GB1175287A - Improvements in Sealing Means for Turbomachinery. - Google Patents

Improvements in Sealing Means for Turbomachinery.

Info

Publication number
GB1175287A
GB1175287A GB38437/67A GB3843767A GB1175287A GB 1175287 A GB1175287 A GB 1175287A GB 38437/67 A GB38437/67 A GB 38437/67A GB 3843767 A GB3843767 A GB 3843767A GB 1175287 A GB1175287 A GB 1175287A
Authority
GB
United Kingdom
Prior art keywords
turbomachinery
division
sealing means
core layer
seal
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
GB38437/67A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1175287A publication Critical patent/GB1175287A/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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

1,175,287. Seals. GENERAL ELECTRIC CO. 21 Aug., 1967 [23 Nov., 1966], No. 38437/67. Heading F2B. [Also in Division F1] A seal between parallel flat or cylindrical surfaces for use with turbomachinery comprises a core layer 45 of honeycomb material having surface layers 50, 58 of abradable imperforate material. As shown for a blade tip seal (Division F1), the core layer 45 is made of expanded metal and the surface layer 58 made of metal 0.003 to 0.006 inch thick.
GB38437/67A 1966-11-23 1967-08-21 Improvements in Sealing Means for Turbomachinery. Expired GB1175287A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US59661366A 1966-11-23 1966-11-23

Publications (1)

Publication Number Publication Date
GB1175287A true GB1175287A (en) 1969-12-23

Family

ID=24387988

Family Applications (1)

Application Number Title Priority Date Filing Date
GB38437/67A Expired GB1175287A (en) 1966-11-23 1967-08-21 Improvements in Sealing Means for Turbomachinery.

Country Status (6)

Country Link
US (1) US3423070A (en)
BE (1) BE701461A (en)
CH (1) CH473307A (en)
DE (1) DE1551183A1 (en)
GB (1) GB1175287A (en)
NL (1) NL6710449A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105492726A (en) * 2013-09-06 2016-04-13 通用电气公司 A gas turbine laminate seal assembly comprising first and second honeycomb layer and a perforated intermediate seal plate in-between

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3529905A (en) * 1966-12-12 1970-09-22 Gen Motors Corp Cellular metal and seal
US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
US3846899A (en) * 1972-07-28 1974-11-12 Gen Electric A method of constructing a labyrinth seal
US4135851A (en) * 1977-05-27 1979-01-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
US4207024A (en) * 1977-05-27 1980-06-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
GB2053367B (en) * 1979-07-12 1983-01-26 Rolls Royce Cooled shroud for a gas turbine engine
GB2081817B (en) * 1980-08-08 1984-02-15 Rolls Royce Turbine blade shrouding
GB2095749B (en) * 1981-03-25 1984-12-12 Rolls Royce Gas turbine engine having improved resistance for foreign object ingestion damage
EP0081010A3 (en) * 1981-08-10 1983-08-03 George T. Straza Interrupted cell honeycomb structure
GB2125111B (en) * 1982-03-23 1985-06-05 Rolls Royce Shroud assembly for a gas turbine engine
US4478552A (en) * 1982-11-08 1984-10-23 Thompson Stanley E Method and apparatus for fan blade tip clearance
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
US5197281A (en) * 1990-04-03 1993-03-30 General Electric Company Interstage seal arrangement for airfoil stages of turbine engine counterrotating rotors
US5165848A (en) * 1991-07-09 1992-11-24 General Electric Company Vane liner with axially positioned heat shields
US5174714A (en) * 1991-07-09 1992-12-29 General Electric Company Heat shield mechanism for turbine engines
US5195868A (en) * 1991-07-09 1993-03-23 General Electric Company Heat shield for a compressor/stator structure
US5314304A (en) * 1991-08-15 1994-05-24 The United States Of America As Represented By The Secretary Of The Air Force Abradeable labyrinth stator seal
US5169159A (en) * 1991-09-30 1992-12-08 General Electric Company Effective sealing device for engine flowpath
US5292138A (en) * 1992-09-21 1994-03-08 General Elecric Company Rotor to rotor split ring seal
US5524846A (en) * 1993-12-21 1996-06-11 The Boeing Company Fire protection system for airplanes
WO1995021319A1 (en) * 1994-02-01 1995-08-10 United Technologies Corporation Honeycomb abradable seals
DE10020673C2 (en) * 2000-04-27 2002-06-27 Mtu Aero Engines Gmbh Ring structure in metal construction
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
GB2382380A (en) * 2001-11-24 2003-05-28 Rolls Royce Plc A removable abradable lining for the casing assembly of a gas turbine engine
DE102004010236A1 (en) * 2004-03-03 2005-09-15 Mtu Aero Engines Gmbh Metal ring structure for sealing gap between rotor blade tips and stator in e.g. gas turbine, has inner wall formed by metal fabric or felt
DE102004018585B4 (en) * 2004-04-16 2013-12-05 Rolls-Royce Deutschland Ltd & Co Kg Engine inlet cone for a gas turbine engine
US20090053045A1 (en) * 2007-08-22 2009-02-26 General Electric Company Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud
FR2922950B1 (en) * 2007-10-31 2014-05-09 Snecma CARTRIDGE OF ABRADABLE MATERIAL
US20110206502A1 (en) * 2010-02-25 2011-08-25 Samuel Ross Rulli Turbine shroud support thermal shield
FR2979664B1 (en) * 2011-09-01 2017-10-13 Snecma STATOR WINDOW OF TURBOMACHINE COVERED WITH ABRADABLE COATING WITH LOW AERODYNAMIC ROUGHNESS
US9574455B2 (en) 2012-07-16 2017-02-21 United Technologies Corporation Blade outer air seal with cooling features
US20170089213A1 (en) 2015-09-28 2017-03-30 United Technologies Corporation Duct with additive manufactured seal
US10472980B2 (en) * 2017-02-14 2019-11-12 General Electric Company Gas turbine seals
US11674396B2 (en) 2021-07-30 2023-06-13 General Electric Company Cooling air delivery assembly
US11674405B2 (en) 2021-08-30 2023-06-13 General Electric Company Abradable insert with lattice structure

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
GB450524A (en) * 1934-10-15 1935-04-23 Andre Abel Auguste Brugier Improvements in or relating to heat-insulating panels
US2477852A (en) * 1945-07-04 1949-08-02 Owens Corning Fiberglass Corp Structural panel construction
US2963307A (en) * 1954-12-28 1960-12-06 Gen Electric Honeycomb seal
US2952442A (en) * 1957-05-28 1960-09-13 Studebaker Packard Corp Rotating shroud
US3068016A (en) * 1958-03-31 1962-12-11 Gen Motors Corp High temperature seal
US3053694A (en) * 1961-02-20 1962-09-11 Gen Electric Abradable material
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
GB1085329A (en) * 1964-01-21
GB995228A (en) * 1964-05-08 1965-06-16 Rolls Royce Bladed structure, for example, for a gas turbine engine compressor
US3339933A (en) * 1965-02-24 1967-09-05 Gen Electric Rotary seal
US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105492726A (en) * 2013-09-06 2016-04-13 通用电气公司 A gas turbine laminate seal assembly comprising first and second honeycomb layer and a perforated intermediate seal plate in-between

Also Published As

Publication number Publication date
US3423070A (en) 1969-01-21
DE1551183A1 (en) 1970-04-16
CH473307A (en) 1969-05-31
NL6710449A (en) 1968-05-24
BE701461A (en) 1968-01-02

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Legal Events

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