BR112012007827A2 - turbina de geometria variável. - Google Patents
turbina de geometria variável.Info
- Publication number
- BR112012007827A2 BR112012007827A2 BR112012007827A BR112012007827A BR112012007827A2 BR 112012007827 A2 BR112012007827 A2 BR 112012007827A2 BR 112012007827 A BR112012007827 A BR 112012007827A BR 112012007827 A BR112012007827 A BR 112012007827A BR 112012007827 A2 BR112012007827 A2 BR 112012007827A2
- Authority
- BR
- Brazil
- Prior art keywords
- input
- inlet
- extending
- palettes
- turbine
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
- F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/18—Final actuators arranged in stator parts varying effective number of nozzles or guide conduits, e.g. sequentially operable valves for steam turbines
-
- 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
- F05D2220/40—Application in turbochargers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Control Of Turbines (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
turbina de geometria variável - é descrita de geometria variável compreendendo uma roda de turbina montada para rotação em torno de um eixo geométrico da turbina dentro de um alojamento, o alojamento definido uma entrada anular envolvendo a roda de turbina e definida entre primeira e segunda paredes laterais de entrada; e uma camisa cilíndrica axialmente móvel através da entrada anular para variar o tamanho do caminho de fluxo de gás através da entrada; em que a entrada anular é dividida em uma primeira porção de entrada anular e uma segunda porção de entrada anular axialmente deslocada da primeira porção de entrada, paletas de entrada que estendem-se axialmente até cada qual da primeira e segunda porções de entrada, as paletas de entrada definindo passagens de entrada axialmente adjacentes; em que a configuração das paletas de entrada que estendem-se até a primeira porção de entrada difere da configuração das paletas de entrada que estendem-se até a segunda porção de entrada, em que as plaetas que estendem-se até a primeira porção de entrada são circunferencialmente deslocadas das paletas que estendem-se até a segunda porção de entrada.
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0917513A GB0917513D0 (en) | 2009-10-06 | 2009-10-06 | Axially divided nozzle VG |
GBGB1005680.2A GB201005680D0 (en) | 2010-04-06 | 2010-04-06 | Variable geometry turbine |
GBGB1012538.3A GB201012538D0 (en) | 2010-07-27 | 2010-07-27 | Turbomachine |
GBGB1012744.7A GB201012744D0 (en) | 2010-07-29 | 2010-07-29 | Turbomachine |
PCT/GB2010/001861 WO2011042691A2 (en) | 2009-10-06 | 2010-10-05 | Turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
BR112012007827A2 true BR112012007827A2 (pt) | 2016-03-08 |
Family
ID=43857218
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR112012007827A BR112012007827A2 (pt) | 2009-10-06 | 2010-10-05 | turbina de geometria variável. |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP2486259A2 (pt) |
CN (1) | CN102770624B (pt) |
BR (1) | BR112012007827A2 (pt) |
IN (1) | IN2012DN02808A (pt) |
WO (1) | WO2011042691A2 (pt) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB201105726D0 (en) | 2011-04-04 | 2011-05-18 | Cummins Ltd | A turbine |
CN102536330A (zh) * | 2012-01-03 | 2012-07-04 | 大同北方天力增压技术有限公司 | 一种丰满型可调喷嘴叶片的设计方法 |
US9188019B2 (en) * | 2012-11-15 | 2015-11-17 | Honeywell International, Inc. | Turbocharger and variable-nozzle assembly therefor |
US20140286758A1 (en) * | 2013-03-19 | 2014-09-25 | Abb Turbo Systems Ag | Nozzle ring with non-uniformly distributed airfoils and uniform throat area |
WO2014175765A1 (en) * | 2013-04-25 | 2014-10-30 | Siemens Aktiengesellschaft | Set of channel nozzles for a centripetal turboexpander |
FR3014150B1 (fr) * | 2013-11-29 | 2018-03-02 | Safran Aircraft Engines | Soufflante, en particulier pour une turbomachine |
CN115387856A (zh) * | 2022-09-02 | 2022-11-25 | 清华大学 | 可变进气轴流式涡轮机 |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3071347A (en) * | 1959-12-30 | 1963-01-01 | Garrett Corp | Variable area nozzle device |
FR2226025A5 (pt) * | 1973-03-13 | 1974-11-08 | Berry Ets | |
EP0034915A1 (en) * | 1980-02-22 | 1981-09-02 | Holset Engineering Company Limited | Radially inward flow turbine |
US4492520A (en) * | 1982-05-10 | 1985-01-08 | Marchand William C | Multi-stage vane stator for radial inflow turbine |
DE3377587D1 (en) | 1982-05-28 | 1988-09-08 | Holset Engineering Co | A variable inlet area turbine |
DE3734386A1 (de) * | 1987-10-10 | 1989-04-20 | Daimler Benz Ag | Abgasturbolader fuer eine brennkraftmaschine |
JPH05133238A (ja) * | 1991-11-11 | 1993-05-28 | Mitsubishi Heavy Ind Ltd | 可変容量過給機 |
JP3725287B2 (ja) | 1996-04-25 | 2005-12-07 | アイシン精機株式会社 | 可変容量ターボチャージャ |
GB2326198A (en) | 1997-06-10 | 1998-12-16 | Holset Engineering Co | Variable geometry turbine |
GB0025244D0 (en) | 2000-10-12 | 2000-11-29 | Holset Engineering Co | Turbine |
US6931849B2 (en) | 2002-11-19 | 2005-08-23 | Holset Engineering Company, Limited | Variable geometry turbine |
US7207176B2 (en) | 2002-11-19 | 2007-04-24 | Cummins Inc. | Method of controlling the exhaust gas temperature for after-treatment systems on a diesel engine using a variable geometry turbine |
WO2005040560A1 (en) * | 2003-10-24 | 2005-05-06 | Honeywell International Inc | Sector-divided turbine assembly with axial piston variable-geometry mechanism |
WO2006048042A1 (en) | 2004-11-08 | 2006-05-11 | Honeywell International, Inc. | Variable geometry compressor |
DE102005011482B4 (de) * | 2005-03-12 | 2018-05-30 | Daimler Ag | Abgasturbolader mit einem Verdichter und einer Abgasturbine |
US20070177349A1 (en) * | 2005-11-23 | 2007-08-02 | Himanshu Pokharna | High efficiency fluid mover |
US8123470B2 (en) * | 2007-08-10 | 2012-02-28 | Honeywell International Inc. | Turbine assembly with semi-divided nozzle and half-collar piston |
DE102007058246B4 (de) | 2007-12-04 | 2020-01-09 | BMTS Technology GmbH & Co. KG | Aufladeeinrichtung |
DE102008005405B4 (de) * | 2008-01-21 | 2021-03-04 | BMTS Technology GmbH & Co. KG | Turbine, insbesondere für einen Abgasturbolader, sowie Abgasturbolader |
GB2462266A (en) | 2008-07-30 | 2010-02-03 | Cummins Turbo Tech Ltd | Variable geometry turbine with filter |
-
2010
- 2010-10-05 CN CN201080055328.3A patent/CN102770624B/zh not_active Expired - Fee Related
- 2010-10-05 BR BR112012007827A patent/BR112012007827A2/pt not_active Application Discontinuation
- 2010-10-05 IN IN2808DEN2012 patent/IN2012DN02808A/en unknown
- 2010-10-05 WO PCT/GB2010/001861 patent/WO2011042691A2/en active Application Filing
- 2010-10-05 EP EP10773664A patent/EP2486259A2/en not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
IN2012DN02808A (pt) | 2015-07-24 |
EP2486259A2 (en) | 2012-08-15 |
CN102770624A (zh) | 2012-11-07 |
WO2011042691A3 (en) | 2011-11-10 |
CN102770624B (zh) | 2015-02-25 |
WO2011042691A2 (en) | 2011-04-14 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B06F | Objections, documents and/or translations needed after an examination request according art. 34 industrial property law | ||
B06U | Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure | ||
B11B | Dismissal acc. art. 36, par 1 of ipl - no reply within 90 days to fullfil the necessary requirements |