BR102012024670B8 - gas turbine engine, and, method to disassemble a front architecture of a gas turbine engine - Google Patents

gas turbine engine, and, method to disassemble a front architecture of a gas turbine engine

Info

Publication number
BR102012024670B8
BR102012024670B8 BR102012024670A BR102012024670A BR102012024670B8 BR 102012024670 B8 BR102012024670 B8 BR 102012024670B8 BR 102012024670 A BR102012024670 A BR 102012024670A BR 102012024670 A BR102012024670 A BR 102012024670A BR 102012024670 B8 BR102012024670 B8 BR 102012024670B8
Authority
BR
Brazil
Prior art keywords
gas turbine
turbine engine
disassemble
architecture
grooves
Prior art date
Application number
BR102012024670A
Other languages
Portuguese (pt)
Other versions
BR102012024670A2 (en
BR102012024670B1 (en
Inventor
P Cigal Brian
r otto John
Sharma Sunil
A Davis Todd
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
Priority claimed from US13/282,919 external-priority patent/US8366385B2/en
Priority claimed from US13/407,916 external-priority patent/US8360714B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of BR102012024670A2 publication Critical patent/BR102012024670A2/en
Publication of BR102012024670B1 publication Critical patent/BR102012024670B1/en
Publication of BR102012024670B8 publication Critical patent/BR102012024670B8/en

Links

Classifications

    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

motor de turbina a gás, e, método para desmontar uma arquitetura frontal de um motor de turbina a gás. um motor de turbina a gás inclui um suporte de corpo central que provê uma parede anular interna para um trajeto de fluxo de núcleo. o suporte de corpo central inclui primeiras estrias. uma arquitetura engrenada interconecta um carretel e uma ventoinha girável ao redor de um eixo. u, suporte flexível interconecta a arquitetura engrenada e o suporte de corpo central. o suporte flexível inclui segundas estrias que se interconectam com as primeiras estrias para transferir torque entre elas.gas turbine engine, and, method to disassemble a front architecture of a gas turbine engine. a gas turbine engine includes a central body support that provides an internal annular wall for a core flow path. the central body support includes first grooves. a meshed architecture interconnects a spool and a rotatable fan around an axis. u, flexible support interconnects the meshed architecture and the central body support. the flexible support includes second grooves that interconnect with the first grooves to transfer torque between them.

BR102012024670A 2011-10-27 2012-09-27 gas turbine engine, and, method to disassemble a front architecture of a gas turbine engine BR102012024670B8 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US13/282,919 US8366385B2 (en) 2011-04-15 2011-10-27 Gas turbine engine front center body architecture
US13/282,919 2011-10-27
US13/407,916 2012-02-29
US13/407,916 US8360714B2 (en) 2011-04-15 2012-02-29 Gas turbine engine front center body architecture

Publications (3)

Publication Number Publication Date
BR102012024670A2 BR102012024670A2 (en) 2013-11-12
BR102012024670B1 BR102012024670B1 (en) 2020-12-08
BR102012024670B8 true BR102012024670B8 (en) 2021-01-19

Family

ID=48173963

Family Applications (1)

Application Number Title Priority Date Filing Date
BR102012024670A BR102012024670B8 (en) 2011-10-27 2012-09-27 gas turbine engine, and, method to disassemble a front architecture of a gas turbine engine

Country Status (4)

Country Link
JP (1) JP5650181B2 (en)
CN (1) CN103089450B (en)
BR (1) BR102012024670B8 (en)
CA (1) CA2789325C (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9631558B2 (en) 2012-01-03 2017-04-25 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
US9133729B1 (en) * 2011-06-08 2015-09-15 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US9523422B2 (en) 2011-06-08 2016-12-20 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US9239012B2 (en) 2011-06-08 2016-01-19 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US9182011B2 (en) * 2012-10-01 2015-11-10 United Technologies Corporation Fan drive gear system flexible support features
EP2811120B1 (en) * 2013-06-03 2017-07-12 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
EP3359791B1 (en) * 2015-10-05 2020-11-25 Safran Aircraft Engines Turbine engine with fan and reduction of speed on the shaft of the power turbine
US10436151B2 (en) * 2015-11-17 2019-10-08 General Electric Company Modular fan for a gas turbine engine
CN106870681A (en) * 2015-12-12 2017-06-20 熵零技术逻辑工程院集团股份有限公司 A kind of fluid planetary mechanism
US10392970B2 (en) * 2016-11-02 2019-08-27 General Electric Company Rotor shaft architectures for a gas turbine engine and methods of assembly thereof
US10711693B2 (en) * 2017-07-12 2020-07-14 General Electric Company Gas turbine engine with an engine rotor element turning device

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Publication number Priority date Publication date Assignee Title
US11028A (en) * 1854-06-06 Excavator
US7002A (en) * 1850-01-08 Obe-washek
US12026A (en) * 1854-12-05 Machibtb for rounding the backs op books
US5433674A (en) * 1994-04-12 1995-07-18 United Technologies Corporation Coupling system for a planetary gear train
US6223616B1 (en) * 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
US7309210B2 (en) * 2004-12-17 2007-12-18 United Technologies Corporation Turbine engine rotor stack
US7493754B2 (en) * 2005-10-19 2009-02-24 General Electric Company Gas turbine engine assembly and methods of assembling same
US7493753B2 (en) * 2005-10-19 2009-02-24 General Electric Company Gas turbine engine assembly and methods of assembling same
US7704178B2 (en) * 2006-07-05 2010-04-27 United Technologies Corporation Oil baffle for gas turbine fan drive gear system
FR2909146B1 (en) * 2006-11-28 2009-06-05 Snecma Sa DEVICE FOR CONNECTING TWO ROTARY TREES, PARTICULARLY IN A TURBOMACHINE.
US8465373B2 (en) * 2009-12-29 2013-06-18 Rolls-Royce Corporation Face coupling

Also Published As

Publication number Publication date
BR102012024670A2 (en) 2013-11-12
JP5650181B2 (en) 2015-01-07
BR102012024670B1 (en) 2020-12-08
CN103089450A (en) 2013-05-08
CN103089450B (en) 2015-11-25
CA2789325C (en) 2015-04-07
JP2013096413A (en) 2013-05-20
CA2789325A1 (en) 2013-04-27

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Legal Events

Date Code Title Description
B03A Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]
B03H Publication of an application: rectification [chapter 3.8 patent gazette]
B25G Requested change of headquarter approved

Owner name: UNITED TECHNOLOGIES CORPORATION (US)

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 [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 27/09/2012, OBSERVADAS AS CONDICOES LEGAIS.

B16C Correction of notification of the grant [chapter 16.3 patent gazette]

Free format text: REF. RPI 2605 DE 08/12/2020 QUANTO AO INVENTOR.