Patents by Inventor Leslie John Faulder
Leslie John Faulder 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: 9677423Abstract: An aft hub sealing assembly for a gas turbine engine is disclosed. The aft hub sealing assembly includes an aft hub, a bearing cap, an aft baffle, a first seal, and a second seal. The aft hub includes a body portion and a disk portion aft surface. The bearing cap includes a bearing cap inner portion spaced apart from the body portion. The aft baffle is located adjacent the disk portion. The aft baffle includes a baffle forward surface following a contour of the disk portion aft surface. The first seal is between the bearing cap inner portion and the body portion. The second seal is between the bearing cap inner portion and the body portion.Type: GrantFiled: June 20, 2014Date of Patent: June 13, 2017Assignee: Solar Turbines IncorporatedInventor: Leslie John Faulder
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Patent number: 9650901Abstract: A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper includes a width dimension, a height dimension, and a length dimension and a forward plate. The damper further includes an aft plate that is larger than the forward plate along the width and height dimension and having a lower portion including two legs extending in the height dimension. The damper also includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate.Type: GrantFiled: May 31, 2012Date of Patent: May 16, 2017Assignee: Solar Turbines IncorporatedInventors: Qingxuan Michael Zhang, Theresa A. Brown, Leslie John Faulder
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Patent number: 9476324Abstract: An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel. The side panel includes a circumferential portion, a first contoured portion, and a second contoured portion. The circumferential portion extends about the exhaust collector axis with a constant radius. The first contoured portion and the second contoured portion are each between the circumferential portion and the exhaust outlet and include a plurality of curved sections with alternating concavity. Each of the plurality of curved sections extends from the front panel to the rear panel.Type: GrantFiled: September 19, 2013Date of Patent: October 25, 2016Assignee: Solar Turbines IncorporatedInventors: Kevin Kiyoto Hirako, Brian Alan Fox, Leslie John Faulder
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Patent number: 9353629Abstract: A turbine blade is disclosed. The turbine blade may include a platform, an airfoil extending from one side of the platform, and a neck extending from another side of the platform, wherein the neck includes a forward buttress and an aft buttress. The turbine blade may further include a root extending from the neck, a pocket defined by a plurality of walls and located between the forward buttress and the aft buttress, and a variable radius fillet. The variable radius fillet may be disposed within the pocket and extend between the forward buttress and the aft buttress, wherein a radius of the variable radius fillet increases from the forward buttress to the aft buttress.Type: GrantFiled: November 30, 2012Date of Patent: May 31, 2016Assignee: Solar Turbines IncorporatedInventor: Leslie John Faulder
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Patent number: 9347325Abstract: A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate with a forward face and an aft face, and an aft plate with a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be greater than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a pocket on the forward face of the forward plate.Type: GrantFiled: October 31, 2012Date of Patent: May 24, 2016Assignee: Solar Turbines IncorporatedInventors: Leslie John Faulder, Jeffrey Eugene Tarczy
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Patent number: 9303519Abstract: A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate including a forward face and an aft face, and an aft plate including a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be larger than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a nub projecting from a lower portion of the aft face of the aft plate.Type: GrantFiled: October 31, 2012Date of Patent: April 5, 2016Assignee: Solar Turbines IncorporatedInventors: Jeffrey Eugene Tarczy, Leslie John Faulder
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Patent number: 9297263Abstract: A turbine blade for a gas turbine engine may include a platform, an airfoil extending above the platform, and a root structure extending below the platform. The root structure may extend from a forward face to an aft face and include a shank region proximate the platform and a lower portion distal to the platform. The forward face of the shank region may project outward from the forward face of the lower portion.Type: GrantFiled: October 31, 2012Date of Patent: March 29, 2016Assignee: Solar Turbines IncorporatedInventors: Jeffrey Eugene Tarczy, Leslie John Faulder
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Patent number: 9228443Abstract: A turbine rotor assembly may include a turbine rotor with a plurality of turbine blade slots and a plurality of turbine blades. A root structure of each turbine blade may include a portion shaped to be received in a corresponding turbine blade slot of the rotor. The rotor assembly may also include a seal plate attached to the forward end of the rotor. The seal plate may extend upwards from a first end below the inner end of the blade slots to a second end located between an outermost lobe of the blade slots and the outer rim of the rotor.Type: GrantFiled: October 31, 2012Date of Patent: January 5, 2016Assignee: Solar Turbines IncorporatedInventors: Jeffrey Eugene Tarczy, Leslie John Faulder
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Publication number: 20150369074Abstract: An aft hub sealing assembly for a gas turbine engine is disclosed. The aft hub sealing assembly includes an aft hub, a bearing cap, an aft baffle, a first seal, and a second seal. The aft hub includes a body portion and a disk portion aft surface. The bearing cap includes a bearing cap inner portion spaced apart from the body portion. The aft baffle is located adjacent the disk portion. The aft baffle includes a baffle forward surface following a contour of the disk portion aft surface. The first seal is between the bearing cap inner portion and the body portion. The second seal is between the bearing cap inner portion and the body portion.Type: ApplicationFiled: June 20, 2014Publication date: December 24, 2015Inventor: Leslie John Faulder
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Patent number: 9140132Abstract: A turbine blade is disclosed. The turbine blade includes a platform, an airfoil extending from one side of the platform, a root extending radially from another side of the platform, and a pocket located beneath the platform. The pocket is defined by a plurality of walls, and a pad is disposed in a corner of the pocket. The pad includes three pad corners and three sides connecting the three pad corners, wherein each side extends along a different one of the plurality of walls.Type: GrantFiled: May 31, 2012Date of Patent: September 22, 2015Assignee: Solar Turbines IncorporatedInventors: Leslie John Faulder, Olivier Jacques Lamicq
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Publication number: 20150075131Abstract: An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel. The side panel includes a circumferential portion, a first contoured portion, and a second contoured portion. The circumferential portion extends about the exhaust collector axis with a constant radius. The first contoured portion and the second contoured portion are each between the circumferential portion and the exhaust outlet and include a plurality of curved sections with alternating concavity. Each of the plurality of curved sections extends from the front panel to the rear panel.Type: ApplicationFiled: September 19, 2013Publication date: March 19, 2015Applicant: SOLAR TURBINES INCORPORATEDInventors: Kevin Kiyoto Hirako, Brian Alan Fox, Leslie John Faulder
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Publication number: 20140119916Abstract: A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate with a forward face and an aft face, and an aft plate with a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be greater than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a pocket on the forward face of the forward plate.Type: ApplicationFiled: October 31, 2012Publication date: May 1, 2014Applicant: Solar Turbines IncorporatedInventors: Leslie John FAULDER, Jeffrey Eugene Tarczy
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Publication number: 20140119943Abstract: A turbine rotor assembly may include a turbine rotor with a plurality of turbine blade slots and a plurality of turbine blades. A root structure of each turbine blade may include a portion shaped to be received in a corresponding turbine blade slot of the rotor. The rotor assembly may also include a seal plate attached to the forward end of the rotor. The seal plate may extend upwards from a first end below the inner end of the blade slots to a second end located between an outermost lobe of the blade slots and the outer rim of the rotor.Type: ApplicationFiled: October 31, 2012Publication date: May 1, 2014Applicant: Solar Turbines IncorporatedInventors: Jeffrey Eugene Tarczy, Leslie John Faulder
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Publication number: 20140119918Abstract: A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate including a forward face and an aft face, and an aft plate including a forward face and an aft face. The aft face of the forward plate may he connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be larger than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a nub projecting from a lower portion of the aft face of the aft plate.Type: ApplicationFiled: October 31, 2012Publication date: May 1, 2014Applicant: Solar Turbines IncorporatedInventors: Jeffrey Eugene TARCZY, Leslie John FAULDER
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Publication number: 20130323031Abstract: A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper includes a width dimension, a height dimension, and a length dimension and a forward plate. The damper further includes an aft plate that is larger than the forward plate along the width and height dimension and having a lower portion including two legs extending in the height dimension. The damper also includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate.Type: ApplicationFiled: May 31, 2012Publication date: December 5, 2013Inventors: Qingxuan Michael Zhang, Theresa A. Brown, Leslie John Faulder
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Publication number: 20130319008Abstract: A turbine blade is disclosed. The turbine blade includes a platform, an airfoil extending from one side of the platform, a root extending radially from another side of the platform, and a pocket located beneath the platform. The pocket is defined by a plurality of walls, and a pad is disposed in a corner of the pocket. The pad includes three pad corners and three sides connecting the three pad corners, wherein each side extends along a different one of the plurality of walls.Type: ApplicationFiled: May 31, 2012Publication date: December 5, 2013Inventors: Leslie John Faulder, Olivier Jacques Lamicq
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Patent number: 8522528Abstract: In one aspect, the present disclosure is directed an apparatus configured to diffuse a flow of bleed air. The apparatus having an inlet collar configured to receive the flow of bleed air in a direction substantially along a longitudinal axis of the apparatus. The apparatus further having an end wall longitudinally spaced apart from the inlet collar and configured to block the flow of bleed air in a direction substantially along the longitudinal axis. The apparatus also having a first diffuser wall spaced concentrically relative to a second diffuser wall, each of the first and second diffuser walls positioned between the inlet collar and the end wall and including a plurality of perforations configured to permit the flow of bleed air to exit the apparatus at an angle relative to the longitudinal axis.Type: GrantFiled: June 30, 2008Date of Patent: September 3, 2013Assignee: Solar Turbines Inc.Inventors: Leslie John Faulder, Philip H. Schneider, Vin-King Yang, John Richard Wiltshire, Jeffrey Eugene Tarczy, Neil Pryke
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Publication number: 20090320496Abstract: In one aspect, the present disclosure is directed an apparatus configured to diffuse a flow of bleed air. The apparatus having an inlet collar configured to receive the flow of bleed air in a direction substantially along a longitudinal axis of the apparatus. The apparatus further having an end wall longitudinally spaced apart from the inlet collar and configured to block the flow of bleed air in a direction substantially along the longitudinal axis. The apparatus also having a first diffuser wall spaced concentrically relative to a second diffuser wall, each of the first and second diffuser walls positioned between the inlet collar and the end wall and including a plurality of perforations configured to permit the flow of bleed air to exit the apparatus at an angle relative to the longitudinal axis.Type: ApplicationFiled: June 30, 2008Publication date: December 31, 2009Inventors: Leslie John Faulder, Philip H. Schneider, Vin-King Yang, John Richard Wiltshire, Jeffrey Eugene Tarczy, Neil Pryke