Title:
GAS TURBINE ENGINE FOR LONG RANGE AIRCRAFT
Document Type and Number:
WIPO Patent Application WO/2015/116283
Kind Code:
A3
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.
Inventors:
SCHWARZ FREDERICK M (US)
SUCIU GABRIEL L (US)
SUCIU GABRIEL L (US)
Application Number:
PCT/US2014/064477
Publication Date:
October 15, 2015
Filing Date:
November 07, 2014
Export Citation:
Assignee:
UNITED TECHNOLOGIES CORP (US)
International Classes:
F02K3/06; F02C9/16; F02K3/075
Domestic Patent References:
| WO2013116257A1 | 2013-08-08 |
Foreign References:
| US20130219859A1 | 2013-08-29 | |||
| US20030163983A1 | 2003-09-04 | |||
| US20130195647A1 | 2013-08-01 | |||
| US20130192197A1 | 2013-08-01 |
Other References:
See also references of EP 3084195A4
Attorney, Agent or Firm:
OLDS, Theodore W. (Gaskey & Olds/Pratt & Whitney400 W. Maple Road, Ste. 35, Birmingham Michigan, US)
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