EP0924388A3 - System to keep the blade tip clearance in a gas turbine constant - Google Patents

System to keep the blade tip clearance in a gas turbine constant Download PDF

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Publication number
EP0924388A3
EP0924388A3 EP98121690A EP98121690A EP0924388A3 EP 0924388 A3 EP0924388 A3 EP 0924388A3 EP 98121690 A EP98121690 A EP 98121690A EP 98121690 A EP98121690 A EP 98121690A EP 0924388 A3 EP0924388 A3 EP 0924388A3
Authority
EP
European Patent Office
Prior art keywords
turbine
gas turbine
annular chamber
duct system
gap
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.)
Granted
Application number
EP98121690A
Other languages
German (de)
French (fr)
Other versions
EP0924388B1 (en
EP0924388A2 (en
Inventor
Alexander Böck
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 Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP0924388A2 publication Critical patent/EP0924388A2/en
Publication of EP0924388A3 publication Critical patent/EP0924388A3/en
Application granted granted Critical
Publication of EP0924388B1 publication Critical patent/EP0924388B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • 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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Die Erfindung betrifft ein passives Spalthaltungssystem im Turbinenteil einer Gasturbine, in deren Turbinengehäuse neben Leitschaufeln auf einem Rotor angeordnete, vorzugsweise ein Deckband aufweisende Laufschaufeln vorgesehen sind, deren oder dessen Spitzen von im Turbinengehäuse aufgehängten Mantelringsegmenten unter Bildung eines von einem Temperierkanalsystem hinsichtlich seiner Breite gesteuerten Spaltes umgeben sind, wobei diesem Temperierkanalsystem ein vom Verdichterteil der Gasturbine an deren Brennkammer vorebi geförderter Luftstrom zuführbar ist, der über eine Vielzahl von Zumessbohrungen in eine von einem Statorring begrenzte Ringkammer gelangt. Erfindungsgemäß ist bevorzugt innerhalb der Ringkammer ein mit den Zumessbohrungen zusammenwirkender Blendenring vorgesehen, der in Abhängigkeit von der Temperatur des dem Temperierkanalsystem zugeführten Luftstromes diese Zumessbohrungen mehr oder weniger verschließt, wobei über einen Spalt zwischen dem Statorring und den Mantelringsegmenten zumindest bei niedriger Turbinenlast ein Bruchteil des über die Leitschaufeln und Laufschaufeln strömenden Heißgases in die Ringkammer gelangen kann.

Figure 00000001
The invention relates to a passive gap holding system in the turbine part of a gas turbine, in the turbine housing of which, in addition to guide vanes, rotor blades arranged on a rotor, preferably having a shroud, are provided, the tips of which are surrounded by jacket ring segments suspended in the turbine housing to form a gap controlled in terms of its width by a temperature control duct system are, this tempering duct system from the compressor part of the gas turbine at its combustion chamber vorebi supplied air flow can be fed through a plurality of metering holes in an annular chamber delimited by a stator ring. According to the invention, an orifice ring which interacts with the metering bores is preferably provided within the annular chamber and more or less closes these metering bores as a function of the temperature of the air flow supplied to the temperature control duct system, a fraction of which over a gap between the stator ring and the jacket ring segments, at least when the turbine load is low the guide vanes and blades flowing hot gas can get into the annular chamber.
Figure 00000001
EP98121690A 1997-12-19 1998-11-13 System to keep the blade tip clearance in a gas turbine constant Expired - Lifetime EP0924388B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19756734 1997-12-19
DE19756734A DE19756734A1 (en) 1997-12-19 1997-12-19 Passive gap system of a gas turbine

Publications (3)

Publication Number Publication Date
EP0924388A2 EP0924388A2 (en) 1999-06-23
EP0924388A3 true EP0924388A3 (en) 2000-08-16
EP0924388B1 EP0924388B1 (en) 2003-09-24

Family

ID=7852654

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98121690A Expired - Lifetime EP0924388B1 (en) 1997-12-19 1998-11-13 System to keep the blade tip clearance in a gas turbine constant

Country Status (3)

Country Link
US (1) US6126390A (en)
EP (1) EP0924388B1 (en)
DE (2) DE19756734A1 (en)

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US20040219011A1 (en) * 2003-05-02 2004-11-04 General Electric Company High pressure turbine elastic clearance control system and method
US7086233B2 (en) * 2003-11-26 2006-08-08 Siemens Power Generation, Inc. Blade tip clearance control
US7452184B2 (en) * 2004-12-13 2008-11-18 Pratt & Whitney Canada Corp. Airfoil platform impingement cooling
US7708518B2 (en) * 2005-06-23 2010-05-04 Siemens Energy, Inc. Turbine blade tip clearance control
FR2899273B1 (en) * 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS ON A TURBINE HOUSING OF A TURBOMACHINE
US7686575B2 (en) 2006-08-17 2010-03-30 Siemens Energy, Inc. Inner ring with independent thermal expansion for mounting gas turbine flow path components
US7690885B2 (en) * 2006-11-30 2010-04-06 General Electric Company Methods and system for shielding cooling air to facilitate cooling integral turbine nozzle and shroud assemblies
US8296037B2 (en) * 2008-06-20 2012-10-23 General Electric Company Method, system, and apparatus for reducing a turbine clearance
EP2239423A1 (en) * 2009-03-31 2010-10-13 Siemens Aktiengesellschaft Axial turbomachine with passive blade tip gap control
GB0908373D0 (en) * 2009-05-15 2009-06-24 Rolls Royce Plc Fluid flow control device
US20100296912A1 (en) 2009-05-22 2010-11-25 General Electric Company Active Rotor Alignment Control System And Method
US8177483B2 (en) * 2009-05-22 2012-05-15 General Electric Company Active casing alignment control system and method
US8342798B2 (en) 2009-07-28 2013-01-01 General Electric Company System and method for clearance control in a rotary machine
GB2477736B (en) * 2010-02-10 2014-04-09 Rolls Royce Plc A seal arrangement
US20110255959A1 (en) 2010-04-15 2011-10-20 General Electric Company Turbine alignment control system and method
US8651809B2 (en) 2010-10-13 2014-02-18 General Electric Company Apparatus and method for aligning a turbine casing
CH704124A1 (en) * 2010-11-19 2012-05-31 Alstom Technology Ltd Rotating machine, in particular gas turbine.
RU2547351C2 (en) * 2010-11-29 2015-04-10 Альстом Текнолоджи Лтд Axial gas turbine
RU2543101C2 (en) * 2010-11-29 2015-02-27 Альстом Текнолоджи Лтд Axial gas turbine
RU2547542C2 (en) * 2010-11-29 2015-04-10 Альстом Текнолоджи Лтд Axial gas turbine
US8932002B2 (en) 2010-12-03 2015-01-13 Hamilton Sundstrand Corporation Air turbine starter
CH704995A1 (en) * 2011-05-24 2012-11-30 Alstom Technology Ltd Turbomachinery.
US8939709B2 (en) 2011-07-18 2015-01-27 General Electric Company Clearance control for a turbine
FR2983518B1 (en) * 2011-12-06 2014-02-07 Snecma UNLOCKING DEVICE FOR AXIAL STOP OF A SEALED CROWN CONTACTED BY A MOBILE WHEEL OF AIRCRAFT TURBOMACHINE MODULE
US9238971B2 (en) 2012-10-18 2016-01-19 General Electric Company Gas turbine casing thermal control device
US9422824B2 (en) 2012-10-18 2016-08-23 General Electric Company Gas turbine thermal control and related method
DE102013210876B4 (en) 2013-06-11 2015-02-26 MTU Aero Engines AG Composite component for thermal clearance control in a turbomachine and this turbomachine containing
EP2853685A1 (en) * 2013-09-25 2015-04-01 Siemens Aktiengesellschaft Insert element and gas turbine
ITFI20130237A1 (en) * 2013-10-14 2015-04-15 Nuovo Pignone Srl "SEALING CLEARANCE CONTROL IN TURBOMACHINES"
DE102013017713B4 (en) * 2013-10-24 2022-10-27 Man Energy Solutions Se turbomachine
US9266618B2 (en) 2013-11-18 2016-02-23 Honeywell International Inc. Gas turbine engine turbine blade tip active clearance control system and method
DE102014209057A1 (en) * 2014-05-14 2015-11-19 MTU Aero Engines AG Gas turbine casing assembly
DE102014217832A1 (en) * 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Cooling device and aircraft engine with cooling device
US10138752B2 (en) * 2016-02-25 2018-11-27 General Electric Company Active HPC clearance control
US10837637B2 (en) * 2016-03-22 2020-11-17 Raytheon Technologies Corporation Gas turbine engine having a heat shield
EP3324003B1 (en) 2016-11-18 2020-03-18 Ansaldo Energia Switzerland AG Blade to stator heat shield interface in a gas turbine
US10731500B2 (en) 2017-01-13 2020-08-04 Raytheon Technologies Corporation Passive tip clearance control with variable temperature flow
US10655495B2 (en) * 2017-02-24 2020-05-19 General Electric Company Spline for a turbine engine
US11236631B2 (en) 2018-11-19 2022-02-01 Rolls-Royce North American Technologies Inc. Mechanical iris tip clearance control
US11015475B2 (en) 2018-12-27 2021-05-25 Rolls-Royce Corporation Passive blade tip clearance control system for gas turbine engine
US11692448B1 (en) * 2022-03-04 2023-07-04 General Electric Company Passive valve assembly for a nozzle of a gas turbine engine

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Publication number Priority date Publication date Assignee Title
US3814313A (en) * 1968-10-28 1974-06-04 Gen Motors Corp Turbine cooling control valve
US3975901A (en) * 1974-07-31 1976-08-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Device for regulating turbine blade tip clearance
US4023731A (en) * 1974-12-19 1977-05-17 General Electric Company Thermal actuated valve for clearance control
US4005946A (en) * 1975-06-20 1977-02-01 United Technologies Corporation Method and apparatus for controlling stator thermal growth
GB1581566A (en) * 1976-08-02 1980-12-17 Gen Electric Minimum clearance turbomachine shroud apparatus
US4541775A (en) * 1983-03-30 1985-09-17 United Technologies Corporation Clearance control in turbine seals
US4613280A (en) * 1984-09-21 1986-09-23 Avco Corporation Passively modulated cooling of turbine shroud
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Also Published As

Publication number Publication date
EP0924388B1 (en) 2003-09-24
EP0924388A2 (en) 1999-06-23
DE59809709D1 (en) 2003-10-30
US6126390A (en) 2000-10-03
DE19756734A1 (en) 1999-06-24

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