BR112017012593A2 - conjunto de turbina de turbomáquina de aeronave - Google Patents

conjunto de turbina de turbomáquina de aeronave

Info

Publication number
BR112017012593A2
BR112017012593A2 BR112017012593-5A BR112017012593A BR112017012593A2 BR 112017012593 A2 BR112017012593 A2 BR 112017012593A2 BR 112017012593 A BR112017012593 A BR 112017012593A BR 112017012593 A2 BR112017012593 A2 BR 112017012593A2
Authority
BR
Brazil
Prior art keywords
stator
cavity
rotor
turbomachine turbine
turbine set
Prior art date
Application number
BR112017012593-5A
Other languages
English (en)
Other versions
BR112017012593B1 (pt
Inventor
Bernard Quelven Damien
Vincent Desforges Jean-Baptiste
Guy Judet Maurice
Tang Ba-Phuc
Original Assignee
Safran Aircraft Engines
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=53059194&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=BR112017012593(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Safran Aircraft Engines filed Critical Safran Aircraft Engines
Publication of BR112017012593A2 publication Critical patent/BR112017012593A2/pt
Publication of BR112017012593B1 publication Critical patent/BR112017012593B1/pt

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
    • 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
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

a presente invenção se refere a um conjunto de turbina (10) de turbomáquina (1) que compreende pelo menos um primeiro rotor com lâminas (12), um estator com lâminas (13) e um segundo rotor com lâminas (14) dispostos sucessivamente, em que os rotores (12, 14) são montados sobre um eixo (2), uma platina de vedação (20) que se estende entre o estator (13) e o eixo (2) e que separa uma primeira cavidade (c1), disposta entre o primeiro rotor (12) e o estator (13), de uma segunda cavidade (c2), disposta entre o estator (13) e o segundo rotor (14), em que meios (300, 31) de diminuição da pressão são posicionados no seio da primeira cavidade (c1), sendo que o conjunto é distinguido pelo fato de que os ditos meios (300, 31) de diminuição da pressão compreendem uma pluralidade de aletas de recompressão (300) substancialmente radiais que se estendem na primeira cavidade (c1).
BR112017012593-5A 2014-12-17 2015-12-17 Conjunto de turbina de turbomáquina de aeronave BR112017012593B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1462655 2014-12-17
FR1462655A FR3030614B1 (fr) 2014-12-17 2014-12-17 Ensemble de turbine haute pression de turbomachine
PCT/FR2015/053597 WO2016097632A1 (fr) 2014-12-17 2015-12-17 Ensemble de turbine de turbomachine d'aéronef

Publications (2)

Publication Number Publication Date
BR112017012593A2 true BR112017012593A2 (pt) 2018-02-27
BR112017012593B1 BR112017012593B1 (pt) 2022-11-29

Family

ID=53059194

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112017012593-5A BR112017012593B1 (pt) 2014-12-17 2015-12-17 Conjunto de turbina de turbomáquina de aeronave

Country Status (9)

Country Link
US (1) US10280776B2 (pt)
EP (1) EP3234309B1 (pt)
JP (1) JP6882979B2 (pt)
CN (1) CN107109956B (pt)
BR (1) BR112017012593B1 (pt)
CA (1) CA2970715C (pt)
FR (1) FR3030614B1 (pt)
RU (1) RU2705319C2 (pt)
WO (1) WO2016097632A1 (pt)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2016277549B2 (en) * 2016-10-24 2018-10-18 Intex Holdings Pty Ltd A multi-stage axial flow turbine adapted to operate at low steam temperatures
US10767485B2 (en) * 2018-01-08 2020-09-08 Raytheon Technologies Corporation Radial cooling system for gas turbine engine compressors
FR3086971B1 (fr) * 2018-10-04 2021-01-22 Safran Aircraft Engines Ensemble de regulation de flux auxiliaire
FR3107718B1 (fr) 2020-02-28 2022-01-28 Safran Aircraft Engines Ensemble de turbine
FR3117531B1 (fr) 2020-12-11 2022-11-04 Safran Aircraft Engines Ensemble de turbine
FR3126014B1 (fr) * 2021-08-05 2024-06-14 Safran Aircraft Engines Distributeur pour turbomachine
FR3126022A1 (fr) * 2021-08-05 2023-02-10 Safran Aircraft Engines Ensemble pour turbomachine d’aeronef comprenant une anneau de recouvrement pour l’isolement d’organes de fixation mecanique vis-a-vis d’un flux d’air

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL192865A (pt) * 1953-12-02
US4759688A (en) 1986-12-16 1988-07-26 Allied-Signal Inc. Cooling flow side entry for cooled turbine blading
JPH0742863U (ja) * 1993-12-29 1995-08-11 三菱重工業株式会社 ガスタービン構造
GB2307520B (en) * 1995-11-14 1999-07-07 Rolls Royce Plc A gas turbine engine
DE69825959T2 (de) * 1997-06-19 2005-09-08 Mitsubishi Heavy Industries, Ltd. Vorrichtung zum dichten der leitschaufeln von gasturbinen
FR2771446B1 (fr) * 1997-11-27 1999-12-31 Snecma Aube de distributeur de turbine refroidie
US5984636A (en) * 1997-12-17 1999-11-16 Pratt & Whitney Canada Inc. Cooling arrangement for turbine rotor
RU2226609C2 (ru) * 2002-06-17 2004-04-10 Открытое акционерное общество "Авиадвигатель" Турбина газотурбинного двигателя
FR2851288B1 (fr) * 2003-02-14 2006-07-28 Snecma Moteurs Dispositif de refroidissement de disques de turbines
FR2892454B1 (fr) * 2005-10-21 2008-01-25 Snecma Sa Dispositif de ventilation de disques de turbine dans un moteur a turbine a gaz
GB0722511D0 (en) * 2007-11-19 2007-12-27 Rolls Royce Plc Turbine arrangement
JP2013181577A (ja) * 2012-02-29 2013-09-12 Mitsubishi Heavy Ind Ltd シール装置、及びこれを備えている回転機械
US9291071B2 (en) * 2012-12-03 2016-03-22 United Technologies Corporation Turbine nozzle baffle
GB201514650D0 (en) * 2015-08-18 2015-09-30 Rolls Royce Plc A levered joint

Also Published As

Publication number Publication date
CA2970715C (fr) 2022-10-04
EP3234309B1 (fr) 2018-10-17
WO2016097632A1 (fr) 2016-06-23
US20170328227A1 (en) 2017-11-16
JP2018505336A (ja) 2018-02-22
FR3030614B1 (fr) 2019-09-20
FR3030614A1 (fr) 2016-06-24
RU2017124883A (ru) 2019-01-18
CA2970715A1 (fr) 2016-06-23
CN107109956A (zh) 2017-08-29
BR112017012593B1 (pt) 2022-11-29
EP3234309A1 (fr) 2017-10-25
US10280776B2 (en) 2019-05-07
JP6882979B2 (ja) 2021-06-02
RU2705319C2 (ru) 2019-11-06
RU2017124883A3 (pt) 2019-06-26
CN107109956B (zh) 2019-04-12

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Legal Events

Date Code Title Description
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 17/12/2015, OBSERVADAS AS CONDICOES LEGAIS