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1. (WO2015116283) GAS TURBINE ENGINE FOR LONG RANGE AIRCRAFT

Pub. No.:    WO/2015/116283    International Application No.:    PCT/US2014/064477
Publication Date: Fri Aug 07 01:59:59 CEST 2015 International Filing Date: Sat Nov 08 00:59:59 CET 2014
IPC: F02K 3/06
F02K 3/075
F02C 9/16
Applicants: UNITED TECHNOLOGIES CORPORATION
Inventors: SCHWARZ, Frederick M.
SUCIU, Gabriel L.
Title: GAS TURBINE ENGINE FOR LONG RANGE AIRCRAFT
Abstract:
A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors. A bypass ratio is defined as a volume of air delivered as bypass flow compared to a volume of air delivered into the core housing. The overall pressure ratio is greater than or equal to about 45.0, and the bypass ratio is greater than or equal to about 11.0.