GB1308963A - Gap control apparatus - Google Patents

Gap control apparatus

Info

Publication number
GB1308963A
GB1308963A GB2618670A GB1308963DA GB1308963A GB 1308963 A GB1308963 A GB 1308963A GB 2618670 A GB2618670 A GB 2618670A GB 1308963D A GB1308963D A GB 1308963DA GB 1308963 A GB1308963 A GB 1308963A
Authority
GB
United Kingdom
Prior art keywords
clearance
tube
control
members
tubes
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
GB2618670A
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.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Publication of GB1308963A publication Critical patent/GB1308963A/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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S277/00—Seal for a joint or juncture
    • Y10S277/931—Seal including temperature responsive feature

Landscapes

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

Abstract

1308963 Seals DEFENCE SECRETARY OF STATE FOR 1 June 1971 [30 May 1970] 26186/70 Heading F2B [Also in Division F1] A mechanism for maintaining the clearance between two relatively movable members substantially constant comprises means for varying the temperature of a temperature responsive control member when the clearance changes, the control member expanding or contracting so as to produce relative movement between the two members and thus restore the clearance to its desired value. In one arrangement means to maintain the clearance between a sealing member 61 and a rib 62 on the shround 63 of a gas turbine rotor blade 64 comprises a control tube 60 anchored at its end remote from member 61 and supplied at the fixed end with low pressure cooling air. At its free end tube 60 has an orifice 65, the leakage of hot working gas through which depends on the position of flange 66 on shroud 63, i.e. on the clearance between member 61 and rib 62. Thus when the clearance increases more hot gas flows through orifice 65 causing tube 60 to expand and thus restore the clearance to its desired value. Figs. 5, 6 (not shown) illustrate slightly modified arrangements of tube 60. In a more elaborate arrangement (Fig. 2, not shown), the control tube (26) is surrounded by two further tubes (40, 42) spaced therefrom to provide ported flow passages for the flow of hot gas and cooling air, the rest of tubes being disposed in the by-pass duct of a gas turbine by-pass engine. Several such tube assemblies are angularly spaced about the engine to prevent skewing of the sealing member. In modifications the control tubes may be replaced by solid rods or bimetallic strips and heating of the control members may be effected by burners which play hot gases on to the members in dependence upon the size of the sealing clearance.
GB2618670A 1970-05-30 1970-05-30 Gap control apparatus Expired GB1308963A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2618670 1970-05-30

Publications (1)

Publication Number Publication Date
GB1308963A true GB1308963A (en) 1973-03-07

Family

ID=10239687

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2618670A Expired GB1308963A (en) 1970-05-30 1970-05-30 Gap control apparatus

Country Status (4)

Country Link
US (1) US3736751A (en)
DE (1) DE2126270C3 (en)
FR (1) FR2093885A5 (en)
GB (1) GB1308963A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6129513A (en) * 1998-04-23 2000-10-10 Rolls-Royce Plc Fluid seal
US9309777B2 (en) 2011-08-01 2016-04-12 Rolls-Royce Plc Tip clearance control device

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1504129A (en) * 1974-06-29 1978-03-15 Rolls Royce Matching differential thermal expansions of components in heat engines
FR2280791A1 (en) * 1974-07-31 1976-02-27 Snecma IMPROVEMENTS IN ADJUSTING THE CLEARANCE BETWEEN THE BLADES AND THE STATOR OF A TURBINE
GB1605255A (en) * 1975-12-02 1986-08-13 Rolls Royce Clearance control apparatus for bladed fluid flow machine
US4069662A (en) * 1975-12-05 1978-01-24 United Technologies Corporation Clearance control for gas turbine engine
GB1581566A (en) * 1976-08-02 1980-12-17 Gen Electric Minimum clearance turbomachine shroud apparatus
US4338061A (en) * 1980-06-26 1982-07-06 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Control means for a gas turbine engine
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
US7207768B2 (en) * 2005-01-15 2007-04-24 Siemens Power Generation, Inc. Warning system for turbine component contact

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1857961A (en) * 1927-12-15 1932-05-10 Westinghouse Electric & Mfg Co Bi-metal packing
US3029064A (en) * 1958-07-11 1962-04-10 Napier & Son Ltd Temperature control apparatus for turbine cases
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
US3375015A (en) * 1966-09-30 1968-03-26 Judson S. Swearingen Shaft seal employing seal gas with means for indicating proper flow thereof
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
GB1277212A (en) * 1968-09-26 1972-06-07 Rolls Royce A sealing device

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6129513A (en) * 1998-04-23 2000-10-10 Rolls-Royce Plc Fluid seal
US9309777B2 (en) 2011-08-01 2016-04-12 Rolls-Royce Plc Tip clearance control device

Also Published As

Publication number Publication date
DE2126270C3 (en) 1979-10-04
US3736751A (en) 1973-06-05
DE2126270A1 (en) 1971-12-23
FR2093885A5 (en) 1972-01-28
DE2126270B2 (en) 1979-02-15

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLE Entries relating assignments, transmissions, licences in the register of patents
PCNP Patent ceased through non-payment of renewal fee