statorelementen in einem Turbomaschinengehäuse
WO2003018962A1 (fr) * 2001-08-30 2003-03-06 Snecma Moteurs Carter de stator de turbomachine
FR2829176A1 (fr) * 2001-08-30 2003-03-07 Snecma Moteurs Carter de stator de turbomachine
US7070387B2 (en) 2001-08-30 2006-07-04 Snecma Moteurs Gas turbine stator housing
CN1325765C (zh) * 2001-08-30 2007-07-11 斯内克马·莫特尔斯 涡轮机的定子的壳体
FR2846997A1 (fr) * 2002-11-07 2004-05-14 Snecma Moteurs Agencement de montage de secteurs de redresseur
EP2518278A1 (de) 2011-04-28 2012-10-31 Siemens Aktiengesellschaft Kühlleitung eines Turbinengehäuses mit stromaufwärts fliessender Kühlflüssigkeit
WO2012146481A1 (en) 2011-04-28 2012-11-01 Siemens Aktiengesellschaft Casing cooling duct
US9759092B2 (en) 2011-04-28 2017-09-12 Siemens Aktiengesellschaft Casing cooling duct
EP2696037A1 (de) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Abdichtung des Strömungskanals einer Strömungsmaschine
US9512734B2 (en) 2012-08-09 2016-12-06 MTU Aero Engines AG Sealing of the flow channel of a turbomachine
EP2725203A1 (de) * 2012-10-23 2014-04-30 MTU Aero Engines GmbH Kühlluftführung in einer Gehäusestruktur einer Strömungsmaschine
US9488069B2 (en) 2012-10-23 2016-11-08 MTU Aero Engines AG Cooling-air guidance in a housing structure of a turbomachine
EP3000990B1 (de) 2014-09-26 2019-05-29 Rolls-Royce plc Halter einer turbinenummantelung
EP3179053A1 (de) * 2015-12-07 2017-06-14 MTU Aero Engines GmbH Gehäusestruktur einer strömungsmaschine mit hitzeschutzschild
US10422247B2 (en) 2015-12-07 2019-09-24 MTU Aero Engines AG Housing structure of a turbomachine with heat protection shield
US10975721B2 (en) 2016-01-12 2021-04-13 Pratt & Whitney Canada Corp. Cooled containment case using internal plenum
CN109339873A (zh) * 2018-09-30 2019-02-15 东方电气集团东方汽轮机有限公司 用于高背压供热的汽轮机末级叶片保护装置

Also Published As

Publication number Publication date
GB9306719D0 (en) 1993-06-02

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