EP1475516A1 - Système et procédé de réglage élastique du jeu d'extrémité d'une turbine à haute pression - Google Patents
Système et procédé de réglage élastique du jeu d'extrémité d'une turbine à haute pression Download PDFInfo
- Publication number
- EP1475516A1 EP1475516A1 EP04252521A EP04252521A EP1475516A1 EP 1475516 A1 EP1475516 A1 EP 1475516A1 EP 04252521 A EP04252521 A EP 04252521A EP 04252521 A EP04252521 A EP 04252521A EP 1475516 A1 EP1475516 A1 EP 1475516A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- case
- shroud
- blade
- control system
- clearance control
- 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- Withdrawn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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
Definitions
- the present invention relates to the active clearance control system of a high-pressure turbine and, more particularly, to casing mechanical deflection for the high-pressure turbine.
- the active clearance control system (ACC) of a high-pressure turbine (HPT) has two basic functions. The first is to maintain tight blade-shroud clearances during transient operation, to minimize exhaust gas temperature (EGT). The second is to close the tip clearances during steady-state operation to increase turbine efficiency and reduce fuel burn.
- the case will shrink or grow, depending on the air-cooling temperature and the effect on the temperature of the case. Changing the case temperature will result in a clearance change.
- the thermal part of the clearance system is a slow response deflection approximately 30-60 seconds.
- the present invention provides a system and method for achieving clearance control for a high-pressure turbine by means of casing mechanical deflection.
- An active clearance control system is provided to act on a blade that rotates near a shroud.
- the shroud is attached to a case at a shroud supporting location, or shroud hanger.
- a clearance is required between a tip of the blade and the shroud.
- the blade tip and shroud are surrounded with an elastic case. This case can deflect radially in response not only to thermal expansion, but also to a difference in pressures acting on the inner and outer diameters of the case.
- Modern gas turbine engine control systems typically require an active clearance control system for maintaining blade-shroud clearances and tip clearances during operation.
- the appropriate clearance 18 between the blade 14 and the shroud 16 is achieved by controlling the case 10 temperature.
- the case is heated and cooled by air coming from compressor mid stage 12 and discharge pressure source.
- the first stage turbine case is controlled by compressor discharge pressure air.
- the second stage is controlled by compressor inter-stage bleed air.
- the case is cooled by fan air in order to reduce case ring 25 temperatures.
- the shroud 16 is a piece of metal that defines the distances, or clearances, between the blade 14 tip and the shroud 16 itself.
- the purpose of the active clearance control system is to minimize-clearance 18. The larger the clearance, the less efficient the turbine will be.
- the shroud 16 is attached to the case of the ACC by a hanger 22. Case growth causes the shroud 16 to move radially. In the existing art, the case 10 grows only by thermal expansion. With the present invention, the case will deflect due to thermal expansion and pressure acting on the outer and inner diameter of the case.
- the present invention proposes a system and method for improving an existing high-pressure turbine active clearance control system by modifying the turbine case, as illustrated in Fig. 3.
- the elastic case 24 will be a continuous 360-degree shell flexible enough to deflect radially due to the difference between the pressures P low acting on the outer diameter of the case 24 and P high acting on the inner diameter of the case 24.
- the case 24 flexibility will be achieved by making the case average thickness in the locations supporting the hangers thin, so that the casing elastic deflection is increased from the prior art design.
- the thickness of the casing at the location where the shroud supports are attached to the casing will be substantially thicker than that proposed by the present invention, with the prior art configuration therefore having negligible casing deflection.
- the thickness will be thinner than the current design by eliminating the case rings 25, typically, by way of example only, on the order of approximately 0.1 inches to 0.2 inches, or otherwise significantly thinner than the 1 to 2 inch thickness of existing casings. It will be obvious to those skilled in the art, however, that the thickness can vary beyond the thickness of a preferred embodiment, still being thinner than the existing art provides for, without departing from the scope of the invention.
- the shrouds 16 will be attached to the case 24 by shroud hangers 22.
- the shroud and the case will be made of a high temperature alloy.
- the blade 14 to shroud 16 clearance 18 will change when the case 24 deflects radially due to pressure.
- the blade tip to shroud clearance will depend on the magnitude of the pressure acting on the case.
- the pressure acting on the case depends on the engine operating condition. Referring now to Fig. 4 the relationship between pressure and speed is shown.
- the present invention takes advantage of this pressure and speed, resulting in the illustration of Fig. 5.
- the pressure is at a minimum when the engine is at idle conditions, in region 26. It will reach a maximum during high power at low altitude, in region 28. At cruise conditions, in region 30, when the engine is at high altitudes, the pressure will decrease ( ⁇ 30% change) while the speed remains almost constant ( ⁇ 10% change).
- Fig. 5 illustrates the stator and rotor deflection when the elastic case of the present invention is applied to a single or dual stage high pressure turbine.
- the elasticity of the case is indicated by dotted line 32 in Fig. 5.
- the prior art stator response is shown by line 34, indicating the thermal expansion.
- the rotor response for both the invention and the prior art is shown by line 36, indicating disk elastic stretch and blade thermal expansion during periods of idle, acceleration and cruise.
- the present invention will provide a protection against airfoil to shroud contact due to instantaneous acceleration (reburst).
- the pressure will increase at nearly the same rate as the rotor speed during an instantaneous acceleration allowing the case to deflect to avoid airfoil to shroud contact (rubs).
- an alternative embodiment for the thin case active clearance control can be applied by modifying the case elastic deflection to account for airfoil tip loss over operation time.
- the alternative embodiment comprises a band 38 attached to the case outer diameter.
- the band is preferably comprised of any suitable high temperature alloy or coating.
- the band thickness will be sized depending on the amount of airfoil material loss.
- the band will cause the case elastic deflection to be less by the same amount of airfoil material loss.
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 |
---|---|---|---|
US10/428,219 US20040219011A1 (en) | 2003-05-02 | 2003-05-02 | High pressure turbine elastic clearance control system and method |
US428219 | 2003-05-02 |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1475516A1 true EP1475516A1 (fr) | 2004-11-10 |
Family
ID=32990469
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04252521A Withdrawn EP1475516A1 (fr) | 2003-05-02 | 2004-04-30 | Système et procédé de réglage élastique du jeu d'extrémité d'une turbine à haute pression |
Country Status (4)
Country | Link |
---|---|
US (1) | US20040219011A1 (fr) |
EP (1) | EP1475516A1 (fr) |
JP (1) | JP2004332731A (fr) |
CN (1) | CN1542259A (fr) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2418955A (en) * | 2004-07-09 | 2006-04-12 | United Technologies Corp | Blade tip clearance control |
WO2006046969A2 (fr) * | 2004-05-17 | 2006-05-04 | Cardarella L James Jr | Renforcement de carter de turbine dans un moteur propulseur a turbine a gaz |
WO2011026921A1 (fr) | 2009-09-04 | 2011-03-10 | Turbomeca | Dispositif de support d'un anneau de turbine, turbine avec un tel dispositif et turbomoteur avec une telle turbine |
FR2952965A1 (fr) * | 2009-11-25 | 2011-05-27 | Snecma | Isolation d'un rebord circonferentiel d'un carter externe de turbomachine vis-a-vis d'un secteur d'anneau correspondant |
CN102352778A (zh) * | 2011-10-20 | 2012-02-15 | 西北工业大学 | 一种用于主动控制涡轮叶尖间隙的电子机械式作动装置 |
US8191254B2 (en) | 2004-09-23 | 2012-06-05 | Carlton Forge Works | Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine |
FR2973069A1 (fr) * | 2011-03-24 | 2012-09-28 | Snecma | Anneau de carter de stator de turbomachine |
US8727709B2 (en) | 2009-09-28 | 2014-05-20 | Rolls-Royce Plc | Casing component |
EP3351732A1 (fr) * | 2017-01-18 | 2018-07-25 | United Technologies Corporation | Aubes rotatives |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2404953A (en) * | 2003-08-15 | 2005-02-16 | Rolls Royce Plc | Blade tip clearance system |
DE102004016222A1 (de) * | 2004-03-26 | 2005-10-06 | Rolls-Royce Deutschland Ltd & Co Kg | Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine |
US8126628B2 (en) * | 2007-08-03 | 2012-02-28 | General Electric Company | Aircraft gas turbine engine blade tip clearance control |
US8434997B2 (en) * | 2007-08-22 | 2013-05-07 | United Technologies Corporation | Gas turbine engine case for clearance control |
FR2933458B1 (fr) * | 2008-07-01 | 2010-09-03 | Snecma | Compresseur axialo-centrifuge a systeme de pilotage |
WO2010103213A1 (fr) * | 2009-03-09 | 2010-09-16 | Snecma | Ensemble d'anneau de turbine |
US9726043B2 (en) | 2011-12-15 | 2017-08-08 | General Electric Company | Mounting apparatus for low-ductility turbine shroud |
WO2014186099A1 (fr) | 2013-05-17 | 2014-11-20 | General Electric Company | Système de support de flasque cmc d'une turbine à gaz |
US9266618B2 (en) | 2013-11-18 | 2016-02-23 | Honeywell International Inc. | Gas turbine engine turbine blade tip active clearance control system and method |
JP6529013B2 (ja) | 2013-12-12 | 2019-06-12 | ゼネラル・エレクトリック・カンパニイ | Cmcシュラウド支持システム |
CA2951431C (fr) | 2014-06-12 | 2019-03-26 | General Electric Company | Ensemble dispositif de suspension de carenage a multiples pieces |
CA2951638A1 (fr) | 2014-06-12 | 2015-12-17 | General Electric Company | Ensemble dispositif de suspension de carenage |
CN106460560B (zh) | 2014-06-12 | 2018-11-13 | 通用电气公司 | 护罩吊架组件 |
US11008890B2 (en) * | 2014-11-25 | 2021-05-18 | Raytheon Technologies Corporation | Sealing interface for a case of a gas turbine engine |
US9874104B2 (en) | 2015-02-27 | 2018-01-23 | General Electric Company | Method and system for a ceramic matrix composite shroud hanger assembly |
US9915153B2 (en) * | 2015-05-11 | 2018-03-13 | General Electric Company | Turbine shroud segment assembly with expansion joints |
FR3036432B1 (fr) * | 2015-05-22 | 2019-04-19 | Safran Ceramics | Ensemble d'anneau de turbine avec maintien axial |
US10443417B2 (en) * | 2015-09-18 | 2019-10-15 | General Electric Company | Ceramic matrix composite ring shroud retention methods-finger seals with stepped shroud interface |
FR3041993B1 (fr) * | 2015-10-05 | 2019-06-21 | Safran Aircraft Engines | Ensemble d'anneau de turbine avec maintien axial |
US10344769B2 (en) | 2016-07-18 | 2019-07-09 | United Technologies Corporation | Clearance control between rotating and stationary structures |
EP3332894A1 (fr) * | 2016-12-08 | 2018-06-13 | Siemens Aktiengesellschaft | Procédé de fabrication d'un composant de turbine à gaz |
US10815816B2 (en) * | 2018-09-24 | 2020-10-27 | General Electric Company | Containment case active clearance control structure |
KR102579798B1 (ko) * | 2018-10-15 | 2023-09-15 | 한화에어로스페이스 주식회사 | 터보기기 |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4439982A (en) * | 1979-02-28 | 1984-04-03 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Arrangement for maintaining clearances between a turbine rotor and casing |
US4529355A (en) * | 1982-04-01 | 1985-07-16 | Rolls-Royce Limited | Compressor shrouds and shroud assemblies |
US4683716A (en) * | 1985-01-22 | 1987-08-04 | Rolls-Royce Plc | Blade tip clearance control |
US5407320A (en) * | 1991-04-02 | 1995-04-18 | Rolls-Royce, Plc | Turbine cowling having cooling air gap |
US5593278A (en) * | 1982-12-31 | 1997-01-14 | Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Gas turbine engine rotor blading sealing device |
EP1013894A2 (fr) * | 1998-12-23 | 2000-06-28 | United Technologies Corporation | Revêtement pour la virole d'une soufflante |
US6116852A (en) * | 1997-12-11 | 2000-09-12 | Pratt & Whitney Canada Corp. | Turbine passive thermal valve for improved tip clearance control |
US6126390A (en) * | 1997-12-19 | 2000-10-03 | Rolls-Royce Deutschland Gmbh | Passive clearance control system for a gas turbine |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3039737A (en) * | 1959-04-13 | 1962-06-19 | Int Harvester Co | Device for controlling clearance between rotor and shroud of a turbine |
US4513567A (en) * | 1981-11-02 | 1985-04-30 | United Technologies Corporation | Gas turbine engine active clearance control |
FR2540939A1 (fr) * | 1983-02-10 | 1984-08-17 | Snecma | Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux |
US4728255A (en) * | 1985-02-25 | 1988-03-01 | General Electric Company | Removable stiffening disk |
US6487491B1 (en) * | 2001-11-21 | 2002-11-26 | United Technologies Corporation | System and method of controlling clearance between turbine engine blades and case based on engine components thermal growth model |
GB2388407B (en) * | 2002-05-10 | 2005-10-26 | Rolls Royce Plc | Gas turbine blade tip clearance control structure |
-
2003
- 2003-05-02 US US10/428,219 patent/US20040219011A1/en not_active Abandoned
-
2004
- 2004-04-30 EP EP04252521A patent/EP1475516A1/fr not_active Withdrawn
- 2004-04-30 CN CNA2004100421045A patent/CN1542259A/zh active Pending
- 2004-04-30 JP JP2004135246A patent/JP2004332731A/ja not_active Withdrawn
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4439982A (en) * | 1979-02-28 | 1984-04-03 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Arrangement for maintaining clearances between a turbine rotor and casing |
US4529355A (en) * | 1982-04-01 | 1985-07-16 | Rolls-Royce Limited | Compressor shrouds and shroud assemblies |
US5593278A (en) * | 1982-12-31 | 1997-01-14 | Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Gas turbine engine rotor blading sealing device |
US4683716A (en) * | 1985-01-22 | 1987-08-04 | Rolls-Royce Plc | Blade tip clearance control |
US5407320A (en) * | 1991-04-02 | 1995-04-18 | Rolls-Royce, Plc | Turbine cowling having cooling air gap |
US6116852A (en) * | 1997-12-11 | 2000-09-12 | Pratt & Whitney Canada Corp. | Turbine passive thermal valve for improved tip clearance control |
US6126390A (en) * | 1997-12-19 | 2000-10-03 | Rolls-Royce Deutschland Gmbh | Passive clearance control system for a gas turbine |
EP1013894A2 (fr) * | 1998-12-23 | 2000-06-28 | United Technologies Corporation | Revêtement pour la virole d'une soufflante |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2006046969A2 (fr) * | 2004-05-17 | 2006-05-04 | Cardarella L James Jr | Renforcement de carter de turbine dans un moteur propulseur a turbine a gaz |
WO2006046969A3 (fr) * | 2004-05-17 | 2006-06-22 | Cardarella L James Jr | Renforcement de carter de turbine dans un moteur propulseur a turbine a gaz |
EP2314831A1 (fr) * | 2004-05-17 | 2011-04-27 | Carlton Forge Works | Renforcement de carter de turbine dans un moteur propulseur à turbine |
GB2418955B (en) * | 2004-07-09 | 2009-07-08 | United Technologies Corp | Blade clearance control |
GB2418955A (en) * | 2004-07-09 | 2006-04-12 | United Technologies Corp | Blade tip clearance control |
US8191254B2 (en) | 2004-09-23 | 2012-06-05 | Carlton Forge Works | Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine |
US8454298B2 (en) | 2004-09-23 | 2013-06-04 | Carlton Forge Works | Fan case reinforcement in a gas turbine jet engine |
US8317456B2 (en) | 2004-09-23 | 2012-11-27 | Carlton Forge Works | Fan case reinforcement in a gas turbine jet engine |
WO2011026921A1 (fr) | 2009-09-04 | 2011-03-10 | Turbomeca | Dispositif de support d'un anneau de turbine, turbine avec un tel dispositif et turbomoteur avec une telle turbine |
US8727709B2 (en) | 2009-09-28 | 2014-05-20 | Rolls-Royce Plc | Casing component |
WO2011064496A1 (fr) * | 2009-11-25 | 2011-06-03 | Snecma | Isolation d'un rebord circonférentiel d'un carter externe de turbomachine vis-à-vis d'un secteur d'anneau correspondant |
FR2952965A1 (fr) * | 2009-11-25 | 2011-05-27 | Snecma | Isolation d'un rebord circonferentiel d'un carter externe de turbomachine vis-a-vis d'un secteur d'anneau correspondant |
US8961117B2 (en) | 2009-11-25 | 2015-02-24 | Snecma | Insulating a circumferential rim of an outer casing of a turbine engine from a corresponding ring sector |
FR2973069A1 (fr) * | 2011-03-24 | 2012-09-28 | Snecma | Anneau de carter de stator de turbomachine |
CN102352778A (zh) * | 2011-10-20 | 2012-02-15 | 西北工业大学 | 一种用于主动控制涡轮叶尖间隙的电子机械式作动装置 |
CN102352778B (zh) * | 2011-10-20 | 2013-11-27 | 西北工业大学 | 一种用于主动控制涡轮叶尖间隙的电子机械式作动装置 |
EP3351732A1 (fr) * | 2017-01-18 | 2018-07-25 | United Technologies Corporation | Aubes rotatives |
US10968782B2 (en) | 2017-01-18 | 2021-04-06 | Raytheon Technologies Corporation | Rotatable vanes |
Also Published As
Publication number | Publication date |
---|---|
CN1542259A (zh) | 2004-11-03 |
US20040219011A1 (en) | 2004-11-04 |
JP2004332731A (ja) | 2004-11-25 |
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