Michael G Mcpherson

US Patent:

7200985, Apr 10, 2007

Filed:

May 18, 2004

Appl. No.:

10/847813

Inventors:

David J. Tuttle - South Bend IN, US
Steven Fisher - South Bend IN, US
Christopher D. Eick - Phoenix AZ, US
Michael A. McPherson - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morris Township NJ

International Classification:

F02C 7/232
F02C 9/26

US Classification:

60 39094, 60 39281

Abstract:

A fuel control system for a gas turbine engine is disclosed that includes a flow path carrying fuel from a fuel source to a combustion chamber, an ecology valve for removing a quantity of fuel from the flow path, the ecology valve being shiftable in a first direction from a first position to a second position and in a second direction from said second position to said first position and a fuel line connected between the flow path and the ecology valve for moving fuel between the flow path and the ecology valve to bias the ecology valve toward the second position, where the fuel line is configured, such as by the inclusion of an orificed check valve 150 therein, to allow fuel to move therethrough away from the ecology valve at a greater rate than toward the ecology valve.

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:

20200198764, Jun 25, 2020

Filed:

Dec 21, 2018

Appl. No.:

16/230201

Inventors:

- Morris Plains NJ, US
Sammuel Tillich - South Bend IN, US
Steven Alan Lewis - South Bend IN, US
Christopher Douglas Eick - Phoenix AZ, US
Donald Striker - Chandler AZ, US
Michael Albert McPherson - Phoenix AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morris Plains NJ

International Classification:

B64C 11/40
B64C 11/30

Abstract:

A propeller pitch control system for a turboprop engine of an aircraft includes an engine control unit and a pitch control unit. The engine control unit is operable to determine a phase of flight of the aircraft and is configured to supply control commands. The pitch control unit is coupled to receive the control commands from the engine control unit and includes a housing, a beta piston, a position sensor, a beta tube, and an electrohydraulic valve. The engine control unit only commands the electrohydraulic valve to move the beta piston from the fully retracted position when the engine control unit determines the aircraft is conducting pre-takeoff roll taxiing operations or is conducting post landing touchdown operations.

US Patent:

20200198765, Jun 25, 2020

Filed:

Dec 20, 2018

Appl. No.:

16/227175

Inventors:

- Morris Plains NJ, US
Sammuel Tillich - South Bend IN, US
Steven Alan Lewis - South Bend IN, US
Christopher Douglas Eick - Phoenix AZ, US
Donald Striker - Chandler AZ, US
Michael Albert McPherson - Phoenix AZ, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morris Plains NJ

International Classification:

B64C 11/44
F02D 29/02
F02B 61/04
B64C 11/40
B64C 11/38

Abstract:

A propeller oil control system for a turboprop engine of an aircraft includes an engine control unit and a propeller oil controller. The engine control unit is operable to determine a flight phase of the aircraft and is configured to supply control commands. The propeller oil controller is coupled to receive a supply of oil and to discharge the oil at a discharge oil pressure. The propeller oil controller includes an electrohydraulic servo valve that receives the control commands moves to a plurality of positions between a first position and a mid-position, and a plurality of positions between the mid-position and a second position. The engine control unit only commands the electrohydraulic servo valve to move out of the first position when the engine control unit determines the aircraft is conducting a take-off roll or the aircraft is in flight.

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.