Patents by Inventor Karl D. Blume
Karl D. Blume 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: 11549434Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. A bleed tap taps air from the compressor section through a bleed valve. The bleed valve is selectively opened by a control to dump air from the compressor section to a dump outlet. A heat exchanger duct includes a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet. The dump outlet is within the heat exchanger duct.Type: GrantFiled: July 16, 2021Date of Patent: January 10, 2023Assignee: Raytheon Technologies CorporationInventors: Steven H. Zysman, Karl D. Blume, James H. Anderson, Holly Teufel, Jesse W. Clauson, Xiaojun Campbell, William O. Taylor, Graham A. Kaiser, Karl Milenkovic, Michael C. Rhodes, Tsering Dolma
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Publication number: 20210363923Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. A bleed tap taps air from the compressor section through a bleed valve. The bleed valve is selectively opened by a control to dump air from the compressor section to a dump outlet. A heat exchanger duct includes a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet. The dump outlet is within the heat exchanger duct.Type: ApplicationFiled: July 16, 2021Publication date: November 25, 2021Inventors: Steven H. Zysman, Karl D. Blume, James H. Anderson, Holly Teufel, Jesse W. Clauson, Xiaojun Campbell, William O. Taylor, Graham A. Kaiser, Karl Milenkovic, Michael C. Rhodes, Tsering Dolma
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Patent number: 11078837Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. A bleed tap taps air from the compressor section through a bleed valve. The bleed valve is selectively opened by a control to dump air from the compressor section to a dump outlet. A heat exchanger duct includes a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet. The dump outlet is within the heat exchanger duct.Type: GrantFiled: February 6, 2019Date of Patent: August 3, 2021Assignee: Raytheon Technologies CorporationInventors: Steven H. Zysman, Karl D. Blume, James H. Anderson, Holly Teufel, Jesse W. Clauson, Xiaojun Campbell, William O. Taylor, Graham A. Kaiser, Karl Milenkovic, Michael C. Rhodes, Tsering Dolma
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Patent number: 10815891Abstract: An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.Type: GrantFiled: September 27, 2013Date of Patent: October 27, 2020Assignee: Raytheon Technologies CorporationInventors: Chris J. Niggemeier, Karl D. Blume, John H. Mosley, Andreas Sadil
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Publication number: 20200248620Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. A bleed tap taps air from the compressor section through a bleed valve. The bleed valve is selectively opened by a control to dump air from the compressor section to a dump outlet. A heat exchanger duct includes a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet. The dump outlet is within the heat exchanger duct.Type: ApplicationFiled: February 6, 2019Publication date: August 6, 2020Inventors: Steven H. Zysman, Karl D. Blume, James H. Anderson, Holly Teufel, Jesse W. Clauson, Xiaojun Campbell, William O. Taylor, Graham A. Kaiser, Karl Milenkovic, Michael C. Rhodes, Tsering Dolma
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Publication number: 20200149475Abstract: A disclosed gas turbine engine includes a compressor section, a combustor section, a first turbine section and a second turbine section. An outer case structure for the gas turbine engine includes a single-piece case structure with a turbine case portion and a transition case portion. The transition case portion is integrally formed with the turbine case portion as a single part module. A combustor case houses the combustor and an aft turbine case supports the low pressure turbine. The outer case includes a forward end attachable to the combustor case and an aft end attachable to the aft turbine.Type: ApplicationFiled: October 8, 2019Publication date: May 14, 2020Inventors: Dale William Petty, Karl D. Blume, Joseph T. Caprario, Steven J. Bauer
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Patent number: 10161409Abstract: A disclosed fan drive gear system for a gas turbine engine includes a first fan shaft coupled to a second fan shaft, a first shaft support bearing assembly disposed about the first fan shaft and a second shaft support bearing assembly disposed about the second fan shaft. A planetary gear system is coupled to the second fan shaft. A transfer bearing is configured to receive lubricant from a lubricant input and is positioned between the first and second fan shaft support bearings. A second bearing is configured to rotate with the second fan shaft and receive lubricant from the transfer bearing and communicate lubricant to at least one lubricant passage and a conduit fluidly connecting the at least one lubricant passage to the planetary gear system.Type: GrantFiled: November 25, 2014Date of Patent: December 25, 2018Assignee: United Technologies CorporationInventors: William G. Sheridan, Karl D. Blume
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Publication number: 20170009915Abstract: An adapter and seal system is provided. The system may comprise a cylindrical body centered about an axis and a first thread disposed about an outer diameter of the cylindrical body. A protrusion on the cylindrical body may extend radially outward from the cylindrical body with a surface orthogonal to the axis partially defining the protrusion. A circular trench may be formed in the surface and may open in an axial direction towards the first thread. A metallic C-seal may be disposed in the circular trench.Type: ApplicationFiled: July 7, 2015Publication date: January 12, 2017Applicant: United Technologies CorporationInventors: Joseph N. Cerino, Christopher Hall, Karl D. Blume, James Schubauer, Kurt Link
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Publication number: 20160319830Abstract: A disclosed fan drive gear system for a gas turbine engine includes a first fan shaft coupled to a second fan shaft, a first shaft support bearing assembly disposed about the first fan shaft and a second shaft support bearing assembly disposed about the second fan shaft. A planetary gear system is coupled to the second fan shaft. A transfer bearing is configured to receive lubricant from a lubricant input and is positioned between the first and second fan shaft support bearings. A second bearing is configured to rotate with the second fan shaft and receive lubricant from the transfer bearing and communicate lubricant to at least one lubricant passage and a conduit fluidly connecting the at least one lubricant passage to the planetary gear system.Type: ApplicationFiled: November 25, 2014Publication date: November 3, 2016Inventors: William G. Sheridan, Karl D. Blume
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Patent number: 9291070Abstract: A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.Type: GrantFiled: December 2, 2011Date of Patent: March 22, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Bruce Fielding, Assaf Farah, Karl D. Blume, Lam Nguyen, Theodore W Kapustka
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Publication number: 20150252729Abstract: An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.Type: ApplicationFiled: September 27, 2013Publication date: September 10, 2015Inventors: Chris J. Niggemeier, Karl D. Blume, John H. Mosley, Andreas Sadil
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Publication number: 20150240662Abstract: A case for a gas turbine engine includes an integrated HPC Diffuser case operable to contain a combustor section and a portion of a High Pressure Compressor.Type: ApplicationFiled: September 30, 2013Publication date: August 27, 2015Inventors: Chris J. Niggemeier, Karl D. Blume
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Publication number: 20150226125Abstract: A disclosed gas turbine engine includes a compressor section, a combustor section, a first turbine section and a second turbine section. An outer case structure for the gas turbine engine includes a single-piece case structure with a turbine case portion and a transition case portion. The transition case portion is integrally formed with the turbine case portion as a single part module. A combustor case houses the combustor and an aft turbine case supports the low pressure turbine. The outer case includes a forward end attachable to the combustor case and an aft end attachable to the aft turbine.Type: ApplicationFiled: March 14, 2013Publication date: August 13, 2015Inventors: Dale William Petty, Karl D. Blume, Joseph T. Caprario, Steven J. Bauer
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Patent number: 8911203Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend aftward and outward from the engine case to the fan case. A forward frame comprises a plurality of vanes radially across the gaspath. A torque box couples the fan case vanes to the forward frame. A transmission couples a shaft to a fan shaft to drive the fan. A fan bearing assembly couples a stationary forward hub structure to the fan shaft.Type: GrantFiled: June 15, 2012Date of Patent: December 16, 2014Assignee: United Technologies CorporationInventors: Gregory E. Reinhardt, Karl D. Blume, John P. Tirone, III, John C. Ditomasso, Enzo DiBenedetto, Jason W. Mazanec
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Publication number: 20120251306Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend aftward and outward from the engine case to the fan case. A forward frame comprises a plurality of vanes radially across the gaspath. A torque box couples the fan case vanes to the forward frame. A transmission couples a shaft to a fan shaft to drive the fan. A fan bearing assembly couples a stationary forward hub structure to the fan shaft.Type: ApplicationFiled: June 15, 2012Publication date: October 4, 2012Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Gregory E. Reinhardt, Karl D. Blume, John P. Tirone, III, John C. Ditomasso, Enzo DiBenedetto, Jason W. Mazanec
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Publication number: 20120141294Abstract: A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.Type: ApplicationFiled: December 2, 2011Publication date: June 7, 2012Inventors: Bruce Fielding, Assaf Farah, Karl D. Blume, Lam Nguyen, Theodore W. Kapustka
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Patent number: 5471743Abstract: A method and apparatus which facilitate separation of a gas turbofan powerplant into modules for shipping, maintenance and repair is disclosed. Various construction details are developed which provide means for mounting a fan cowling to an engine core in a manner which permits transference of operational loads from the fan cowling to the engine core and separation of the fan cowling from the engine core. In one embodiment, a fan cowling (46) is attached to an engine core (18) by a plurality of radially extending through struts (64). The through struts include a bolted joint (72) which permits separation of a powerplant (12) into a first module and a second module. For this embodiment, a method for varying between an assembled and disassembled condition is comprised of manipulating the joints between an engaged and disengaged position and axially moving the separate modules along a longitudinal centerline (14).Type: GrantFiled: February 27, 1995Date of Patent: December 5, 1995Assignee: United Technologies CorporationInventors: Alan D. Munroe, Karl D. Blume, Robert E. Gurney
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Patent number: 5224341Abstract: A method and apparatus which facilitate separation of a gas turbofan powerplant into modules for shipping, maintenance and repair is disclosed. Various construction details are developed which provide means for mounting a fan cowling to an engine core in a manner which permits transference of operational loads from the fan cowling to the engine core and separation of the fan cowling from the engine core. In one embodiment, a fan cowling (46) is attached to an engine core (18) by a plurality of radially extending through struts (64). The through struts include a bolted joint (72) which permits separation of a powerplant (12) into a first module and a second module. For this embodiment, a method for varying between an assembled and disassembled condition is comprised of manipulating the joints between an engaged and disengaged position and axially moving the separate modules along a longitudinal centerline (14).Type: GrantFiled: January 6, 1992Date of Patent: July 6, 1993Assignee: United Technologies CorporationInventors: Alan D. Munroe, Karl D. Blume, Robert E. Gurney