Alejandro Dejesus Perez

US Patent:

20180215475, Aug 2, 2018

Filed:

Feb 1, 2017

Appl. No.:

15/421692

Inventors:

- Schenectady NY, US
Robert Gregory Carita - Needham MA, US
Thomas Edward Brinson - Mason OH, US
Matthew Robert Cerny - West Chester OH, US
David Vickery Parker - Middleton MA, US
Alejandro Yatzail Perez Valdez - Cincinnati OH, US

International Classification:

B64D 13/08
F02C 6/08

Abstract:

Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.

US Patent:

20150321767, Nov 12, 2015

Filed:

Nov 26, 2013

Appl. No.:

14/651583

Inventors:

- Schenectady NY, US
Mehdi Milani BALADI - Cincinnati OH, US
Sergei A. JEREBETS - Mason OH, US
Robert Lawrence MAYER - Cincinnati OH, US
Scott Chandler MORTON - Cincinnati OH, US
Alejandro Yatzail PEREZ VALADEZ - Cincinnati OH, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

B64D 37/34

Abstract:

A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels. The system includes a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel, a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system, and a fuel-to-fuel cooler (FFC) configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system.