Patents by Inventor Jeffrey S. Beattie

Jeffrey S. Beattie 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).

  • Publication number: 20140000282
    Abstract: A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.
    Type: Application
    Filed: June 29, 2012
    Publication date: January 2, 2014
    Inventors: Mark F. Zelesky, Ricardo Trindade, Bret M. Teller, Scott D. Lewis, Jeffrey S. Beattie, Jeffrey Michael Jacques, Brandon M. Rapp
  • Publication number: 20130323078
    Abstract: A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.
    Type: Application
    Filed: May 31, 2012
    Publication date: December 5, 2013
    Inventors: Jeffrey S. Beattie, Jeffrey Michael Jacques, Justin D. Piggush
  • Publication number: 20130280080
    Abstract: An airfoil includes a body. The body includes leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface. First and second cooling passages extend in a radial direction from a root to a tip. The first cooling passage includes a tip flag passage that is radially inboard from the tip and extends in a chord-wise direction to a first end that penetrates the trailing edge. The second cooling passage includes a second end terminates adjacent the tip flag passage and a dirt purge passage interconnects the second end to the tip flag passage. A core for making the airfoil is also disclosed.
    Type: Application
    Filed: April 23, 2012
    Publication date: October 24, 2013
    Inventors: Jeffrey R. Levine, Jeffrey S. Beattie
  • Publication number: 20130238109
    Abstract: A method is provided for inspecting a plurality of parts with an electronic measurement device and a processing system. The method includes a step of creating surface geometry maps of the parts utilizing the electronic measurement device, where each part was manufactured utilizing the manufacturing device. Geometric part models of the parts are generated from the surface geometry maps. The part models can subsequently be analyzed to determine whether a manufacturing device that manufactured the plurality of parts manufactures parts that comply with a part design specification.
    Type: Application
    Filed: March 12, 2012
    Publication date: September 12, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: James Romanelli, Jeffrey S. Beattie, Jesse R. Boyer, Robert E. Erickson, Randall W. Joyner, Daniel A. Snyder, David A. Krause, Kun Tong
  • Patent number: 8356978
    Abstract: A gas turbine engine component has a platform and an airfoil extending from the platform. The platform has a pressure side and a suction side. A cooling passage is formed within the platform, and extends along a pressure side of the platform. Air leaves the passage through an air outlet on a suction side of the platform.
    Type: Grant
    Filed: November 23, 2009
    Date of Patent: January 22, 2013
    Assignee: United Technologies Corporation
    Inventors: Jeffrey S. Beattie, Matthew A. Devore, Matthew S. Gleiner, Douglas C. Jenne
  • Patent number: 8257045
    Abstract: Platforms with curved side edges and gas turbine engine systems involving such platforms are provided. In this regard, a representative airfoil assembly for a gas turbine engine includes: a platform having a gas path side, a non-gas path side, a leading edge, a trailing edge, a first side edge extending between the leading edge and the trailing edge and exhibiting a first curve along a length thereof, and a second side edge extending between the leading edge and the trailing edge and exhibiting a second curve along a length thereof; and an airfoil extending from the gas path side of the platform; the platform and the airfoil exhibiting a unitary construction such that a continuous exterior surface blends from the airfoil to the platform.
    Type: Grant
    Filed: August 15, 2008
    Date of Patent: September 4, 2012
    Assignee: United Technologies Corp.
    Inventors: Brandon W. Spangler, Jeffrey S. Beattie, Scott D. Hjelm
  • Patent number: 8240987
    Abstract: Gas turbine engine systems involving baffle assemblies are provided. In this regard, a representative baffle assembly for a gas turbine engine includes: a cooling plenum defining a cooling air path; and a baffle sized and shaped to extend between surfaces of the cooling plenum such that a cooling air path of reduced cross-section is formed between the baffle and the surfaces, the baffle being operative to increase a flow rate of cooling air as the cooling air directed to the cooling air path is redirected through the cooling air path of reduced cross-section.
    Type: Grant
    Filed: August 15, 2008
    Date of Patent: August 14, 2012
    Assignee: United Technologies Corp.
    Inventors: Brandon W. Spangler, Jeffrey S. Beattie
  • Publication number: 20110123310
    Abstract: A gas turbine engine component has a platform and an airfoil extending from the platform. The platform has a pressure side and a suction side. A cooling passage is formed within the platform, and extends along a pressure side of the platform. Air leaves the passage through an air outlet on a suction side of the platform.
    Type: Application
    Filed: November 23, 2009
    Publication date: May 26, 2011
    Inventors: Jeffrey S. Beattie, Matthew A. Devore, Matthew S. Gleiner, Douglas C. Jenne
  • Publication number: 20100040460
    Abstract: Platforms with curved side edges and gas turbine engine systems involving such platforms are provided. In this regard, a representative airfoil assembly for a gas turbine engine includes: a platform having a gas path side, a non-gas path side, a leading edge, a trailing edge, a first side edge extending between the leading edge and the trailing edge and exhibiting a first curve along a length thereof, and a second side edge extending between the leading edge and the trailing edge and exhibiting a second curve along a length thereof; and an airfoil extending from the gas path side of the platform; the platform and the airfoil exhibiting a unitary construction such that a continuous exterior surface blends from the airfoil to the platform.
    Type: Application
    Filed: August 15, 2008
    Publication date: February 18, 2010
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Brandon W. Spangler, Jeffrey S. Beattie, Scott D. Hjelm
  • Publication number: 20100040479
    Abstract: Gas turbine engine systems involving baffle assemblies are provided. In this regard, a representative baffle assembly for a gas turbine engine includes: a cooling plenum defining a cooling air path; and a baffle sized and shaped to extend between surfaces of the cooling plenum such that a cooling air path of reduced cross-section is formed between the baffle and the surfaces, the baffle being operative to increase a flow rate of cooling air as the cooling air directed to the cooling air path is redirected through the cooling air path of reduced cross-section.
    Type: Application
    Filed: August 15, 2008
    Publication date: February 18, 2010
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Brandon W. Spangler, Jeffrey S. Beattie
  • Publication number: 20080131285
    Abstract: A process for forming an airfoil portion of a turbine engine component, such as a turbine blade, is described. The process comprises the steps of placing a ceramic core having a configuration of a passageway to be formed in the airfoil portion within a mold, attaching a refractory metal core element to the ceramic core to stabilize a tip region of the ceramic core, and casting the airfoil portion.
    Type: Application
    Filed: November 30, 2006
    Publication date: June 5, 2008
    Inventors: Jason Edward Albert, Francisco J. Cunha, Jeffrey S. Beattie