Patents by Inventor Christopher W. Ross
Christopher W. Ross 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: 12037926Abstract: A rotor of a gas turbine having two adjacent rotor discs, on each of which moving blades are fastened, an annular rotor component being arranged between the rotor discs and having at its opposite ends circumferential annular grooves, in each of which a circumferential fastening projection on the respective rotor disc engages. When the rotor is stationary a first outer flank of the first annular groove rests under pressure against a first outer flank of the first fastening projection and there is play between a first inner flank of the first annular groove and a first inner flank of the first fastening projection.Type: GrantFiled: June 18, 2020Date of Patent: July 16, 2024Assignee: Siemens Energy Global GmbH & Co. KGInventors: Peter Kury, Mirko Milazar, Christopher W Ross, Yulia Bagaeva, Karsten Kolk, Ivan Lbov, Alexander Romanov, Harald Hoell, Kevin Kampka, Rene Mahnke, Andreas Andreas, Daniel Hofsommer, Ekkehard Maldfeld, Jörg Richter
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Publication number: 20240084708Abstract: A rotor of a gas turbine having two adjacent rotor discs, on each of which moving blades are fastened, an annular rotor component being arranged between the rotor discs and having at its opposite ends circumferential annular grooves, in each of which a circumferential fastening projection on the respective rotor disc engages. When the rotor is stationary a first outer flank of the first annular groove rests under pressure against a first outer flank of the first fastening projection and there is play between a first inner flank of the first annular groove and a first inner flank of the first fastening projection.Type: ApplicationFiled: June 18, 2020Publication date: March 14, 2024Applicant: Siemens Energy Global GmbH & Co. KGInventors: Peter Kury, Mirko Milazar, Christopher W Ross, Yulia Bagaeva, Karsten Kolk, Ivan Lbov, Alexander Romanov, Harald Hoell, Kevin Kampka, Rene Mahnke, Andreas Andreas, Daniel Hofsommer, Ekkehard Maldfeld, Jörg Richter
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Patent number: 11377956Abstract: A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to an aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from the blade root for cooling the turbine blade.Type: GrantFiled: July 23, 2018Date of Patent: July 5, 2022Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Peter Schröder, Christopher W. Ross, Santiago R. Salazar, Patrick M. Pilapil, Roger Matthews, Kevin Kampka, Joana Verheyen, Ching-Pang Lee, Javan Albright, James McCoy, Sin Chien Siw, Kok-Mun Tham
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Patent number: 11339662Abstract: A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.Type: GrantFiled: July 24, 2019Date of Patent: May 24, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventors: Peter Kury, Harald Hoell, Karsten Kolk, Vyacheslav Veitsman, Yulia Bagaeva, Christopher W Ross, Peter Schröder, Andrew Waddell
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Patent number: 11319823Abstract: A sealing element and a rotor of a gas turbine having at least one rotor disc and having an annular rotor component arranged adjacently to the rotor disc and having a plurality of sealing elements arranged distributed around the circumference. The sealing elements are fastened to the rotor disc at least in the axial direction. An inner edge portion of each of the sealing elements is adjacent to a sealing portion of the rotor component. In order to provide a seal between the sealing element and rotor component whilst at the same time enabling a relative axial displacement, a ring seal is arranged in a receiving space formed by the sealing element and rotor component.Type: GrantFiled: January 7, 2019Date of Patent: May 3, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventors: Peter Schroder, Karsten Kolk, Peter Kury, Dirk Springborn, Kevin Kampka, Christopher W. Ross, Yulia Bagaeva
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Publication number: 20210310359Abstract: A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.Type: ApplicationFiled: July 24, 2019Publication date: October 7, 2021Applicant: Siemens Energy Global GmbH & Co. KGInventors: Peter Kury, Harald Hoell, Karsten Kolk, Vyacheslav Veitsman, Yulia Bagaeva, Christopher W Ross, Peter Schröder, Andrew Waddell
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Publication number: 20210301664Abstract: A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from blade root for cooling the turbine blade.Type: ApplicationFiled: July 23, 2018Publication date: September 30, 2021Inventors: Peter Schröder, Christopher W. Ross, Santiago R. Salazar, Patrick M. Pilapil, Roger Matthews, Kevin Kampka, Joana Verheyen, Ching-Pang Lee, Javan Albright, James McCoy, Sin Chien Siw, Kok-Mun Tham
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Publication number: 20200392857Abstract: A sealing element and a rotor of a gas turbine having at least one rotor disc and having an annular rotor component arranged adjacently to the rotor disc and having a plurality of sealing elements arranged distributed around the circumference. The sealing elements are fastened to the rotor disc at least in the axial direction. An inner edge portion of each of the sealing elements is adjacent to a sealing portion of the rotor component. In order to provide a seal between the sealing element and rotor component whilst at the same time enabling a relative axial displacement, a ring seal is arranged in a receiving space formed by the sealing element and rotor component.Type: ApplicationFiled: January 7, 2019Publication date: December 17, 2020Applicant: Siemens AktiengesellschaftInventors: Peter Schroder, Karsten Kolk, Peter Kury, Dirk Springborn, Kevin Kampka, Christopher W. Ross, Yulia Bagaeva
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Patent number: 10012084Abstract: A sealing band arrangement for a gas turbine including first and second adjoining rotor disks separated by a gap wherein the first rotor disk includes an aperture. The sealing band arrangement includes at least one seal strip segment located within the gap, wherein the seal strip segment includes a first mating surface. The sealing band arrangement further includes a block having a locking section located within the aperture to stop circumferential movement of the seal strip segment relative to the first and second disks. A tapered pin element extends through the seal strip segment and the block. The tapered pin element is friction welded to both the seal strip segment and the block to attach the block to the first mating surface of the seal strip segment.Type: GrantFiled: September 9, 2014Date of Patent: July 3, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Sachin R. Shinde, Phillip W. Gravett, Santosh Narasimhachary, Christopher W. Ross
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Patent number: 9857242Abstract: A method for analyzing a three-dimensional stress concentrating feature of a component (60), such as a borehole (62), using a two-dimensional probabilistic technique. A circumferentially-dependent stress concentration profile around the stress concentrating feature is determined, and then a probability of failure of the component is calculated using a 2D probabilistic failure analysis of the stress concentration profile. The probabilistic failure analysis may include a Monte Carlo theta integration approach.Type: GrantFiled: June 25, 2014Date of Patent: January 2, 2018Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Kai Kadau, Christopher W. Ross, Chirag B. Patel, Christian Amann
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Patent number: 9771802Abstract: A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk A non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk A compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk.Type: GrantFiled: February 25, 2014Date of Patent: September 26, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Christopher W. Ross, Bulent Acar
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Patent number: 9291063Abstract: A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).Type: GrantFiled: February 29, 2012Date of Patent: March 22, 2016Assignee: SIEMENS ENERGY, INC.Inventors: David A. Little, Reinhard Schilp, Christopher W. Ross
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Publication number: 20160069202Abstract: A sealing band arrangement for a gas turbine including first and second adjoining rotor disks separated by a gap wherein the first rotor disk includes an aperture. The sealing band arrangement includes at least one seal strip segment located within the gap, wherein the seal strip segment includes a first mating surface. The sealing band arrangement further includes a block having a locking section located within the aperture to stop circumferential movement of the seal strip segment relative to the first and second disks. A tapered pin element extends through the seal strip segment and the block. The tapered pin element is friction welded to both the seal strip segment and the block to attach the block to the first mating surface of the seal strip segment.Type: ApplicationFiled: September 9, 2014Publication date: March 10, 2016Inventors: Sachin R. Shinde, Phillip W. Gravett, Santosh Narasimhachary, Christopher W. Ross
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Publication number: 20150377766Abstract: A method for analyzing a three-dimensional stress concentrating feature of a component (60), such as a borehole (62), using a two-dimensional probabilistic technique. A circumferentially-dependent stress concentration profile around the stress concentrating feature is determined, and then a probability of failure of the component is calculated using a 2D probabilistic failure analysis of the stress concentration profile. The probabilistic failure analysis may include a Monte Carlo theta integration approach.Type: ApplicationFiled: June 25, 2014Publication date: December 31, 2015Inventors: Kai Kadau, Christopher W. Ross, Chirag B. Patel, Christian Amann
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Publication number: 20150240644Abstract: A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces.Type: ApplicationFiled: February 25, 2014Publication date: August 27, 2015Applicant: Siemens Energy, Inc.Inventors: Christopher W. Ross, Bulent Acar
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Patent number: 8893512Abstract: A compressor bleed cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor to a turbine airfoil cooling system to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The compressor bleed cooling fluid feed system may enable cooling fluids to be exhausted from a compressor exhaust plenum through a downstream compressor bleed collection chamber and into the turbine airfoil cooling system. As such, the suction created in the compressor exhaust plenum mitigates boundary layer growth along the inner surface while providing flow of cooling fluids to the turbine airfoils.Type: GrantFiled: October 25, 2011Date of Patent: November 25, 2014Assignee: Siemens Energy, Inc.Inventors: Eric E. Donahoo, Christopher W. Ross
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Publication number: 20140230400Abstract: A gas turbine engine including a compressor section, a combustor section, and a turbine section operating to produce a power output during a first mode of operation. A heat retention and distribution system is provided to the engine wherein the heat retention system operates in a second mode of operation, following a shutdown of the engine, to maintain an elevated temperature in components of each of the compressor section, the combustor section and the turbine section in order to effect (1) a reduction in an effective cyclic life consumption of the components and extend a maintenance interval associated with the effective cyclic life consumption, and (2) clearances by maintaining a higher vane carrier temperature with time during a non-power producing mode and more uniform temperature of most stationary components in the circumferential orientation.Type: ApplicationFiled: February 15, 2013Publication date: August 21, 2014Inventors: KEVIN M. LIGHT, CHRISTOPHER W. ROSS
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Patent number: 8573932Abstract: The compressor blade root heating system may be formed from one or more induction heaters formed from one or more induction coils positioned in close proximity to a root of a compressor blade. In one embodiment, the induction heater may be coupled to a static casing component positioned immediately upstream of a first row of compressor blades on a rotor assembly such that the induction heater is stationary during turbine engine operation. The induction heater causes eddy current formation, which heats the row one compressor blades. This heating increases the fracture toughness of the material forming the rotor and compressor blades, thereby increasing the mechanical life cycle.Type: GrantFiled: August 9, 2010Date of Patent: November 5, 2013Assignee: Siemens Energy, Inc.Inventors: Christopher W. Ross, Keith A. Miller
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Publication number: 20130219853Abstract: A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).Type: ApplicationFiled: February 29, 2012Publication date: August 29, 2013Inventors: David A. Little, Reinhard Schilp, Christopher W. Ross
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Publication number: 20130098062Abstract: A compressor bleed cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor to a turbine airfoil cooling system to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The compressor bleed cooling fluid feed system may enable cooling fluids to be exhausted from a compressor exhaust plenum through a downstream compressor bleed collection chamber and into the turbine airfoil cooling system. As such, the suction created in the compressor exhaust plenum mitigates boundary layer growth along the inner surface while providing flow of cooling fluids to the turbine airfoils.Type: ApplicationFiled: October 25, 2011Publication date: April 25, 2013Inventors: ERIC E. DONAHOO, Christopher W. Ross