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).

  • Patent number: 11680645
    Abstract: 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: Grant
    Filed: December 21, 2020
    Date of Patent: June 20, 2023
    Assignee: General Electric Company
    Inventors: Rahul Anil Bidkar, Christopher Edward Wolfe, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Deepak Trivedi, Quang Tue Nguyen Tran
  • Publication number: 20230106380
    Abstract: 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: Application
    Filed: March 30, 2020
    Publication date: April 6, 2023
    Inventors: Rahul Anil Bidkar, Deepak Trivedi, Christopher Edward Wolfe, Darren Lee Hallman, Kristopher Frutschy, Mark Bowen
  • Patent number: 11591965
    Abstract: 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: Grant
    Filed: March 29, 2021
    Date of Patent: February 28, 2023
    Assignee: General Electric Company
    Inventors: 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
  • Publication number: 20220307419
    Abstract: 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: Application
    Filed: March 29, 2021
    Publication date: September 29, 2022
    Inventors: 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
  • Publication number: 20220128236
    Abstract: 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: Application
    Filed: January 6, 2022
    Publication date: April 28, 2022
    Inventors: Jinjie Shi, Robert Proctor, Jason Paul Hoppa, Stephen Gerard Schadewald, Christopher Edward Wolfe, Kirk Douglas Gallier
  • Patent number: 11221140
    Abstract: 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: Grant
    Filed: June 19, 2020
    Date of Patent: January 11, 2022
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jinjie Shi, Stephen Gerard Schadewald, Jason Paul Hoppa, Kirk Douglas Gallier, Christopher Edward Wolfe, Robert Proctor
  • Patent number: 10989058
    Abstract: 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: Grant
    Filed: April 19, 2018
    Date of Patent: April 27, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Deepak Trivedi, Rahul Anil Bidkar, Xiaoqing Zheng, Christopher Edward Wolfe
  • Publication number: 20210108730
    Abstract: 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: Application
    Filed: December 21, 2020
    Publication date: April 15, 2021
    Inventors: Rahul Anil Bidkar, Christopher Edward Wolfe, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Deepak Trivedi, Quang Tue Nguyen Tran
  • Patent number: 10934873
    Abstract: 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: Grant
    Filed: November 7, 2018
    Date of Patent: March 2, 2021
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Christopher Edward Wolfe, John Patrick Pollinger
  • Patent number: 10900570
    Abstract: 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: Grant
    Filed: November 27, 2018
    Date of Patent: January 26, 2021
    Assignee: General Electric Company
    Inventors: Rahul Anil Bidkar, Christopher Edward Wolfe, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Deepak Trivedi, Quang Tue Nguyen Tran
  • Patent number: 10895324
    Abstract: 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: Grant
    Filed: November 27, 2018
    Date of Patent: January 19, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Quang Tue Nguyen Tran, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Christopher Edward Wolfe, Steven Douglas Johnson, Antonio Guijarro Valencia
  • Patent number: 10823596
    Abstract: 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: Grant
    Filed: December 4, 2015
    Date of Patent: November 3, 2020
    Assignee: Baker Hughes Oilfield Operations LLC
    Inventors: Jing Ye, Yan Mei, Xiaolei Ao, Weihua Shang, Ran Niu, Gregory Ronald Gillette, Christopher Edward Wolfe, Robert Arnold Judge
  • Publication number: 20200318831
    Abstract: 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: Application
    Filed: June 19, 2020
    Publication date: October 8, 2020
    Inventors: Jinjie Shi, Stephen Gerard Schadewald, Jason Paul Hoppa, Kirk Douglas Gallier, Christopher Edward Wolfe, Robert Proctor
  • Patent number: 10788130
    Abstract: 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: Grant
    Filed: January 8, 2020
    Date of Patent: September 29, 2020
    Assignee: General Electric Company
    Inventors: Deepak Trivedi, Christopher Edward Wolfe, Nathan EvanMcCurdy Gibson, Brian Joseph Prenger
  • Patent number: 10738644
    Abstract: 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: Grant
    Filed: August 30, 2017
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Jinjie Shi, Dennis Paul Dry, Christopher Edward Wolfe, Andres Jose Garcia-Crespo, Yun Zhu
  • Publication number: 20200166143
    Abstract: 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: Application
    Filed: November 27, 2018
    Publication date: May 28, 2020
    Inventors: Quang Tue Nguyen Tran, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Christopher Edward Wolfe, Steven Douglas Johnson, Antonio Guijarro Valencia
  • Publication number: 20200166142
    Abstract: 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: Application
    Filed: November 27, 2018
    Publication date: May 28, 2020
    Inventors: Rahul Anil Bidkar, Christopher Edward Wolfe, Nathan Evan McCurdy Gibson, Rodrigo Rodriguez Erdmenger, Deepak Trivedi, Quang Tue Nguyen Tran
  • Patent number: 10655489
    Abstract: 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: Grant
    Filed: January 4, 2018
    Date of Patent: May 19, 2020
    Assignee: General Electric Company
    Inventors: Neelesh Nandkumar Sarawate, Christopher Edward Wolfe, Victor John Morgan, Jason Ray Gregg
  • Publication number: 20200149638
    Abstract: 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: Application
    Filed: January 8, 2020
    Publication date: May 14, 2020
    Inventors: Deepak Trivedi, Christopher Edward Wolfe, Nathan EvanMcCurdy Gibson, Brian Joseph Prenger
  • Publication number: 20200141276
    Abstract: 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: Application
    Filed: November 7, 2018
    Publication date: May 7, 2020
    Applicant: General Electric Company
    Inventors: Christopher Edward Wolfe, Neelesh Nandkumar Sarawate