Patents by Inventor Kevin J. Lowe

Kevin J. Lowe 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: 11226102
    Abstract: A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator.
    Type: Grant
    Filed: March 14, 2018
    Date of Patent: January 18, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Kevin J. Low, Joey Wong, Chris J. Niggemeier
  • Patent number: 10808937
    Abstract: A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: James P. Bangerter, Kevin J. Low
  • Patent number: 10655855
    Abstract: A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: May 19, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: James P. Bangerter, Kevin J. Low, Russell B. Hanson, Nurhak Erbas-Sen, Frank J. Cunha
  • Patent number: 10488046
    Abstract: A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages that define an angle ? with respect to a hot side of the bulkhead support shell and a second multiple of cooling impingement passages that define an angle ? with respect to the hot side of the bulkhead support shell. The angle ? is different than the angle ?.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Kevin J. Low, Nurhak Erbas-Sen
  • Patent number: 10473330
    Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge. The liner panel also includes a second liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first and the second liner panel side edges are non-perpendicular to the liner panel forward and aft edge edges.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: November 12, 2019
    Assignee: United Technologies Corporation
    Inventors: Seth A. Max, Kevin J. Low
  • Patent number: 10228467
    Abstract: A device and method for inspecting the deposition of hot melt onto an object to be assembled. A comparison is made between sensed images of the object after application of the hot melt and a predetermined standard to determine if the construction integrity of the object made with the hot melt is within the range established by the standard. Composite images from a sensor operating in the infrared band and another sensor reveal physical features of the object, as well as provide registration information about the placement of the hot melt on the assembled object. Composite images also present a way to visually ascertain ongoing or past production operations in order to trace problems with the raw material used for the object, as well as for the construction process of the object with the hot melt.
    Type: Grant
    Filed: April 4, 2017
    Date of Patent: March 12, 2019
    Assignee: Valco Cincinnati, Inc.
    Inventors: Kevin J. Lowe, Graham T. Manders, Stelian N. Vasiu, James Brashear, Aiqiu Zuo, Denis Tran, Mehdi Bahrami
  • Patent number: 10197285
    Abstract: A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes an end rail. The contoured region is deformable to selectively contact at least a portion of the end rail. A method of assembling a wall assembly within a gas turbine engine is also provided. This method includes locating a stud that extends from a cold side of a liner panel through a support shell; and attaching a fastener onto the stud to at least partially close a gap defined between the panel and shell.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: February 5, 2019
    Assignee: United Technologies Corporation
    Inventors: James P. Bangerter, Thomas R. Russo, Russell B. Hanson, Kevin J. Low
  • Publication number: 20180209652
    Abstract: A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator.
    Type: Application
    Filed: March 14, 2018
    Publication date: July 26, 2018
    Inventors: Kevin J. Low, Joey Wong, Chris J. Niggemeier
  • Publication number: 20170205509
    Abstract: A device and method for inspecting the deposition of hot melt onto an object to be assembled. A comparison is made between sensed images of the object after application of the hot melt and a predetermined standard to determine if the construction integrity of the object made with the hot melt is within the range established by the standard. Composite images from a sensor operating in the infrared band and another sensor reveal physical features of the object, as well as provide registration information about the placement of the hot melt on the assembled object. Composite images also present a way to visually ascertain ongoing or past production operations in order to trace problems with the raw material used for the object, as well as for the construction process of the object with the hot melt.
    Type: Application
    Filed: April 4, 2017
    Publication date: July 20, 2017
    Inventors: Kevin J. Lowe, Graham T. Manders, Stelian N. Vasiu, James Brashear, Aiqiu Zuo, Denis Tran, Mehdi Bahrami
  • Publication number: 20160377296
    Abstract: A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes an end rail. The contoured region is deformable to selectively contact at least a portion of the end rail. A method of assembling a wall assembly within a gas turbine engine is also provided. This method includes locating a stud that extends from a cold side of a liner panel through a support shell; and attaching a fastener onto the stud to at least partially close a gap defined between the panel and shell.
    Type: Application
    Filed: August 29, 2014
    Publication date: December 29, 2016
    Inventors: James P. Bangerter, Thomas R. Russo, Russell B. Hanson, Kevin J. Low
  • Publication number: 20160265771
    Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge. The liner panel also includes a second liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first and the second liner panel side edges are non-perpendicular to the liner panel forward and aft edge edges.
    Type: Application
    Filed: November 18, 2014
    Publication date: September 15, 2016
    Inventors: Seth A. MAX, Kevin J. LOW
  • Publication number: 20160265784
    Abstract: A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height.
    Type: Application
    Filed: August 29, 2014
    Publication date: September 15, 2016
    Inventors: James P. Bangerter, Kevin J. Low
  • Publication number: 20160201909
    Abstract: A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.
    Type: Application
    Filed: August 29, 2014
    Publication date: July 14, 2016
    Inventors: James P. Bangerter, Kevin J. Low, Russell B. Hanson, Nurhak Erbas-Sen, Frank J. Cunha
  • Publication number: 20160169516
    Abstract: A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages that define an angle ? with respect to a hot side of the bulkhead support shell and a second multiple of cooling impingement passages that define an angle ? with respect to the hot side of the bulkhead support shell. The angle ? is different than the angle ?.
    Type: Application
    Filed: August 13, 2014
    Publication date: June 16, 2016
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Kevin J. Low, Nurhak Erbas-Sen
  • Publication number: 20160033130
    Abstract: A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator.
    Type: Application
    Filed: March 13, 2014
    Publication date: February 4, 2016
    Inventors: Kevin J. LOW, Joey WONG, Chris J. NIGGEMEIER
  • Publication number: 20150260399
    Abstract: A liner for a gas turbine engine includes a cold side having a partition which extends therefrom to define a forward cavity and an aft cavity, each cavity having a plurality of film holes to communicate a coolant from the cold side to the hot side.
    Type: Application
    Filed: September 30, 2013
    Publication date: September 17, 2015
    Inventor: Kevin J. Low
  • Patent number: 8733800
    Abstract: The tube (60) includes first and second portions (66, 58) that each have mating spherical sections (82, 84) at adjacent ends (72, 74) of each portion (66, 68). The second portion (68) includes a spring sleeve (92) configured to surround an outlet end (72) of the first portion (66). A spring (102) is captured inside the spring sleeve (92) and secured between a retaining clip (100) and a shoulder (88) protruding from the exterior surface of an outlet end (72) of the first portion (66) to maintain fluid seals between the spherical sections (82, 84). The spherical sections (82, 84) permit slidable motion relative to each other thereby facilitating rotational and angular motion between the tube portions (66, 68). One of the two portions (66, 68) may include a telescope mount (110) to permit limited axial motion of the tube (60).
    Type: Grant
    Filed: November 20, 2012
    Date of Patent: May 27, 2014
    Assignee: United Technologies Corporation
    Inventors: Jose E. Ruperte Sanchez, Russell B. Hanson, Kevin J. Low
  • Publication number: 20140138945
    Abstract: The tube (60) includes first and second portions (66, 68) that each have mating spherical sections (82, 84) at adjacent ends (72, 74) of each portion (66, 68). The second portion (68) includes a spring sleeve (92) configured to surround an outlet end (72) of the first portion (66). A spring (102) is captured inside the spring sleeve (92) and secured between a retaining clip (100) and a shoulder (88) protruding from the exterior surface of an outlet end (72) of the first portion (66) to maintain fluid seals between the spherical sections (82, 84). The spherical sections (82, 84) permit, slidable motion relative to each other thereby facilitating rotational and angular motion between the tube portions (66, 68). One of the two portions (66, 68) may include a telescope mount (110) to permit limited axial motion of the tube (60).
    Type: Application
    Filed: November 20, 2012
    Publication date: May 22, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jose E. RUPERTE SANCHEZ, Russell B. HANSON, Kevin J. LOW
  • Publication number: 20100242483
    Abstract: A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber. The liner assembly includes an inner liner and an outer liner that circumscribes the inner liner. The inner liner has a plurality of first combustion air admission holes passing therethrough and the second liner has a plurality of second combustion air admission holes passing therethrough. Each of the first and the second combustion air admission holes has a swirler disposed therein.
    Type: Application
    Filed: March 30, 2009
    Publication date: September 30, 2010
    Applicant: United Technologies Corporation
    Inventors: Timothy S. Snyder, Kevin J. Low
  • Publication number: 20030124036
    Abstract: The present invention is a retainer and a method of manufacture therefor that can incorporate the ability to condition the flow of a fluid therethrough. The retainer defines an bearing surface for buttressing an element having a fluid flowing therethrough. The retainer is comprised of a plurality of members that if given the proper aspect ratio can condition the flow of a fluid.
    Type: Application
    Filed: January 3, 2002
    Publication date: July 3, 2003
    Inventors: Kevin J. Low, Warren F. Smith, William C. Pfefferle, Subir Roychoudhury