Patents by Inventor Christopher Edward Wolfe
Christopher Edward Wolfe 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: 11680645Abstract: A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.Type: GrantFiled: December 21, 2020Date of Patent: June 20, 2023Assignee: General Electric CompanyInventors: Rahul Anil Bidkar, Christopher Edward Wolfe, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Deepak Trivedi, Quang Tue Nguyen Tran
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Publication number: 20230106380Abstract: A rotary machine seal assembly (200) includes seal segments (102) configured to circumferentially extend around a rotor (108) between a stator (106) and the rotor (108) of a rotary machine. One or more seal segments include a shoe plate (110, 410, 710, 910), a seal base (112, 412, 712, 912), and at least one intermediate member (114, 414, 714). The shoe plate is disposed along the rotor. The seal base is disposed radially outward of the shoe plate. At least one intermediate member is coupled to and disposed between the seal base and the shoe plate. The at least one intermediate member includes an actuator portion (302, 402, 702, 902) having first coefficient of thermal expansion and a constrictor portion (304, 404, 704, 904) having a different, second coefficient of thermal expansion.Type: ApplicationFiled: March 30, 2020Publication date: April 6, 2023Inventors: Rahul Anil Bidkar, Deepak Trivedi, Christopher Edward Wolfe, Darren Lee Hallman, Kristopher Frutschy, Mark Bowen
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Patent number: 11591965Abstract: A thermal management system for transferring heat between fluids includes a thermal transport bus through which a heat exchange fluid flows. Additionally, the system includes a heat source heat exchanger arranged along the bus such that heat is added to the fluid flowing through the heat source heat exchanger. Moreover, the system includes a plurality of heat sink heat exchangers arranged along the bus such that heat is removed from the fluid flowing through the plurality of heat sink heat exchangers. Furthermore, the system includes a bypass conduit fluidly coupled to the bus such that the bypass conduit allows the fluid to bypass one of the heat source heat exchanger or one of the heat sink heat exchangers. In addition, the system includes a valve configured to control a flow of the fluid through the bypass conduit based on a pressure of the fluid within the bus.Type: GrantFiled: March 29, 2021Date of Patent: February 28, 2023Assignee: General Electric CompanyInventors: Christopher Edward Wolfe, Hendrik Pieter Jacobus de Bock, William Dwight Gerstler, Brian Gene Brzek, Brandon Wayne Miller, Daniel Alan Niergarth, Kevin Robert Feldmann, Kevin Edward Hinderliter
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Publication number: 20220307419Abstract: A thermal management system for transferring heat between fluids includes a thermal transport bus through which a heat exchange fluid flows. Additionally, the system includes a heat source heat exchanger arranged along the bus such that heat is added to the fluid flowing through the heat source heat exchanger. Moreover, the system includes a plurality of heat sink heat exchangers arranged along the bus such that heat is removed from the fluid flowing through the plurality of heat sink heat exchangers. Furthermore, the system includes a bypass conduit fluidly coupled to the bus such that the bypass conduit allows the fluid to bypass one of the heat source heat exchanger or one of the heat sink heat exchangers. In addition, the system includes a valve configured to control a flow of the fluid through the bypass conduit based on a pressure of the fluid within the bus.Type: ApplicationFiled: March 29, 2021Publication date: September 29, 2022Inventors: Christopher Edward Wolfe, Hendrik Pieter Jacobus de Bock, William Dwight Gerstler, Brian Gene Brzek, Brandon Wayne Miller, Daniel Alan Niergarth, Kevin Robert Feldmann, Kevin Edward Hinderliter
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Publication number: 20220128236Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.Type: ApplicationFiled: January 6, 2022Publication date: April 28, 2022Inventors: Jinjie Shi, Robert Proctor, Jason Paul Hoppa, Stephen Gerard Schadewald, Christopher Edward Wolfe, Kirk Douglas Gallier
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Patent number: 11221140Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.Type: GrantFiled: June 19, 2020Date of Patent: January 11, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Jinjie Shi, Stephen Gerard Schadewald, Jason Paul Hoppa, Kirk Douglas Gallier, Christopher Edward Wolfe, Robert Proctor
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Patent number: 10989058Abstract: The subject matter described herein relate to a segmented piston seal system. The segmented piston seal includes a first semi-circular section (FSCS) that includes a first locking structure at opposite ends of the FSCS. The segmented piston seal includes a second semi-circular section (SSCS) that includes a second locking structure at opposite ends of the SSCS. The first and second locking structures are configured to lock the FSCS and the SSCS together to form a piston seal.Type: GrantFiled: April 19, 2018Date of Patent: April 27, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Deepak Trivedi, Rahul Anil Bidkar, Xiaoqing Zheng, Christopher Edward Wolfe
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Publication number: 20210108730Abstract: A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.Type: ApplicationFiled: December 21, 2020Publication date: April 15, 2021Inventors: Rahul Anil Bidkar, Christopher Edward Wolfe, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Deepak Trivedi, Quang Tue Nguyen Tran
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Patent number: 10934873Abstract: A turbine shroud is disposed between stages of stationary turbine nozzles. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface and opposite ends. Each end includes an end face, an end cutback face spaced from the end face, and an intermediate surface extending between the end face and the end cutback face to define a recess. One or more seals overlap the recess of a circumferentially adjacent pair of shroud segments to produce a sealed joint.Type: GrantFiled: November 7, 2018Date of Patent: March 2, 2021Assignee: General Electric CompanyInventors: Neelesh Nandkumar Sarawate, Christopher Edward Wolfe, John Patrick Pollinger
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Patent number: 10900570Abstract: A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.Type: GrantFiled: November 27, 2018Date of Patent: January 26, 2021Assignee: General Electric CompanyInventors: Rahul Anil Bidkar, Christopher Edward Wolfe, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Deepak Trivedi, Quang Tue Nguyen Tran
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Patent number: 10895324Abstract: A seal assembly for a rotary machine includes a seal bearing face that opposes a rotating component of the machine and a slide device coupled with the seal bearing face. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing includes feed ports. The feed ports extend through the seal bearing face to form aerostatic portions of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component has a non-planar surface that, during rotating motion of the rotating component relative to the face of the seal bearing face, forms aerodynamic portions of the film bearing.Type: GrantFiled: November 27, 2018Date of Patent: January 19, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Quang Tue Nguyen Tran, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Christopher Edward Wolfe, Steven Douglas Johnson, Antonio Guijarro Valencia
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Patent number: 10823596Abstract: An ultrasonic flow meter system includes a conduit defining a channel, at least one pair of first transducers, at least one second transducer, and a processor. The pair of first transducers is mounted on the conduit and includes a transmitting transducer and a receiving transducer for generating a first responsive signal. The transmitting transducer and the receiving transducer are arranged on a chordal path. The second transducer is mounted on the conduit for generating a second responsive signal. The processor is configured to receive the first responsive signal and the second responsive signal, select one responsive signal according to a relationship of the first responsive signal and noise thereof and a relationship of the second responsive signal and noise thereof, and determine a flow rate of a flow medium according to the selected responsive signal. A method for measuring the flow rate of the fluid medium is also provided.Type: GrantFiled: December 4, 2015Date of Patent: November 3, 2020Assignee: Baker Hughes Oilfield Operations LLCInventors: Jing Ye, Yan Mei, Xiaolei Ao, Weihua Shang, Ran Niu, Gregory Ronald Gillette, Christopher Edward Wolfe, Robert Arnold Judge
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Publication number: 20200318831Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.Type: ApplicationFiled: June 19, 2020Publication date: October 8, 2020Inventors: Jinjie Shi, Stephen Gerard Schadewald, Jason Paul Hoppa, Kirk Douglas Gallier, Christopher Edward Wolfe, Robert Proctor
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Patent number: 10788130Abstract: A seal assembly that includes a rotatable seal component, a non-rotatable seal component, and a plurality of pairs of flexures. The non-rotatable seal component is disposed facing the rotatable seal component. The plurality of pairs of flexures is spaced apart from each other along a circumferential direction of the seal assembly. Each pair of the plurality of pairs of flexures has a center line and includes a first flexure and a second flexure disposed in a stressed condition such that a portion of the first flexure and a portion of the second flexure are in contact with each other. Further, the first end of the first flexure is inclined at a first angle relative to the center line and a first end of the second flexure is inclined at a second angle relative to the center line. Also, first end of the first flexure and a first end of the second flexure are coupled to each other and to the non-rotatable seal component.Type: GrantFiled: January 8, 2020Date of Patent: September 29, 2020Assignee: General Electric CompanyInventors: Deepak Trivedi, Christopher Edward Wolfe, Nathan EvanMcCurdy Gibson, Brian Joseph Prenger
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Patent number: 10738644Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.Type: GrantFiled: August 30, 2017Date of Patent: August 11, 2020Assignee: General Electric CompanyInventors: Jinjie Shi, Dennis Paul Dry, Christopher Edward Wolfe, Andres Jose Garcia-Crespo, Yun Zhu
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Publication number: 20200166143Abstract: A seal assembly for a rotary machine includes a seal bearing face that opposes a rotating component of the machine and a slide device coupled with the seal bearing face. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing includes feed ports. The feed ports extend through the seal bearing face to form aerostatic portions of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component has a non-planar surface that, during rotating motion of the rotating component relative to the face of the seal bearing face, forms aerodynamic portions of the film bearing.Type: ApplicationFiled: November 27, 2018Publication date: May 28, 2020Inventors: Quang Tue Nguyen Tran, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Christopher Edward Wolfe, Steven Douglas Johnson, Antonio Guijarro Valencia
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Publication number: 20200166142Abstract: A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.Type: ApplicationFiled: November 27, 2018Publication date: May 28, 2020Inventors: Rahul Anil Bidkar, Christopher Edward Wolfe, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Deepak Trivedi, Quang Tue Nguyen Tran
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Patent number: 10655489Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.Type: GrantFiled: January 4, 2018Date of Patent: May 19, 2020Assignee: General Electric CompanyInventors: Neelesh Nandkumar Sarawate, Christopher Edward Wolfe, Victor John Morgan, Jason Ray Gregg
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Publication number: 20200149638Abstract: A seal assembly that includes a rotatable seal component, a non-rotatable seal component, and a plurality of pairs of flexures. The non-rotatable seal component is disposed facing the rotatable seal component. The plurality of pairs of flexures is spaced apart from each other along a circumferential direction of the seal assembly. Each pair of the plurality of pairs of flexures has a center line and includes a first flexure and a second flexure disposed in a stressed condition such that a portion of the first flexure and a portion of the second flexure are in contact with each other. Further, the first end of the first flexure is inclined at a first angle relative to the center line and a first end of the second flexure is inclined at a second angle relative to the center line. Also, first end of the first flexure and a first end of the second flexure are coupled to each other and to the non-rotatable seal component.Type: ApplicationFiled: January 8, 2020Publication date: May 14, 2020Inventors: Deepak Trivedi, Christopher Edward Wolfe, Nathan EvanMcCurdy Gibson, Brian Joseph Prenger
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Publication number: 20200141276Abstract: A turbine shroud is disposed about a row of rotating turbine blades. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface, a first end, and a second end. The first end includes a first end face, a first end cutback face spaced from the first end face, and an intermediate surface extending between the first end face and the end cutback face to define a recess. The second end includes a second end face, a second end cutback face spaced from the second end face, and a projecting surface extending between the second end face and the second end cutback face. The projecting surface of each shroud segment overlaps the recess of a circumferentially adjacent shroud segment to produce a sealed joint.Type: ApplicationFiled: November 7, 2018Publication date: May 7, 2020Applicant: General Electric CompanyInventors: Christopher Edward Wolfe, Neelesh Nandkumar Sarawate