GB1381277A – Sealing clearance control apparatus for gas turbine engines
– Google Patents
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
1971-08-26
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.)
1971-08-26
Filing date
1971-08-26
Publication date
1975-01-22
1971-08-26
Application filed by Rolls Royce PLC
filed
Critical
Rolls Royce PLC
1971-08-26
Priority to GB4019071A
priority
Critical
patent/GB1381277A/en
1975-01-22
Publication of GB1381277A
publication
Critical
patent/GB1381277A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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
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
1971
1971-08-26
GB
GB4019071A
patent/GB1381277A/en
not_active
Expired
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
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Legal Events
Date
Code
Title
Description
1975-06-04
PS
Patent sealed
1977-03-30
PLNP
Patent lapsed through nonpayment of renewal fees
