EP0618349A1 - Turbinengehäuse für eine Gasturbine - Google Patents
Turbinengehäuse für eine Gasturbine Download PDFInfo
- 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- Withdrawn
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Images
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)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB939306719A GB9306719D0 (en) | 1993-03-31 | 1993-03-31 | A turbine assembly for a gas turbine engine |
GB9306719 | 1993-03-31 |
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)
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)
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 |
-
1993
- 1993-03-31 GB GB939306719A patent/GB9306719D0/en active Pending
-
1994
- 1994-03-03 EP EP94301535A patent/EP0618349A1/de not_active Withdrawn
Patent Citations (6)
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)
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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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): DE FR GB |
|
17P | Request for examination filed |
Effective date: 19940823 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN |
|
18W | Application withdrawn |
Withdrawal date: 19950223 |