GB1451901A - Sealing devices for gas turbine engines - Google Patents

Sealing devices for gas turbine engines

Info

Publication number
GB1451901A
GB1451901A GB3037773A GB3037773A GB1451901A GB 1451901 A GB1451901 A GB 1451901A GB 3037773 A GB3037773 A GB 3037773A GB 3037773 A GB3037773 A GB 3037773A GB 1451901 A GB1451901 A GB 1451901A
Authority
GB
United Kingdom
Prior art keywords
flange
clearance
lever
stator casing
received
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
GB3037773A
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 GB3037773A priority Critical patent/GB1451901A/en
Publication of GB1451901A publication Critical patent/GB1451901A/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
    • F01D11/08—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

Abstract

1451901 Turbines-rotor blade tip sealing ROLLS-ROYCE (1971) Ltd 20 Sept 1974 [26 June 1973] 30377/73 Heading FIT The invention relates to a gas turbine engine and to an arrangement for sealing rotor blade tips in which blade tip seal members mounted on the stator casing may be moved radially inwardly or outwardly so as to adjust the tip clearance in response to temperature of the gas leakage through the clearance. The engine shown comprises rotor blades 24 having blade tips 45 which rotate in close proximity to segmental shroud members 25 each of which is formed with a radial flange 26 received between a pair of flanges 27, 28 formed integrally with the stator casing member 23. A further flange 31 is formed integrally with the stator casing member and a lever 29 is pivotally mounted within an opening 32 formed in the flange 31, one end 30 of the lever passing through an opening in the flange 28 to be received within an opening in the flange 26 of the shroud segment. The other end 33 of the lever is received within a flange member 35 to which is secured a temperature responsive ring member 42. The flange member 35 is mounted for radial sliding movement between flanges 37, 38 of the stator casing members 23, 39. Thus in the event of the blade tip clearance increasing, increased flow of turbine working fluid will pass through the clearance, the ring member 42 is heated and expands. The lever 29 thereby pivots about the point 32 in an anti-clockwise direction and so the shroud member 25 is caused to move inwardly whereby the clearance is reduced.
GB3037773A 1973-06-26 1973-06-26 Sealing devices for gas turbine engines Expired GB1451901A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3037773A GB1451901A (en) 1973-06-26 1973-06-26 Sealing devices for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3037773A GB1451901A (en) 1973-06-26 1973-06-26 Sealing devices for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1451901A true GB1451901A (en) 1976-10-06

Family

ID=10306730

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3037773A Expired GB1451901A (en) 1973-06-26 1973-06-26 Sealing devices for gas turbine engines

Country Status (1)

Country Link
GB (1) GB1451901A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2240818A (en) * 1990-02-12 1991-08-14 Gen Electric Blade tip clearance control apparatus in a gas turbine engine
GB2260371A (en) * 1991-10-09 1993-04-14 Rolls Royce Plc Shroud and liner construction surrounding rotor blade tips in turbines.

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2240818A (en) * 1990-02-12 1991-08-14 Gen Electric Blade tip clearance control apparatus in a gas turbine engine
GB2260371A (en) * 1991-10-09 1993-04-14 Rolls Royce Plc Shroud and liner construction surrounding rotor blade tips in turbines.
US5295787A (en) * 1991-10-09 1994-03-22 Rolls-Royce Plc Turbine engines
GB2260371B (en) * 1991-10-09 1994-11-09 Rolls Royce Plc Turbine engines

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Legal Events

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