US20040219011A1 - 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
US20040219011A1
US20040219011A1 US10/428,219 US42821903A US2004219011A1 US 20040219011 A1 US20040219011 A1 US 20040219011A1 US 42821903 A US42821903 A US 42821903A US 2004219011 A1 US2004219011 A1 US 2004219011A1
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US
United States
Prior art keywords
case
shroud
control system
clearance control
blade
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.)
Abandoned
Application number
US10/428,219
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English (en)
Inventor
Robert Albers
Rafael 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
Priority to US10/428,219 priority Critical patent/US20040219011A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ALBERS, ROBERT J., BOYLE, MARCIA, RUIZ, RAFAEL
Priority to JP2004135246A priority patent/JP2004332731A/ja
Priority to EP04252521A priority patent/EP1475516A1/en
Priority to CNA2004100421045A priority patent/CN1542259A/zh
Publication of US20040219011A1 publication Critical patent/US20040219011A1/en
Abandoned legal-status Critical Current

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    • 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.
  • a system and method are proposed wherein casing elastic deflection is used to improve active clearance control of a high-pressure turbine.
  • 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.
  • FIG. 1 is a schematic illustration of a single stage active clearance control system of the type that may employ the casing mechanical deflection technique of the present invention
  • FIG. 2 is a schematic illustration of a dual stage active clearance control system of the type that may employ the casing mechanical deflection technique of the present invention
  • FIG. 3 illustrates the thin case active clearance control according to the present invention
  • FIG. 4 is a diagram that shows the relation between pressure and rotor speed for idle to cruise conditions
  • FIG. 5 is a diagram comparing the radial deflection of the rotor and stator for a state of the art system and for the system applying the present invention.
  • FIG. 6 illustrates an alternative embodiment of the thin case active clearance control according to the present invention.
  • 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 shroud 16 is attached to the case of the ACC by a hanger 22 . Case growth causes the shroud 16 to move radially.
  • 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 .
  • 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US10/428,219 2003-05-02 2003-05-02 High pressure turbine elastic clearance control system and method Abandoned US20040219011A1 (en)

Priority Applications (4)

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
JP2004135246A JP2004332731A (ja) 2003-05-02 2004-04-30 高圧タービンの弾性間隙制御システム及び方法
EP04252521A EP1475516A1 (en) 2003-05-02 2004-04-30 High pressure turbine elastic clearance control system and method
CNA2004100421045A CN1542259A (zh) 2003-05-02 2004-04-30 高压涡轮机弹性间隙控制系统和方法

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
US20040219011A1 true US20040219011A1 (en) 2004-11-04

Family

ID=32990469

Family Applications (1)

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

Country Status (4)

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

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050089401A1 (en) * 2003-08-15 2005-04-28 Phipps Anthony B. Turbine blade tip clearance system
US20050254939A1 (en) * 2004-03-26 2005-11-17 Thomas Wunderlich Arrangement for the automatic running gap control on a two or multi-stage turbine
US20060005529A1 (en) * 2004-07-09 2006-01-12 Penda Allan R Blade clearance control
US20060013681A1 (en) * 2004-05-17 2006-01-19 Cardarella L J Jr Turbine case reinforcement in a gas turbine jet engine
US20060059889A1 (en) * 2004-09-23 2006-03-23 Cardarella Louis J Jr Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
US20090037035A1 (en) * 2007-08-03 2009-02-05 John Erik Hershey Aircraft gas turbine engine blade tip clearance control
US20090053041A1 (en) * 2007-08-22 2009-02-26 Pinero Hector M Gas turbine engine case for clearance control
US20120027572A1 (en) * 2009-03-09 2012-02-02 Snecma Propulsion Solide, Le Haillan Turbine ring assembly
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
US9266618B2 (en) 2013-11-18 2016-02-23 Honeywell International Inc. Gas turbine engine turbine blade tip active clearance control system and method
US20160146049A1 (en) * 2014-11-25 2016-05-26 United Technologies Corporation Sealing interface for a case of a gas turbine engine
US20160333703A1 (en) * 2015-05-11 2016-11-17 General Electric Company Turbine shroud segment assembly with expansion joints
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US9874104B2 (en) 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
US20180156069A1 (en) * 2015-05-22 2018-06-07 Safran Aircraft Engines Turbine ring assembly with axial retention
CN108138576A (zh) * 2015-10-05 2018-06-08 赛峰航空器发动机 具有轴向保持的涡轮环组件
US10309244B2 (en) 2013-12-12 2019-06-04 General Electric Company CMC shroud support system
US10344769B2 (en) 2016-07-18 2019-07-09 United Technologies Corporation Clearance control between rotating and stationary structures
US10378387B2 (en) 2013-05-17 2019-08-13 General Electric Company CMC shroud support system of a gas turbine
US10400619B2 (en) 2014-06-12 2019-09-03 General Electric Company Shroud hanger assembly
US10465558B2 (en) 2014-06-12 2019-11-05 General Electric Company Multi-piece shroud hanger assembly
US11668207B2 (en) 2014-06-12 2023-06-06 General Electric Company Shroud hanger assembly

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Publication number Priority date Publication date Assignee Title
FR2933458B1 (fr) * 2008-07-01 2010-09-03 Snecma Compresseur axialo-centrifuge a systeme de pilotage
FR2949810B1 (fr) 2009-09-04 2013-06-28 Turbomeca Dispositif de support d'un anneau de turbine, turbine avec un tel dispositif et turbomoteur avec une telle turbine
GB0916892D0 (en) 2009-09-28 2009-11-11 Rolls Royce Plc A casing component
FR2973069B1 (fr) * 2011-03-24 2014-09-12 Snecma Anneau de carter de stator de turbomachine
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
US10443417B2 (en) * 2015-09-18 2019-10-15 General Electric Company Ceramic matrix composite ring shroud retention methods-finger seals with stepped shroud interface
EP3332894A1 (de) * 2016-12-08 2018-06-13 Siemens Aktiengesellschaft Verfahren zur herstellung eines gasturbinenbauteils
US10968782B2 (en) * 2017-01-18 2021-04-06 Raytheon Technologies Corporation Rotatable vanes
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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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
US4596116A (en) * 1983-02-10 1986-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Sealing ring for a turbine rotor of a turbo machine and turbo machine installations provided with such rings
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
US20040018084A1 (en) * 2002-05-10 2004-01-29 Halliwell Mark A. Gas turbine blade tip clearance control structure

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DE2907748A1 (de) * 1979-02-28 1980-09-04 Motoren Turbinen Union Einrichtung zur minimierung und konstanthaltung der bei axialturbinen vorhandenen schaufelspitzenspiele, insbesondere fuer gasturbinentriebwerke
GB2117843B (en) * 1982-04-01 1985-11-06 Rolls Royce Compressor shrouds
FR2724973B1 (fr) * 1982-12-31 1996-12-13 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine avec controle actif des jeux en temps reel et methode de determination dudit dispositif
GB2169962B (en) * 1985-01-22 1988-07-13 Rolls Royce Blade tip clearance control
DE69205568T2 (de) * 1991-04-02 1996-04-11 Rolls Royce Plc Turbinengehaeuse.
US6116852A (en) * 1997-12-11 2000-09-12 Pratt & Whitney Canada Corp. Turbine passive thermal valve for improved tip clearance control
DE19756734A1 (de) * 1997-12-19 1999-06-24 Bmw Rolls Royce Gmbh Passives Spalthaltungssystem einer Gasturbine
JP2000220472A (ja) * 1998-12-23 2000-08-08 United Technol Corp <Utc> ファンケ―スライナ―

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* Cited by examiner, † Cited by third party
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
US4596116A (en) * 1983-02-10 1986-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Sealing ring for a turbine rotor of a turbo machine and turbo machine installations provided with such rings
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
US20040018084A1 (en) * 2002-05-10 2004-01-29 Halliwell Mark A. Gas turbine blade tip clearance control structure

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050089401A1 (en) * 2003-08-15 2005-04-28 Phipps Anthony B. Turbine blade tip clearance system
US7524164B2 (en) * 2004-03-26 2009-04-28 Rolls-Royce Deutschland Ltd & Co Kg Arrangement for the automatic running gap control on a two or multi-stage turbine
US20050254939A1 (en) * 2004-03-26 2005-11-17 Thomas Wunderlich Arrangement for the automatic running gap control on a two or multi-stage turbine
US20060013681A1 (en) * 2004-05-17 2006-01-19 Cardarella L J Jr Turbine case reinforcement in a gas turbine jet engine
US20060005529A1 (en) * 2004-07-09 2006-01-12 Penda Allan R Blade clearance control
US7596954B2 (en) 2004-07-09 2009-10-06 United Technologies Corporation Blade clearance control
US8317456B2 (en) 2004-09-23 2012-11-27 Carlton Forge Works Fan case reinforcement in a gas turbine jet engine
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
US20060059889A1 (en) * 2004-09-23 2006-03-23 Cardarella Louis J Jr 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
US20090037035A1 (en) * 2007-08-03 2009-02-05 John Erik Hershey Aircraft gas turbine engine blade tip clearance control
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
US20090053041A1 (en) * 2007-08-22 2009-02-26 Pinero Hector M Gas turbine engine case for clearance control
US9080463B2 (en) * 2009-03-09 2015-07-14 Snecma Turbine ring assembly
US20120027572A1 (en) * 2009-03-09 2012-02-02 Snecma Propulsion Solide, Le Haillan Turbine ring assembly
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
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
US10309244B2 (en) 2013-12-12 2019-06-04 General Electric Company CMC shroud support system
US11668207B2 (en) 2014-06-12 2023-06-06 General Electric Company Shroud hanger assembly
US11092029B2 (en) 2014-06-12 2021-08-17 General Electric Company Shroud hanger assembly
US10465558B2 (en) 2014-06-12 2019-11-05 General Electric Company Multi-piece shroud hanger assembly
US10400619B2 (en) 2014-06-12 2019-09-03 General Electric Company Shroud hanger assembly
US20160146049A1 (en) * 2014-11-25 2016-05-26 United Technologies Corporation Sealing interface for a case of a gas turbine engine
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
US20160333703A1 (en) * 2015-05-11 2016-11-17 General Electric Company Turbine shroud segment assembly with expansion joints
US20180156069A1 (en) * 2015-05-22 2018-06-07 Safran Aircraft Engines Turbine ring assembly with axial retention
US10690007B2 (en) * 2015-05-22 2020-06-23 Safran Aircraft Engines Turbine ring assembly with axial retention
US20190040758A1 (en) * 2015-10-05 2019-02-07 Safran Aircraft Engines Turbine ring assembly with axial retention
CN108138576A (zh) * 2015-10-05 2018-06-08 赛峰航空器发动机 具有轴向保持的涡轮环组件
US10787924B2 (en) * 2015-10-05 2020-09-29 Safran Aircraft Engines Turbine ring assembly with axial retention
US10344769B2 (en) 2016-07-18 2019-07-09 United Technologies Corporation Clearance control between rotating and stationary structures

Also Published As

Publication number Publication date
CN1542259A (zh) 2004-11-03
EP1475516A1 (en) 2004-11-10
JP2004332731A (ja) 2004-11-25

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Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ALBERS, ROBERT J.;RUIZ, RAFAEL;BOYLE, MARCIA;REEL/FRAME:014041/0944

Effective date: 20030428

STCB Information on status: application discontinuation

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