Patents by Inventor Christina A. Stenman

Christina A. Stenman 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).

  • Convergent-divergent gas turbine nozzle comprising movable flaps having a variable thickness in a lateral direction
    Patent number: 9163582
    Abstract: A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plurality of flaps has a thickness between the inner surface and the outer surface, and thickness varies in a lateral direction between the lateral sides.
    Type: Grant
    Filed: May 30, 2012
    Date of Patent: October 20, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher Treat, Christina A. Stenman, Shelton O. Duelm, Alex J. Simpson
  • Corrugated mid-turbine frame thermal radiation shield
    Patent number: 9151226
    Abstract: A corrugated shield comprises a mounting base and a corrugated ring section. The mounting base is disposed at an aft end of the ring section for securing the shield ring section within a generally annular cavity. The generally annular cavity is defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The corrugated ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.
    Type: Grant
    Filed: July 6, 2012
    Date of Patent: October 6, 2015
    Assignee: United Technologies Corporation
    Inventors: Alisha M. Zimmermann, Christina A. Stenman, Conway Chuong
  • Shield system for gas turbine engine
    Patent number: 9133723
    Abstract: A shield system for a gas turbine engine extends between an inner case structure and a vane pack.
    Type: Grant
    Filed: May 21, 2012
    Date of Patent: September 15, 2015
    Assignee: United Technologies Corporation
    Inventors: Tuan David Vo, Christina A. Stenman, Shelton O. Duelm
  • Gas turbine exhaust nozzle divergent flap seal
    Patent number: 9016695
    Abstract: A seal assembly for a nozzle in a gas turbine engine includes a connector having a first hinge portion for attaching to the nozzle, a flat portion for sealing against a wall of the engine; and a first hinge for attaching the connector to the flat portion wherein the connector is adapted to rotate relative to the nozzle and the flat portion is adapted to rotate relative to the connector.
    Type: Grant
    Filed: August 2, 2011
    Date of Patent: April 28, 2015
    Assignee: United Technologies Corporation
    Inventors: Christopher Treat, Christina A. Stenman
  • CORRUGATED MID-TURBINE FRAME THERMAL RADIATION SHIELD
    Publication number: 20140007589
    Abstract: A corrugated shield comprises a mounting base and a corrugated ring section. The mounting base is disposed at an aft end of the ring section for securing the shield ring section within a generally annular cavity. The generally annular cavity is defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The corrugated ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.
    Type: Application
    Filed: July 6, 2012
    Publication date: January 9, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Alisha M. Zimmermann, Christina A. Stenman, Conway Chuong
  • LINER ASSEMBLY
    Publication number: 20130318978
    Abstract: A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plurality of flaps has a thickness between the inner surface and the outer surface, and thickness varies in a lateral direction between the lateral sides.
    Type: Application
    Filed: May 30, 2012
    Publication date: December 5, 2013
    Inventors: Christopher Treat, Christina A. Stenman, Shelton O. Duelm, Alex J. Simpson
  • SHIELD SYSTEM FOR GAS TURBINE ENGINE
    Publication number: 20130309078
    Abstract: A shield system for a gas turbine engine extends between an inner case structure and a vane pack.
    Type: Application
    Filed: May 21, 2012
    Publication date: November 21, 2013
    Inventors: Tuan David Vo, Christina A. Stenman, Shelton O. Duelm
  • GAS TURBINE EXHAUST NOZZLE DIVERGENT FLAP SEAL
    Publication number: 20130033005
    Abstract: A seal assembly for a nozzle in a gas turbine engine includes a connector having a first hinge portion for attaching to the nozzle, a flat portion for sealing against a wall of the engine; and a first hinge for attaching the connector to the flat portion wherein the connector is adapted to rotate relative to the nozzle and the flat portion is adapted to rotate relative to the connector.
    Type: Application
    Filed: August 2, 2011
    Publication date: February 7, 2013
    Inventors: Christopher Treat, Christina A. Stenman