GB1484288A - Gas turbine engines - Google Patents

Gas turbine engines

Info

Publication number
GB1484288A
GB1484288A GB5299874A GB5299874A GB1484288A GB 1484288 A GB1484288 A GB 1484288A GB 5299874 A GB5299874 A GB 5299874A GB 5299874 A GB5299874 A GB 5299874A GB 1484288 A GB1484288 A GB 1484288A
Authority
GB
United Kingdom
Prior art keywords
member
projections
annular
dec
ring
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.)
Expired
Application number
GB5299874A
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 PLC
Original Assignee
Rolls Royce PLC
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 PLC filed Critical Rolls Royce PLC
Priority to GB5299874A priority Critical patent/GB1484288A/en
Publication of GB1484288A publication Critical patent/GB1484288A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18Adjusting 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

Abstract

1484288 Gas turbines ROLLS-ROYCE (1971) Ltd 3 Dec 1975 [7 Dec 1974] 52998/74 Heading F1T A turbine rotor blade tip seal ring 21 is mounted on the casing by a first annular member 19 which expands rapidly on heating up, on starting the engine, but which is restrained from contracting rapidly on cooling down by a second more massive annular member 27 co-operating with the first annular member. As shown, the sealing ring 21 is formed from segments mounted on member 19 by lip 25 at one end and dowel rods 22 at the other. The member 19, has projections 30, 31 resting on similar projections 29, 28 on member 27, which allow member 19 to expand relative to member 27 but restrain it from contracting relative thereto after member 27 has also expanded. A layer 37 of abradable material is provided on the sealing ring. Hot air from the high-pressure compressor passes through holes 32 to a space 33 between member 19 at the ring 21 and, after initial expansion of member 19, between an annular gap between projections 28 and 31.
GB5299874A 1975-12-03 1975-12-03 Gas turbine engines Expired GB1484288A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB5299874A GB1484288A (en) 1975-12-03 1975-12-03 Gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5299874A GB1484288A (en) 1975-12-03 1975-12-03 Gas turbine engines

Publications (1)

Publication Number Publication Date
GB1484288A true GB1484288A (en) 1977-09-01

Family

ID=10466221

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5299874A Expired GB1484288A (en) 1975-12-03 1975-12-03 Gas turbine engines

Country Status (1)

Country Link
GB (1) GB1484288A (en)

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2360750A1 (en) * 1976-08-02 1978-03-03 Gen Electric A method of reducing the running clearance between a turbine rotor and the ferrule which surrounds
FR2407342A1 (en) * 1977-10-31 1979-05-25 Gen Electric support structure for a turbomachine
FR2412697A1 (en) * 1977-12-21 1979-07-20 United Technologies Corp adjustment system of the game tightness for a gas turbine engine
FR2416345A1 (en) * 1978-01-31 1979-08-31 Snecma A impingement cooling of the sealing rings of turbine of a turbojet
DE2940308A1 (en) * 1978-10-06 1980-04-17 Snecma Arrangement for temperature control in gas turbines
DE2907748A1 (en) * 1979-02-28 1980-09-04 Mtu Muenchen Gmbh Device for minimizing and maintaining the shovel tip games existing with axial turbines, in particular for gas turbine engines
US4303371A (en) * 1978-06-05 1981-12-01 General Electric Company Shroud support with impingement baffle
FR2491138A1 (en) * 1980-10-01 1982-04-02 United Technologies Corp Method for controlling the radial game between the fins and the stator in a gas turbine engine and gas turbine engine with a device for implementing the method
FR2494764A1 (en) * 1980-11-22 1982-05-28 Rolls Royce Device for adjusting the expansion and contraction speed of the turbine blades of a gas turbine engine
US4419044A (en) * 1980-12-18 1983-12-06 Rolls-Royce Limited Gas turbine engine
FR2540560A1 (en) * 1983-02-03 1984-08-10 Snecma Device for sealing mobile blades of a turbomachine
FR2540937A1 (en) * 1983-02-10 1984-08-17 Snecma Ring for a turbine machine turbine rotor
FR2548733A1 (en) * 1983-07-07 1985-01-11 Snecma Device for sealing mobile turbine carriers
FR2560293A1 (en) * 1984-02-29 1985-08-30 Snecma Device for fixing a sealing ring for controlling the clearances of a turbomachine labyrinth seal
FR2570764A1 (en) * 1984-09-27 1986-03-28 Snecma Device for automatically controlling the play of a turbomachine labyrinth seal
GB2169037A (en) * 1984-12-21 1986-07-02 United Technologies Corp Coolable turbomachine seal segment having interrupted mounting flanges
FR2577281A1 (en) * 1985-02-13 1986-08-14 Snecma Turbomachine casing associated with a device for adjusting the game between mobile aubes and carter
US4642024A (en) * 1984-12-05 1987-02-10 United Technologies Corporation Coolable stator assembly for a rotary machine
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US4679981A (en) * 1984-11-22 1987-07-14 S.N.E.C.M.A. Turbine ring for a gas turbine engine
US4730982A (en) * 1986-06-18 1988-03-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Assembly for controlling the flow of cooling air in an engine turbine
US4732534A (en) * 1985-10-02 1988-03-22 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Rotor blade jacket for axial gas turbines
GB2195715A (en) * 1986-10-08 1988-04-13 Rolls Royce Plc Rotor blade tip-shroud
US4767260A (en) * 1986-11-07 1988-08-30 United Technologies Corporation Stator vane platform cooling means
EP0381895A1 (en) * 1989-02-10 1990-08-16 ROLLS-ROYCE plc A blade tip clearance control arrangement for a gas turbine engine
GB2251895A (en) * 1980-10-03 1992-07-22 Rolls Royce Gas turbine shroud ring
FR2685936A1 (en) * 1992-01-08 1993-07-09 Snecma Device for controlling the games of a turbomachine compressor housing.
GB2267129A (en) * 1992-05-19 1993-11-24 Rolls Royce Plc Rotor shroud assembly.
FR2716496A1 (en) * 1982-12-31 1995-08-25 Snecma Seals for moving blades of turbo-machinery with control of play in real time
EP0770761A1 (en) * 1995-10-23 1997-05-02 United Technologies Corporation Rotor blade outer tip seal apparatus
US6254344B1 (en) 1999-01-06 2001-07-03 Rolls-Royce Plc Seal
EP1048822A3 (en) * 1999-04-29 2002-07-31 Alstom Heat shield for a gas turbine
GB2420830A (en) * 2004-12-01 2006-06-07 Rolls Royce Plc Casing arrangement
US7147431B2 (en) * 2002-11-27 2006-12-12 Rolls-Royce Plc Cooled turbine assembly
US7938621B1 (en) * 1997-12-03 2011-05-10 Rolls-Royce Plc Blade tip clearance system
CN102562169A (en) * 2010-11-29 2012-07-11 阿尔斯通技术有限公司 Gas turbine of the axial flow type
CN102686832A (en) * 2009-12-23 2012-09-19 涡轮梅坎公司 Method for cooling turbine stators and cooling system for implementing said method

Cited By (59)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2360750A1 (en) * 1976-08-02 1978-03-03 Gen Electric A method of reducing the running clearance between a turbine rotor and the ferrule which surrounds
FR2407342A1 (en) * 1977-10-31 1979-05-25 Gen Electric support structure for a turbomachine
FR2412697A1 (en) * 1977-12-21 1979-07-20 United Technologies Corp adjustment system of the game tightness for a gas turbine engine
FR2416345A1 (en) * 1978-01-31 1979-08-31 Snecma A impingement cooling of the sealing rings of turbine of a turbojet
US4303371A (en) * 1978-06-05 1981-12-01 General Electric Company Shroud support with impingement baffle
DE2940308A1 (en) * 1978-10-06 1980-04-17 Snecma Arrangement for temperature control in gas turbines
FR2438165A1 (en) * 1978-10-06 1980-04-30 Snecma Temperature control device for gas turbines
US4329113A (en) * 1978-10-06 1982-05-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Temperature control device for gas turbines
DE2907748A1 (en) * 1979-02-28 1980-09-04 Mtu Muenchen Gmbh Device for minimizing and maintaining the shovel tip games existing with axial turbines, in particular for gas turbine engines
FR2491138A1 (en) * 1980-10-01 1982-04-02 United Technologies Corp Method for controlling the radial game between the fins and the stator in a gas turbine engine and gas turbine engine with a device for implementing the method
GB2251895A (en) * 1980-10-03 1992-07-22 Rolls Royce Gas turbine shroud ring
GB2251895B (en) * 1980-10-03 1992-12-09 Rolls Royce Gas turbine engine
FR2494764A1 (en) * 1980-11-22 1982-05-28 Rolls Royce Device for adjusting the expansion and contraction speed of the turbine blades of a gas turbine engine
US4419044A (en) * 1980-12-18 1983-12-06 Rolls-Royce Limited Gas turbine engine
FR2724973A1 (en) * 1982-12-31 1996-03-29 Snecma Turbomachine movable blade sealing device with active control of play in real time
FR2716496A1 (en) * 1982-12-31 1995-08-25 Snecma Seals for moving blades of turbo-machinery with control of play in real time
US4527385A (en) * 1983-02-03 1985-07-09 Societe Nationale d'Etude et Je Construction de Moteurs d'Aviation "S.N.E.C.M.A." Sealing device for turbine blades of a turbojet engine
EP0115984A1 (en) * 1983-02-03 1984-08-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Sealing means for rotor blades of a gas-turbine
FR2540560A1 (en) * 1983-02-03 1984-08-10 Snecma Device for sealing mobile blades of a turbomachine
FR2540937A1 (en) * 1983-02-10 1984-08-17 Snecma Ring for a turbine machine turbine rotor
EP0132182A1 (en) * 1983-07-07 1985-01-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbine blade tip seal
FR2548733A1 (en) * 1983-07-07 1985-01-11 Snecma Device for sealing mobile turbine carriers
FR2560293A1 (en) * 1984-02-29 1985-08-30 Snecma Device for fixing a sealing ring for controlling the clearances of a turbomachine labyrinth seal
EP0176447A1 (en) * 1984-09-27 1986-04-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Apparatus for the automatic control of the play of a labyrinth seal of a turbo machine
FR2570764A1 (en) * 1984-09-27 1986-03-28 Snecma Device for automatically controlling the play of a turbomachine labyrinth seal
US4662821A (en) * 1984-09-27 1987-05-05 Societe Nationale D'etude Et De Construction De Moteur D'aviation S.N.E.C.M.A. Automatic control device of a labyrinth seal clearance in a turbo jet engine
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US4679981A (en) * 1984-11-22 1987-07-14 S.N.E.C.M.A. Turbine ring for a gas turbine engine
US4642024A (en) * 1984-12-05 1987-02-10 United Technologies Corporation Coolable stator assembly for a rotary machine
US4650395A (en) * 1984-12-21 1987-03-17 United Technologies Corporation Coolable seal segment for a rotary machine
GB2169037B (en) * 1984-12-21 1989-09-20 United Technologies Corp Coolable seal segment for a rotary machine
GB2169037A (en) * 1984-12-21 1986-07-02 United Technologies Corp Coolable turbomachine seal segment having interrupted mounting flanges
FR2577281A1 (en) * 1985-02-13 1986-08-14 Snecma Turbomachine casing associated with a device for adjusting the game between mobile aubes and carter
US4787817A (en) * 1985-02-13 1988-11-29 Societe Nationale D'etude Et De Construction De Moteurs D-Aviation (Snecma) Device for monitoring clearance between rotor blades and a housing
EP0192556A1 (en) * 1985-02-13 1986-08-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbine cylinder with a device to adjust the tip clearance between the turbine blades and the cylinder
US4732534A (en) * 1985-10-02 1988-03-22 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Rotor blade jacket for axial gas turbines
US4730982A (en) * 1986-06-18 1988-03-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Assembly for controlling the flow of cooling air in an engine turbine
GB2195715A (en) * 1986-10-08 1988-04-13 Rolls Royce Plc Rotor blade tip-shroud
US4844688A (en) * 1986-10-08 1989-07-04 Rolls-Royce Plc Gas turbine engine control system
GB2195715B (en) * 1986-10-08 1990-10-10 Rolls Royce Plc Gas turbine engine rotor blade clearance control
US4767260A (en) * 1986-11-07 1988-08-30 United Technologies Corporation Stator vane platform cooling means
EP0381895A1 (en) * 1989-02-10 1990-08-16 ROLLS-ROYCE plc A blade tip clearance control arrangement for a gas turbine engine
FR2685936A1 (en) * 1992-01-08 1993-07-09 Snecma Device for controlling the games of a turbomachine compressor housing.
US5314303A (en) * 1992-01-08 1994-05-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Device for checking the clearances of a gas turbine compressor casing
GB2267129A (en) * 1992-05-19 1993-11-24 Rolls Royce Plc Rotor shroud assembly.
US5330321A (en) * 1992-05-19 1994-07-19 Rolls Royce Plc Rotor shroud assembly
GB2267129B (en) * 1992-05-19 1995-09-06 Rolls Royce Plc Rotor shroud assembly
EP0770761A1 (en) * 1995-10-23 1997-05-02 United Technologies Corporation Rotor blade outer tip seal apparatus
US7938621B1 (en) * 1997-12-03 2011-05-10 Rolls-Royce Plc Blade tip clearance system
US6254344B1 (en) 1999-01-06 2001-07-03 Rolls-Royce Plc Seal
EP1048822A3 (en) * 1999-04-29 2002-07-31 Alstom Heat shield for a gas turbine
US7147431B2 (en) * 2002-11-27 2006-12-12 Rolls-Royce Plc Cooled turbine assembly
GB2420830A (en) * 2004-12-01 2006-06-07 Rolls Royce Plc Casing arrangement
GB2420830B (en) * 2004-12-01 2007-01-03 Rolls Royce Plc Improved casing arrangement
US7140836B2 (en) 2004-12-01 2006-11-28 Rolls Royce Plc Casing arrangement
CN102686832A (en) * 2009-12-23 2012-09-19 涡轮梅坎公司 Method for cooling turbine stators and cooling system for implementing said method
US9334754B2 (en) 2010-11-29 2016-05-10 Alstom Technology Ltd. Axial flow gas turbine
CN102562169A (en) * 2010-11-29 2012-07-11 阿尔斯通技术有限公司 Gas turbine of the axial flow type
CN102562169B (en) * 2010-11-29 2015-04-08 阿尔斯通技术有限公司 Gas turbine of the axial flow type

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee