BR112014016304A2 - seção da turbiana de um motor de turbina a gás, e, motor de turbina a gás - Google Patents
seção da turbiana de um motor de turbina a gás, e, motor de turbina a gásInfo
- Publication number
- BR112014016304A2 BR112014016304A2 BR112014016304A BR112014016304A BR112014016304A2 BR 112014016304 A2 BR112014016304 A2 BR 112014016304A2 BR 112014016304 A BR112014016304 A BR 112014016304A BR 112014016304 A BR112014016304 A BR 112014016304A BR 112014016304 A2 BR112014016304 A2 BR 112014016304A2
- Authority
- BR
- Brazil
- Prior art keywords
- gas turbine
- turbine engine
- section
- engine
- gas
- Prior art date
Links
Classifications
-
- 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
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/363,154 US20130192196A1 (en) | 2012-01-31 | 2012-01-31 | Gas turbine engine with high speed low pressure turbine section |
US201261619124P | 2012-04-02 | 2012-04-02 | |
US13/446,510 US9611859B2 (en) | 2012-01-31 | 2012-04-13 | Gas turbine engine with high speed low pressure turbine section and bearing support features |
PCT/US2013/022012 WO2013116005A1 (en) | 2012-01-31 | 2013-01-18 | Gas turbine engine with high speed low pressure turbine section and bearing support features |
Publications (2)
Publication Number | Publication Date |
---|---|
BR112014016304A2 true BR112014016304A2 (pt) | 2017-06-13 |
BR112014016304A8 BR112014016304A8 (pt) | 2017-07-04 |
Family
ID=48870370
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR112014016304A BR112014016304A8 (pt) | 2012-01-31 | 2013-01-18 | seção da turbiana de um motor de turbina a gás, e, motor de turbina a gás |
Country Status (7)
Country | Link |
---|---|
US (1) | US9611859B2 (pt) |
EP (1) | EP2809953A4 (pt) |
BR (1) | BR112014016304A8 (pt) |
CA (1) | CA2854077C (pt) |
RU (1) | RU2630628C2 (pt) |
SG (1) | SG11201403615QA (pt) |
WO (1) | WO2013116005A1 (pt) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150345426A1 (en) | 2012-01-31 | 2015-12-03 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US10240526B2 (en) | 2012-01-31 | 2019-03-26 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
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 |
US9222417B2 (en) * | 2012-01-31 | 2015-12-29 | United Technologies Corporation | Geared turbofan gas turbine engine architecture |
US9845726B2 (en) | 2012-01-31 | 2017-12-19 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
US9835052B2 (en) | 2012-01-31 | 2017-12-05 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section and bearing support features |
US10309232B2 (en) * | 2012-02-29 | 2019-06-04 | United Technologies Corporation | Gas turbine engine with stage dependent material selection for blades and disk |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
EP3165754A1 (en) * | 2015-11-03 | 2017-05-10 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section and bearing support features |
EP3165755A1 (en) * | 2015-11-04 | 2017-05-10 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section and bearing support features |
CA2945265A1 (en) * | 2015-11-09 | 2017-05-09 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
DE202018006668U1 (de) | 2017-06-27 | 2021-12-17 | Flooring Industries Limited, Sarl | Wand- oder Deckenpaneel und Wand- oder Deckenanordnung |
DE102019208666A1 (de) * | 2019-06-14 | 2020-12-17 | MTU Aero Engines AG | Rotoren für hochdruckverdichter und niederdruckturbine eines getriebefantriebwerks sowie verfahren zu ihrer herstellung |
US11428160B2 (en) * | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
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US1448019A (en) | 1921-11-09 | 1923-03-13 | Crane Co | Indexed handle structure |
US3287906A (en) | 1965-07-20 | 1966-11-29 | Gen Motors Corp | Cooled gas turbine vanes |
GB1350431A (en) | 1971-01-08 | 1974-04-18 | Secr Defence | Gearing |
US3892358A (en) | 1971-03-17 | 1975-07-01 | Gen Electric | Nozzle seal |
US4130872A (en) | 1975-10-10 | 1978-12-19 | The United States Of America As Represented By The Secretary Of The Air Force | Method and system of controlling a jet engine for avoiding engine surge |
GB1516041A (en) | 1977-02-14 | 1978-06-28 | Secr Defence | Multistage axial flow compressor stators |
GB2041090A (en) | 1979-01-31 | 1980-09-03 | Rolls Royce | By-pass gas turbine engines |
GB2207191B (en) | 1987-07-06 | 1992-03-04 | Gen Electric | Gas turbine engine |
US4916894A (en) | 1989-01-03 | 1990-04-17 | General Electric Company | High bypass turbofan engine having a partially geared fan drive turbine |
FR2644844B1 (fr) | 1989-03-23 | 1994-05-06 | Snecma | Suspension du rotor de la turbine basse pression d'une turbomachine a double corps |
US5447411A (en) | 1993-06-10 | 1995-09-05 | Martin Marietta Corporation | Light weight fan blade containment system |
US5524847A (en) | 1993-09-07 | 1996-06-11 | United Technologies Corporation | Nacelle and mounting arrangement for an aircraft engine |
US5433674A (en) | 1994-04-12 | 1995-07-18 | United Technologies Corporation | Coupling system for a planetary gear train |
US5778659A (en) | 1994-10-20 | 1998-07-14 | United Technologies Corporation | Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems |
WO1997000381A1 (en) | 1994-12-14 | 1997-01-03 | United Technologies Corporation | Compressor stall and surge control using airflow asymmetry measurement |
US5857836A (en) | 1996-09-10 | 1999-01-12 | Aerodyne Research, Inc. | Evaporatively cooled rotor for a gas turbine engine |
GB2322914B (en) * | 1997-03-05 | 2000-05-24 | Rolls Royce Plc | Ducted fan gas turbine engine |
US5975841A (en) | 1997-10-03 | 1999-11-02 | Thermal Corp. | Heat pipe cooling for turbine stators |
US6223616B1 (en) | 1999-12-22 | 2001-05-01 | United Technologies Corporation | Star gear system with lubrication circuit and lubrication method therefor |
US6318070B1 (en) | 2000-03-03 | 2001-11-20 | United Technologies Corporation | Variable area nozzle for gas turbine engines driven by shape memory alloy actuators |
US6619030B1 (en) | 2002-03-01 | 2003-09-16 | General Electric Company | Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors |
US6814541B2 (en) | 2002-10-07 | 2004-11-09 | General Electric Company | Jet aircraft fan case containment design |
US7021042B2 (en) | 2002-12-13 | 2006-04-04 | United Technologies Corporation | Geartrain coupling for a turbofan engine |
GB0406174D0 (en) | 2004-03-19 | 2004-04-21 | Rolls Royce Plc | Turbine engine arrangement |
DE102005018139A1 (de) | 2005-04-20 | 2006-10-26 | Mtu Aero Engines Gmbh | Stahltriebwerk |
EP1928943B1 (en) | 2005-09-28 | 2014-07-09 | Entrotech Composites, LLC. | Linerless prepregs, composite articles therefrom, and related methods |
US7591754B2 (en) | 2006-03-22 | 2009-09-22 | United Technologies Corporation | Epicyclic gear train integral sun gear coupling design |
US7600370B2 (en) | 2006-05-25 | 2009-10-13 | Siemens Energy, Inc. | Fluid flow distributor apparatus for gas turbine engine mid-frame section |
US7926260B2 (en) | 2006-07-05 | 2011-04-19 | United Technologies Corporation | Flexible shaft for gas turbine engine |
US7694505B2 (en) | 2006-07-31 | 2010-04-13 | General Electric Company | Gas turbine engine assembly and method of assembling same |
RU2330170C2 (ru) * | 2006-09-11 | 2008-07-27 | Открытое акционерное общество "Авиадвигатель" | Двухконтурный газотурбинный двигатель сверхвысокой степени двухконтурности |
US7921634B2 (en) | 2006-10-31 | 2011-04-12 | General Electric Company | Turbofan engine assembly and method of assembling same |
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 |
US8017188B2 (en) | 2007-04-17 | 2011-09-13 | General Electric Company | Methods of making articles having toughened and untoughened regions |
US8844265B2 (en) | 2007-08-01 | 2014-09-30 | United Technologies Corporation | Turbine section of high bypass turbofan |
US9957918B2 (en) | 2007-08-28 | 2018-05-01 | United Technologies Corporation | Gas turbine engine front architecture |
US8205432B2 (en) | 2007-10-03 | 2012-06-26 | United Technologies Corporation | Epicyclic gear train for turbo fan engine |
US20090092494A1 (en) | 2007-10-04 | 2009-04-09 | General Electric Company | Disk rotor and method of manufacture |
US8511986B2 (en) | 2007-12-10 | 2013-08-20 | United Technologies Corporation | Bearing mounting system in a low pressure turbine |
US7762086B2 (en) * | 2008-03-12 | 2010-07-27 | United Technologies Corporation | Nozzle extension assembly for ground and flight testing |
US8091371B2 (en) * | 2008-11-28 | 2012-01-10 | Pratt & Whitney Canada Corp. | Mid turbine frame for gas turbine engine |
US8061969B2 (en) | 2008-11-28 | 2011-11-22 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
US8099962B2 (en) | 2008-11-28 | 2012-01-24 | Pratt & Whitney Canada Corp. | Mid turbine frame system and radial locator for radially centering a bearing for gas turbine engine |
US8172716B2 (en) | 2009-06-25 | 2012-05-08 | United Technologies Corporation | Epicyclic gear system with superfinished journal bearing |
US20160032826A1 (en) | 2014-08-04 | 2016-02-04 | MTU Aero Engines AG | Turbofan aircraft engine |
-
2012
- 2012-04-13 US US13/446,510 patent/US9611859B2/en active Active
-
2013
- 2013-01-18 RU RU2014134421A patent/RU2630628C2/ru active
- 2013-01-18 WO PCT/US2013/022012 patent/WO2013116005A1/en active Application Filing
- 2013-01-18 SG SG11201403615QA patent/SG11201403615QA/en unknown
- 2013-01-18 EP EP13743282.9A patent/EP2809953A4/en not_active Withdrawn
- 2013-01-18 BR BR112014016304A patent/BR112014016304A8/pt not_active Application Discontinuation
- 2013-01-18 CA CA2854077A patent/CA2854077C/en active Active
Also Published As
Publication number | Publication date |
---|---|
CA2854077A1 (en) | 2013-08-08 |
WO2013116005A1 (en) | 2013-08-08 |
US9611859B2 (en) | 2017-04-04 |
CA2854077C (en) | 2021-03-16 |
SG11201403615QA (en) | 2014-10-30 |
US20130195648A1 (en) | 2013-08-01 |
RU2014134421A (ru) | 2016-03-20 |
RU2630628C2 (ru) | 2017-09-11 |
EP2809953A4 (en) | 2015-11-25 |
EP2809953A1 (en) | 2014-12-10 |
BR112014016304A8 (pt) | 2017-07-04 |
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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] | ||
B350 | Update of information on the portal [chapter 15.35 patent gazette] | ||
B07A | Application suspended after technical examination (opinion) [chapter 7.1 patent gazette] | ||
B09B | Patent application refused [chapter 9.2 patent gazette] | ||
B09B | Patent application refused [chapter 9.2 patent gazette] |
Free format text: MANTIDO O INDEFERIMENTO UMA VEZ QUE NAO FOI APRESENTADO RECURSO DENTRO DO PRAZO LEGAL |