Patents by Inventor Steven W. Burd

Steven W. Burd 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: 10174621
    Abstract: A method includes building an article by a layer-by-layer additive manufacturing process. While the article is being built, a solid outer wall is formed. An inner structure of the article is integrally formed with the outer wall. The inner structure includes an internal permeable structure.
    Type: Grant
    Filed: September 24, 2014
    Date of Patent: January 8, 2019
    Assignee: United Technologies Corporation
    Inventor: Steven W. Burd
  • Patent number: 10132498
    Abstract: Aspects of the disclosure are directed to a liner associated with a combustor of an aircraft engine, comprising: a thermal barrier coating, and a base metal, wherein the thermal barrier coating comprises a contoured surface on a flowpath side proximate to an exit of a hole formed by the thermal barrier coating and the base metal.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: November 20, 2018
    Assignee: United Technologies Corporation
    Inventor: Steven W. Burd
  • Patent number: 10066836
    Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.
    Type: Grant
    Filed: July 16, 2015
    Date of Patent: September 4, 2018
    Assignee: United Technologies Corporation
    Inventors: Timothy S. Snyder, Steven W. Burd, Randal G. McKinney, George F. Titterton, III
  • Publication number: 20180231251
    Abstract: A combustor for a gas turbine engine including a combustor liner support shell with a furrow formed therein; a forward liner panel mounted to the support shell via a multiple of studs, the forward liner panel including a forward liner panel rail the extends into the furrow; and an aft liner panel mounted to the support shell via a multiple of studs downstream of the forward liner panel, the aft liner panel including an aft liner panel rail that extends into the furrow.
    Type: Application
    Filed: February 14, 2017
    Publication date: August 16, 2018
    Applicant: United Technologies Corporation
    Inventor: Steven W. Burd
  • Publication number: 20180230602
    Abstract: A combustor for a gas turbine engine including a support shell with a shell coating applied thereto and a multiple of liner panels circumferentially mounted within the support shell via a multiple of studs, each of the multiple of liner panels having a liner coating applied thereto.
    Type: Application
    Filed: November 10, 2016
    Publication date: August 16, 2018
    Applicant: United Technologies Corporation
    Inventor: Steven W. Burd
  • Publication number: 20180231249
    Abstract: A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a forward section and an aft section that defines an arcuate surface section therebetween in the axial profile between the forward section and the aft section.
    Type: Application
    Filed: November 10, 2016
    Publication date: August 16, 2018
    Applicant: United Technologies Corporation
    Inventor: Steven W. Burd
  • Publication number: 20180231248
    Abstract: A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a forward section and an aft section that defines an angle therebetween in the axial profile between the forward section and the aft section.
    Type: Application
    Filed: November 10, 2016
    Publication date: August 16, 2018
    Applicant: United Technologies Corporation
    Inventor: Steven W. Burd
  • Publication number: 20180231250
    Abstract: A combustor for a gas turbine engine including a forward liner panel mounted to a support shell via a multiple of studs, the forward liner panel including an aft non-linear circumferential edge and an aft liner panel mounted to the support shell via a multiple of studs, the aft liner panel including a forward non-linear circumferential edge that is complementary to the aft non-linear circumferential edge.
    Type: Application
    Filed: November 10, 2016
    Publication date: August 16, 2018
    Applicant: United Technologies Corporation
    Inventor: Steven W. Burd
  • Patent number: 10030583
    Abstract: An ignition system for a combustor of a gas turbine engine is disclosed. The ignition system may include an igniter operatively associated with the combustor, and an electrode operatively associated with the combustor and spaced from the igniter, wherein an electrical potential is created between the igniter and the electrode to produce an electric arc therebetween.
    Type: Grant
    Filed: November 6, 2013
    Date of Patent: July 24, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Steven W. Burd
  • Publication number: 20180149361
    Abstract: A combustor of a gas turbine engine includes a combustor shell having a diffuser side facing a diffuser chamber and a combustor side facing a combustor chamber. The combustor may include a first combustor panel coupled to the combustor side of the combustor shell and a second combustor panel coupled to the combustor side of the combustor shell. A gap may be defined between the first combustor panel and the second combustor panel and the combustor shell may include a gap impingement hole that is directly open to and is configured to deliver cooling air directly to the gap. In various embodiments, the combustor further includes a throttle plate coupled to the diffuser side of the combustor shell.
    Type: Application
    Filed: November 30, 2016
    Publication date: May 31, 2018
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: STEVEN W. BURD
  • Publication number: 20180128486
    Abstract: A combustor for a gas turbine engine including a non-linear axial edge between the forward edge and the aft edge. A combustor for a gas turbine engine including a multiple of forward liner panels circumferentially mounted within the support shell via a multiple of studs, each of the multiple of forward liner panels having a non-linear axial edge therebetween to define a forward non-linear interface between each adjacent pair of the multiple of forward liner panels and a multiple of aft liner panels circumferentially mounted within the support shell via a multiple of studs aft of the multiple of forward liner panels, each of the multiple of aft liner panels having an aft non-linear axial edge therebetween to define a non-linear interface between each adjacent pair of the multiple of aft liner panels.
    Type: Application
    Filed: November 10, 2016
    Publication date: May 10, 2018
    Applicant: United Technologies Corporation
    Inventor: Steven W. Burd
  • Patent number: 9964214
    Abstract: A seal for use between a first duct and a second duct and, the ducts having relative motion therebetween, includes a first plurality of fingers for attachment to the first duct to be disposed about one of the first duct and the second duct, a seal land attaching to about an other of the first duct and the second duct, and a seal attaching to the seal land and in contact with the plurality of fingers wherein one of the plurality of fingers and the seal is metallic and an other of the seal land or the plurality of fingers is non-metallic.
    Type: Grant
    Filed: April 2, 2012
    Date of Patent: May 8, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Steven W. Burd, Roger W. Bursey, Gonzalo F. Martinez, Meggan H. Harria-Miller
  • Patent number: 9945236
    Abstract: A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.
    Type: Grant
    Filed: May 22, 2014
    Date of Patent: April 17, 2018
    Assignee: United Technologies Corporation
    Inventors: Steven W. Burd, Meggan Harris, John T. Ols, William G. Askey
  • Patent number: 9726034
    Abstract: A gas turbine engine has a first component and a second component. The first and second components have a high-pressure chamber on one side and a low pressure chamber on an opposed side. A three sided seal has one side facing each of the first and second components, and a third side facing a third component. At least one non-metallic wear surface is between one of the three sides of the seal and the facing component.
    Type: Grant
    Filed: February 1, 2016
    Date of Patent: August 8, 2017
    Assignee: United Technologies Corporation
    Inventor: Steven W. Burd
  • Patent number: 9511452
    Abstract: An assembly may comprise a first part including a first surface, and a second part including a second surface and a bottom edge having sloped regions and at least one well between the sloped regions. The assembly may further comprise a brazed joint joining the first surface to the second surface. The at least one well may be configured to collect excess braze material from the brazed joint.
    Type: Grant
    Filed: February 9, 2015
    Date of Patent: December 6, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher M. Pater, Steven W. Burd, Derk S. Philippona, Robert J. Sayers
  • Publication number: 20160312741
    Abstract: The present disclosure relates generally to a system for fan nacelle inlet flow control in a gas turbine engine, the nacelle comprising a nacelle inlet cowl including an inlet lip disposed at a leading edge of the nacelle inlet cowl, an inner surface extending aft from the inlet lip, and an outer surface extending aft from the inlet lip and positioned radially outward of the inner surface; and at least one flow control passage extending through the nacelle inlet cowl, each of the at least one flow control passage including a flow control passage inlet, disposed on the inlet lip, and a flow control passage outlet; wherein air may flow into the flow control passage inlet, through the flow control passage, and exits the flow control passage outlet.
    Type: Application
    Filed: December 12, 2014
    Publication date: October 27, 2016
    Inventor: Steven W. Burd
  • Publication number: 20160273391
    Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.
    Type: Application
    Filed: September 4, 2014
    Publication date: September 22, 2016
    Inventors: Steven W. Burd, Christopher R. Brdar, Derk S. Philippona
  • Publication number: 20160245519
    Abstract: A gas turbine engine component and a method for forming a component with a plurality of apertures are provided. An additive metal manufacturing process for fabricating a component with apertures includes receiving data including a three-dimensional representation of the component, generating an electronic file based on the received data, wherein the electronic file includes fabrication instructions for entire portions of the component, and forming initial and additional portions of the component based on the electronic file.
    Type: Application
    Filed: August 21, 2014
    Publication date: August 25, 2016
    Inventor: Steven W. Burd
  • Publication number: 20160237828
    Abstract: A method includes building an article by a layer-by-layer additive manufacturing process. While the article is being built, a solid outer wall is formed. An inner structure of the article is integrally formed with the outer wall. The inner structure includes an internal permeable structure.
    Type: Application
    Filed: September 24, 2014
    Publication date: August 18, 2016
    Inventor: Steven W. BURD
  • Publication number: 20160237950
    Abstract: A component is provided for a gas turbine engine includes a substrate with an aperture. The component also includes a backside coating on a backside of the substrate and at least partially onto an inner boundary of the aperture, where the backside coating forms a passage with the aperture. A method of forming a shaped aperture in a component of a gas turbine engine is provided. The method includes applying a backside coating on a backside of a substrate and at least partially onto an inner boundary of an aperture. The backside coating forms a passage with the aperture including a convergent section, a divergent section and a throat therebetween.
    Type: Application
    Filed: August 5, 2014
    Publication date: August 18, 2016
    Inventor: Steven W. Burd