BR0103410A - Método e aparelho para reduzir a tensão na borda circunferencial do conjunto do rotor - Google Patents
Método e aparelho para reduzir a tensão na borda circunferencial do conjunto do rotorInfo
- Publication number
- BR0103410A BR0103410A BR0103410-3A BR0103410A BR0103410A BR 0103410 A BR0103410 A BR 0103410A BR 0103410 A BR0103410 A BR 0103410A BR 0103410 A BR0103410 A BR 0103410A
- Authority
- BR
- Brazil
- Prior art keywords
- rotor assembly
- rotor
- platform
- circumferential edge
- edge
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- 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
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/713—Shape curved inflexed
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Patente de Invenção: "MéTODO E APARELHO PARA REDUZIR A TENSãO NA BORDA CIRCUNFERENCIAL DO CONJUNTO DO ROTOR". A presente invenção refere-se a um conjunto do rotor (14) para um motor de turbina a gás (10) opera com tensão de borda circunferencial reduzida. O conjunto do rotor inclui um rotor (16) que inclui uma pluralidade de palhetas de rotor (18) e uma plataforma radialmente externa (48). As palhetas de rotor se estendem radialmente para fora da plataforma. Um filete de raíz (80) se estende circunferencialmente ao redor de cada palheta entre as palhetas e as plataformas. As plataformas incluem uma superfície externa (50) que inclui uma pluralidade de rebaixos (64) que se estendem entre as palhetas de rotor adjacentes. Cada rebaixo se estende de uma borda de ataque (60) da plataforma até uma borda de fuga (62) da plataforma com uma profundidade (72) que se inclina para uma profundidade de aproximadamente zero na borda de fuga.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/643,012 US6524070B1 (en) | 2000-08-21 | 2000-08-21 | Method and apparatus for reducing rotor assembly circumferential rim stress |
Publications (2)
Publication Number | Publication Date |
---|---|
BR0103410A true BR0103410A (pt) | 2002-03-26 |
BR0103410B1 BR0103410B1 (pt) | 2010-06-29 |
Family
ID=24579000
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BRPI0103410-3A BR0103410B1 (pt) | 2000-08-21 | 2001-08-16 | método de fabricação de um conjunto rotor assim como conjunto rotor. |
Country Status (5)
Country | Link |
---|---|
US (1) | US6524070B1 (pt) |
EP (1) | EP1182328A3 (pt) |
JP (1) | JP4636746B2 (pt) |
BR (1) | BR0103410B1 (pt) |
CA (1) | CA2354834C (pt) |
Families Citing this family (47)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6669445B2 (en) * | 2002-03-07 | 2003-12-30 | United Technologies Corporation | Endwall shape for use in turbomachinery |
US6837685B2 (en) * | 2002-12-13 | 2005-01-04 | General Electric Company | Methods and apparatus for repairing a rotor assembly of a turbine |
FR2851798B1 (fr) * | 2003-02-27 | 2005-04-29 | Snecma Moteurs | Aube en fleche de turboreacteur |
US6857853B1 (en) * | 2003-08-13 | 2005-02-22 | General Electric Company | Conical tip shroud fillet for a turbine bucket |
US6905309B2 (en) * | 2003-08-28 | 2005-06-14 | General Electric Company | Methods and apparatus for reducing vibrations induced to compressor airfoils |
GB2411441B (en) * | 2004-02-24 | 2006-04-19 | Rolls Royce Plc | Fan or compressor blisk |
DE102004026386A1 (de) * | 2004-05-29 | 2005-12-22 | Mtu Aero Engines Gmbh | Schaufelblatt einer Strömungsmaschine sowie Strömungsmaschine |
US7249928B2 (en) * | 2005-04-01 | 2007-07-31 | General Electric Company | Turbine nozzle with purge cavity blend |
US7476086B2 (en) * | 2005-04-07 | 2009-01-13 | General Electric Company | Tip cambered swept blade |
US7374403B2 (en) * | 2005-04-07 | 2008-05-20 | General Electric Company | Low solidity turbofan |
US7497664B2 (en) * | 2005-08-16 | 2009-03-03 | General Electric Company | Methods and apparatus for reducing vibrations induced to airfoils |
US7465155B2 (en) | 2006-02-27 | 2008-12-16 | Honeywell International Inc. | Non-axisymmetric end wall contouring for a turbomachine blade row |
JP5283855B2 (ja) * | 2007-03-29 | 2013-09-04 | 株式会社Ihi | ターボ機械の壁、及びターボ機械 |
US8100655B2 (en) * | 2008-03-28 | 2012-01-24 | Pratt & Whitney Canada Corp. | Method of machining airfoil root fillets |
EP2184442A1 (en) * | 2008-11-11 | 2010-05-12 | ALSTOM Technology Ltd | Airfoil fillet |
US8231353B2 (en) * | 2008-12-31 | 2012-07-31 | General Electric Company | Methods and apparatus relating to improved turbine blade platform contours |
JP5297228B2 (ja) * | 2009-02-26 | 2013-09-25 | 三菱重工業株式会社 | タービン翼及びガスタービン |
FR2946083B1 (fr) * | 2009-05-28 | 2011-06-17 | Snecma | Turbine basse-pression |
US8439643B2 (en) * | 2009-08-20 | 2013-05-14 | General Electric Company | Biformal platform turbine blade |
US8403645B2 (en) * | 2009-09-16 | 2013-03-26 | United Technologies Corporation | Turbofan flow path trenches |
US8435006B2 (en) * | 2009-09-30 | 2013-05-07 | Rolls-Royce Corporation | Fan |
US9976433B2 (en) | 2010-04-02 | 2018-05-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured rotor blade platform |
US8904636B2 (en) | 2011-07-22 | 2014-12-09 | Pratt & Whitney Canada Corp. | Method of fabricating integrally bladed rotor using surface positioning in relation to surface priority |
US8844132B2 (en) | 2011-07-22 | 2014-09-30 | Pratt & Whitney Canada Corp. | Method of machining using an automatic tool path generator adapted to individual blade surfaces on an integrally bladed rotor |
US8788083B2 (en) * | 2011-07-22 | 2014-07-22 | Pratt & Whitney Canada Corp. | Compensation for process variables in a numerically-controlled machining operation |
US8631577B2 (en) | 2011-07-22 | 2014-01-21 | Pratt & Whitney Canada Corp. | Method of fabricating integrally bladed rotor and stator vane assembly |
CN103796762B (zh) * | 2011-11-04 | 2016-08-24 | 日本精工株式会社 | 主轴装置以及静电喷涂装置 |
US9267386B2 (en) | 2012-06-29 | 2016-02-23 | United Technologies Corporation | Fairing assembly |
WO2014028056A1 (en) | 2012-08-17 | 2014-02-20 | United Technologies Corporation | Contoured flowpath surface |
US20140154068A1 (en) * | 2012-09-28 | 2014-06-05 | United Technologies Corporation | Endwall Controuring |
WO2014163673A2 (en) | 2013-03-11 | 2014-10-09 | Bronwyn Power | Gas turbine engine flow path geometry |
JP5479624B2 (ja) * | 2013-03-13 | 2014-04-23 | 三菱重工業株式会社 | タービン翼及びガスタービン |
WO2014197062A2 (en) | 2013-03-15 | 2014-12-11 | United Technologies Corporation | Fan exit guide vane platform contouring |
US10352180B2 (en) | 2013-10-23 | 2019-07-16 | General Electric Company | Gas turbine nozzle trailing edge fillet |
US10294805B2 (en) * | 2013-12-20 | 2019-05-21 | United Technologies Corporation | Gas turbine engine integrally bladed rotor with asymmetrical trench fillets |
GB201418948D0 (en) * | 2014-10-24 | 2014-12-10 | Rolls Royce Plc | Row of aerofoil members |
US9890641B2 (en) | 2015-01-15 | 2018-02-13 | United Technologies Corporation | Gas turbine engine truncated airfoil fillet |
US20160245297A1 (en) * | 2015-02-23 | 2016-08-25 | Howden Roots Llc | Impeller comprising variably-dimensioned fillet to secure blades and compressor comprised thereof |
US20170089202A1 (en) * | 2015-09-29 | 2017-03-30 | United Technologies Corporation | Flow path trenches and methods of forming the same |
US10240462B2 (en) | 2016-01-29 | 2019-03-26 | General Electric Company | End wall contour for an axial flow turbine stage |
US10458426B2 (en) | 2016-09-15 | 2019-10-29 | General Electric Company | Aircraft fan with low part-span solidity |
US10502230B2 (en) * | 2017-07-18 | 2019-12-10 | United Technologies Corporation | Integrally bladed rotor having double fillet |
DE102017218886A1 (de) * | 2017-10-23 | 2019-04-25 | MTU Aero Engines AG | Schaufel und Rotor für eine Strömungsmaschine sowie Strömungsmaschine |
US20190178094A1 (en) * | 2017-11-02 | 2019-06-13 | United Technologies Corporation | Integrally bladed rotor |
CN108487938A (zh) * | 2018-04-25 | 2018-09-04 | 哈尔滨电气股份有限公司 | 一种新型燃机透平第一级动叶 |
FR3106626B1 (fr) * | 2020-01-24 | 2022-06-10 | Safran Aircraft Engines | Basculement differencié entre rotor et stator aux entrefers rotor-stator dans un compresseur de turbomachine |
FR3106627B1 (fr) * | 2020-01-24 | 2023-03-17 | Safran Aircraft Engines | Basculement en vagues aux entrefers rotor-stator dans un compresseur de turbomachine |
Family Cites Families (48)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2735612A (en) | 1956-02-21 | hausmann | ||
US1793468A (en) | 1929-05-28 | 1931-02-24 | Westinghouse Electric & Mfg Co | Turbine blade |
CH229266A (de) * | 1942-03-26 | 1943-10-15 | Sulzer Ag | Turbomaschine, deren Schaufelblattflächen am Schaufelfuss mit einer Abrundung in die Grundfläche übergehen. |
US2429324A (en) | 1943-12-30 | 1947-10-21 | Meisser Christian | Rotor for centrifugal compressors |
US2415380A (en) | 1944-11-15 | 1947-02-04 | Weber Max | Propeller blade |
US2790620A (en) | 1952-07-09 | 1957-04-30 | Gen Electric | Multiple finger dovetail attachment for turbine bucket |
US2918254A (en) | 1954-05-10 | 1959-12-22 | Hausammann Werner | Turborunner |
US3095180A (en) | 1959-03-05 | 1963-06-25 | Stalker Corp | Blades for compressors, turbines and the like |
FR1442526A (fr) | 1965-05-07 | 1966-06-17 | Rateau Soc | Perfectionnements aux canaux courbes parcourus par un gaz ou une vapeur |
GB1119392A (en) | 1966-06-03 | 1968-07-10 | Rover Co Ltd | Axial flow rotor for a turbine or the like |
US3481531A (en) | 1968-03-07 | 1969-12-02 | United Aircraft Canada | Impeller boundary layer control device |
US3584969A (en) | 1968-05-25 | 1971-06-15 | Aisin Seiki | Flexible blade fan |
FR1602965A (pt) * | 1968-08-16 | 1971-03-01 | ||
GB1302036A (pt) | 1969-06-26 | 1973-01-04 | ||
US3661475A (en) | 1970-04-30 | 1972-05-09 | Gen Electric | Turbomachinery rotors |
US3890062A (en) | 1972-06-28 | 1975-06-17 | Us Energy | Blade transition for axial-flow compressors and the like |
US3927952A (en) | 1972-11-20 | 1975-12-23 | Garrett Corp | Cooled turbine components and method of making the same |
US3951611A (en) | 1974-11-14 | 1976-04-20 | Morrill Wayne J | Blank for fan blade |
NO146029C (no) | 1976-08-11 | 1982-07-14 | Kongsberg Vapenfab As | Impellerelement i et radialgassturbinhjul |
US4135857A (en) * | 1977-06-09 | 1979-01-23 | United Technologies Corporation | Reduced drag airfoil platforms |
SU756083A1 (ru) | 1978-07-18 | 1980-08-15 | Vladislav D Lubenets | Рабочее колесо вихревой машины 1 |
US4335997A (en) | 1980-01-16 | 1982-06-22 | General Motors Corporation | Stress resistant hybrid radial turbine wheel |
DE3023466C2 (de) | 1980-06-24 | 1982-11-25 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Einrichtung zur Verminderung von Sekundärströmungsverlusten in einem beschaufelten Strömungskanal |
US4671739A (en) | 1980-07-11 | 1987-06-09 | Robert W. Read | One piece molded fan |
JPS57167203U (pt) * | 1981-04-17 | 1982-10-21 | ||
DE3202855C1 (de) | 1982-01-29 | 1983-03-31 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Einrichtung zur Verminderung von Sekundaerstroemungsverlusten in einem beschaufelten Stroemungskanal |
US4587700A (en) | 1984-06-08 | 1986-05-13 | The Garrett Corporation | Method for manufacturing a dual alloy cooled turbine wheel |
US4659288A (en) | 1984-12-10 | 1987-04-21 | The Garrett Corporation | Dual alloy radial turbine rotor with hub material exposed in saddle regions of blade ring |
DE3514122A1 (de) | 1985-04-19 | 1986-10-23 | MAN Gutehoffnungshütte GmbH, 4200 Oberhausen | Verfahren zur herstellung einer leitschaufel fuer ein turbinen- oder verdichter-leitrad und nach dem verfahren hergestellte leitschaufel |
DE3710321C1 (de) | 1987-03-28 | 1988-06-01 | Mtu Muenchen Gmbh | Geblaeseschaufel,insbesondere fuer Prop-Fan-Triebwerke |
DE3726522A1 (de) | 1987-08-10 | 1989-02-23 | Standard Elektrik Lorenz Ag | Aus einer metallblechscheibe hergestelltes luefterrad und verfahren zu seiner herstellung |
US4866985A (en) | 1987-09-10 | 1989-09-19 | United States Of America As Represented By The Secretary Of Interior | Bucket wheel assembly for a flow measuring device |
US5018271A (en) | 1988-09-09 | 1991-05-28 | Airfoil Textron Inc. | Method of making a composite blade with divergent root |
US5061154A (en) | 1989-12-11 | 1991-10-29 | Allied-Signal Inc. | Radial turbine rotor with improved saddle life |
GB2251897B (en) | 1991-01-15 | 1994-11-30 | Rolls Royce Plc | A rotor |
US5215439A (en) | 1991-01-15 | 1993-06-01 | Northern Research & Engineering Corp. | Arbitrary hub for centrifugal impellers |
US5397215A (en) * | 1993-06-14 | 1995-03-14 | United Technologies Corporation | Flow directing assembly for the compression section of a rotary machine |
GB2281356B (en) | 1993-08-20 | 1997-01-29 | Rolls Royce Plc | Gas turbine engine turbine |
US5554004A (en) | 1995-07-27 | 1996-09-10 | Ametek, Inc. | Fan impeller assembly |
FR2738303B1 (fr) | 1995-08-30 | 1997-11-28 | Europ Propulsion | Turbine en materiau composite thermostructural, en particulier a petit diametre, et procede pour sa fabrication |
US5735673A (en) | 1996-12-04 | 1998-04-07 | United Technologies Corporation | Turbine engine rotor blade pair |
DE19650656C1 (de) * | 1996-12-06 | 1998-06-10 | Mtu Muenchen Gmbh | Turbomaschine mit transsonischer Verdichterstufe |
ATE228609T1 (de) * | 1997-04-01 | 2002-12-15 | Siemens Ag | Oberflächenstruktur für die wand eines strömungskanals oder einer turbinenschaufel |
EP0943784A1 (de) * | 1998-03-19 | 1999-09-22 | Asea Brown Boveri AG | Konturierter Kanal einer axialen Strömungsmaschine |
GB9823840D0 (en) * | 1998-10-30 | 1998-12-23 | Rolls Royce Plc | Bladed ducting for turbomachinery |
US6217283B1 (en) * | 1999-04-20 | 2001-04-17 | General Electric Company | Composite fan platform |
US6511294B1 (en) * | 1999-09-23 | 2003-01-28 | General Electric Company | Reduced-stress compressor blisk flowpath |
US6561761B1 (en) * | 2000-02-18 | 2003-05-13 | General Electric Company | Fluted compressor flowpath |
-
2000
- 2000-08-21 US US09/643,012 patent/US6524070B1/en not_active Expired - Lifetime
-
2001
- 2001-08-03 EP EP01306673A patent/EP1182328A3/en not_active Withdrawn
- 2001-08-09 CA CA002354834A patent/CA2354834C/en not_active Expired - Fee Related
- 2001-08-16 BR BRPI0103410-3A patent/BR0103410B1/pt not_active IP Right Cessation
- 2001-08-20 JP JP2001248451A patent/JP4636746B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
CA2354834C (en) | 2009-02-10 |
EP1182328A2 (en) | 2002-02-27 |
US6524070B1 (en) | 2003-02-25 |
EP1182328A3 (en) | 2003-06-04 |
BR0103410B1 (pt) | 2010-06-29 |
JP2002122002A (ja) | 2002-04-26 |
CA2354834A1 (en) | 2002-02-21 |
JP4636746B2 (ja) | 2011-02-23 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B06A | Patent application procedure suspended [chapter 6.1 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 16/08/2001, OBSERVADAS AS CONDICOES LEGAIS. |
|
B21F | Lapse acc. art. 78, item iv - on non-payment of the annual fees in time | ||
B24J | Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12) |
Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2475 DE 12-06-2018 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013. |