Andrew W Fleming

US Patent:

20200180771, Jun 11, 2020

Filed:

Dec 6, 2018

Appl. No.:

16/211972

Inventors:

- Schenectady NY, US
Andrew James Fleming - Franklin OH, US

International Classification:

B64D 13/08
B64D 27/24
B64D 29/00
B64D 31/00
B64D 13/06

Abstract:

An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.

US Patent:

20180194479, Jul 12, 2018

Filed:

Jun 30, 2015

Appl. No.:

15/322842

Inventors:

- Schenectady NY, US
Benjamin Paul Breig - Liberty TWP OH, US
Michael Jay Epstein - Mason OH, US
Javier Armando Parrilla - Fairfield OH, US
Matthew John Hurt - Liberty TWP OH, US
Thomas Edward Brinson - Mason OH, US
Andrew James Fleming - Franklin OH, US
George Eugene Wilmot - East Grandby CT, US

International Classification:

B64D 13/08
F02C 6/08
F02C 7/32
F01D 17/10
B64D 13/00

Abstract:

Methods and devices for cooling systems () are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler () receiving bleed air from the jet engine compressor; a heat exchanger () downstream from the first precooler (); a cooling system compressor () downstream from the first precooler (), wherein the heat exchanger () and the cooling system compressor () are in separate flow paths from the first precooler (); a cooling system precooler () downstream from the cooling system compressor (); a VGT cooling system turbine () downstream from the cooling system precooler (); and a discharge conduit () downstream from the cooling system turbine () and the heat exchanger (). A bypass line () for bypassing the turbine can also be included.

US Patent:

20180194480, Jul 12, 2018

Filed:

Jun 30, 2015

Appl. No.:

15/322844

Inventors:

- Schenectady NY, US
Benajamin Paul BREIG - Liberty Township OH, US
Michael Jay EPSTEIN - Mason OH, US
Javier Armando PARRILLA - Fairfield OH, US
Matthew John Hurt - Liberty Township OH, US
Thomas Edward BRINSON - Mason OH, US
Andrew James FLEMING - Franklin OH, US
George Eugene WILMOT - East Granby CT, US

International Classification:

B64D 13/08
B64D 13/00
F02C 6/08
F01D 17/14

Abstract:

Methods and devices for cooling systems () are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler () receiving bleed air from the jet engine compressor; a heat exchanger () downstream from the first precooler (); a cooling system compressor () downstream from the first precooler (), wherein the heat exchanger () and the cooling system compressor () are in separate flow paths from the first precooler (); a cooling system precooler () downstream from the cooling system compressor (); a cooling system turbine () with variable guide vanes—VGT—and downstream from the cooling system precooler (); and a discharge conduit () downstream from the cooling system turbine () and the heat exchanger (). A bypass line () can also be included that bypasses the cooling system turbine ().

US Patent:

20160153359, Jun 2, 2016

Filed:

Jun 30, 2015

Appl. No.:

14/755398

Inventors:

- Schenectady NY, US
Benjamin Paul Breig - Liberty Twp OH, US
Michael Jay Epstein - Mason OH, US
Javier Armando Parrilla - Fairfield OH, US
Matthew John Hurt - Liberty Twp OH, US
Thomas Edward Brinson - Mason OH, US
Andrew James Fleming - Franklin OH, US

International Classification:

F02C 7/18
F02C 9/18

Abstract:

Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.