Patents by Inventor Joseph B Cooper
Joseph B Cooper 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: 20230200310Abstract: The battery-powered backpack blower includes a back support assembly including a back plate configured to permit a user to mount the blower to the user's back, and a volute assembly including a first volute portion and a second volute portion. The backpack blower further includes a housing assembly including a battery assembly and a motor assembly therein, the housing assembly is provided intermediate to the back assembly and the volute assembly.Type: ApplicationFiled: February 20, 2023Publication date: June 29, 2023Inventors: Brian POOLE, Joshua M SHEFFER, Wong Kun NG, Keith D. FLAHARTY, Joseph B. COOPER, Philip MARTINEZ, David Keith WHEELER, Christopher Wade Shook
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Patent number: 11606917Abstract: The battery-powered backpack blower includes a back support assembly including a back plate configured to permit a user to mount the blower to the user's back, and a volute assembly including a first volute portion and a second volute portion. The backpack blower further includes a housing assembly including a battery assembly and a motor assembly therein, the housing assembly is provided intermediate to the back assembly and the volute assembly.Type: GrantFiled: April 10, 2020Date of Patent: March 21, 2023Assignee: Black & Decker, Inc.Inventors: Brian Poole, Joshua M Sheffer, Wong Kun Ng, Keith D. Flaharty, Joseph B. Cooper, Philip Martinez, David Keith Wheeler, Christopher Wade Shook
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Patent number: 11292605Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. A temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link are each adapted to resist tension and compression, to maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.Type: GrantFiled: April 29, 2019Date of Patent: April 5, 2022Assignee: Rolls-Royce plcInventor: Joseph B. Cooper
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Patent number: 11254447Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. At least one temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link each comprise a respective winch operable to adjust pay out of a respective tension member thereby to provide length adjustment. The temporary forward link and the temporary rearward link maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.Type: GrantFiled: May 9, 2019Date of Patent: February 22, 2022Inventor: Joseph B. Cooper
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Patent number: 11111790Abstract: A method of upgrading a modular gas turbine engine, which includes: a first fan module with a fan having plurality of fan blades; a first engine core module including an engine core and a gearbox providing drive to the fan; and a first fan case module with a fan case arranged to enclose the fan blades, the method including: disassembling the gas turbine engine, replacing one of the first fan module, first engine core module or first fan case module with a replacement fan module, a replacement engine core module or a replacement fan case module; and reassembling the gas turbine engine using the replacement module, which is compatible with the others of the first fan module, first engine core module or first fan case module; and the replacement module designed to different parameters to one of the first fan module, first engine core module or first fan case module.Type: GrantFiled: October 17, 2019Date of Patent: September 7, 2021Assignee: ROLLS-ROYCE plcInventors: Joseph B Cooper, Katie Phillips
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Patent number: 10989145Abstract: A method of replacing a module in a modular gas turbine engine having a first fan module; a first propulsor module including an engine core and a gearbox; and a first fan case module having a fan case; includes the steps of: disassembling the gas turbine engine, replacing one of the fan module, propulsor module or fan case module with a replacement fan module, a replacement propulsor module or a replacement fan case module, the replacement module, having the same configuration as the first module; and reassembling the gas turbine engine using the replacement module.Type: GrantFiled: October 2, 2019Date of Patent: April 27, 2021Assignee: ROLLS-ROYCE plcInventors: Joseph B Cooper, Lawrence M T Bigg
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Method and system for calibrating an engine core by determining power rating data of the engine core
Patent number: 10968769Abstract: A method of calibrating an engine core of a gas turbine engine, wherein the engine core includes a turbine, combustion equipment, a compressor, and a core shaft connecting the turbine to the compressor, the core shaft arranged to drive a propulsive fan of the gas turbine engine, the method including: providing a resistance load on the core shaft, the resistance load arranged to replicate the load of a propulsive fan; driving the engine core; measuring a performance parameter or the engine core; measuring a thrust generated by the engine core; and determining power rating data of the engine core, providing a correlation between the performance parameter and the thrust.Type: GrantFiled: May 14, 2019Date of Patent: April 6, 2021Assignee: ROLLS-ROYCE plcInventor: Joseph B Cooper -
Patent number: 10907476Abstract: A shaft assembly for a gas turbine engine is provided. The shaft assembly comprises: a first shaft having an outer surface; a first coupling ring disposed around the outer surface of the first shaft, an inner surface of the first coupling ring being coupled to the outer surface of the first shaft; a second shaft having an inner surface; and a second coupling ring disposed around the inner surface of the second shaft, an outer surface of the second coupling ring being coupled to the inner surface of the second shaft, wherein an outer surface of the first coupling ring is configured to mate with an inner surface of the second coupling ring, such that concentricity of the first and second shafts is maintained at the shaft assembly by virtue of the mating of the first and second coupling rings. Methods of assembling and re-assembling a shaft assembly are also provided.Type: GrantFiled: April 4, 2019Date of Patent: February 2, 2021Assignee: Rolls-Royce plcInventor: Joseph B. Cooper
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Publication number: 20200248591Abstract: A system and a method for assembling a core engine and a fan case of a gas turbine engine. The system includes a core engine support that detachably supports the core engine. The core engine support includes at least one core engine alignment sensor. The system further includes a fan case support that detachably supports the fan case. The fan case support includes at least one fan case alignment sensor. The system further includes a computer-controllable unit configured to align the core engine support and the fan case support based on signals from the at least one core engine alignment sensor and the at least one fan case alignment sensor. The computer-controllable unit is further configured to guide a movement of at least one of the core engine support and the fan case support to couple the core engine with the fan case.Type: ApplicationFiled: January 23, 2020Publication date: August 6, 2020Inventor: Joseph B. COOPER
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Publication number: 20200236875Abstract: The battery-powered backpack blower includes a back support assembly including a back plate configured to permit a user to mount the blower to the user's back, and a volute assembly including a first volute portion and a second volute portion. The backpack blower further includes a housing assembly including a battery assembly and a motor assembly therein, the housing assembly is provided intermediate to the back assembly and the volute assembly.Type: ApplicationFiled: April 10, 2020Publication date: July 30, 2020Inventors: Brian POOLE, Joshua M. SHEFFER, Wong Kun NG, Keith D. FLAHARTY, Joseph B. COOPER, Philip MARTINEZ, David Keith WHEELER, Christopher Wade Shook
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Patent number: 10645884Abstract: The battery-powered backpack blower includes a back support assembly including a back plate configured to permit a user to mount the blower to the user's back, and a volute assembly including a first volute portion and a second volute portion. The backpack blower further includes a housing assembly including a battery assembly and a motor assembly therein, the housing assembly is provided intermediate to the back assembly and the volute assembly.Type: GrantFiled: January 23, 2018Date of Patent: May 12, 2020Assignee: Black & Decker, Inc.Inventors: Brian Poole, Joshua M. Sheffer, Wong Kun Ng, Keith D. Flaharty, Joseph B. Cooper, Philip Martinez, David Keith Wheeler
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Publication number: 20200141266Abstract: A method of calibrating an engine core of a gas turbine engine, wherein the engine core includes a turbine, combustion equipment, a compressor, and a core shaft connecting the turbine to the compressor, the core shaft arranged to drive a propulsive fan of the gas turbine engine, the method including: providing a resistance load on the core shaft, the resistance load arranged to replicate the load of a propulsive fan; driving the engine core; measuring a performance parameter or the engine core; measuring a thrust generated by the engine core; and determining power rating data of the engine core, providing a correlation between the performance parameter and the thrust.Type: ApplicationFiled: May 14, 2019Publication date: May 7, 2020Applicant: ROLLS-ROYCE plcInventor: Joseph B COOPER
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Publication number: 20200141239Abstract: A method of upgrading a modular gas turbine engine, which includes: a first fan module with a fan having plurality of fan blades; a first engine core module including an engine core and a gearbox providing drive to the fan; and a first fan case module with a fan case arranged to enclose the fan blades, the method including: disassembling the gas turbine engine, replacing one of the first fan module, first engine core module or first fan case module with a replacement fan module, a replacement engine core module or a replacement fan case module; and reassembling the gas turbine engine using the replacement module, which is compatible with the others of the first fan module, first engine core module or first fan case module; and the replacement module designed to different parameters to one of the first fan module, first engine core module or first fan case module.Type: ApplicationFiled: October 17, 2019Publication date: May 7, 2020Applicant: ROLLS-ROYCE PLCInventors: Joseph B. COOPER, Katie PHILLIPS
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Publication number: 20200141313Abstract: A method of replacing a module in a modular gas turbine engine having a first fan module; a first propulsor module including an engine core and a gearbox; and a first fan case module having a fan case; includes the steps of: disassembling the gas turbine engine, replacing one of the fan module, propulsor module or fan case module with a replacement fan module, a replacement propulsor module or a replacement fan case module, the replacement module, having the same configuration as the first module; and reassembling the gas turbine engine using the replacement module.Type: ApplicationFiled: October 2, 2019Publication date: May 7, 2020Applicant: ROLLS-ROYCE plcInventors: Joseph B. COOPER, Lawrence M.T. BIGG
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Publication number: 20200141277Abstract: A fan case for a gas turbine aircraft engine, the fan case formed of a wall extending in a loop around an axis (9?) and along the axis (9?), and having a case length along the axis (9?), and a case perimeter around the axis, wherein the fan case comprises two or more longitudinal segments configured to be assembled to form the wall, wherein each longitudinal segment includes a portion of the wall extending at least part of the length of the fan case and forming an incomplete portion of the perimeter of the fan case.Type: ApplicationFiled: October 10, 2019Publication date: May 7, 2020Applicant: ROLLS-ROYCE plcInventors: Joseph B. COOPER, Geraint REES
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Publication number: 20200141358Abstract: A gas turbine engine for an aircraft includes: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein the engine core extends along a rotational axis, and has an engine core diameter perpendicular to the rotational axis; and a fan having a plurality of fan blades extending radially from the rotational axis, wherein the fan has a fan diameter perpendicular to the rotational axis, wherein a ratio of the engine core diameter to the fan diameter is between 1:1.7 and 1:2.2.Type: ApplicationFiled: May 28, 2019Publication date: May 7, 2020Applicant: ROLLS-ROYCE plcInventors: Joseph B. COOPER, Geraint REES
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Publication number: 20200056541Abstract: A tooling and a method for removing or mounting a fan blade from or to a fan disc of a ducted fan aeroengine are provided. The tooling comprises a cover adapted to be arranged on an inner wall of an air intake of the aeroengine and a boot adapted to be mounted on a leading edge tip of the blade and adapted to slide on the cover during removing or mounting the fan blade from or to the fan disc.Type: ApplicationFiled: July 25, 2019Publication date: February 20, 2020Applicant: ROLLS-ROYCE plcInventor: Joseph B. COOPER
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Publication number: 20190359342Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. A temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link are each adapted to resist tension and compression, to maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.Type: ApplicationFiled: April 29, 2019Publication date: November 28, 2019Applicant: ROLLS-ROYCE plcInventor: Joseph B. COOPER
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Publication number: 20190359352Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. At least one temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link each comprise a respective winch operable to adjust pay out of a respective tension member thereby to provide length adjustment. The temporary forward link and the temporary rearward link maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.Type: ApplicationFiled: May 9, 2019Publication date: November 28, 2019Applicant: ROLLS-ROYCE plcInventor: Joseph B. COOPER
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Publication number: 20190323353Abstract: A shaft assembly for a gas turbine engine is provided. The shaft assembly comprises: a first shaft having an outer surface; a first coupling ring disposed around the outer surface of the first shaft, an inner surface of the first coupling ring being coupled to the outer surface of the first shaft; a second shaft having an inner surface; and a second coupling ring disposed around the inner surface of the second shaft, an outer surface of the second coupling ring being coupled to the inner surface of the second shaft, wherein an outer surface of the first coupling ring is configured to mate with an inner surface of the second coupling ring, such that concentricity of the first and second shafts is maintained at the shaft assembly by virtue of the mating of the first and second coupling rings. Methods of assembling and re-assembling a shaft assembly are also provided.Type: ApplicationFiled: April 4, 2019Publication date: October 24, 2019Applicant: ROLLS-ROYCE plcInventor: Joseph B. COOPER