FR2432105A1 - Bandage pour les tetes d'aubes de l'etage de compression d'une turbine a gaz - Google Patents

Bandage pour les tetes d'aubes de l'etage de compression d'une turbine a gaz

Info

Publication number
FR2432105A1
FR2432105A1 FR7916465A FR7916465A FR2432105A1 FR 2432105 A1 FR2432105 A1 FR 2432105A1 FR 7916465 A FR7916465 A FR 7916465A FR 7916465 A FR7916465 A FR 7916465A FR 2432105 A1 FR2432105 A1 FR 2432105A1
Authority
FR
France
Prior art keywords
gas turbine
compression stage
stage
bandage
compression
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.)
Granted
Application number
FR7916465A
Other languages
English (en)
Other versions
FR2432105B1 (fr
Inventor
Frank Roberts Jr
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.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of FR2432105A1 publication Critical patent/FR2432105A1/fr
Application granted granted Critical
Publication of FR2432105B1 publication Critical patent/FR2432105B1/fr
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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un étage de compression pour une turbine à gaz. Cet étage comprend une enveloppe de ventilateur 22 faisant partie de la paroi extérieure 24 du parcours d'écoulement 26 pour les milieux de travail gazeux de l'étage de ventilation, un bandage 28 logé dans cette enveloppe 22 et comportant une premiere surface 30 dirigée vers l'interieur, renfoncée par rapport à la première surface 30 et comportant des discontinuités superficielles, ainsi que plusieurs aubes de compression 14 dont la tête 18 est en alignement avec la première surface 30. L'invention est utilisee pour améliorer le rendement aérodynamique de l'étage de compression d'une turbine à gaz.
FR7916465A 1978-06-26 1979-06-26 Bandage pour les tetes d'aubes de l'etage de compression d'une turbine a gaz Expired FR2432105B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/919,186 US4239452A (en) 1978-06-26 1978-06-26 Blade tip shroud for a compression stage of a gas turbine engine

Publications (2)

Publication Number Publication Date
FR2432105A1 true FR2432105A1 (fr) 1980-02-22
FR2432105B1 FR2432105B1 (fr) 1986-01-17

Family

ID=25441664

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7916465A Expired FR2432105B1 (fr) 1978-06-26 1979-06-26 Bandage pour les tetes d'aubes de l'etage de compression d'une turbine a gaz

Country Status (5)

Country Link
US (1) US4239452A (fr)
JP (1) JPS5510090A (fr)
DE (1) DE2924336A1 (fr)
FR (1) FR2432105B1 (fr)
GB (1) GB2023733B (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2558900A1 (fr) * 1984-02-01 1985-08-02 Snecma Dispositif d'etancheite peripherique d'aubage de compresseur axial

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JPS6318799Y2 (fr) * 1980-12-02 1988-05-26
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US4682933A (en) * 1984-10-17 1987-07-28 Rockwell International Corporation Labyrinthine turbine-rotor-blade tip seal
US4738586A (en) * 1985-03-11 1988-04-19 United Technologies Corporation Compressor blade tip seal
US4764089A (en) * 1986-08-07 1988-08-16 Allied-Signal Inc. Abradable strain-tolerant ceramic coated turbine shroud
US4884820A (en) * 1987-05-19 1989-12-05 Union Carbide Corporation Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members
US5282718A (en) * 1991-01-30 1994-02-01 United Technologies Corporation Case treatment for compressor blades
JPH04138111U (ja) * 1991-06-19 1992-12-24 いすゞ自動車株式会社 トリムのクリツプ取付部構造
US6375416B1 (en) 1993-07-15 2002-04-23 Kevin J. Farrell Technique for reducing acoustic radiation in turbomachinery
WO1995034745A1 (fr) * 1994-06-14 1995-12-21 United Technologies Corporation Structure de stator a rainures circonferentielles interrompues
RU2136896C1 (ru) * 1997-05-28 1999-09-10 Акционерное общество "Турбомоторный завод" Турбина
US6190124B1 (en) * 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
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US6164911A (en) * 1998-11-13 2000-12-26 Pratt & Whitney Canada Corp. Low aspect ratio compressor casing treatment
US6231301B1 (en) 1998-12-10 2001-05-15 United Technologies Corporation Casing treatment for a fluid compressor
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US6290458B1 (en) * 1999-09-20 2001-09-18 Hitachi, Ltd. Turbo machines
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US6350102B1 (en) * 2000-07-19 2002-02-26 General Electric Company Shroud leakage flow discouragers
GB2373023B (en) 2001-03-05 2004-12-22 Rolls Royce Plc Tip treatment bar components
FR2832180B1 (fr) 2001-11-14 2005-02-18 Snecma Moteurs Revetement abradable pour parois de turbines a gaz
GB0216952D0 (en) * 2002-07-20 2002-08-28 Rolls Royce Plc Gas turbine engine casing and rotor blade arrangement
FR2859002A1 (fr) * 2003-08-18 2005-02-25 Snecma Moteurs Dispositif abradable sur carter de soufflante d'un moteur de turbine a gaz
US7004475B2 (en) * 2003-09-26 2006-02-28 Siemens Westinghouse Power Corporation Flow dam design for labyrinth seals to promote rotor stability
GB2406615B (en) * 2003-10-03 2005-11-30 Rolls Royce Plc A gas turbine engine blade containment assembly
GB2418956B (en) * 2003-11-25 2006-07-05 Rolls Royce Plc A compressor having casing treatment slots
GB2419638A (en) * 2004-10-26 2006-05-03 Rolls Royce Plc Compressor casing with an abradable lining and surge control grooves
CN1313737C (zh) * 2005-01-27 2007-05-02 上海交通大学 轴流通风机防喘振环
GB0600532D0 (en) 2006-01-12 2006-02-22 Rolls Royce Plc A blade and rotor arrangement
GB2435904B (en) * 2006-03-10 2008-08-27 Rolls Royce Plc Compressor Casing
US20080044273A1 (en) * 2006-08-15 2008-02-21 Syed Arif Khalid Turbomachine with reduced leakage penalties in pressure change and efficiency
US7871244B2 (en) * 2007-02-15 2011-01-18 Siemens Energy, Inc. Ring seal for a turbine engine
US20080260522A1 (en) * 2007-04-18 2008-10-23 Ioannis Alvanos Gas turbine engine with integrated abradable seal and mount plate
DE102007053135A1 (de) * 2007-11-08 2009-05-14 Mtu Aero Engines Gmbh Gasturbinenbauteil, insbesondere Flugtriebwerksbauteil bzw. Verdichterbauteil
DE102008010283A1 (de) * 2008-02-21 2009-08-27 Mtu Aero Engines Gmbh Zirkulationsstruktur für einen Turboverdichter
US20100030365A1 (en) * 2008-07-30 2010-02-04 Pratt & Whitney Combined matching and inspection process in machining of fan case rub strips
US8337146B2 (en) * 2009-06-03 2012-12-25 Pratt & Whitney Canada Corp. Rotor casing treatment with recessed baffles
US8602720B2 (en) * 2010-06-22 2013-12-10 Honeywell International Inc. Compressors with casing treatments in gas turbine engines
US10036266B2 (en) 2012-01-17 2018-07-31 United Technologies Corporation Method and apparatus for turbo-machine noise suppression
DE102012200883B4 (de) * 2012-01-23 2015-12-03 MTU Aero Engines AG Strömungsmaschinen-Dichtungsanordnung
US20140212261A1 (en) * 2012-12-19 2014-07-31 United Technologies Corporation Lightweight shrouded fan
US10240471B2 (en) * 2013-03-12 2019-03-26 United Technologies Corporation Serrated outer surface for vortex initiation within the compressor stage of a gas turbine
FR3007063B1 (fr) * 2013-06-13 2015-07-03 Composite Ind Piece de materiau abradable pour la fabrication d'un secteur de joint annulaire abradable pour turbomachine et procede de fabrication d'une telle piece
TW201518607A (zh) * 2013-11-14 2015-05-16 Hon Hai Prec Ind Co Ltd 風扇
CN104632715A (zh) * 2013-11-15 2015-05-20 鸿富锦精密工业（深圳）有限公司 风扇
US9863275B2 (en) 2013-12-17 2018-01-09 Honeywell International, Inc. Turbine shroud contour exducer relief
US8939707B1 (en) * 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone terraced ridges
CN106536861A (zh) * 2014-05-15 2017-03-22 诺沃皮尼奥内股份有限公司 制造涡轮机构件的方法、涡轮机构件以及涡轮机
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EP3088672A1 (fr) * 2015-04-27 2016-11-02 Siemens Aktiengesellschaft Procédé de conception d'un moteur à écoulement de fluide et moteur à écoulement de fluide
US10415591B2 (en) * 2016-09-21 2019-09-17 United Technologies Corporation Gas turbine engine airfoil
FR3065482B1 (fr) * 2017-04-20 2019-07-05 Safran Aircraft Engines Element d'anneau d'etancheite pour turbine comportant une cavite inclinee dans un materiau abradable
US10914318B2 (en) * 2019-01-10 2021-02-09 General Electric Company Engine casing treatment for reducing circumferentially variable distortion
CN110145373B (zh) * 2019-05-10 2022-04-15 沈阳航空航天大学 一种非均匀的横纵槽涡轮外环结构
US11286955B2 (en) 2019-10-11 2022-03-29 General Electric Company Ducted fan with fan casing defining an over-rotor cavity
US11215070B2 (en) 2019-12-13 2022-01-04 Pratt & Whitney Canada Corp. Dual density abradable panels
EP3885537A1 (fr) * 2020-03-26 2021-09-29 Unison Industries LLC Système de confinement de démarrage de turbine à air et procédé de fabrication d´un tel système
CN112983863B (zh) * 2021-03-10 2023-03-14 浙江科力风机有限公司 一种减小噪音的节能环保型轴流风机
US20230151825A1 (en) * 2021-11-17 2023-05-18 Pratt & Whitney Canada Corp. Compressor shroud with swept grooves
US12071959B1 (en) 2023-09-06 2024-08-27 Pratt & Whitney Canada Corp. Compressor casing with slots and grooves
US12385408B1 (en) * 2024-01-26 2025-08-12 Rtx Corporation Life and performance improvement trenches
US12404780B2 (en) * 2024-01-29 2025-09-02 Pratt & Whitney Canada Corp. Containment ring for gas turbine engine
US12258870B1 (en) 2024-03-08 2025-03-25 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with slotted array active fan tip treatment for distortion tolerance
US12286936B1 (en) 2024-05-09 2025-04-29 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with groove array active fan tip treatment for distortion tolerance
US12215712B1 (en) 2024-05-09 2025-02-04 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with dual grooved array active fan tip treatment for distortion tolerance
US12209541B1 (en) 2024-05-09 2025-01-28 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with dual slotted array active fan tip treatment for distortion tolerance
US12209502B1 (en) 2024-06-28 2025-01-28 Rolls-Royce North American Technologies Inc. Active fan tip treatment using rotating drum array with axial channels in fan track liner for distortion tolerance
US12168983B1 (en) 2024-06-28 2024-12-17 Rolls-Royce North American Technologies Inc. Active fan tip treatment using rotating drum array in fan track liner with axial and circumferential channels for distortion tolerance

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DE1031805B (de) * 1956-11-20 1958-06-12 Karl Roeder Dr Ing Spaltdichtung fuer deckbandlose Leit- oder Laufschaufelkraenze von Turbomaschinen
FR1189849A (fr) * 1955-08-18 1959-10-07 Stromungsmaschinen Ges M B H A Couronne fixe pour rotor de turbines à gaz
GB839915A (en) * 1958-01-20 1960-06-29 Rolls Royce Labyrinth seals
US3843278A (en) * 1973-06-04 1974-10-22 United Aircraft Corp Abradable seal construction
US3893782A (en) * 1974-03-20 1975-07-08 Westinghouse Electric Corp Turbine blade damping
FR2343944A1 (fr) * 1976-03-09 1977-10-07 Westinghouse Electric Corp Joint tournant en labyrinthe
US4057362A (en) * 1975-05-09 1977-11-08 Maschinenfabrik Augsburg-Nurnberg Ag Apparatus for raising the dynamic performance limit of steam flow and gas flow turbines and compressors

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FR833985A (fr) * 1937-02-24 1938-11-08 Rheinmetall Borsig Ag Perfectionnements apportés aux turbo-compresseurs en vue d'empêcher les filets fluides de se détacher de la paroi
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Publication number Priority date Publication date Assignee Title
FR1189849A (fr) * 1955-08-18 1959-10-07 Stromungsmaschinen Ges M B H A Couronne fixe pour rotor de turbines à gaz
DE1031805B (de) * 1956-11-20 1958-06-12 Karl Roeder Dr Ing Spaltdichtung fuer deckbandlose Leit- oder Laufschaufelkraenze von Turbomaschinen
GB839915A (en) * 1958-01-20 1960-06-29 Rolls Royce Labyrinth seals
US3843278A (en) * 1973-06-04 1974-10-22 United Aircraft Corp Abradable seal construction
US3893782A (en) * 1974-03-20 1975-07-08 Westinghouse Electric Corp Turbine blade damping
US4057362A (en) * 1975-05-09 1977-11-08 Maschinenfabrik Augsburg-Nurnberg Ag Apparatus for raising the dynamic performance limit of steam flow and gas flow turbines and compressors
FR2343944A1 (fr) * 1976-03-09 1977-10-07 Westinghouse Electric Corp Joint tournant en labyrinthe

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2558900A1 (fr) * 1984-02-01 1985-08-02 Snecma Dispositif d'etancheite peripherique d'aubage de compresseur axial
EP0151071A3 (en) * 1984-02-01 1985-09-25 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Tip-sealing device for the blading of an axial compressor
US4767266A (en) * 1984-02-01 1988-08-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Sealing ring for an axial compressor

Also Published As

Publication number Publication date
JPS5510090A (en) 1980-01-24
US4239452A (en) 1980-12-16
GB2023733A (en) 1980-01-03
DE2924336A1 (de) 1980-01-10
FR2432105B1 (fr) 1986-01-17
GB2023733B (en) 1982-09-15
JPS6244120B2 (fr) 1987-09-18

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