BR112015015772A2 - plataforma de pá de ventoinha, conjunto de rotor, motor de turbina a gás e método para montar um conjunto de rotor - Google Patents
plataforma de pá de ventoinha, conjunto de rotor, motor de turbina a gás e método para montar um conjunto de rotorInfo
- Publication number
- BR112015015772A2 BR112015015772A2 BR112015015772A BR112015015772A BR112015015772A2 BR 112015015772 A2 BR112015015772 A2 BR 112015015772A2 BR 112015015772 A BR112015015772 A BR 112015015772A BR 112015015772 A BR112015015772 A BR 112015015772A BR 112015015772 A2 BR112015015772 A2 BR 112015015772A2
- Authority
- BR
- Brazil
- Prior art keywords
- rotor assembly
- fan
- mounting
- gas turbine
- turbine engine
- Prior art date
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion 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
- 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
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F02K3/06—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 front fan
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
-
- 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
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
resumo plataforma de pá de ventoinha, conjunto de rotor, motor de turbina a gás e método para montar um conjunto de rotor são descritos uma plataforma de pá de ventoinha de motor de turbina a gás, motor de turbina a gás e conjunto de rotor relacionado bem como um método para montar os mesmos. a plataforma tem uma porção dianteira proximal a um eixo geométrico de rotação, uma porção traseira e uma porção de transição entre as porções dianteira e traseira. a porção dianteira tem uma superfície de interface dianteira voltada axialmente para frente, a porção traseira tem uma superfície de interface traseira voltada radialmente para fora, e a porção de transição tem pelo menos um recurso de montagem. para o método de montagem, um suporte traseiro é instalado em um conjunto de bobina de arranque e disco de ventoinha. uma pluralidade de pás de ventoinha são instaladas em um disco de ventoinha, seguido da instalação de uma plataforma de ventoinha entre pás adjacentes e fixação dos recursos de montagem ao disco, preenchendo, desse modo, o espaço anular do disco de ventoinha. por fim, um suporte dianteiro é instalado no disco de ventoinha.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/731,459 US9399922B2 (en) | 2012-12-31 | 2012-12-31 | Non-integral fan blade platform |
PCT/US2013/076935 WO2014105701A2 (en) | 2012-12-31 | 2013-12-20 | Non-integral fan blade platform |
Publications (1)
Publication Number | Publication Date |
---|---|
BR112015015772A2 true BR112015015772A2 (pt) | 2017-07-11 |
Family
ID=49918928
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR112015015772A BR112015015772A2 (pt) | 2012-12-31 | 2013-12-20 | plataforma de pá de ventoinha, conjunto de rotor, motor de turbina a gás e método para montar um conjunto de rotor |
Country Status (7)
Country | Link |
---|---|
US (1) | US9399922B2 (pt) |
EP (1) | EP2941542A2 (pt) |
JP (1) | JP2016509646A (pt) |
CN (1) | CN104884743B (pt) |
BR (1) | BR112015015772A2 (pt) |
CA (1) | CA2896508A1 (pt) |
WO (1) | WO2014105701A2 (pt) |
Families Citing this family (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20160053636A1 (en) * | 2013-03-15 | 2016-02-25 | United Technologies Corporation | Injection Molded Composite Fan Platform |
GB201314542D0 (en) * | 2013-08-14 | 2013-09-25 | Rolls Royce Plc | Annulus Filler |
GB201314541D0 (en) * | 2013-08-14 | 2013-09-25 | Rolls Royce Plc | Annulus Filler |
US10094282B2 (en) * | 2014-07-30 | 2018-10-09 | United Technologies Corporation | Spinner aft-extended forward return flange |
FR3029563B1 (fr) * | 2014-12-08 | 2020-01-17 | Safran Aircraft Engines | Plateforme a faible rapport de moyeu |
FR3039854B1 (fr) | 2015-08-03 | 2019-08-16 | Safran Aircraft Engines | Carter intermediaire de turbomachine comportant des moyens de fixation ameliores |
US10605117B2 (en) | 2015-10-08 | 2020-03-31 | General Electric Company | Fan platform for a gas turbine engine |
US10215046B2 (en) * | 2015-11-23 | 2019-02-26 | United Technologies Corporation | Airfoil platform having dual pin apertures and a vertical stiffener |
FR3048997B1 (fr) * | 2016-03-21 | 2020-03-27 | Safran Aircraft Engines | Plateforme d'aube et disque de soufflante de turbomachine aeronautique |
US10458425B2 (en) | 2016-06-02 | 2019-10-29 | General Electric Company | Conical load spreader for composite bolted joint |
US10557350B2 (en) | 2017-03-30 | 2020-02-11 | General Electric Company | I beam blade platform |
KR102176954B1 (ko) | 2017-09-14 | 2020-11-10 | 두산중공업 주식회사 | 가스 터빈용 압축기 로터 디스크 |
GB201718600D0 (en) | 2017-11-10 | 2017-12-27 | Rolls Royce Plc | Annulus filler |
FR3073907B1 (fr) * | 2017-11-17 | 2020-12-11 | Safran Aircraft Engines | Organe de retention pour plateforme de turbomachine |
US10738630B2 (en) | 2018-02-19 | 2020-08-11 | General Electric Company | Platform apparatus for propulsion rotor |
FR3082871B1 (fr) * | 2018-06-21 | 2020-05-29 | Safran Aircraft Engines | Soufflante comprenant une plateforme et un verrou de blocage |
FR3082876B1 (fr) * | 2018-06-21 | 2021-01-22 | Safran Aircraft Engines | Soufflante comprenant une plateforme et un verrou de blocage |
US10704400B2 (en) * | 2018-10-17 | 2020-07-07 | Pratt & Whitney Canada Corp. | Rotor assembly with rotor disc lip |
FR3088367B1 (fr) * | 2018-11-09 | 2020-11-20 | Safran Aircraft Engines | Ensemble de redresseur de flux |
FR3089548B1 (fr) * | 2018-12-07 | 2021-03-19 | Safran Aircraft Engines | Soufflante comprenant une plateforme inter-aubes fixee a l’amont par une virole |
FR3090733B1 (fr) * | 2018-12-21 | 2020-12-04 | Safran Aircraft Engines | Ensemble de turbomachine comprenant des aubes de soufflante à bord de fuite prolongé |
FR3094400B1 (fr) | 2019-03-28 | 2022-12-16 | Safran | Rotor de soufflante pour turbomachine |
CN111852906B (zh) * | 2019-04-28 | 2022-02-22 | 中国航发商用航空发动机有限责任公司 | 航空发动机风扇装置及航空发动机 |
CN113495002B (zh) * | 2020-04-03 | 2023-01-06 | 中国航发商用航空发动机有限责任公司 | 航空发动机非全环风扇叶片的旋转冲击试验装置 |
CN114321006A (zh) * | 2020-09-29 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | 风扇流道板及其变形控制方法、风扇 |
FR3123088B1 (fr) | 2021-05-18 | 2023-11-24 | Safran Aircraft Engines | Plateforme de roue aubagée |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB9208409D0 (en) * | 1992-04-16 | 1992-06-03 | Rolls Royce Plc | Rotors for gas turbine engines |
FR2715975B1 (fr) | 1994-02-10 | 1996-03-29 | Snecma | Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées. |
US6145300A (en) | 1998-07-09 | 2000-11-14 | Pratt & Whitney Canada Corp. | Integrated fan / low pressure compressor rotor for gas turbine engine |
EP1124038A1 (de) | 2000-02-09 | 2001-08-16 | Siemens Aktiengesellschaft | Turbinenschaufelanordnung |
US6447250B1 (en) | 2000-11-27 | 2002-09-10 | General Electric Company | Non-integral fan platform |
JP4269829B2 (ja) | 2003-07-04 | 2009-05-27 | 株式会社Ihi | シュラウドセグメント |
US7950899B2 (en) | 2005-05-31 | 2011-05-31 | United Technologies Corporation | Modular fan inlet case |
JP4911286B2 (ja) | 2006-03-14 | 2012-04-04 | 株式会社Ihi | ファンのダブテール構造 |
FR2920187B1 (fr) | 2007-08-24 | 2014-07-04 | Snecma | Soufflante pour turbomachine d'aeronef comprenant une bride d'equilibrage masqueee par le cone d'entree. |
GB0803366D0 (en) | 2008-02-26 | 2008-04-02 | Rolls Royce Plc | Nose cone assembly |
GB0804260D0 (en) | 2008-03-07 | 2008-04-16 | Rolls Royce Plc | Annulus filler |
GB0814718D0 (en) | 2008-08-13 | 2008-09-17 | Rolls Royce Plc | Annulus filler |
GB0908422D0 (en) | 2009-05-18 | 2009-06-24 | Rolls Royce Plc | Annulus filler |
GB0914060D0 (en) | 2009-08-12 | 2009-09-16 | Rolls Royce Plc | A rotor assembly for a gas turbine |
GB0922422D0 (en) | 2009-12-23 | 2010-02-03 | Rolls Royce Plc | Annulus Filler Assembly for a Rotor of a Turbomachine |
FR2979662B1 (fr) | 2011-09-07 | 2013-09-27 | Snecma | Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine et turbine ou compresseur incorporant un distributeur ou un redresseur forme de tels secteurs |
US8438832B1 (en) | 2012-01-31 | 2013-05-14 | United Technologies Corporation | High turning fan exit stator |
US9650902B2 (en) | 2013-01-11 | 2017-05-16 | United Technologies Corporation | Integral fan blade wear pad and platform seal |
-
2012
- 2012-12-31 US US13/731,459 patent/US9399922B2/en active Active
-
2013
- 2013-12-20 BR BR112015015772A patent/BR112015015772A2/pt not_active IP Right Cessation
- 2013-12-20 CA CA2896508A patent/CA2896508A1/en not_active Abandoned
- 2013-12-20 JP JP2015550694A patent/JP2016509646A/ja active Pending
- 2013-12-20 CN CN201380068968.1A patent/CN104884743B/zh active Active
- 2013-12-20 EP EP13818163.1A patent/EP2941542A2/en not_active Withdrawn
- 2013-12-20 WO PCT/US2013/076935 patent/WO2014105701A2/en active Application Filing
Also Published As
Publication number | Publication date |
---|---|
WO2014105701A3 (en) | 2014-08-28 |
US20140186187A1 (en) | 2014-07-03 |
EP2941542A2 (en) | 2015-11-11 |
WO2014105701A2 (en) | 2014-07-03 |
CN104884743B (zh) | 2017-03-15 |
CA2896508A1 (en) | 2014-07-03 |
JP2016509646A (ja) | 2016-03-31 |
CN104884743A (zh) | 2015-09-02 |
US9399922B2 (en) | 2016-07-26 |
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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 5A ANUIDADE. |
|
B08K | Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette] |
Free format text: EM VIRTUDE DO ARQUIVAMENTO PUBLICADO NA RPI 2495 DE 30-10-2018 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDO O ARQUIVAMENTO DO PEDIDO DE PATENTE, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013. |