Charles B Travelbee

US Patent:

20100037623, Feb 18, 2010

Filed:

Aug 12, 2008

Appl. No.:

12/189908

Inventors:

Gordon F. Jewess - San Diego CA, US
Charles Travelbee - San Diego CA, US

International Classification:

F02K 1/00
F02K 3/04

US Classification:

60770, 415144

Abstract:

A by-pass turbofan gas turbine engine, comprises: a by-pass fan with a by-pass fan outlet; a generally annular core engine duct with a core engine duct inlet coupled to the by-pass fan outlet and a core engine duct outlet; a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct with a by-pass duct inlet coupled to the by-pass fan outlet and a by-pass duct outlet; an upstream axial compressor with an axial upstream compressor inlet coupled to the core engine duct outlet and an axial upstream compressor outlet; a downstream radial compressor with an axial downstream compressor inlet coupled to the upstream compressor outlet and a radial downstream compressor outlet; a generally annular recuperator with a cool side inlet coupled to the downstream compressor outlet, a cool side outlet, a warm side inlet and a warm side outlet; a generally annular combustor with a combustor inlet coupled to the recuperator cool side outlet and a combustor outlet; a radial turbine with a radial turbine inlet coupled to the combustor inlet and a turbine outlet coupled to the recuperator warm side inlet; at least one exhaust nozzle with an exhaust nozzle inlet coupled to the recuperator warm side outlet and an exhaust nozzle outlet that discharges into the by-pass duct between the by-pass duct inlet and outlet; and a propelling nozzle coupled to the by-pass duct outlet.

US Patent:

20140208714, Jul 31, 2014

Filed:

Dec 19, 2012

Appl. No.:

13/719706

Inventors:

United Technologies Corporation - , US
Charles Brian Travelbee - San Diego CA, US
Patrick M. Lydon - San Marcos CA, US
Eric J. Alexander - San Diego CA, US
Nagamany Thayalakhandan - San Diego CA, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Connecticut CT

International Classification:

F02K 3/02
F42B 15/10
B64C 39/02

US Classification:

602261, 415108, 60737

Abstract:

A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with the gas turbine engine.