Patents by Inventor Timothy REDFORD
Timothy REDFORD 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: 11746670Abstract: An impeller shroud assembly for a gas turbine engine includes an annular impeller shroud disposed about an axial centerline. The impeller shroud includes a shroud inducer portion and a shroud exducer portion disposed radially outward of the shroud inducer portion and extending to an outer radial end of the impeller shroud. The shroud inducer portion and the shroud exducer portion defining an impeller-facing surface of the impeller shroud. The impeller shroud has a pivot point defined between the shroud inducer portion and the shroud exducer portion. The impeller shroud assembly further includes a clearance control device connected to the shroud exducer portion of the impeller shroud proximate the outer radial end. The clearance control device is configured to pivot the shroud exducer portion of the impeller shroud about the pivot point between a first axial position and a second axial position.Type: GrantFiled: December 27, 2021Date of Patent: September 5, 2023Assignee: Pratt & Whitney Canada Corp.Inventors: David Menheere, Timothy Redford
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Publication number: 20230203962Abstract: An impeller shroud assembly for a gas turbine engine includes an annular impeller shroud disposed about an axial centerline. The impeller shroud includes a shroud inducer portion and a shroud exducer portion disposed radially outward of the shroud inducer portion and extending to an outer radial end of the impeller shroud. The shroud inducer portion and the shroud exducer portion defining an impeller-facing surface of the impeller shroud. The impeller shroud has a pivot point defined between the shroud inducer portion and the shroud exducer portion. The impeller shroud assembly further includes a clearance control device connected to the shroud exducer portion of the impeller shroud proximate the outer radial end. The clearance control device is configured to pivot the shroud exducer portion of the impeller shroud about the pivot point between a first axial position and a second axial position.Type: ApplicationFiled: December 27, 2021Publication date: June 29, 2023Inventors: David Menheere, Timothy Redford
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Patent number: 11623756Abstract: The gas turbine engine for an aircraft includes at least a low pressure spool with a low pressure turbine shaft operatively connected to at least one turbine, the low pressure turbine shaft rotatable about an engine axis, and a low pressure compressor operatively connected to a low pressure compressor shaft that is independently rotatable relative to the low pressure turbine shaft. A differential gearbox has an input operatively connected to the low pressure turbine shaft, a first output and a second output, the first output of the differential gearbox operatively connected to the low pressure compressor shaft and the second output of the differential gearbox operatively connected to an output shaft of the gas turbine engine. The differential gearbox permits the output shaft, the low pressure compressor shaft and the low pressure turbine shaft to rotate at different speeds.Type: GrantFiled: February 7, 2020Date of Patent: April 11, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: David Menheere, Santo Chiappetta, Timothy Redford, Daniel Van Den Ende
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Patent number: 11585280Abstract: The aircraft can have a first engine secured to a first wing on a first side of a fuselage, and a second engine secured to a second wing on a second side of the fuselage, the second wing having a proximal end secured to the fuselage, and a distal end extending away from the fuselage. While operating the first engine, compressed gas can be conveyed from the first engine to a thrust generating device located at the distal end of the second wing.Type: GrantFiled: November 3, 2020Date of Patent: February 21, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Santo Chiappetta, David H. Menheere, Timothy Redford, Daniel Van Den Ende
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Patent number: 11519337Abstract: An auxiliary power unit (APU) includes, in serial flow communication: an engine compressor, a combustor and a turbine, the turbine rotatable about an engine axis. A first shaft operatively connects the turbine to the engine compressor and extends non-parallel to the engine axis. A second shaft operatively connects the turbine to a load and extends non-parallel to the engine axis. A method of operating an APU is also described.Type: GrantFiled: June 24, 2019Date of Patent: December 6, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Timothy Redford, David Menheere
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Patent number: 11459953Abstract: The gas turbine engine includes a combustion section including an annular swirl combustor having a combustor inlet, and a compressor section including a centrifugal compressor with an impeller, the impeller compressing and swirling an airflow and discharging the compressed and swirled airflow from the impeller outlet into the combustor inlet. The turbine section includes a radial turbine having a turbine fuel inlet and a turbine fuel outlet, the radial turbine receiving a flow of fuel at the turbine fuel inlet and discharging the flow of fuel from the turbine fuel outlet of the radial turbine into the combustor inlet.Type: GrantFiled: February 24, 2020Date of Patent: October 4, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Daniel Van Den Ende, David Menheere, Timothy Redford
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Patent number: 11390386Abstract: Systems and methods for conditioning a fluid using bleed air from a bypass duct of a turbofan engine are disclosed. In one embodiment, such system comprises a heat exchanger configured to facilitate heat transfer between a flow of bleed air from the bypass duct of the turbofan engine and the fluid, and a fluid-driven fluid propeller configured to drive the bleed air through the heat exchanger.Type: GrantFiled: August 27, 2019Date of Patent: July 19, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Daniel Van Den Ende, Timothy Redford, David Menheere, Santo Chiappetta
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Publication number: 20220136448Abstract: The aircraft can have a first engine secured to a first wing on a first side of a fuselage, and a second engine secured to a second wing on a second side of the fuselage, the second wing having a proximal end secured to the fuselage, and a distal end extending away from the fuselage. While operating the first engine, compressed gas can be conveyed from the first engine to a thrust generating device located at the distal end of the second wing.Type: ApplicationFiled: November 3, 2020Publication date: May 5, 2022Inventors: Santo CHIAPPETTA, David H. MENHEERE, Timothy REDFORD, Daniel VAN DEN ENDE
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Patent number: 11215124Abstract: Systems and methods for conditioning a fluid using bleed air from a bypass duct of a turbofan engine are disclosed. The system comprises a heat exchanger configured to facilitate heat transfer between a flow of bleed air from the bypass duct of the turbofan engine and the fluid, and a fluid propeller configured to drive the bleed air through the heat exchanger. The fluid propeller is disposed downstream of the heat exchanger.Type: GrantFiled: August 27, 2019Date of Patent: January 4, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Daniel Van Den Ende, Timothy Redford, David Menheere, Santo Chiappetta
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Publication number: 20210276724Abstract: The gas turbine engine for an aircraft includes at least a low pressure spool with a low pressure turbine shaft operatively connected to at least one turbine, the low pressure turbine shaft rotatable about an engine axis, and a low pressure compressor operatively connected to a low pressure compressor shaft that is independently rotatable relative to the low pressure turbine shaft. A differential gearbox has an input operatively connected to the low pressure turbine shaft, a first output and a second output, the first output of the differential gearbox operatively connected to the low pressure compressor shaft and the second output of the differential gearbox operatively connected to an output shaft of the gas turbine engine. The differential gearbox permits the output shaft, the low pressure compressor shaft and the low pressure turbine shaft to rotate at different speeds.Type: ApplicationFiled: February 7, 2020Publication date: September 9, 2021Inventors: David MENHEERE, Santo CHIAPPETTA, Timothy REDFORD, Daniel VAN DEN ENDE
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Publication number: 20210262391Abstract: The gas turbine engine includes a combustion section including an annular swirl combustor having a combustor inlet, and a compressor section including a centrifugal compressor with an impeller, the impeller compressing and swirling an airflow and discharging the compressed and swirled airflow from the impeller outlet into the combustor inlet. The turbine section includes a radial turbine having a turbine fuel inlet and a turbine fuel outlet, the radial turbine receiving a flow of fuel at the turbine fuel inlet and discharging the flow of fuel from the turbine fuel outlet of the radial turbine into the combustor inlet.Type: ApplicationFiled: February 24, 2020Publication date: August 26, 2021Inventors: Daniel VAN DEN ENDE, David MENHEERE, Timothy REDFORD
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Patent number: 11085319Abstract: A system for controlling gas turbine engine rotor blades tip clearance is described. A rotor is mounted to an engine shaft, supported by a thrust bearing, for rotation within a gas path shroud circumscribing blades of the rotor, the gas path shroud having a non-cylindrical shape in the vicinity of the rotor blades. A rotary actuator is associated with the thrust bearing and configured for axial translation of the thrust bearing, to thereby axially translate the engine shaft and the rotor blades relative to the gas path shroud. This translation is configured to vary the blade tip clearance of the rotor.Type: GrantFiled: June 21, 2019Date of Patent: August 10, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Timothy Redford, David Menheere, Richard Kostka
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Publication number: 20210062727Abstract: Systems and methods for conditioning a fluid using bleed air from a bypass duct of a turbofan engine are disclosed. The system comprises a heat exchanger configured to facilitate heat transfer between a flow of bleed air from the bypass duct of the turbofan engine and the fluid, and a fluid propeller configured to drive the bleed air through the heat exchanger. The fluid propeller is disposed downstream of the heat exchanger.Type: ApplicationFiled: August 27, 2019Publication date: March 4, 2021Inventors: Daniel VAN DEN ENDE, Timothy REDFORD, David MENHEERE, Santo CHIAPPETTA
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Publication number: 20210061476Abstract: Systems and methods for conditioning a fluid using bleed air from a bypass duct of a turbofan engine are disclosed. In one embodiment, such system comprises a heat exchanger configured to facilitate heat transfer between a flow of bleed air from the bypass duct of the turbofan engine and the fluid, and a fluid-driven fluid propeller configured to drive the bleed air through the heat exchanger.Type: ApplicationFiled: August 27, 2019Publication date: March 4, 2021Inventors: Daniel VAN DEN ENDE, Timothy REDFORD, David MENHEERE, Santo CHIAPPETTA
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Publication number: 20200400034Abstract: A system for controlling gas turbine engine rotor blades tip clearance is described. A rotor is mounted to an engine shaft, supported by a thrust bearing, for rotation within a gas path shroud circumscribing blades of the rotor, the gas path shroud having a non-cylindrical shape in the vicinity of the rotor blades. A rotary actuator is associated with the thrust bearing and configured for axial translation of the thrust bearing, to thereby axially translate the engine shaft and the rotor blades relative to the gas path shroud. This translation is configured to vary the blade tip clearance of the rotor.Type: ApplicationFiled: June 21, 2019Publication date: December 24, 2020Inventors: Timothy REDFORD, David MENHEERE, Richard KOSTKA
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Publication number: 20200400036Abstract: A gas turbine engine system includes, in serial flow communication, an engine compressor configured to compress air, a combustor in which the compressed air is mixed with fuel and ignited to generate a stream of combustion gases, and a turbine configured to extract energy from the combustion gases. An electric generator is configured to be driven by the turbine and generate electric energy during use. An electric motor is configured to be driven by electric energy generated by the electric generator. The electric motor is configured in use to drive the engine compressor.Type: ApplicationFiled: June 24, 2019Publication date: December 24, 2020Inventors: Timothy REDFORD, David MENHEERE
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Publication number: 20200400077Abstract: An auxiliary power unit (APU) includes, in serial flow communication: an engine compressor, a combustor and a turbine, the turbine rotatable about an engine axis. A first shaft operatively connects the turbine to the engine compressor and extends non-parallel to the engine axis. A second shaft operatively connects the turbine to a load and extends non-parallel to the engine axis. A method of operating an APU is also described.Type: ApplicationFiled: June 24, 2019Publication date: December 24, 2020Applicants: PRATT & WHITNEY CANADA CORP., PRATT & WHITNEY CANADA CORP.Inventors: Timothy REDFORD, David MENHEERE
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Publication number: 20200386406Abstract: The aircraft engine can have a core gas path extending from an intake across a core compressor, and then manifolding to a plurality turbine intake paths, each turbine intake path leading to a respective turbine unit via a respective combustor unit, and gearing drivingly connecting the collective rotary power of the turbine units to at least one power output shaft. During operation, the different core-turbine units can be operated simultaneously and efficiently, or one or more of the core-turbine units can be selectively shut down while the other core-turbine units continue to operate efficiently to lower the power output.Type: ApplicationFiled: December 18, 2019Publication date: December 10, 2020Inventors: Timothy REDFORD, David MENHEERE, Daniel VAN DEN ENDE, Santo CHIAPPETTA
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Publication number: 20200386407Abstract: The gas turbine engine can have a core gas path extending sequentially across a core compressor, a core combustor, and a core turbine, an auxiliary air intake path and a bypass intake path leading in parallel to the core compressor, an auxiliary compressor in the auxiliary air intake path, an auxiliary gas path downstream of the core compressor, the auxiliary gas path extending in sequence across an auxiliary combustor and an auxiliary turbine, in parallel with the core combustor and core turbine, and valves operable to control the flow through the bypass gas path and the auxiliary gas path. Accordingly, the auxiliary components can be operated to increase power output, or deactivated while allowing the core components to run efficiently while meeting a lower power output.Type: ApplicationFiled: December 18, 2019Publication date: December 10, 2020Inventors: David MENHEERE, Santo CHIAPPETTA, Timothy REDFORD, Daniel VAN DEN ENDE
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Publication number: 20200386405Abstract: The aircraft engine can have a core gas path having a first combustor, a second gas path parallel to the core gas path, the second gas path having a second combustor, a turbine driven by the second gas path, a gearbox driven by the turbine, and a valve configured for selectively opening and closing the second gas path.Type: ApplicationFiled: June 6, 2019Publication date: December 10, 2020Inventors: David MENHEERE, Santo CHIAPPETTA, Timothy REDFORD, Daniel VAN DEN ENDE