Patents by Inventor Patrice REMY
Patrice REMY 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: 11891902Abstract: A measurement system for an aircraft gas turbine engine includes an instrumentation hub disposed about a rotational axis. The instrumentation hub includes at least one probe. The measurement system further includes a shield hub disposed about the rotational axis and positioned axially adjacent the instrumentation hub. The shield hub includes at least one shield configured to be radially aligned with the at least one probe of the instrumentation hub. The shield hub is rotatable about the rotational axis independent of the instrumentation hub. The at least one shield is axially translatable between a first axial position and a second axial position. The at least one shield in the first axial position is axially aligned with the at least one probe. The at least one shield in the second axial position is axially separated from the at least one probe.Type: GrantFiled: April 15, 2022Date of Patent: February 6, 2024Assignee: Pratt & Whitney Canada Corp.Inventor: Patrice Remy
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Patent number: 11821811Abstract: A measurement system for an aircraft gas turbine engine includes an instrumentation hub including at least one probe, and a shield hub positioned axially adjacent the instrumentation hub. The instrumentation hub is rotatable about a rotational axis. The shield hub includes at least one shield which is radially aligned with the at least one probe of the instrumentation hub. The shield hub is rotatable about the rotational axis independent of the instrumentation hub.Type: GrantFiled: February 4, 2022Date of Patent: November 21, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Patrice Rémy, Christian Bissonnette
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Publication number: 20230332511Abstract: A measurement system for an aircraft gas turbine engine includes an instrumentation hub disposed about a rotational axis. The instrumentation hub includes at least one probe. The measurement system further includes a shield hub disposed about the rotational axis and positioned axially adjacent the instrumentation hub. The shield hub includes at least one shield configured to be radially aligned with the at least one probe of the instrumentation hub. The shield hub is rotatable about the rotational axis independent of the instrumentation hub. The at least one shield is axially translatable between a first axial position and a second axial position. The at least one shield in the first axial position is axially aligned with the at least one probe. The at least one shield in the second axial position is axially separated from the at least one probe.Type: ApplicationFiled: April 15, 2022Publication date: October 19, 2023Inventor: Patrice Remy
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Patent number: 11745863Abstract: Methods and systems for controlling windmilling in an engine are described. An electric starter motor is coupled to the engine, a circuit element is coupled to the electric starter engine and to a DC signal source, and a control system coupled to the engine and to the circuit element. The control system is configured for: determining whether the engine is in a windmilling state; when the engine is in a windmilling state, commanding the circuit element to apply a DC signal to the electric starter motor; and modulating the DC signal applied to the electric starter motor to control a level of rotational motion of the engine.Type: GrantFiled: March 28, 2019Date of Patent: September 5, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Kashif Mohammed, Patrick Manoukian, Patrice Remy
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Publication number: 20230251164Abstract: A measurement system for an aircraft gas turbine engine includes an instrumentation hub including at least one probe, and a shield hub positioned axially adjacent the instrumentation hub. The instrumentation hub is rotatable about a rotational axis. The shield hub includes at least one shield which is radially aligned with the at least one probe of the instrumentation hub. The shield hub is rotatable about the rotational axis independent of the instrumentation hub.Type: ApplicationFiled: February 4, 2022Publication date: August 10, 2023Inventors: Patrice Rémy, Christian Bissonnette
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Patent number: 11692481Abstract: An inertial particle separator (IPS) duct assembly is disclosed having a duct having an inlet section extending downstream from an intake flow opening for receiving airflow to a junction, a scavenge flow section and a core flow section, the scavenge flow section and the core flow section splitting from the inlet section at the junction, the scavenge flow section having a scavenge flow outlet downstream of the junction, the core flow section having a core flow outlet downstream of the junction and fluidly connectable to the air intake of an engine core. A splitter cartridge is removably mounted at the junction, the splitter cartridge including a splitter body extending between a duct wall of the scavenge flow section and a duct wall of the core flow section.Type: GrantFiled: April 29, 2022Date of Patent: July 4, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Patrice Remy
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Publication number: 20230184115Abstract: A computer program product contains computer-readable instructions, which, when operated on by a computer, performs the following method. A combination is determined of relative circumferential positions of the individual rotor components associated to a bow shape configuration of the centers of mass along the axially-extending sequence based on geometrical reference values concerning individual rotor components each having a center of mass and configured to be assembled to one another in an axial sequence to form a rotor assembly, the geometrical reference values being stored in a computer readable memory accessible to the computer.Type: ApplicationFiled: February 2, 2023Publication date: June 15, 2023Inventors: Patrice REMY, Pierre GAUDET, Jiemin WANG
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Patent number: 11630016Abstract: A measurement system for an aircraft gas turbine engine includes a probe and a heated-gas source in fluid communication with the pressure probe. The probe includes a probe body defining an internal cavity of the probe. The probe further includes a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow. The probe further includes a plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.Type: GrantFiled: August 20, 2021Date of Patent: April 18, 2023Assignee: Pratt & Whitney Canada Corp.Inventors: Patrice Rémy, Frédéric Doucet, Christian Bissonnette, Luc Archambault
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Patent number: 11608742Abstract: The method of assembling the rotor assembly can include obtaining geometrical reference values about the individual rotor components, based on the geometrical reference values, determining a combination of relative circumferential positions of the individual rotor components associated to a bow shape configuration of the centers of mass along the axially-extending sequence; and assembling the rotor components to one another in said determined combination of relative circumferential positions, into the rotor assembly.Type: GrantFiled: October 3, 2019Date of Patent: March 21, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Patrice Remy, Pierre Gaudet, Jiemin Wang
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Publication number: 20230054983Abstract: A measurement system for an aircraft gas turbine engine includes a probe and a heated-gas source in fluid communication with the pressure probe. The probe includes a probe body defining an internal cavity of the probe. The probe further includes a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow. The probe further includes a plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.Type: ApplicationFiled: August 20, 2021Publication date: February 23, 2023Inventors: Patrice Rémy, Frédéric Doucet, Christian Bissonnette, Luc Archambault
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Patent number: 11187104Abstract: A method of assembling a first part to a second part while applying thermal energy to at least one of the parts. The application of thermal energy is terminated when the first part and second part are in a completed assembly position relative to each other. The thermal energy absorbed by the at least one of: the first part; and the second part is then dissipated until the first part and second part are engaged in an interference fit.Type: GrantFiled: October 28, 2019Date of Patent: November 30, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Patrice Remy, Pierre Gaudet
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Publication number: 20210123359Abstract: A method of assembling a first part to a second part while applying thermal energy to at least one of the parts. The application of thermal energy is terminated when the first part and second part are in a completed assembly position relative to each other. The thermal energy absorbed by the at least one of: the first part; and the second part is then dissipated until the first part and second part are engaged in an interference fit.Type: ApplicationFiled: October 28, 2019Publication date: April 29, 2021Inventors: Patrice REMY, Pierre GAUDET
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Publication number: 20210102465Abstract: The method of assembling the rotor assembly can include obtaining geometrical reference values about the individual rotor components, based on the geometrical reference values, determining a combination of relative circumferential positions of the individual rotor components associated to a bow shape configuration of the centers of mass along the axially-extending sequence; and assembling the rotor components to one another in said determined combination of relative circumferential positions, into the rotor assembly.Type: ApplicationFiled: October 3, 2019Publication date: April 8, 2021Inventors: Patrice REMY, Pierre GAUDET, Jiemin WANG
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Publication number: 20200283138Abstract: Methods and systems for controlling windmilling in an engine are described. An electric starter motor is coupled to the engine, a circuit element is coupled to the electric starter engine and to a DC signal source, and a control system coupled to the engine and to the circuit element. The control system is configured for: determining whether the engine is in a windmilling state; when the engine is in a windmilling state, commanding the circuit element to apply a DC signal to the electric starter motor; and modulating the DC signal applied to the electric starter motor to control a level of rotational motion of the engine.Type: ApplicationFiled: March 28, 2019Publication date: September 10, 2020Inventors: Kashif Mohammed, Patrick Manoukian, Patrice Remy
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Publication number: 20180283283Abstract: Herein provided are methods and systems for controlling operation of a deprime valve of an engine of an aircraft. A windmilling condition for an engine, indicative of at least one rotatable component of the engine being driven while the engine is inoperative, is detected. A fire event condition, indicative of a fire in proximity to the engine, is detected. When the windmilling and fire event conditions are detected concurrently, a command is sent to the deprime valve to cause the deprime valve to be open for a predetermined period of time.Type: ApplicationFiled: March 28, 2017Publication date: October 4, 2018Inventors: Patrick MANOUKIAN, Patrice REMY, Sarah THERIAULT
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Patent number: 10048144Abstract: A method of validating a compressive axial preload on adjacent rotatable elements serially arranged around a shaft, created through application of a progressively increasing axial tension to a tensioning member configured to compress the elements when the axial tension is applied. The method includes monitoring a load in the tensioning member and/or in one or more of the elements, and an elongation of the tensioning member, during application of the axial tension, determining at least one validation parameter from the load and the elongation, comparing each validation parameter with a respective predetermined range therefor; and if at least one of the at least one validation parameter is out of the respective predetermined range, correcting the preload on the elements, and repeating the method. A method of applying the compressive preload and a system for validating the compressive preload are also described.Type: GrantFiled: July 12, 2013Date of Patent: August 14, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Patrice Remy, Pierre Gaudet
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Patent number: 9702267Abstract: A method for centering an engine structure such as a bearing housing is provided which may be used for example, during assembly of a mid turbine frame or other engine case structure. The method according to one embodiment may include machining spokes with an outer case of the mid turbine frame in situ to eliminate stack-up and then applying the retaining device to retain the spokes with respect to the outer case, thereby assuring the co-axial relationship between the outer case and the bearing housing supported within the mid turbine frame.Type: GrantFiled: October 15, 2014Date of Patent: July 11, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eugene Gekht, Patrice Remy, Danny Mills
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Publication number: 20160107276Abstract: A method for centering an engine structure such as a bearing housing is provided which may be used for example, during assembly of a mid turbine frame or other engine case structure. The method according to one embodiment may include machining spokes with an outer case of the mid turbine frame in situ to eliminate stack-up and then applying the retaining device to retain the spokes with respect to the outer case, thereby assuring the co-axial relationship between the outer case and the bearing housing supported within the mid turbine frame.Type: ApplicationFiled: October 15, 2014Publication date: April 21, 2016Inventors: Eugene GEKHT, Patrice REMY, Danny MILLS
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Publication number: 20150019144Abstract: A method of validating a compressive axial preload on adjacent rotatable elements serially arranged around a shaft, created through application of a progressively increasing axial tension to a tensioning member configured to compress the elements when the axial tension is applied. The method includes monitoring a load in the tensioning member and/or in one or more of the elements, and an elongation of the tensioning member, during application of the axial tension, determining at least one validation parameter from the load and the elongation, comparing each validation parameter with a respective predetermined range therefor; and if at least one of the at least one validation parameter is out of the respective predetermined range, correcting the preload on the elements, and repeating the method. A method of applying the compressive preload and a system for validating the compressive preload are also described.Type: ApplicationFiled: July 12, 2013Publication date: January 15, 2015Inventors: Patrice REMY, Pierre GAUDET