BR112012010257A2 - turbine-to-turbine stage, and turbocharger, such as a turbo-propeller or an airplane turboprop - Google Patents

turbine-to-turbine stage, and turbocharger, such as a turbo-propeller or an airplane turboprop

Info

Publication number
BR112012010257A2
BR112012010257A2 BR112012010257A BR112012010257A BR112012010257A2 BR 112012010257 A2 BR112012010257 A2 BR 112012010257A2 BR 112012010257 A BR112012010257 A BR 112012010257A BR 112012010257 A BR112012010257 A BR 112012010257A BR 112012010257 A2 BR112012010257 A2 BR 112012010257A2
Authority
BR
Brazil
Prior art keywords
turbine
turbocharger
turbo
propeller
airplane turboprop
Prior art date
Application number
BR112012010257A
Other languages
Portuguese (pt)
Inventor
Emmanuel Berche
Vicent Philippot
Original Assignee
Snecma
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 Snecma filed Critical Snecma
Publication of BR112012010257A2 publication Critical patent/BR112012010257A2/en

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
    • 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)
BR112012010257A 2009-12-18 2010-12-14 turbine-to-turbine stage, and turbocharger, such as a turbo-propeller or an airplane turboprop BR112012010257A2 (en)

Applications Claiming Priority (2)

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

Publications (1)

Publication Number Publication Date
BR112012010257A2 true BR112012010257A2 (en) 2016-03-29

Family

ID=42331016

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012010257A BR112012010257A2 (en) 2009-12-18 2010-12-14 turbine-to-turbine stage, and turbocharger, such as a turbo-propeller or an airplane turboprop

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)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2846001B1 (en) * 2013-09-06 2023-01-11 MTU Aero Engines AG Assembly and disassembly methods of a rotor of a gas turbine and corresponding tool
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
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

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CA2777370A1 (en) 2011-06-23
FR2954400A1 (en) 2011-06-24
RU2012130351A (en) 2014-01-27
EP2513428A1 (en) 2012-10-24
CN102667066A (en) 2012-09-12
FR2954400B1 (en) 2012-03-09
WO2011073570A1 (en) 2011-06-23
US20120237342A1 (en) 2012-09-20

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Legal Events

Date Code Title Description
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE A 6A ANUIDADE.

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]