Patents by Inventor Yusuf Syed
Yusuf Syed 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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Publication number: 20240113513Abstract: A hybrid-electric powerplant (HEP) of an aircraft comprises a thermal engine providing a first torque input to the HEP and an electric motor providing a second torque input to the HEP. A power management system connected to one or both of the thermal engine and the electric motor comprises an engine control unit (ECU) connected to the thermal engine. The ECU controls fuel supplied to the thermal engine. An electric propulsion control (EPC) is connected to the electric motor and controls power supplied to the electric motor. The EPC includes an EPC protection module in communication with a power source for the electric motor. The EPC protection module disables power supplied to the electric motor upon receipt of a signal indicative of one or more of an over-speed condition and an over-torque condition detected in the HEP.Type: ApplicationFiled: October 4, 2022Publication date: April 4, 2024Inventors: Yusuf SYED, Thomas Trevor RICCI, James Robert JARVO
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Patent number: 11591985Abstract: There are described a system and method for operating a thrust reverser of an aircraft engine, the thrust reverser having a deployed state and a stowed state. The method comprises placing the thrust reverser in the stowed state when the thrust reverser is in the deployed state, a thrust lever associated with the engine is in a forward position, and the engine is rotating at a speed below an idle speed, wherein hydraulic pressure for stowing the thrust reverser is provided by a pump driven by the engine rotating at the speed below the idle speed.Type: GrantFiled: October 21, 2020Date of Patent: February 28, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Hamza Assi, Yusuf Syed, Ioan Sabau
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Publication number: 20220120239Abstract: There are described a system and method for operating a thrust reverser of an aircraft engine, the thrust reverser having a deployed state and a stowed state. The method comprises placing the thrust reverser in the stowed state when the thrust reverser is in the deployed state, a thrust lever associated with the engine is in a forward position, and the engine is rotating at a speed below an idle speed, wherein hydraulic pressure for stowing the thrust reverser is provided by a pump driven by the engine rotating at the speed below the idle speed.Type: ApplicationFiled: October 21, 2020Publication date: April 21, 2022Inventors: Hamza ASSI, Yusuf SYED, Ioan SABAU
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Patent number: 10850863Abstract: At least a selected one of a first and second engine are connected to a drive train for driving an aircraft accessory. A gearbox is connected to a primer mover propulsor and an actuator operatively associated with the selected engine is moveable between a position in which the selected engine drivingly engages the gearbox for driving the propulsor and a position in which the selected engine disengages from the gearbox. A position signal, a status signal, and a request signal respectively indicative of a present position of the actuator, a governing state and present speed of each engine, and a request for movement of the actuator from the present position to the other position are received. If the selected engine's speed differs from a predetermined threshold, a control signal is output for causing the engine's speed to be adjusted towards the threshold. A control signal indicating that movement of the actuator is permitted is then output.Type: GrantFiled: March 4, 2014Date of Patent: December 1, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean-Francois Bisson, Carmine Lisio, Romain Chevalier, Dave Sellors, Yusuf Syed, Guy Riverin, Matthew Chiasson
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Publication number: 20200080497Abstract: Methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft are described. The method comprises detecting an abnormal engine response as a function of a fuel flow error, the fuel flow error indicative of a presence of excess thrust; in response to detecting the fuel flow error, detecting a UHT event based on the excess thrust and as a function of a threshold; and accommodating the UHT event when the UHT event is detected.Type: ApplicationFiled: September 5, 2019Publication date: March 12, 2020Inventors: Yusuf SYED, Michael KRYNSKI, Antwan SHENOUDA, Frederic GIROUX, Ioan SABAU
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Patent number: 10443512Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, detecting a fuel flow error when an actual fuel flow minus a commanded fuel flow exceeds a first threshold, the fuel flow error indicative of a presence of excess thrust, detecting a UHT event based on excess thrust and as a function of a second threshold, upon detection of the fuel flow error, and accommodating the UHT event.Type: GrantFiled: March 31, 2017Date of Patent: October 15, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Yusuf Syed, Michael Krynski, Antwan Shenouda, Frederic Giroux, Ioan Sabau
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Publication number: 20190292936Abstract: Systems and methods for detecting shear of a rotating shaft are described herein. A first measurement and a second measurement of a rotational speed of the shaft are acquired. The first measurement is taken at a first location along the shaft and the second measurement taken at a second location along the shaft. The first location is axially-spaced from the second location. The first and second location are on opposite sides of an expected breakage point of the shaft. A first rate of change of the rotational speed is determined from the first measurement. A second rate of change is determined from the second measurement. Shear of the shaft is detected when the first rate of change is positive and the second rate of change is negative.Type: ApplicationFiled: September 14, 2018Publication date: September 26, 2019Inventors: Glenn BIRCH, Yusuf SYED
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Patent number: 10302021Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, comparing an engine fan speed to a reference target and detecting a first condition when a first threshold is exceeded, comparing a rate of change of a high pressure rotor speed to a reference deceleration schedule and detecting a second condition when a second threshold is exceeded, detecting a UHT event based on excess thrust when the first condition and the second condition are detected, and accommodating the UHT event.Type: GrantFiled: May 3, 2017Date of Patent: May 28, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Krynski, Poi Loon Tang, David Mathews, Antwan Shenouda, Yusuf Syed
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Publication number: 20180320599Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, comparing an engine fan speed to a reference target and detecting a first condition when a first threshold is exceeded, comparing a rate of change of a high pressure rotor speed to a reference deceleration schedule and detecting a second condition when a second threshold is exceeded, detecting a UHT event based on excess thrust when the first condition and the second condition are detected, and accommodating the UHT event.Type: ApplicationFiled: May 3, 2017Publication date: November 8, 2018Inventors: Michael KRYNSKI, Poi Loon TANG, David MATHEWS, Antwan SHENOUDA, Yusuf SYED
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Publication number: 20180283286Abstract: Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, detecting a fuel flow error when an actual fuel flow minus a commanded fuel flow exceeds a first threshold, the fuel flow error indicative of a presence of excess thrust, detecting a UHT event based on excess thrust and as a function of a second threshold, upon detection of the fuel flow error, and accommodating the UHT event.Type: ApplicationFiled: March 31, 2017Publication date: October 4, 2018Inventors: Yusuf SYED, Michael KRYNSKI, Antwan SHENOUDA, Frederic GIROUX, Ioan SABAU
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Publication number: 20150251770Abstract: A first and second engine are connected to a drive train for driving an aircraft accessory. A gearbox is connected to a primer mover propulsor and an actuator operatively associated with a selected engine is moveable between a position in which the selected engine drivingly engages the gearbox for driving the propulsor and a position in which the selected engine disengages from the gearbox. A position signal, a status signal, and a request signal respectively indicative of a present position of the actuator, a governing state and present speed of each engine, and a request for movement of the actuator from the present position to the other position are received. If the selected engine's speed differs from a predetermined threshold, a control signal is output for causing the engine's speed to be adjusted towards the threshold. A control signal indicating that movement of the actuator is permitted is then output.Type: ApplicationFiled: March 4, 2014Publication date: September 10, 2015Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Jean-Francois BISSON, Carmine LISIO, Romain CHEVALIER, Dave SELLORS, Yusuf SYED, Guy RIVERIN, Matthew CHIASSON
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Patent number: 9114885Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.Type: GrantFiled: September 13, 2013Date of Patent: August 25, 2015Assignee: Pratt & Whitney Canada Corp.Inventors: Salvatore Calandra, Frederic Giroux, Mark Iacobacci, Martin Chabot, Simon Hartropp, Yusuf Syed, Dariusz Chmiel, Adrienne Bajaj
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Publication number: 20140012481Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.Type: ApplicationFiled: September 13, 2013Publication date: January 9, 2014Applicant: Pratt & Whitney Canada Corp.Inventors: Salvatore Calandra, Frederic Giroux, Mark Iacobacci, Martin Chabot, Simon Hartropp, Yusuf Syed, Dariusz Chmiel, Adrienne Bajaj
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Patent number: 8560203Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.Type: GrantFiled: July 26, 2011Date of Patent: October 15, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Salvatore Calandra, Frederic Giroux, Mark Iacobacci, Martin Chabot, Simon Hartropp, Yusuf Syed, Dariusz Chmiel, Adrienne Bajaj
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Publication number: 20120029786Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.Type: ApplicationFiled: July 26, 2011Publication date: February 2, 2012Applicant: Pratt & Whitney Canada Corp.Inventors: Salvatore Calandra, Frederic Giroux, Mark Iacobacci, Martin Chabot, Simon Hartropp, Yusuf Syed, Dariusz Chmiel, Adrienne Bajaj
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Publication number: 20050261820Abstract: A system, method and apparatus for monitoring the performance of a gas turbine engine. A counter value Indicative of the comparison between the engine condition and the threshold condition is adjusted. The aircraft operator is warned of an impending maintenance condition based on the counter value and determines an appropriate course of action.Type: ApplicationFiled: May 21, 2004Publication date: November 24, 2005Inventors: Mark Feeney, Keith Leslie, Yusuf Syed, Simon Hartropp