EP1475516A1 - High pressure turbine elastic clearance control system and method - Google Patents

High pressure turbine elastic clearance control system and method Download PDF

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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Withdrawn
Application number
EP04252521A
Other languages
German (de)
English (en)
French (fr)
Inventor
Robert J. Albers
Rafel Ruiz
Marcia Boyle
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP1475516A1 publication Critical patent/EP1475516A1/en
Withdrawn legal-status Critical Current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
    • 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)
EP04252521A 2003-05-02 2004-04-30 High pressure turbine elastic clearance control system and method Withdrawn EP1475516A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US428219 1989-10-27
US10/428,219 US20040219011A1 (en) 2003-05-02 2003-05-02 High pressure turbine elastic clearance control system and method

Publications (1)

Publication Number Publication Date
EP1475516A1 true EP1475516A1 (en) 2004-11-10

Family

ID=32990469

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04252521A Withdrawn EP1475516A1 (en) 2003-05-02 2004-04-30 High pressure turbine elastic clearance control system and method

Country Status (4)

Country Link
US (1) US20040219011A1 (ja)
EP (1) EP1475516A1 (ja)
JP (1) JP2004332731A (ja)
CN (1) CN1542259A (ja)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2418955A (en) * 2004-07-09 2006-04-12 United Technologies Corp Blade tip clearance control
WO2006046969A2 (en) * 2004-05-17 2006-05-04 Cardarella L James Jr Turbine 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
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 (en) * 2017-01-18 2018-07-25 United Technologies Corporation Rotatable vanes

Families Citing this family (23)

* Cited by examiner, † Cited by third party
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
RU2522264C2 (ru) * 2009-03-09 2014-07-10 Снекма Сборка обоймы турбины
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US10378387B2 (en) 2013-05-17 2019-08-13 General Electric Company CMC shroud support system of a gas turbine
US9266618B2 (en) 2013-11-18 2016-02-23 Honeywell International Inc. Gas turbine engine turbine blade tip active clearance control system and method
EP3080403B1 (en) * 2013-12-12 2019-05-01 General Electric Company Cmc shroud support system
JP6574208B2 (ja) 2014-06-12 2019-09-11 ゼネラル・エレクトリック・カンパニイ シュラウドハンガアセンブリ
CN106460560B (zh) 2014-06-12 2018-11-13 通用电气公司 护罩吊架组件
JP6775425B2 (ja) 2014-06-12 2020-10-28 ゼネラル・エレクトリック・カンパニイ シュラウドハンガーアセンブリ
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 (de) * 2016-12-08 2018-06-13 Siemens Aktiengesellschaft Verfahren zur herstellung eines gasturbinenbauteils
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

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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 (en) * 1998-12-23 2000-06-28 United Technologies Corporation Fan case liner
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

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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

Patent Citations (8)

* Cited by examiner, † Cited by third party
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 (en) * 1998-12-23 2000-06-28 United Technologies Corporation Fan case liner

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006046969A2 (en) * 2004-05-17 2006-05-04 Cardarella L James Jr Turbine case reinforcement in a gas turbine jet engine
WO2006046969A3 (en) * 2004-05-17 2006-06-22 Cardarella L James Jr Turbine case reinforcement in a gas turbine jet engine
EP2314831A1 (en) * 2004-05-17 2011-04-27 Carlton Forge Works Turbine case reinforcement in a gas turbine jet engine
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 (en) * 2017-01-18 2018-07-25 United Technologies Corporation Rotatable vanes
US10968782B2 (en) 2017-01-18 2021-04-06 Raytheon Technologies Corporation Rotatable vanes

Also Published As

Publication number Publication date
US20040219011A1 (en) 2004-11-04
JP2004332731A (ja) 2004-11-25
CN1542259A (zh) 2004-11-03

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