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Patent Searching and Data


Title:
EXHAUST SECTION FOR AN AIRCRAFT GAS TURBINE ENGINE
Document Type and Number:
WIPO Patent Application WO/2015/126489
Kind Code:
A3
Abstract:
An exhaust section for an aircraft gas turbine engine includes an exhaust nozzle in a downstream serial flow relationship with the gas turbine engine having a fan section, a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section compresses intake air from the fan section, which is mixed with fuel and combusted into hot gases in the combustion section. The hot gases drive the turbines of the turbine section, and are expelled from the gas turbine engine at the exhaust section.

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Inventors:
ENGELHARDT, Michel (1000 MacArthur Memorial Highway, Bohemia, NY, 11716, US)
Application Number:
US2014/066959
Publication Date:
January 07, 2016
Filing Date:
November 21, 2014
Export Citation:
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Assignee:
GE AVIATION SYSTEMS LLC (3290 Patterson Avenue, SEGrand Rapids, MI, 49512-1991, US)
International Classes:
H02K44/08; F01D15/10; H02K44/10; B64D33/04; B64D41/00
Foreign References:
US3678306A1972-07-18
US3940640A1976-02-24
US4185213A1980-01-22
GB1125408A1968-08-28
US3360666A1967-12-26
Attorney, Agent or Firm:
ANDES, William, Scott et al. (General Electric Company, Global Patent Operation2 Corporation Drive, Suite 64, Shelton CT, 06484, US)
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