Scot J Coffey from 2549 N Rowen Cir, Mesa, AZ 85207, age 50, Phone: (480)9852126

System And Method For Turbine Engine Igniter Lifing
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US Patent:

20070135987, Jun 14, 2007
Filed:

Nov 22, 2005
Appl. No.:

11/285812
Inventors:

Scot Coffey - Mesa AZ, US
Kevin Jones - Laveen AZ, US
Michael James - Phoenix AZ, US
International Classification:

G01M 19/02
F02P 17/02
G01N 3/56
US Classification:

701100000, 702035000, 073007000, 073118100
Abstract:

An igniter lifing system and method is provided that facilitates improved igniter plug wear and remaining life prediction. The igniter lifing system and method uses operating conditions measured during ignition to estimate how much wear has occurred on an igniter. Specifically, the igniter lifing system and method uses ignition time and pressure data to predict wear on the igniter plug and make an estimate of the remaining life. In one embodiment, the igniter lifing system calculates the incremental igniter wear for each use of the igniter as a function of the turbine combustor pressure during that use. Then, by summing the incremental igniter wear calculations, the accumulated igniter wear can be calculated, and an estimate of the remaining igniter life can be determined.

Single Lever Turboprop Control Systems And Methods Utilizing Torque-Based And Power-Based Scheduling
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US Patent:

20190047714, Feb 14, 2019
Filed:

Jul 20, 2018
Appl. No.:

16/041515
Inventors:

- Morris Plains NJ, US
Scot Coffey - Mesa AZ, US
Yufei Xiong - Phoenix AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morris Plains NJ
International Classification:

B64D 31/06
B64D 31/14
B64D 31/04
B64C 11/40
B64C 11/34
B64D 27/10
Abstract:

Embodiments of a single lever turboprop control method and system are provided, which utilize torque-based and/or power-based scheduling to achieve a desired (e.g., substantially proportional) relationship between control lever position and the power output of a turboprop engine. In one embodiment, the method includes the step or process of monitoring, at an Engine Control Unit (ECU), for receipt of a Power Lever Angle (PLA) signal from a single lever control device. When a PLA control signal received at the ECU, a target torque or power output is established as a function of at least the PLA control signal. A first engine setpoint, such as a blade angle setpoint or an engine rotational speed setpoint, is determined utilizing the target torque output. An operational parameter of the turboprop engine is then adjusted in accordance with the first engine setpoint.

Turbofan Gas Turbine Engine Shaft Break Detection System And Method
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US Patent:

20180051585, Feb 22, 2018
Filed:

Aug 16, 2016
Appl. No.:

15/237834
Inventors:

- Morris Plains NJ, US
Ronnie Haugland - Scottsdale AZ, US
Scot Coffey - Mesa AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morris Plains NJ
International Classification:

F01D 21/00
F01D 5/02
F04D 19/00
G01M 15/14
Abstract:

A system and method for detecting a shaft break in a turbofan gas turbine engine includes sensing fan rotational speed and sensing turbine engine rotational speed. A rate of change of rotational speed difference between the sensed fan rotational speed and the sensed turbine engine rotational speed is determined in a processor, and a determination that a shaft break has occurred is made in the processor based at least in part on the rate of change of the rotational speed difference.

Single Lever Turboprop Control Systems And Methods Utilizing Torque-Based And Power-Based Scheduling
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US Patent:

20170081038, Mar 23, 2017
Filed:

Sep 22, 2015
Appl. No.:

14/861712
Inventors:

- Morristown NJ, US
Scot Coffey - Mesa AZ, US
Yufei Xiong - Phoenix AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

B64D 31/06
B64C 11/40
B64D 27/10
B64C 11/34
Abstract:

Embodiments of a single lever turboprop control method and system are provided, which utilize torque-based and/or power-based scheduling to achieve a desired (e.g., substantially proportional) relationship between control lever position and the power output of a turboprop engine. In one embodiment, the method includes the step or process of monitoring, at an Engine Control Unit (ECU), for receipt of a Power Lever Angle (PLA) signal from a single lever control device. When a PLA control signal received at the ECU, a target torque or power output is established as a function of at least the PLA control signal. A first engine setpoint, such as a blade angle setpoint or an engine rotational speed setpoint, is determined utilizing the target torque output. An operational parameter of the turboprop engine is then adjusted in accordance with the first engine setpoint.

Gas Turbine Engine Uncontrolled High Thrust Detection System And Method
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US Patent:

20170081974, Mar 23, 2017
Filed:

Sep 23, 2015
Appl. No.:

14/863140
Inventors:

- Morristown NJ, US
Dave Faymon - Phoenix AZ, US
Scot Coffey - Mesa AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

F01D 17/06
F02C 3/10
Abstract:

A system and method of detecting an uncontrolled high thrust (UHT) condition in a turbofan gas turbine engine includes processing data to determine when a current commanded fan speed value is greater than a predetermined speed value. A current UHT commanded fan speed value is processed to determine if it will cause a target fan speed value to increase, remain steady, or decrease. The target fan speed value is set equal to the current UHT commanded fan speed value when the current UHT commanded fan speed value will cause the target fan speed value to increase or remain steady, and to a deceleration threshold value when the current UHT commanded fan speed value will cause the target fan speed value to decrease. An uncontrolled high thrust alert signal is generated when actual engine fan speed exceeds the target fan speed value by a predetermined amount for a preset time period.

Aircraft Gas Turbine Propulsion Engine Control Without Aircraft Total Air Temperature Sensors
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US Patent:

20160368612, Dec 22, 2016
Filed:

Jun 18, 2015
Appl. No.:

14/742985
Inventors:

- Morristown NJ, US
Dave Faymon - Phoenix AZ, US
Scot Coffey - Mesa AZ, US
Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ
International Classification:

B64D 31/06
G07C 5/08
B64D 27/16
Abstract:

A control system for an aircraft gas turbine propulsion engine includes an engine control that is adapted to receive at least engine inlet temperature data and aircraft altitude data. The engine control is configured to determine the availability of the engine inlet temperature data and implements a measured temperature engine thrust setting schedule when the engine inlet temperature data is available, and a default temperature engine thrust setting schedule when the engine inlet temperature data is unavailable. The default temperature engine thrust setting schedule ensures that the gas turbine propulsion engine will generate at least 90% of rated engine thrust at all actual engine inlet temperatures at the sensed aircraft altitude.