BR112014007438A2 - motor de turbina a gás, e, arranjo para um motor de turbina a gás - Google Patents

motor de turbina a gás, e, arranjo para um motor de turbina a gás

Info

Publication number
BR112014007438A2
BR112014007438A2 BR112014007438A BR112014007438A BR112014007438A2 BR 112014007438 A2 BR112014007438 A2 BR 112014007438A2 BR 112014007438 A BR112014007438 A BR 112014007438A BR 112014007438 A BR112014007438 A BR 112014007438A BR 112014007438 A2 BR112014007438 A2 BR 112014007438A2
Authority
BR
Brazil
Prior art keywords
gas turbine
turbine engine
compressor section
section
pressure
Prior art date
Application number
BR112014007438A
Other languages
English (en)
Other versions
BR112014007438B1 (pt
Inventor
D Merry Brian
M Dye Christopher
L Suciu Gabriel
B Staubach Joseph
L Hasel Karl
Original Assignee
United Technologies Corp
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=48698587&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=BR112014007438(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Priority claimed from US13/337,354 external-priority patent/US8337147B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of BR112014007438A2 publication Critical patent/BR112014007438A2/pt
Publication of BR112014007438B1 publication Critical patent/BR112014007438B1/pt

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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • 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)
  • Control Of Positive-Displacement Air Blowers (AREA)

Abstract

1 / 1 resumo “motor de turbina a gã�s, e, arranjo para um motor de turbina a gã�sâ€� um motor de turbina a gã¡s inclui uma seã§ã£o de ventoinha, um arranjo de engrenagens configurado para acionar a seã§ã£o de ventoinha, uma seã§ã£o de compressor e uma seã§ã£o de turbina. a seã§ã£o de compressor inclui uma seã§ã£o de compressor de baixa pressã£o e uma seã§ã£o de compressor de alta pressã£o. a seã§ã£o de turbina ã© configurada para acionar a seã§ã£o de compressor e o arranjo de engrenagens. uma razã£o de pressã£o geral, que ã© provida por uma combinaã§ã£o de uma razã£o de pressã£o atravã©s da dita seã§ã£o de compressor de baixa pressã£o e uma razã£o de pressã£o atravã©s da dita seã§ã£o de compressor de alta pressã£o, ser maior do que cerca de 35. a razã£o de pressã£o atravã©s da seã§ã£o de compressor de baixa pressã£o fica entre cerca de 3 e cerca de 8, enquanto a razã£o de pressã£o atravã©s da seã§ã£o de compressor de alta pressã£o fica entre cerca de 7 e cerca de 15.
BR112014007438-0A 2011-12-27 2012-12-26 Motor de turbina a gás BR112014007438B1 (pt)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US13/337354 2011-12-27
US13/337,354 US8337147B2 (en) 2007-09-21 2011-12-27 Gas turbine engine compressor arrangement
US201261604646P 2012-02-29 2012-02-29
US61/604646 2012-02-29
PCT/US2012/071614 WO2013101805A1 (en) 2011-12-27 2012-12-26 Gas turbine engine compressor arrangement

Publications (2)

Publication Number Publication Date
BR112014007438A2 true BR112014007438A2 (pt) 2017-04-04
BR112014007438B1 BR112014007438B1 (pt) 2021-08-10

Family

ID=48698587

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112014007438-0A BR112014007438B1 (pt) 2011-12-27 2012-12-26 Motor de turbina a gás

Country Status (7)

Country Link
EP (2) EP2937509A1 (pt)
JP (6) JP5676825B2 (pt)
CN (1) CN103764952B (pt)
BR (1) BR112014007438B1 (pt)
CA (1) CA2850225C (pt)
RU (1) RU2647287C2 (pt)
WO (1) WO2013101805A1 (pt)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US10240526B2 (en) 2012-01-31 2019-03-26 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
US9845726B2 (en) 2012-01-31 2017-12-19 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US9915225B2 (en) * 2015-02-06 2018-03-13 United Technologies Corporation Propulsion system arrangement for turbofan gas turbine engine
FR3032495B1 (fr) * 2015-02-09 2017-01-13 Snecma Ensemble de redressement a performances aerodynamiques optimisees
CA2945264A1 (en) * 2015-11-05 2017-05-05 United Technologies Corporation Gas turbine engine with mount for low pressure turbine section
CA2945265A1 (en) * 2015-11-09 2017-05-09 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
US11111858B2 (en) * 2017-01-27 2021-09-07 General Electric Company Cool core gas turbine engine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US4896499A (en) * 1978-10-26 1990-01-30 Rice Ivan G Compression intercooled gas turbine combined cycle
FR2645911B1 (fr) * 1989-04-18 1991-06-07 Snecma Moteur a grand taux de dilution a soufflante amont et soufflante aval
US6134880A (en) 1997-12-31 2000-10-24 Concepts Eti, Inc. Turbine engine with intercooler in bypass air passage
US6732502B2 (en) * 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor
JP2005226584A (ja) * 2004-02-13 2005-08-25 Honda Motor Co Ltd コンプレッサ及びガスタービンエンジン
US8561383B2 (en) * 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US7721549B2 (en) 2007-02-08 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system
US8075261B2 (en) * 2007-09-21 2011-12-13 United Technologies Corporation Gas turbine engine compressor case mounting arrangement
US20090293495A1 (en) * 2008-05-29 2009-12-03 General Electric Company Turbine airfoil with metered cooling cavity
US20110167792A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Adaptive engine
US8256229B2 (en) * 2010-04-09 2012-09-04 United Technologies Corporation Rear hub cooling for high pressure compressor

Also Published As

Publication number Publication date
CN103764952A (zh) 2014-04-30
JP2017133516A (ja) 2017-08-03
JP2019190467A (ja) 2019-10-31
JP2014529707A (ja) 2014-11-13
JP6290137B2 (ja) 2018-03-07
RU2647287C2 (ru) 2018-03-15
JP2014156861A (ja) 2014-08-28
EP2776677B1 (en) 2015-06-24
JP2015163794A (ja) 2015-09-10
CN103764952B (zh) 2016-06-08
RU2014119916A (ru) 2016-02-20
JP2018197549A (ja) 2018-12-13
JP6386604B2 (ja) 2018-09-05
WO2013101805A1 (en) 2013-07-04
EP2776677A4 (en) 2014-10-08
JP5676825B2 (ja) 2015-02-25
EP2776677A1 (en) 2014-09-17
JP6560418B2 (ja) 2019-08-14
EP2937509A1 (en) 2015-10-28
CA2850225A1 (en) 2013-07-04
JP5805809B2 (ja) 2015-11-10
CA2850225C (en) 2015-10-13
BR112014007438B1 (pt) 2021-08-10

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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]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 26/12/2012, OBSERVADAS AS CONDICOES LEGAIS.