IT1246921B - Disposizione di tenuta interstadio per stadi di profili aerodinamici di motori controrotanti di turbomotori - Google Patents

Disposizione di tenuta interstadio per stadi di profili aerodinamici di motori controrotanti di turbomotori

Info

Publication number
IT1246921B
IT1246921B ITMI910920A ITMI910920A IT1246921B IT 1246921 B IT1246921 B IT 1246921B IT MI910920 A ITMI910920 A IT MI910920A IT MI910920 A ITMI910920 A IT MI910920A IT 1246921 B IT1246921 B IT 1246921B
Authority
IT
Italy
Prior art keywords
internal
external
rotor
counter
vanes
Prior art date
Application number
ITMI910920A
Other languages
English (en)
Inventor
James Charles Przytulski
Richard Lee Horvath
Robert James Corsmeier
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of ITMI910920A0 publication Critical patent/ITMI910920A0/it
Publication of ITMI910920A1 publication Critical patent/ITMI910920A1/it
Application granted granted Critical
Publication of IT1246921B publication Critical patent/IT1246921B/it

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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B64C11/48—Units of two or more coaxial propellers
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

Un turbomotore a gas ha rotori anulari di turbina esterni ed interni controrotanti e pluralità di palette di turbina disposte in file alternate e montate su ed estendentesi tra rispettivi rotori. Una disposizione di tenuta interstadio per il motore è composta da una sequenza di tenute alterne interne ed esterne. Ciascuna tenuta esterna è disposta tra un lato interno del rotore esterno ed estremi esterni delle palette in una loro pluralità che è distanziata radialmente verso l'interno ai loro estremi esterni dal rotore esterno e montata ai loro estremi interni sul lato esterno del rotore interno. Ciascuna tenuta interna è disposta tra il lato esterno del rotore interno e gli estremi interni delle palette di un'altra sua pluralità che viene distanziata radialmente all'esterno ai loro estremi interni dal rotore interno e viene montata ai loro estremi esterni sul lato interno del rotore esterno. Ciascuna tenuta interna è composta da una componente anulare a nido d'api attaccato agli estremi interni di palette e da una pluralità di elementi o denti anulari di tenuta montati sul lato esterno del rotore interno e sporgenti radialmente all'esterno dal medesimo per interfacciarsi a tenuta con il componente a nido d'api contemporaneamente mentre i rotori esterni ed interni controruotano tra di loro.
ITMI910920A 1990-04-03 1991-04-03 Disposizione di tenuta interstadio per stadi di profili aerodinamici di motori controrotanti di turbomotori IT1246921B (it)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/505,120 US5197281A (en) 1990-04-03 1990-04-03 Interstage seal arrangement for airfoil stages of turbine engine counterrotating rotors

Publications (3)

Publication Number Publication Date
ITMI910920A0 ITMI910920A0 (it) 1991-04-03
ITMI910920A1 ITMI910920A1 (it) 1992-10-03
IT1246921B true IT1246921B (it) 1994-11-29

Family

ID=24009099

Family Applications (1)

Application Number Title Priority Date Filing Date
ITMI910920A IT1246921B (it) 1990-04-03 1991-04-03 Disposizione di tenuta interstadio per stadi di profili aerodinamici di motori controrotanti di turbomotori

Country Status (7)

Country Link
US (1) US5197281A (it)
JP (1) JPH0692741B2 (it)
CA (1) CA2034469A1 (it)
DE (1) DE4110244A1 (it)
FR (1) FR2660371A1 (it)
GB (1) GB2242709B (it)
IT (1) IT1246921B (it)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5443590A (en) * 1993-06-18 1995-08-22 General Electric Company Rotatable turbine frame
US5429478A (en) * 1994-03-31 1995-07-04 United Technologies Corporation Airfoil having a seal and an integral heat shield
FR2724412B1 (fr) * 1994-09-14 1996-10-25 Snecma Aube de turbomachine en materiau composite munie d'un joint d'etancheite et son procede de realisation
US5702050A (en) * 1995-04-28 1997-12-30 Mitsubishi Jukogyo Kabushiki Kaisha Method of brazing a honeycomb
US5749701A (en) * 1996-10-28 1998-05-12 General Electric Company Interstage seal assembly for a turbine
DE19938443A1 (de) * 1999-08-13 2001-02-15 Abb Alstom Power Ch Ag Befestigungs- und Fixierungsvorrichtung
US6503051B2 (en) * 2001-06-06 2003-01-07 General Electric Company Overlapping interference seal and methods for forming the seal
US6896483B2 (en) 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
ITMI20021219A1 (it) * 2002-06-05 2003-12-05 Nuovo Pignone Spa Dispositivo di supporto semplificato per ugelli di uno stadio di una turbina a gas
US6890150B2 (en) * 2003-08-12 2005-05-10 General Electric Company Center-located cutter teeth on shrouded turbine blades
US6899520B2 (en) * 2003-09-02 2005-05-31 General Electric Company Methods and apparatus to reduce seal rubbing within gas turbine engines
US20050200080A1 (en) * 2004-03-10 2005-09-15 Siemens Westinghouse Power Corporation Seal for a turbine engine
US8444371B2 (en) 2010-04-09 2013-05-21 General Electric Company Axially-oriented cellular seal structure for turbine shrouds and related method
DE102012200883B4 (de) * 2012-01-23 2015-12-03 MTU Aero Engines AG Strömungsmaschinen-Dichtungsanordnung
DE102012201050B4 (de) * 2012-01-25 2017-11-30 MTU Aero Engines AG Dichtungsanordnung, Verfahren sowie Strömungsmaschine
EP2647795B1 (de) * 2012-04-04 2018-11-07 MTU Aero Engines AG Dichtungssystem für eine Strömungsmaschine
EP2808491A1 (en) * 2013-05-29 2014-12-03 Alstom Technology Ltd Stator vane and corresponding assembly
CN106801620B (zh) * 2015-11-25 2019-03-22 熵零股份有限公司 一种对转冲压叶轮机构
US10774668B2 (en) * 2017-09-20 2020-09-15 General Electric Company Intersage seal assembly for counter rotating turbine
FR3093541B1 (fr) * 2019-03-08 2021-07-16 Safran Aircraft Engines Turbine à gaz pour aéronef à double rotor
IT201900014736A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di tenuta integrali per pale trattenute in un rotore a tamburo esterno anulare girevole in una turbomacchina.
IT201900014739A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
IT201900014724A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
US11365629B1 (en) 2021-04-14 2022-06-21 General Electric Company Flow structure for turbine engine
WO2024059189A1 (en) * 2022-09-15 2024-03-21 Maglev Aero Inc. Systems and methods for vertical takeoff and landing vehicle with improved rotor sizing

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR379209A (fr) * 1906-07-03 1907-10-29 Sebastian Ziani De Ferranti Perfectionnements aux turbines à fluide élastique
US2410804A (en) * 1942-01-19 1946-11-12 Vickers Electrical Co Ltd Turbine
CH336660A (de) * 1954-10-18 1959-02-28 Vickers Electrical Co Ltd Labyrinthgasdichtung
US2963307A (en) * 1954-12-28 1960-12-06 Gen Electric Honeycomb seal
GB840573A (en) * 1958-01-20 1960-07-06 Rolls Royce Labyrinth seals
US3262635A (en) * 1964-11-06 1966-07-26 Gen Electric Turbomachine sealing means
US3423070A (en) * 1966-11-23 1969-01-21 Gen Electric Sealing means for turbomachinery
US3529905A (en) * 1966-12-12 1970-09-22 Gen Motors Corp Cellular metal and seal
US3537713A (en) * 1968-02-21 1970-11-03 Garrett Corp Wear-resistant labyrinth seal
US3501089A (en) * 1968-07-17 1970-03-17 Gen Electric Jet pump ejector
US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
US3836156A (en) * 1971-07-19 1974-09-17 United Aircraft Canada Ablative seal
US3846899A (en) * 1972-07-28 1974-11-12 Gen Electric A method of constructing a labyrinth seal
US3861139A (en) * 1973-02-12 1975-01-21 Gen Electric Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
FR2535795B1 (fr) * 1982-11-08 1987-04-10 Snecma Dispositif de suspension d'aubes statoriques de compresseur axial pour le controle actif des jeux entre rotor et stator
FR2552159B1 (fr) * 1983-09-21 1987-07-10 Snecma Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
US4867639A (en) * 1987-09-22 1989-09-19 Allied-Signal Inc. Abradable shroud coating
US4979755A (en) * 1988-02-18 1990-12-25 Westinghouse Electric Corp. Flow dams in labyrinth seals to improve rotor stability
FR2635562B1 (fr) * 1988-08-18 1993-12-24 Snecma Anneau de stator de turbine associe a un support de liaison au carter de turbine
US5010729A (en) * 1989-01-03 1991-04-30 General Electric Company Geared counterrotating turbine/fan propulsion system

Also Published As

Publication number Publication date
US5197281A (en) 1993-03-30
JPH04228836A (ja) 1992-08-18
GB2242709B (en) 1993-08-18
CA2034469A1 (en) 1991-10-04
DE4110244A1 (de) 1991-10-10
FR2660371A1 (fr) 1991-10-04
GB9106594D0 (en) 1991-05-15
JPH0692741B2 (ja) 1994-11-16
GB2242709A (en) 1991-10-09
ITMI910920A0 (it) 1991-04-03
ITMI910920A1 (it) 1992-10-03

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