RU2012130351A - TURBINE STEP IN A TURBO MACHINE - Google Patents

TURBINE STEP IN A TURBO MACHINE Download PDF

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Publication number
RU2012130351A
RU2012130351A RU2012130351/06A RU2012130351A RU2012130351A RU 2012130351 A RU2012130351 A RU 2012130351A RU 2012130351/06 A RU2012130351/06 A RU 2012130351/06A RU 2012130351 A RU2012130351 A RU 2012130351A RU 2012130351 A RU2012130351 A RU 2012130351A
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RU
Russia
Prior art keywords
annular
casing
turbine stage
stage according
tab
Prior art date
Application number
RU2012130351/06A
Other languages
Russian (ru)
Inventor
Эмманюэль БЕРШ
Венсан ФИЛИППО
Original Assignee
Снекма
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 Снекма filed Critical Снекма
Publication of RU2012130351A publication Critical patent/RU2012130351A/en

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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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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

Landscapes

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

Abstract

1. Ступень турбины для турбомашины, содержащая лопаточное колесо, вращающееся внутри разделенного на секторы колеса (54) из композитного материала, закрепленного на кожухе (14), при этом каждый кольцевой сектор содержит выходную окружную реборду (52), опирающуюся в радиальном направлении на кольцевую лапку (56) кожуха (14) устройством крепления С-образной формы,кольцевая лапка (56) кожуха (14) установлена в радиальном направлении в кольцевую канавку (50) выходной окружной реборды (52) кольца (54) с осевым зазором в холодном состоянии, исчезающем в горячем состоянии при работе и обеспечивающим герметичное осевое сжатие кольцевой лапки (56) кожуха (14) в кольцевой канавке (50) кольцевого сектора.2. Ступень турбины по п.1,кольцевая лапка (56) кожуха (14) содержит входную (62) и выходную (64) радиальные поверхности, предназначенные для обеспечения упора в горячем состоянии на радиальные фланцы (58, 60) канавки (50).3. Ступень турбины по п.1,осевой зазор в холодном состоянии составляет порядка десятой доли миллиметра.4. Ступень турбины по п.1,в кольцевой канавке (40) поверхности (66) кольцевой лапки, которая опирается на дно (68) кольцевой канавки (50) кольцевого сектора, расположено уплотнительное герметизирующее кольцо (38).5. Ступень турбины по п.1,композитный материал выполнен на керамической основе, а кожух (14) выполнен из металлического материала.6. Турбомашина, такая как авиационный турбореактивный или турбовинтовой двигатель,она содержит ступень турбины высокого давления по п.1.1. A turbine stage for a turbomachine, comprising a blade wheel rotating inside a sectorized wheel (54) made of composite material mounted on a casing (14), each annular sector comprising an output circumferential flange (52), radially supported by an annular the tab (56) of the casing (14) with a C-shaped attachment device, the annular tab (56) of the casing (14) is installed radially in the annular groove (50) of the output circumferential flange (52) of the ring (54) with axial clearance in the cold state fading in hot state during operation and ensuring tight axial compression of the annular tab (56) of the casing (14) in the annular groove (50) of the annular sector. 2. The turbine stage according to claim 1, the annular tab (56) of the casing (14) contains inlet (62) and output (64) radial surfaces designed to provide hot stop on the radial flanges (58, 60) of the groove (50) .3 . The turbine stage according to claim 1, the axial clearance in the cold state is about a tenth of a millimeter. The turbine stage according to claim 1, in the annular groove (40) of the surface (66) of the annular foot, which rests on the bottom (68) of the annular groove (50) of the annular sector, there is a sealing sealing ring (38) .5. The turbine stage according to claim 1, the composite material is made on a ceramic basis, and the casing (14) is made of metal material. A turbomachine, such as an aircraft turbojet or turboprop engine, comprises a stage of a high pressure turbine according to claim 1.

Claims (6)

1. Ступень турбины для турбомашины, содержащая лопаточное колесо, вращающееся внутри разделенного на секторы колеса (54) из композитного материала, закрепленного на кожухе (14), при этом каждый кольцевой сектор содержит выходную окружную реборду (52), опирающуюся в радиальном направлении на кольцевую лапку (56) кожуха (14) устройством крепления С-образной формы, отличающаяся тем, что кольцевая лапка (56) кожуха (14) установлена в радиальном направлении в кольцевую канавку (50) выходной окружной реборды (52) кольца (54) с осевым зазором в холодном состоянии, исчезающем в горячем состоянии при работе и обеспечивающим герметичное осевое сжатие кольцевой лапки (56) кожуха (14) в кольцевой канавке (50) кольцевого сектора.1. A turbine stage for a turbomachine, comprising a blade wheel rotating inside a sectorized wheel (54) made of composite material mounted on a casing (14), each annular sector comprising an output circumferential flange (52), radially supported by an annular the tab (56) of the casing (14) with a C-shaped attachment device, characterized in that the annular tab (56) of the casing (14) is installed in the radial direction in the annular groove (50) of the output circumferential flange (52) of the ring (54) with an axial cold clearance , Fading in the hot condition during operation and provides a tight axial compression of the annular foot (56) of the casing (14) in the annular groove (50) of the annular sector. 2. Ступень турбины по п.1, отличающаяся тем, что кольцевая лапка (56) кожуха (14) содержит входную (62) и выходную (64) радиальные поверхности, предназначенные для обеспечения упора в горячем состоянии на радиальные фланцы (58, 60) канавки (50).2. The turbine stage according to claim 1, characterized in that the annular tab (56) of the casing (14) contains inlet (62) and output (64) radial surfaces designed to provide hot stop on radial flanges (58, 60) grooves (50). 3. Ступень турбины по п.1, отличающаяся тем, что осевой зазор в холодном состоянии составляет порядка десятой доли миллиметра.3. The turbine stage according to claim 1, characterized in that the axial clearance in the cold state is about a tenth of a millimeter. 4. Ступень турбины по п.1, отличающаяся тем, что в кольцевой канавке (40) поверхности (66) кольцевой лапки, которая опирается на дно (68) кольцевой канавки (50) кольцевого сектора, расположено уплотнительное герметизирующее кольцо (38).4. The turbine stage according to claim 1, characterized in that in the annular groove (40) of the surface (66) of the annular foot, which rests on the bottom (68) of the annular groove (50) of the annular sector, there is a sealing sealing ring (38). 5. Ступень турбины по п.1, отличающаяся тем, что композитный материал выполнен на керамической основе, а кожух (14) выполнен из металлического материала.5. The turbine stage according to claim 1, characterized in that the composite material is made on a ceramic basis, and the casing (14) is made of metal material. 6. Турбомашина, такая как авиационный турбореактивный или турбовинтовой двигатель, отличающаяся тем, что она содержит ступень турбины высокого давления по п.1. 6. A turbomachine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a high-pressure turbine stage according to claim 1.
RU2012130351/06A 2009-12-18 2010-12-14 TURBINE STEP IN A TURBO MACHINE RU2012130351A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0906162A FR2954400B1 (en) 2009-12-18 2009-12-18 TURBINE STAGE IN A TURBOMACHINE
FR09/06162 2009-12-18
PCT/FR2010/052721 WO2011073570A1 (en) 2009-12-18 2010-12-14 Turbine stage of a turbine engine

Publications (1)

Publication Number Publication Date
RU2012130351A true RU2012130351A (en) 2014-01-27

Family

ID=42331016

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2012130351/06A RU2012130351A (en) 2009-12-18 2010-12-14 TURBINE STEP IN A TURBO MACHINE

Country Status (8)

Country Link
US (1) US20120237342A1 (en)
EP (1) EP2513428A1 (en)
CN (1) CN102667066A (en)
BR (1) BR112012010257A2 (en)
CA (1) CA2777370A1 (en)
FR (1) FR2954400B1 (en)
RU (1) RU2012130351A (en)
WO (1) WO2011073570A1 (en)

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ES2935815T3 (en) * 2013-09-06 2023-03-10 MTU Aero Engines AG (Dis)assembly of a gas turbine rotor, in particular front
US10100659B2 (en) 2014-12-16 2018-10-16 Rolls-Royce North American Technologies Inc. Hanger system for a turbine engine component
GB201508323D0 (en) * 2015-05-15 2015-06-24 Rolls Royce Plc A wall cooling arrangement for a gas turbine engine
JP6614407B2 (en) * 2015-06-10 2019-12-04 株式会社Ｉｈｉ Turbine
FR3041993B1 (en) * 2015-10-05 2019-06-21 Safran Aircraft Engines TURBINE RING ASSEMBLY WITH AXIAL RETENTION
FR3045715B1 (en) * 2015-12-18 2018-01-26 Safran Aircraft Engines TURBINE RING ASSEMBLY WITH COLD AND HOT HOLDING
US12037926B2 (en) 2016-02-05 2024-07-16 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor discs
FR3056637B1 (en) * 2016-09-27 2018-10-19 Safran Aircraft Engines TURBINE RING ASSEMBLY WITH COLD SETTING
FR3061738B1 (en) * 2017-01-12 2019-05-31 Safran Aircraft Engines TURBINE RING ASSEMBLY
US10815812B2 (en) * 2017-05-12 2020-10-27 Raytheon Technologies Corporation Geometry optimized blade outer air seal for thermal loads
EP4013950B1 (en) * 2019-10-18 2023-11-08 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor discs
CN113898414B (en) * 2021-12-09 2022-03-18 成都中科翼能科技有限公司 Reinforcing structure for preventing thermal vibration deformation of high-pressure rotor of gas turbine

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FR951446A (en) 1942-09-01 1949-10-25 Dynamit Nobel Ag Railway crossing
FR2780443B1 (en) * 1998-06-25 2000-08-04 Snecma HIGH PRESSURE TURBINE STATOR RING OF A TURBOMACHINE
JP4269829B2 (en) * 2003-07-04 2009-05-27 株式会社Ｉｈｉ Shroud segment
DE102005013798A1 (en) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Heat release segment for sealing a flow channel of a flow rotary machine
FR2885168A1 (en) * 2005-04-27 2006-11-03 Snecma Moteurs Sa SEALING DEVICE FOR A TURBOMACHINE ENCLOSURE, AND AIRCRAFT ENGINE EQUIPPED WITH SAME
US7452183B2 (en) * 2005-08-06 2008-11-18 General Electric Company Thermally compliant turbine shroud assembly
FR2899275A1 (en) * 2006-03-30 2007-10-05 Snecma Sa Ring sector fixing device for e.g. turboprop of aircraft, has cylindrical rims engaged on casing rail, where each cylindrical rim comprises annular collar axially clamped on casing rail using annular locking unit
FR2899274B1 (en) * 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE
US7686577B2 (en) * 2006-11-02 2010-03-30 Siemens Energy, Inc. Stacked laminate fiber wrapped segment
FR2913717A1 (en) * 2007-03-15 2008-09-19 Snecma Propulsion Solide Sa Ring assembly for e.g. aircraft engine gas turbine, has centering unit constituted of metallic ring gear and bracket, and centering complete ring, where elastically deformable tab blocks rotation of ring around axis of ring

Also Published As

Publication number Publication date
US20120237342A1 (en) 2012-09-20
CN102667066A (en) 2012-09-12
FR2954400A1 (en) 2011-06-24
EP2513428A1 (en) 2012-10-24
FR2954400B1 (en) 2012-03-09
BR112012010257A2 (en) 2016-03-29
CA2777370A1 (en) 2011-06-23
WO2011073570A1 (en) 2011-06-23

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