GB1381277A - Sealing clearance control apparatus for gas turbine engines - Google Patents

Sealing clearance control apparatus for gas turbine engines

Info

Publication number
GB1381277A
GB1381277A GB4019071A GB4019071A GB1381277A GB 1381277 A GB1381277 A GB 1381277A GB 4019071 A GB4019071 A GB 4019071A GB 4019071 A GB4019071 A GB 4019071A GB 1381277 A GB1381277 A GB 1381277A
Authority
GB
United Kingdom
Prior art keywords
metallic
motor device
secured
ring
gas turbine
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
GB4019071A
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 GB4019071A priority Critical patent/GB1381277A/en
Publication of GB1381277A publication Critical patent/GB1381277A/en
Expired 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations

Landscapes

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

Abstract

1381277 Bi-metallic temperature responsive elements ROLLS-ROYCE (1971) Ltd 29 Aug 1972 [26 Aug 1971] 40190/71 Heading G1D [Also in Divisions Fl and F2] A gas turbine seal includes a bi-metallic motor device which causes axial movement of a circular sealing surface with change in temperature. In one arrangement, Fig.8, the motor device comprises rings 40, 41 secured together by part-spiral members 42. Since the latter have a different coefficient of expansion to one or other of rings 40, 41, heating of the assembly causes rotation of ring 41 relative to fixed ring 40. Inter-engaging helical splines (45), Fig.7 (not shown) cause the rotation to be accompanied by corresponding axial movement of ring 41 to maintain the sealing clearances. Wedge shaped fillets (44), Fig.10 (not shown) fill the spaces left by part-spiral members 42. In a modification, Fig.4, the motor device comprises a centre spine 24 secured on both sides to shims 27 and bi-metallic stacks 26, secured in turn to fixed end-plates 25. Each stack comprises laminae, e.g. of higher and lower specified nickel content, having different coefficients of expansion and secured together at alternate ends in the manner shown by laminae 21, 22 in Fig.3. Change in temperature causes each stack 26 to deform from its normal rectangular shape into a parallelogram causing centre spine 24 and an attached sealing surface to move to the left or right to maintain the sealing clearances.
GB4019071A 1971-08-26 1971-08-26 Sealing clearance control apparatus for gas turbine engines Expired GB1381277A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4019071A GB1381277A (en) 1971-08-26 1971-08-26 Sealing clearance control apparatus for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4019071A GB1381277A (en) 1971-08-26 1971-08-26 Sealing clearance control apparatus for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1381277A true GB1381277A (en) 1975-01-22

Family

ID=10413666

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4019071A Expired GB1381277A (en) 1971-08-26 1971-08-26 Sealing clearance control apparatus for gas turbine engines

Country Status (1)

Country Link
GB (1) GB1381277A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2395403A1 (en) * 1977-06-24 1979-01-19 Gen Electric IMPROVED TURBOMACHINE ROTOR PROTECTION RING BRACKET
FR2519374A1 (en) * 1982-01-07 1983-07-08 Snecma DEVICE FOR COOLING THE HEELS OF MOBILE BLADES OF A TURBINE
US4415307A (en) * 1980-06-09 1983-11-15 United Technologies Corporation Temperature regulation of air cycle refrigeration systems
US4447190A (en) * 1981-12-15 1984-05-08 Rolls-Royce Limited Fluid pressure control in a gas turbine engine
US4526511A (en) * 1982-11-01 1985-07-02 United Technologies Corporation Attachment for TOBI
FR2577280A1 (en) * 1985-02-12 1986-08-14 Rolls Royce GAS TURBINE ENGINE
US5142859A (en) * 1991-02-22 1992-09-01 Solar Turbines, Incorporated Turbine cooling system
US6146090A (en) * 1998-12-22 2000-11-14 General Electric Co. Cooling/heating augmentation during turbine startup/shutdown using a seal positioned by thermal response of turbine parts and consequent relative movement thereof
DE10347335A1 (en) * 2003-10-11 2005-05-12 Alstom Technology Ltd Baden Gas turbine with honeycomb heat shield, provided with discontinuous air cooling device for honeycomb
EP1876327A2 (en) * 2006-07-06 2008-01-09 United Technologies Corporation Seal for turbine engine
DE102008033560A1 (en) * 2008-07-17 2010-01-21 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine with adjustable vanes
CN109804138A (en) * 2016-10-13 2019-05-24 西门子股份公司 The thermomechanical actuator of bimetallic

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2395403A1 (en) * 1977-06-24 1979-01-19 Gen Electric IMPROVED TURBOMACHINE ROTOR PROTECTION RING BRACKET
US4415307A (en) * 1980-06-09 1983-11-15 United Technologies Corporation Temperature regulation of air cycle refrigeration systems
US4447190A (en) * 1981-12-15 1984-05-08 Rolls-Royce Limited Fluid pressure control in a gas turbine engine
JPH0115683B2 (en) * 1982-01-07 1989-03-20 Nashionaru Dechuudo E Do Konsutoryukushion De Motooru Dabiashion Soc
FR2519374A1 (en) * 1982-01-07 1983-07-08 Snecma DEVICE FOR COOLING THE HEELS OF MOBILE BLADES OF A TURBINE
EP0083896A1 (en) * 1982-01-07 1983-07-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Cooling device for the shroud of the rotor blades of a turbine
JPS58128401A (en) * 1982-01-07 1983-08-01 ソシエテ・ナシオナル・デテユ−ド・エ・ドウ・コンストリユクシオン・ドウ・モト−ル・ダヴイアシオン“エス・エヌ・ウ・セ・エム・ア−” Apparatus for cooling heel part of turbine blade
US4522557A (en) * 1982-01-07 1985-06-11 S.N.E.C.M.A. Cooling device for movable turbine blade collars
US4526511A (en) * 1982-11-01 1985-07-02 United Technologies Corporation Attachment for TOBI
FR2577280A1 (en) * 1985-02-12 1986-08-14 Rolls Royce GAS TURBINE ENGINE
US4702670A (en) * 1985-02-12 1987-10-27 Rolls-Royce Gas turbine engines
US5142859A (en) * 1991-02-22 1992-09-01 Solar Turbines, Incorporated Turbine cooling system
US6146090A (en) * 1998-12-22 2000-11-14 General Electric Co. Cooling/heating augmentation during turbine startup/shutdown using a seal positioned by thermal response of turbine parts and consequent relative movement thereof
DE10347335A1 (en) * 2003-10-11 2005-05-12 Alstom Technology Ltd Baden Gas turbine with honeycomb heat shield, provided with discontinuous air cooling device for honeycomb
EP1876327A2 (en) * 2006-07-06 2008-01-09 United Technologies Corporation Seal for turbine engine
EP1876327A3 (en) * 2006-07-06 2011-03-09 United Technologies Corporation Seal for turbine engine
DE102008033560A1 (en) * 2008-07-17 2010-01-21 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine with adjustable vanes
US8257021B2 (en) 2008-07-17 2012-09-04 Rolls Royce Deutschland Ltd Co KG Gas-turbine engine with variable stator vanes
CN109804138A (en) * 2016-10-13 2019-05-24 西门子股份公司 The thermomechanical actuator of bimetallic

Similar Documents

Publication Publication Date Title
GB1381277A (en) Sealing clearance control apparatus for gas turbine engines
US4407512A (en) High pressure rotary mechanical seal
CA951921A (en) Gas turbine engine cooling system incorporating a vortex shaft valve
FR2455698A1 (en) HIGH PRESSURE GASKET FOR MECHANICAL SHAFT
GB908378A (en) Improvements in or relating to rotating combustion engines
GB2212228A (en) Brush seals
GB1422983A (en) Gas turbine engine
CA1031803A (en) Gas turbine engine regenerator seal assembly with floating leaf sealing element
US3120921A (en) Automatically adjusting and compensating seal means for rotary machines
GB1336843A (en) Method and apparatus for making an elastomeric annular seal with enclosed garter spring
US1626237A (en) Turbine gland
US3720419A (en) Fabricated labyrinth seal structure
US3167115A (en) Regenerator rim attachment
US3861838A (en) Rotary piston internal combustion engine, especially of trochoidal construction
DE1181984B (en) Radial seal for rotary piston engines, especially internal combustion engines
US3324007A (en) Fluid seal and nuclear reactor system including same
US3718335A (en) Hydrostatic ring seal construction
US2208976A (en) Rod or shaft packing
US3180402A (en) Temperature-compensated regenerator seal
ATE50336T1 (en) POETRY.
US2132010A (en) Stuffing box packing
GB1120253A (en) Sealing member for a rotary piston of an internal combustion engine having a toroidal combustion chamber
GB2131895A (en) Improvements in or relating to seals
US3280895A (en) Rotary regenerator seal construction
US1332062A (en) Gland for packing rotating shafts

Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees