Patents by Inventor Mark Borja
Mark Borja 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: 10815818Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.Type: GrantFiled: July 18, 2017Date of Patent: October 27, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Tracy A. Propheter-Hinckley, Raymond Surace, Robert L. Hazzard, Mark Borja
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Publication number: 20200308976Abstract: A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.Type: ApplicationFiled: February 25, 2020Publication date: October 1, 2020Inventor: Mark Borja
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Patent number: 10612408Abstract: A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.Type: GrantFiled: May 6, 2015Date of Patent: April 7, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Mark Borja
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Patent number: 10544679Abstract: An example method of balancing a shaft includes inserting a balancing insert into one of a plurality of cavities. The plurality of cavities are radially inside an outermost surface of the shaft.Type: GrantFiled: January 9, 2015Date of Patent: January 28, 2020Assignee: United Technologies CorporationInventors: Jesus S. Lopez, Mark Borja
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Patent number: 10378363Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction. A serpentine cooling passage is provided between the pressure and suction side walls. A passageway adjoins a passage wall and is fluidly interconnected to an upstream turn that has radially spaced apart innermost and outermost contours. The innermost contour is provided at the wall. A resupply hole is configured to exit downstream from the innermost contour.Type: GrantFiled: April 10, 2017Date of Patent: August 13, 2019Assignee: United Technologies CorporationInventors: Christopher Whitfield, Carey Clum, Mark Borja
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Patent number: 10280782Abstract: A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors.Type: GrantFiled: February 26, 2013Date of Patent: May 7, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Michael G. McCaffrey, Igor S. Garcia, John R. Farris, Brian R. Pelletier, Thomas Almy, Brandon T. Rouse, Mark Borja
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Publication number: 20190024530Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.Type: ApplicationFiled: July 18, 2017Publication date: January 24, 2019Inventors: Tracy A. Propheter-Hinckley, Raymond Surace, Robert L. Hazzard, Mark Borja
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Publication number: 20180291748Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction. A serpentine cooling passage is provided between the pressure and suction side walls. A passageway adjoins a passage wall and is fluidly interconnected to an upstream turn that has radially spaced apart innermost and outermost contours. The innermost contour is provided at the wall. A resupply hole is configured to exit downstream from the innermost contour.Type: ApplicationFiled: April 10, 2017Publication date: October 11, 2018Inventors: Christopher Whitfield, Carey Clum, Mark Borja
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Patent number: 10053999Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.Type: GrantFiled: April 7, 2014Date of Patent: August 21, 2018Assignee: United Technologies CorporationInventors: Michael G. McCaffrey, Brandon T. Rouse, Mark Borja, Igor S. Garcia, John R. Farris, Thomas Almy, Brian R. Pelletier
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Patent number: 9976435Abstract: A rotating blade tip clearance system includes a control ring carrier defining a centerline axis. The control ring carrier has a connecting portion, a retaining portion radially inward of the connecting portion, and a flange connecting radially between the connecting portion and the retaining portion. The flange isolates the retaining portion of the control ring carrier from the thermal deflection of a case and assists in keeping the control ring carrier aligned about centerline axis A during thermal deflection. The retaining portion includes radially inner and outer diameter sides defining a retaining cavity therebetween. The system includes a control ring within the retaining cavity. The control ring has a different thermal response rate from the control ring carrier so that the control ring thermally deflects slower than the control ring carrier, thereby controlling the rate and/or extent of thermal deflection of the control ring carrier.Type: GrantFiled: October 15, 2015Date of Patent: May 22, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mark Borja, Paul W. Palmer
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Patent number: 9957830Abstract: A control ring extends circumferentially about a central axis. A plurality of circumferentially spaced carrier portions have a cavity receiving the control ring. There are circumferential gaps between the carrier portions. A blade outer air seal is mounted on the carrier portions radially inwardly of the control ring. The control ring maintains the carrier portions at a radially outwardly expanded position when heated by an electric heater.Type: GrantFiled: March 5, 2014Date of Patent: May 1, 2018Assignee: United Technologies CorporationInventors: Michael G. McCaffrey, Mark Borja, Brandon T. Rouse, John R. Farris, Brian R. Pelletier, Thomas Almy, Igor S. Garcia
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Patent number: 9677407Abstract: A cover plate for a rotor disk in a gas turbine machine includes a cylindrical body having multiple outward facing snaps and multiple inward facing snaps.Type: GrantFiled: January 9, 2013Date of Patent: June 13, 2017Assignee: United Technologies CorporationInventors: Mark Borja, Ehren B. Holt
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Publication number: 20160326876Abstract: An example method of balancing a shaft includes inserting a balancing insert into one of a plurality of cavities. The plurality of cavities are radially inside an outermost surface of the shaft.Type: ApplicationFiled: January 9, 2015Publication date: November 10, 2016Inventors: Jesus S. Lopez, Mark Borja
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Publication number: 20160326900Abstract: A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.Type: ApplicationFiled: May 6, 2015Publication date: November 10, 2016Inventor: Mark Borja
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Patent number: 9447696Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion.Type: GrantFiled: December 27, 2012Date of Patent: September 20, 2016Assignee: United Technologies CorporationInventors: Michael G. McCaffrey, Brandon T. Rouse, Thomas Almy, Igor S. Garcia, John R. Farris, Mark Borja
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Publication number: 20160177768Abstract: A rotating blade tip clearance system includes a control ring carrier defining a centerline axis. The control ring carrier has a connecting portion, a retaining portion radially inward of the connecting portion, and a flange connecting radially between the connecting portion and the retaining portion. The flange isolates the retaining portion of the control ring carrier from the thermal deflection of a case and assists in keeping the control ring carrier aligned about centerline axis A during thermal deflection. The retaining portion includes radially inner and outer diameter sides defining a retaining cavity therebetween. The system includes a control ring within the retaining cavity. The control ring has a different thermal response rate from the control ring carrier so that the control ring thermally deflects slower than the control ring carrier, thereby controlling the rate and/or extent of thermal deflection of the control ring carrier.Type: ApplicationFiled: October 15, 2015Publication date: June 23, 2016Inventors: Mark Borja, Paul W. Palmer
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Publication number: 20160053624Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.Type: ApplicationFiled: April 7, 2014Publication date: February 25, 2016Inventors: Michael G. McCaffrey, Brandon T. Rouse, Mark Borja, Igor S. Garcia, John R. Farris, Thomas Almy, Brian R. Pelletier
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Publication number: 20150369076Abstract: A control ring extends circumferentially about a central axis. A plurality of circumferentially spaced carrier portions have a cavity receiving the control ring. There are circumferential gaps between the carrier portions. A blade outer air seal is mounted on the carrier portions radially inwardly of the control ring. The control ring maintains the carrier portions at a radially outwardly expanded position when heated by an electric heater.Type: ApplicationFiled: March 5, 2014Publication date: December 24, 2015Inventors: Michael G. McCaffrey, Mark Borja, Brandon T. Rouse, John R. Farris, Brian R. Pelletier, Thomas Almy, Igor S. Garcia
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Publication number: 20150337673Abstract: A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors.Type: ApplicationFiled: February 26, 2013Publication date: November 26, 2015Inventors: Michael G. McCaffrey, Igor Garcia, John R. Farris, Brian R. Pelletier, Thomas Almy, Brandon T. Rouse, Mark Borja
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Patent number: 9097122Abstract: A turbine engine system includes a turbine engine shaft, a first rotor, a second rotor and an engine monitoring system. The shaft includes a shaft bore formed by a shaft wall. The shaft bore extends along an axial centerline through the shaft between a first shaft end and a second shaft end. The first rotor is connected to the shaft at the first shaft end, and the second rotor is connected to the shaft at the second shaft end. The engine monitoring system includes a sensor connected to the second rotor, a transmitter arranged at the first shaft end, and a plurality of conduit assemblies. Each conduit assembly includes a conduit that extends axially within the shaft bore and is connected to the shaft wall. A first of the conduit assemblies also includes a wire that extends through a respective conduit and connects the sensor and the transmitter.Type: GrantFiled: January 30, 2012Date of Patent: August 4, 2015Assignee: United Technologies CorporationInventor: Mark Borja