Patents by Inventor Brandon M. Rapp
Brandon M. Rapp 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: 10641109Abstract: A gas turbine engine rotor assembly includes a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. Adjacent platforms are separated from each other by a gap. A damper is positioned at an offset position within the gap to contact the inner surfaces of the adjacent platforms.Type: GrantFiled: March 11, 2014Date of Patent: May 5, 2020Assignee: United Technologies CorporationInventors: Brandon M. Rapp, Matthew Andrew Hough
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Patent number: 10227875Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.Type: GrantFiled: February 7, 2014Date of Patent: March 12, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Scott D. Lewis, Brandon M. Rapp, Jeffrey S. Beattie, Matthew Andrew Hough, Bret M. Teller, Jeffrey Michael Jacques, Max Asterlin
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Patent number: 10180067Abstract: A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.Type: GrantFiled: May 31, 2012Date of Patent: January 15, 2019Assignee: United Technologies CorporationInventors: Jeffrey S. Beattie, Scott D. Lewis, Mark F. Zelesky, Ricardo Trindade, Bret M. Teller, Jeffrey Michael Jacques, Brandon M. Rapp
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Patent number: 10060262Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.Type: GrantFiled: May 28, 2014Date of Patent: August 28, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Robert Knowlton, Max Asterlin, Brandon M. Rapp, Parth Jariwala
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Patent number: 10036260Abstract: A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.Type: GrantFiled: March 7, 2014Date of Patent: July 31, 2018Assignee: United Technologies CorporationInventors: Brandon M. Rapp, Matthew Andrew Hough
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Patent number: 10012085Abstract: A gas turbine engine rotor assembly has a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall.Type: GrantFiled: March 10, 2014Date of Patent: July 3, 2018Assignee: United Technologies CorporationInventors: Matthew Andrew Hough, Brandon M. Rapp
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Publication number: 20160102557Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.Type: ApplicationFiled: May 28, 2014Publication date: April 14, 2016Inventors: Robert Knowlton, Max Asterlin, Brandon M. Rapp, Parth Jariwala
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Patent number: 9243500Abstract: A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.Type: GrantFiled: June 29, 2012Date of Patent: January 26, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mark F. Zelesky, Ricardo Trindade, Bret M. Teller, Scott D. Lewis, Jeffrey S. Beattie, Jeffrey Michael Jacques, Brandon M. Rapp
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Publication number: 20150377032Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.Type: ApplicationFiled: February 7, 2014Publication date: December 31, 2015Inventors: Scott D. LEWIS, Brandon M. RAPP, Jeffrey S. BEATTIE, Matthew Andrew HOUGH, Bret M. TELLER, Jeffrey Michael JACQUES, Max ASTERLIN
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Publication number: 20150369048Abstract: A gas turbine engine rotor assembly has a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall.Type: ApplicationFiled: March 10, 2014Publication date: December 24, 2015Inventors: Matthew Andrew HOUGH, Brandon M. RAPP
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Publication number: 20150369057Abstract: A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.Type: ApplicationFiled: March 7, 2014Publication date: December 24, 2015Inventors: Brandon M. Rapp, Matthew Andrew Hough
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Publication number: 20150125304Abstract: A gas turbine engine rotor assembly includes a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. Adjacent platforms are separated from each other by a gap. A damper is positioned at an offset position within the gap to contact the inner surfaces of the adjacent platforms.Type: ApplicationFiled: March 11, 2014Publication date: May 7, 2015Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Brandon M. Rapp, Matthew Andrew Hough
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Publication number: 20140321961Abstract: A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.Type: ApplicationFiled: May 31, 2012Publication date: October 30, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey S. Beattie, Scott D. Lewis, Mark F. Zelesky, Ricardo Trindade, Bret M. Teller, Jeffrey Michael Jacques, Brandon M. Rapp
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Publication number: 20140000282Abstract: A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.Type: ApplicationFiled: June 29, 2012Publication date: January 2, 2014Inventors: Mark F. Zelesky, Ricardo Trindade, Bret M. Teller, Scott D. Lewis, Jeffrey S. Beattie, Jeffrey Michael Jacques, Brandon M. Rapp