Patents by Inventor Harold Riley
Harold Riley has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11339721Abstract: A system and method for supplying compressed air from an auxiliary power unit to a main engine starter motor. The inlet guide vanes are controlled using either first or second inlet guide vane control logic and the surge control valve is controlled using either first or second surge control valve control logic. When the first inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand signal, when the second inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand schedule, when the first surge control valve logic is used, the surge control valve can be commanded to repeatedly move to only a fully-closed position and a fully-open position, and when the second surge control valve logic is used, the surge control valve can be commanded to the fully-closed position only when maximum flow is commanded.Type: GrantFiled: November 14, 2018Date of Patent: May 24, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Harold Riley, Michael Dwyer
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Patent number: 11192660Abstract: An auxiliary power unit (APU) oil quantity indication system and method provides a stable and accurate oil quantity indication during startup, mission duration and shutdown. The system determines a gulp value at various stages of operation, which is combined with a raw oil quantity indication to provide an indicated oil quantity.Type: GrantFiled: June 21, 2019Date of Patent: December 7, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Robert Mallette, Harold Riley
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Patent number: 10946973Abstract: A system and method provide aircraft-specific customization of gas turbine engine operation. The system includes a gas turbine engine, a first processing unit, and an engine controller. The first processing unit is configured to selectively transmit an activation key. The engine controller is in operable communication with the first processing unit and the gas turbine engine. The engine controller is configured to receive the activation key transmitted by the first processing unit and is operable, upon receipt of the activation key, to: verify the received activation key is correct, enable operational parameters in the gas turbine engine and the engine controller when the received activation key is correct, and control the gas turbine engine using the enabled operational parameters.Type: GrantFiled: March 18, 2019Date of Patent: March 16, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Harold Riley, Paul Topper, Brian Petterson, Timothy Ray O'Brien
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Publication number: 20200149476Abstract: A system and method for supplying compressed air from an auxiliary power unit to a main engine starter motor. The inlet guide vanes are controlled using either first or second inlet guide vane control logic and the surge control valve is controlled using either first or second surge control valve control logic. When the first inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand signal, when the second inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand schedule, when the first surge control valve logic is used, the surge control valve can be commanded to repeatedly move to only a fully-closed position and a fully-open position, and when the second surge control valve logic is used, the surge control valve can be commanded to the fully-closed position only when maximum flow is commanded.Type: ApplicationFiled: November 14, 2018Publication date: May 14, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Harold Riley, Michael Dwyer
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Publication number: 20200002019Abstract: A system and method provide aircraft-specific customization of gas turbine engine operation. The system includes a gas turbine engine, a first processing unit, and an engine controller. The first processing unit is configured to selectively transmit an activation key. The engine controller is in operable communication with the first processing unit and the gas turbine engine. The engine controller is configured to receive the activation key transmitted by the first processing unit and is operable, upon receipt of the activation key, to: verify the received activation key is correct, enable operational parameters in the gas turbine engine and the engine controller when the received activation key is correct, and control the gas turbine engine using the enabled operational parameters.Type: ApplicationFiled: March 18, 2019Publication date: January 2, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Harold Riley, Paul Topper, Brian Petterson, Timothy Ray O'Brien
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Publication number: 20190308742Abstract: An auxiliary power unit (APU) oil quantity indication system and method provides a stable and accurate oil quantity indication during startup, mission duration and shutdown. The system determines a gulp value at various stages of operation, which is combined with a raw oil quantity indication to provide an indicated oil quantity.Type: ApplicationFiled: June 21, 2019Publication date: October 10, 2019Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Robert Mallette, Harold Riley
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Patent number: 10378692Abstract: An auxiliary power unit (APU) oil quantity indication system and method provides a stable and accurate oil quantity indication during startup, mission duration and shutdown. The system determines a gulp value at various stages of operation, which is combined with a raw oil quantity indication to provide an indicated oil quantity.Type: GrantFiled: February 11, 2016Date of Patent: August 13, 2019Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Robert Mallette, Harold Riley
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Publication number: 20170234483Abstract: An auxiliary power unit (APU) oil quantity indication system and method provides a stable and accurate oil quantity indication during startup, mission duration and shutdown. The system determines a gulp value at various stages of operation, which is combined with a raw oil quantity indication to provide an indicated oil quantity.Type: ApplicationFiled: February 11, 2016Publication date: August 17, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Robert Mallette, Harold Riley
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Patent number: 8401760Abstract: A system and method of monitoring oil consumption in a gas turbine engine system are provided. When the gas turbine engine is not running the reservoir oil level, reservoir oil temperature, and reservoir attitude are sensed. The current gas turbine engine system oil quantity is determined based on at least the sensed reservoir oil level, the sensed reservoir oil temperature, and the sensed reservoir attitude. When a predetermined event has occurred, an average gas turbine engine system oil quantity is automatically calculated. The gas turbine engine system oil consumption rate is determined from a plurality of the average oil quantities.Type: GrantFiled: July 7, 2009Date of Patent: March 19, 2013Assignee: Honeywell International Inc.Inventors: David A. Payne, Harold Riley
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Patent number: 8321120Abstract: A system and method are provided for controlling the start-up of a gas turbine engine having an exhaust gas temperature (EGT) sensor. A determination is made as to whether the EGT sensor is available or unavailable. The gas turbine engine is commanded to accelerate at a nominal acceleration rate during the start-up operation if the EGT sensor is available, and to accelerate at an off-nominal acceleration rate during the start-up operation if the EGT sensor is unavailable. The off-nominal acceleration rate is lower than the nominal acceleration rate.Type: GrantFiled: January 16, 2009Date of Patent: November 27, 2012Assignee: Honeywell International Inc.Inventor: Harold Riley
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Publication number: 20110010069Abstract: A system and method of monitoring oil consumption in a gas turbine engine system are provided. When the gas turbine engine is not running the reservoir oil level, reservoir oil temperature, and reservoir attitude are sensed. The current gas turbine engine system oil quantity is determined based on at least the sensed reservoir oil level, the sensed reservoir oil temperature, and the sensed reservoir attitude. When a predetermined event has occurred, an average gas turbine engine system oil quantity is automatically calculated. The gas turbine engine system oil consumption rate is determined from a plurality of the average oil quantities.Type: ApplicationFiled: July 7, 2009Publication date: January 13, 2011Applicant: Honeywell International Inc.Inventors: David A. Payne, Harold Riley
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Publication number: 20100185377Abstract: A system and method are provided for controlling the start-up of a gas turbine engine having an exhaust gas temperature (EGT) sensor. A determination is made as to whether the EGT sensor is available or unavailable. The gas turbine engine is commanded to accelerate at a nominal acceleration rate during the start-up operation if the EGT sensor is available, and to accelerate at an off-nominal acceleration rate during the start-up operation if the EGT sensor is unavailable. The off-nominal acceleration rate is lower than the nominal acceleration rate.Type: ApplicationFiled: January 16, 2009Publication date: July 22, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventor: Harold Riley
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Publication number: 20070095070Abstract: Conventional auxiliary power units (APUs) may experience over-temperature shutdowns when attempting to start them at high altitudes. Further, such conventional APUs may also experience overspeed conditions when a generator load is removed during on-speed operations. A fuel control logic that controls the fuel flow cutback below the minimum blowout fuel schedule is provided. A temperature trim loop measures engine temperature to determine the onset of a possible over-temperature condition. The fuel flow may then be trimmed accordingly to correct this over-temperature onset. Further, when the onset of an overspeed condition is detected, such as when a generator load is removed, the fuel flow may be trimmed accordingly to correct this overspeed onset. The fuel control logic allows the control to find the individual minimum fuel flow for each fuel control without risking blowout of the APU itself.Type: ApplicationFiled: November 7, 2006Publication date: May 3, 2007Inventor: Harold Riley
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Publication number: 20070068169Abstract: An auxiliary power unit (APU) includes a controller that controls the position of an APU inlet door, and thus ram air flow to the APU, to ensure optimal starting conditions are attained and maintained in the APU during APU startup operations. The controller receives a signal representative of an APU operational parameter and, in response, to supplies APU inlet door position commands. An APU inlet door actuator is coupled to the APU inlet door and, in response to the APU inlet door position commands, moves the APU inlet door to the commanded position.Type: ApplicationFiled: September 27, 2005Publication date: March 29, 2007Inventor: Harold Riley
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Publication number: 20070051090Abstract: Conventional auxiliary power units (APUs) may experience over-temperature shutdowns when attempting to start them at high altitudes. Further, such conventional APUs may also experience overspeed conditions when a generator load is removed during on-speed operations. A fuel control logic that controls the fuel flow cutback below the minimum blowout fuel schedule is provided. A temperature trim loop measures engine temperature to determine the onset of a possible over-temperature condition. The fuel flow may then be trimmed accordingly to correct this over-temperature onset. Further, when the onset of an overspeed condition is detected, such as when a generator load is removed, the fuel flow may be trimmed accordingly to correct this overspeed onset. The fuel control logic allows the control to find the individual minimum fuel flow for each fuel control without risking blowout of the APU itself.Type: ApplicationFiled: November 7, 2006Publication date: March 8, 2007Inventor: Harold Riley
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Publication number: 20060254282Abstract: Conventional auxiliary power units (APUs) may experience over-temperature shutdowns when attempting to start them at high altitudes. Further, such conventional APUs may also experience overspeed conditions when a generator load is removed during on-speed operations. A fuel control logic that controls the fuel flow cutback below the minimum blowout fuel schedule is provided. A temperature trim loop measures engine temperature to determine the onset of a possible over-temperature condition. The fuel flow may then be trimmed accordingly to correct this over-temperature onset. Further, when the onset of an overspeed condition is detected, such as when a generator load is removed, the fuel flow may be trimmed accordingly to correct this overspeed onset. The fuel control logic allows the control to find the individual minimum fuel flow for each fuel control without risking blowout of the APU itself.Type: ApplicationFiled: February 17, 2004Publication date: November 16, 2006Applicant: Honeywell International Inc.Inventor: Harold Riley