Michael R Mcpherson

US Patent:

20130219911, Aug 29, 2013

Filed:

Feb 28, 2012

Appl. No.:

13/406780

Inventors:

Rodolphe Dudebout - Phoenix AZ, US
Richard Bohman - Mesa AZ, US
Don Striker - Chandler AZ, US
Michael McPherson - Phoenix AZ, US
Matt Greenman - Phoenix AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F02C 7/228
F02C 7/26

US Classification:

60778, 60746

Abstract:

Disclosed is a combustion system for a gas turbine engine, which includes a combustor and a plurality of fuel injector nozzles within the combustor. The plurality of fuel injector nozzles include at least one start nozzle and at least of run nozzle, wherein each of the plurality of fuel injector nozzles is a single-circuit fuel injector nozzle. The combustion system further includes a fuel flow directing system to selectively deliver fuel flow to each of the at least one start nozzle and at least one run nozzle, wherein the fuel flow directing system is configured to deliver preferential flow of fuel to the at least one start nozzle during an engine start-up procedure and is further configured to deliver an equalized flow both of the at least one start nozzle and the at least one run nozzle as a total engine fuel flow is near or above an idle setting.

US Patent:

20180143082, May 24, 2018

Filed:

Nov 22, 2016

Appl. No.:

15/359442

Inventors:

- Morris Plains NJ, US
Grant A. Gordon - Peoria AZ, US
Michael Albert McPherson - Phoenix AZ, US

International Classification:

G01K 1/08

Abstract:

Systems and methods for icing resistant total air temperature probes are provided. In one embodiment, a total air temperature data probe comprises: a probe base; a probe body comprising: a first interior airflow passage comprising a first annulus; a temperature sensor positioned within the first annulus; a heating element; a notched intake port positioned at a distal end, wherein the probe body provides a conductive thermal path from the heating element to the intake port, the intake port including an open channel extending inward into an intake aperture of the probe body, and a cutaway region that defines a recessed second face inset from the first face and exposes the open channel at least partially from the leading edge. The notched intake port further comprises a slot inset from the recessed second face that traverses across at least a portion of the intake aperture perpendicularly to the open channel.

US Patent:

20160076452, Mar 17, 2016

Filed:

Sep 11, 2014

Appl. No.:

14/483955

Inventors:

- Morristown NJ, US
Michael McPherson - Phoenix AZ, US
Elmer Greenbank - Chandler AZ, US
Paul W. Futa - North Liberty IN, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

F02C 7/236
F02C 9/28
F02C 7/22

Abstract:

A gas turbine engine fuel delivery system includes a mechanically-driven fuel pump, an electrically-driven fuel pump, and an engine control. The mechanically-driven fuel pump is adapted to receive a drive torque from a gas turbine engine draw fuel into its fuel inlet and discharge the fuel from its fuel outlet. The electrically-driven fuel pump has a first fuel inlet/outlet that is in fluid communication with the mechanically-driven fuel pump fuel inlet, and also has a second fuel inlet/outlet. The engine control is responsive to an engine start signal to cause the electrically-driven fuel pump to be temporarily energized to pump fuel from the first fuel inlet/outlet to the second fuel inlet/outlet, and is responsive to an engine shutdown signal to cause the electrically-driven pump to be temporarily energized to pump fuel from the second fuel inlet/outlet to the first fuel inlet/outlet.