GB1528421A - Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance - Google Patents

Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance

Info

Publication number
GB1528421A
GB1528421A GB39331/76A GB3933176A GB1528421A GB 1528421 A GB1528421 A GB 1528421A GB 39331/76 A GB39331/76 A GB 39331/76A GB 3933176 A GB3933176 A GB 3933176A GB 1528421 A GB1528421 A GB 1528421A
Authority
GB
United Kingdom
Prior art keywords
seal member
turbine
shroud
compressor
rotor
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
GB39331/76A
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.)
Nissan Motor Co Ltd
Original Assignee
Nissan Motor Co Ltd
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 Nissan Motor Co Ltd filed Critical Nissan Motor Co Ltd
Publication of GB1528421A publication Critical patent/GB1528421A/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
    • F01D11/122—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 erodable or abradable material
    • 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

1528421 Turbines and compressors; abradable rotor blade shrouding NISSAN MOTOR CO Ltd 22 Sept 1976 [22 Sept 1975] 39331/76 Heading F1C and FIT The invention relates to a machine such as a turbine or compressor in which an abradable seal is provided on a shroud member adjacent the tips of the rotor or impeller blades. In accordance with the invention, the abradable seal comprises a layer of a baked mixture of a ceramic fibre and an inorganic binder attached to the inner surface of the shroud member. The turbine shown in Fig. 1 comprises a stator casing or shroud 16 formed with an annular recess 22 in which an abradable seal member 24 mounted so as to surround the tips 14a of the rotor blades 14 with a minimum clearance 26. The seal member is maintained in concentric relation with the stator casing by means of a series of radial pins 30 mounted in the casing and extending through holes in the seal member. The invention is shown applied to a centrifugal turbine in Fig. 4, the abradable seal member being shown at 50 located within recess 48 in stator casing 46; the seal member is located by radial pins 52; a ring member 58 is provided to prevent gas leakage outwardly of the seal member. The invention is also shown applied to an axial-flow compressor and a centrifugal compressor.
GB39331/76A 1975-09-22 1976-09-22 Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance Expired GB1528421A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP1975128907U JPS5242906U (en) 1975-09-22 1975-09-22

Publications (1)

Publication Number Publication Date
GB1528421A true GB1528421A (en) 1978-10-11

Family

ID=14996300

Family Applications (1)

Application Number Title Priority Date Filing Date
GB39331/76A Expired GB1528421A (en) 1975-09-22 1976-09-22 Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance

Country Status (3)

Country Link
JP (1) JPS5242906U (en)
DE (1) DE2642631A1 (en)
GB (1) GB1528421A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2483008A1 (en) * 1980-05-24 1981-11-27 Mtu Muenchen Gmbh DEVICE FOR MINIMIZING AND MAINTAINING CONSTANT EXTERMITY SETTING OF AXIAL TURBINE BLADES OF GAS TURBINE ENGINES
EP0416954A1 (en) * 1989-09-08 1991-03-13 Toyota Jidosha Kabushiki Kaisha Abradable material for a turbo machine
GB2239678A (en) * 1989-12-08 1991-07-10 Rolls Royce Plc Gas turbine engine shroud assembly
EP1113146A2 (en) * 1999-12-27 2001-07-04 General Electric Company Rotatory machine having a seal assembly
EP1992419A3 (en) * 2007-03-30 2010-03-03 Nuovo Pignone S.P.A. Abradable and anti-encrustation coating for rotating fluid machines
FR2947016A1 (en) * 2009-06-17 2010-12-24 Snecma Centrifugal compressor i.e. axial centrifugal compressor, for turboshaft engine i.e. turbojet engine, has abradable layer placed on casing and limiting circulation of flow of air between casing and rotor, where layer includes abradables
US20130004305A1 (en) * 2009-10-30 2013-01-03 Lacopo Giovannetti Machine with Abradable Ridges and Method
EP2226472A3 (en) * 2009-03-05 2014-03-12 United Technologies Corporation Turbine engine sealing arrangement
CN108979738A (en) * 2017-06-02 2018-12-11 赛峰航空助推器股份有限公司 The sealing system of turbomachine compressor
US10989203B2 (en) 2019-07-15 2021-04-27 Pratt & Whitney Canada Corp. Centrifugal compressor and shroud therefore
US11421689B2 (en) 2016-12-19 2022-08-23 Edwards Limited Pump assembly with sealing protrusion on stator bore portion

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4247249A (en) * 1978-09-22 1981-01-27 General Electric Company Turbine engine shroud
DE2931766C2 (en) * 1979-08-04 1982-08-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Sealing device for the free blade ends of an adjustable diffuser of a gas turbine
DE3018620C2 (en) * 1980-05-16 1982-08-26 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Thermally insulating and sealing lining for a thermal turbo machine
JPH0746798Y2 (en) * 1988-03-04 1995-10-25 株式会社荏原製作所 Pump liner structure
EP1609953A1 (en) * 2004-06-24 2005-12-28 BorgWarner Inc. Assembly method for a turbomachine
EP2835504A1 (en) * 2013-08-09 2015-02-11 Siemens Aktiengesellschaft Insert element and gas turbine
PL239521B1 (en) 2017-03-19 2021-12-13 Mariusz Staszowski Compressor efficiency increasing ring

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB938123A (en) * 1960-05-19 1963-10-02 Studebaker Packard Corp Improvements in or relating to an axial flow compressor
BE792224A (en) * 1971-12-01 1973-03-30 Penny Robert N LONG COMPOSITE ELEMENT WITH A PREDETERMINED EFFECTIVE LINEAR EXPANSION COEFFICIENT
DE2401951A1 (en) * 1973-01-17 1974-07-25 Rolls Royce 1971 Ltd SEAL ARRANGEMENT FOR TURBO MACHINERY

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2483008A1 (en) * 1980-05-24 1981-11-27 Mtu Muenchen Gmbh DEVICE FOR MINIMIZING AND MAINTAINING CONSTANT EXTERMITY SETTING OF AXIAL TURBINE BLADES OF GAS TURBINE ENGINES
EP0416954A1 (en) * 1989-09-08 1991-03-13 Toyota Jidosha Kabushiki Kaisha Abradable material for a turbo machine
US5185217A (en) * 1989-09-08 1993-02-09 Toyota Jidosha Kabushiki Kaisha Relatively displacing apparatus
GB2239678A (en) * 1989-12-08 1991-07-10 Rolls Royce Plc Gas turbine engine shroud assembly
GB2239678B (en) * 1989-12-08 1993-03-03 Rolls Royce Plc Gas turbine engine blade shroud assembly
EP1113146A3 (en) * 1999-12-27 2003-01-08 General Electric Company Rotatory machine having a seal assembly
EP1113146A2 (en) * 1999-12-27 2001-07-04 General Electric Company Rotatory machine having a seal assembly
EP1992419A3 (en) * 2007-03-30 2010-03-03 Nuovo Pignone S.P.A. Abradable and anti-encrustation coating for rotating fluid machines
EP2226472A3 (en) * 2009-03-05 2014-03-12 United Technologies Corporation Turbine engine sealing arrangement
FR2947016A1 (en) * 2009-06-17 2010-12-24 Snecma Centrifugal compressor i.e. axial centrifugal compressor, for turboshaft engine i.e. turbojet engine, has abradable layer placed on casing and limiting circulation of flow of air between casing and rotor, where layer includes abradables
US20130004305A1 (en) * 2009-10-30 2013-01-03 Lacopo Giovannetti Machine with Abradable Ridges and Method
US11421689B2 (en) 2016-12-19 2022-08-23 Edwards Limited Pump assembly with sealing protrusion on stator bore portion
CN108979738A (en) * 2017-06-02 2018-12-11 赛峰航空助推器股份有限公司 The sealing system of turbomachine compressor
CN108979738B (en) * 2017-06-02 2022-05-31 赛峰航空助推器股份有限公司 Sealing system for a turbomachine compressor
US10989203B2 (en) 2019-07-15 2021-04-27 Pratt & Whitney Canada Corp. Centrifugal compressor and shroud therefore

Also Published As

Publication number Publication date
DE2642631A1 (en) 1977-03-31
JPS5242906U (en) 1977-03-26

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Legal Events

Date Code Title Description
PS Patent sealed
746 Register noted 'licences of right' (sect. 46/1977)
PCNP Patent ceased through non-payment of renewal fee