BR112015007512A2 - motor de turbina a gás - Google Patents
motor de turbina a gásInfo
- Publication number
- BR112015007512A2 BR112015007512A2 BR112015007512A BR112015007512A BR112015007512A2 BR 112015007512 A2 BR112015007512 A2 BR 112015007512A2 BR 112015007512 A BR112015007512 A BR 112015007512A BR 112015007512 A BR112015007512 A BR 112015007512A BR 112015007512 A2 BR112015007512 A2 BR 112015007512A2
- Authority
- BR
- Brazil
- Prior art keywords
- ratio
- stages
- gas turbine
- airfoil
- turbine engine
- Prior art date
Links
Classifications
-
- 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
- F02K3/075—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 controlling flow ratio between flows
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Retarders (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
- Control Of Turbines (AREA)
Abstract
1 / 1 resumo âmotor de turbina a gãsâ um motor de turbina a gã¡s tipicamente estã¡ compreendido de um estã¡gio de ventilador, mãºltiplos estã¡gios de compressor, e mãºltiplos estã¡gios de turbina. estes estã¡gios sã£o compostos de fileiras de lã¢mina rotativas e fileiras de palheta estã¡tica alternadas. o nãºmero total de lã¢minas e palhetas ã© a contagem de aerofã³lio. uma razã£o de pressã£o global ã© maior do que 30. uma razã£o de desvio ã© maior do que 8. uma razã£o de estã¡gio ã© o produto da razã£o de desvio e a razã£o de pressã£o global dividido pelo nãºmero de estã¡gios. uma razã£o de aerofã³lio ã© que o produto dividido pela contagem de aerofã³lio. a razã£o de estã¡gio ã© maior do que ou igual a 22 e/ou a razã£o de aerofã³lio ã© maior do que ou igual a 0,12.
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201261710465P | 2012-10-05 | 2012-10-05 | |
US61/710465 | 2012-10-05 | ||
US13/716253 | 2012-12-17 | ||
US13/716,253 US20140096509A1 (en) | 2012-10-05 | 2012-12-17 | Geared Turbofan Engine With Increased Bypass Ratio and Compressor Ratio ... |
PCT/US2013/063341 WO2014107202A2 (en) | 2012-10-05 | 2013-10-04 | Geared turbofan engine with increased bypass ratio and compressor ratio achieved with low stage and total airfoil count |
Publications (2)
Publication Number | Publication Date |
---|---|
BR112015007512A2 true BR112015007512A2 (pt) | 2017-07-04 |
BR112015007512B1 BR112015007512B1 (pt) | 2022-12-06 |
Family
ID=50431649
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR112015007512-6A BR112015007512B1 (pt) | 2012-10-05 | 2013-10-04 | Motor de turbina a gás |
Country Status (6)
Country | Link |
---|---|
US (1) | US20140096509A1 (pt) |
EP (1) | EP2909458A4 (pt) |
JP (1) | JP6055927B2 (pt) |
BR (1) | BR112015007512B1 (pt) |
CA (1) | CA2886267C (pt) |
WO (1) | WO2014107202A2 (pt) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9869190B2 (en) | 2014-05-30 | 2018-01-16 | General Electric Company | Variable-pitch rotor with remote counterweights |
US10072510B2 (en) | 2014-11-21 | 2018-09-11 | General Electric Company | Variable pitch fan for gas turbine engine and method of assembling the same |
US10100653B2 (en) | 2015-10-08 | 2018-10-16 | General Electric Company | Variable pitch fan blade retention system |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1435432B1 (en) * | 2001-10-10 | 2016-05-18 | Mitsubishi Hitachi Power Systems, Ltd. | Turbine blade |
US6732502B2 (en) * | 2002-03-01 | 2004-05-11 | General Electric Company | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor |
US7395657B2 (en) * | 2003-10-20 | 2008-07-08 | General Electric Company | Flade gas turbine engine with fixed geometry inlet |
DE102004031255B4 (de) * | 2004-06-29 | 2014-02-13 | MTU Aero Engines AG | Einlaufbelag |
US20070000232A1 (en) * | 2005-06-29 | 2007-01-04 | General Electric Company | Gas turbine engine and method of operating same |
US20070245708A1 (en) * | 2006-04-20 | 2007-10-25 | United Technologies Corporation | High cycle fatigue management for gas turbine engines |
US7694505B2 (en) * | 2006-07-31 | 2010-04-13 | General Electric Company | Gas turbine engine assembly and method of assembling same |
US7765789B2 (en) * | 2006-12-15 | 2010-08-03 | General Electric Company | Apparatus and method for assembling gas turbine engines |
US20080310956A1 (en) * | 2007-06-13 | 2008-12-18 | Jain Ashok K | Variable geometry gas turbine engine nacelle assembly with nanoelectromechanical system |
US8277174B2 (en) * | 2007-09-21 | 2012-10-02 | United Technologies Corporation | Gas turbine engine compressor arrangement |
US8807477B2 (en) * | 2008-06-02 | 2014-08-19 | United Technologies Corporation | Gas turbine engine compressor arrangement |
US20100126178A1 (en) * | 2008-10-08 | 2010-05-27 | Searete Llc, A Limited Liability Corporation Of The State Of Delaware | Hybrid propulsive engine including at least one independently rotatable turbine stator |
US20110004388A1 (en) * | 2009-07-01 | 2011-01-06 | United Technologies Corporation | Turbofan temperature control with variable area nozzle |
US20110167831A1 (en) * | 2009-09-25 | 2011-07-14 | James Edward Johnson | Adaptive core engine |
JP2012188957A (ja) * | 2011-03-09 | 2012-10-04 | Ihi Corp | 軸流タービン |
-
2012
- 2012-12-17 US US13/716,253 patent/US20140096509A1/en not_active Abandoned
-
2013
- 2013-10-04 EP EP13870075.2A patent/EP2909458A4/en not_active Withdrawn
- 2013-10-04 CA CA2886267A patent/CA2886267C/en active Active
- 2013-10-04 BR BR112015007512-6A patent/BR112015007512B1/pt active IP Right Grant
- 2013-10-04 WO PCT/US2013/063341 patent/WO2014107202A2/en active Application Filing
- 2013-10-04 JP JP2015535794A patent/JP6055927B2/ja active Active
Also Published As
Publication number | Publication date |
---|---|
EP2909458A4 (en) | 2016-07-20 |
WO2014107202A3 (en) | 2014-09-18 |
CA2886267A1 (en) | 2014-07-10 |
CA2886267C (en) | 2017-04-25 |
JP2015534624A (ja) | 2015-12-03 |
JP6055927B2 (ja) | 2016-12-27 |
BR112015007512B1 (pt) | 2022-12-06 |
US20140096509A1 (en) | 2014-04-10 |
EP2909458A2 (en) | 2015-08-26 |
WO2014107202A2 (en) | 2014-07-10 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B06F | Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette] | ||
B06U | Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette] | ||
B07A | Application suspended after technical examination (opinion) [chapter 7.1 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 04/10/2013, OBSERVADAS AS CONDICOES LEGAIS |