Patents by Inventor Cheryl A. Schopf

Cheryl A. Schopf 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: 10781751
    Abstract: A gas turbine engine for an aircraft such as a UAV includes a compressor connected to a turbine with a combustor to produce a hot gas stream. The rotor is supported by two radial foil bearings. An axial thrust bearing assembly is positioned between the compressor disk and the turbine disk and includes an axial thrust bearing radial disk extending from a hollow axial tube. Compressed air is bled off from the compressor and passed into an axial thrust balance chamber to provide the axial thrust balance for the rotor. The compressed air from the thrust bearing chamber then flows through both of the radial foil bearings for cooling, is collected in and around the hollow tube, and then discharged into the inlet of the turbine. An orifice can be adjusted to meter and control a pressure occurring in the thrust balance chamber.
    Type: Grant
    Filed: March 22, 2018
    Date of Patent: September 22, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B Jones, Cheryl A Schopf
  • Patent number: 10641123
    Abstract: A power plant for an aircraft such as a UAV with a gas turbine engine that drives an electric generator to produce electrical power. The electric generator is rotatably supported by two foil bearings. A centrifugal compressor is secured to a forward side of the generator rotor shaft. The centrifugal compressor draws in cooling air that flows through the two foil bearings and between a space formed between the rotor coil and the stator coil of the electric generator to provide for cooling of both foil bearings and the coils of the generator.
    Type: Grant
    Filed: March 22, 2018
    Date of Patent: May 5, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Andrew R Narcus, Cheryl A Schopf
  • Patent number: 9714611
    Abstract: A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.
    Type: Grant
    Filed: February 15, 2013
    Date of Patent: July 25, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Clinton A. Mayer, Jesse Eng, Cheryl A. Schopf
  • Patent number: 9316153
    Abstract: A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.
    Type: Grant
    Filed: January 22, 2013
    Date of Patent: April 19, 2016
    Assignee: Siemens Energy, Inc.
    Inventors: Harry Patat, Cheryl A. Schopf, Jerome H. Katy, Adam Wallace, David J. Wiebe
  • Publication number: 20140230441
    Abstract: A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.
    Type: Application
    Filed: February 15, 2013
    Publication date: August 21, 2014
    Inventors: Clinton A. Mayer, Jesse Eng, Cheryl A. Schopf
  • Publication number: 20140205447
    Abstract: A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.
    Type: Application
    Filed: January 22, 2013
    Publication date: July 24, 2014
    Inventors: Harry Patat, Cheryl A. Schopf, Jerome H. Katy, Adam Wallace, David J. Wiebe
  • Patent number: 7748952
    Abstract: A small twin spool gas turbine engine with a bearing support arrangement in which the bearings are dampened by O-rings secured between the bearing races and the support structure, and in which the bearings are arranged in series so that a cooling air can be passed through the bearings to prevent overheating. The aft end of the engine includes high speed and low speed ball bearings supported with preload springs to add additional damping capability. The fore and aft end bearing support assemblies forms a cooling air path for the cooling fluid to flow through a passage within one of the guide vanes, through the bearings and out through a hole in the low pressure turbine rotor disk. the bearing cooling air passage includes a snorkel tube that extends from a guide vane cooling air passage and into the bypass air channel to draw in the cooling air used for the bearings. The snorkel tube includes a slanted opening so that dirt particulates do not enter the bearing cooling air passage.
    Type: Grant
    Filed: August 1, 2008
    Date of Patent: July 6, 2010
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Cheryl A. Schopf, Jack W. Wilson, Jr.
  • Patent number: 7748209
    Abstract: A small single use gas turbine engine with a twin spool rotor shaft and a bypass fan, the rotor shafts being supported for rotation by bearings in the front and rear compartments of the engine. A portion of the bypass fan air is diverted to flow through the bearings in order to provide for cooling of the high speed bearings. Because a large amount of cooling air is required to cool the bearings, an air in tube is positioned in each of the guide vanes in the turbine section to provide for a cooling air passage leading into the rear bearings. In the front bearings, cooling air from the bypass fan is bled off from a location just upstream from the entrance to the centrifugal compressor. A fuel mist tube supplies fuel mist to the cooling air before passing through the bearings to provide extra cooling for the bearings and to provide lubrication to improve the service life of the engine.
    Type: Grant
    Filed: December 8, 2006
    Date of Patent: July 6, 2010
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Cheryl A. Schopf, Jack W. Wilson, Jr., Wesley Brown
  • Patent number: 7740441
    Abstract: A small twin spool gas turbine engine with a bearing support arrangement in which the bearings are dampened by O-rings secured between the bearing races and the support structure, the bearings are arranged in series so that a cooling air can be passed through the bearings to prevent overheating, and the bearings are dry lubricated. The aft end of the engine includes high speed and low speed ball bearings supported with preload springs to add additional damping capability. The end bearing support assemblies form a cooling air path for the cooling fluid to flow through a passage within one of the guide vanes, through the bearings and a hole in the low pressure turbine rotor disk and out the exhaust of the engine. A snorkel tube extends into the bypass air channel drawing air for the bearings, and has a slanted opening preventing dirt particulates from entering the bearing cooling passage.
    Type: Grant
    Filed: August 1, 2008
    Date of Patent: June 22, 2010
    Assignee: Floride Turbine Technologies, Inc.
    Inventors: David J Huber, Cheryl A Schopf, Jack W Wilson, Jr.
  • Patent number: 7658588
    Abstract: A process for optimizing a blade tip clearance for a rub tolerate design in a gas turbine engine that includes evaluating a selection of candidate materials for galling and heat generation, selecting a subset of the candidate materials and analyze engine transient tip clearance for the subset materials, verifying the optimum material cooling and heat shielding for tip clearance and structures, and analyze and select an engine break-in procedure for the optimum tip clearance between turbine and compressor. If one of the subset materials results in a poor performance, than another material from the candidate materials is selected and reanalyzed until the best materials have been found. When the best materials are found, then a finite element method of analysis is performed from the blade and the static parts that form the tip clearance is performed to evaluate the materials for damage. If required, the blade and tip squealer configuration is altered to reduce stress, or blade tip coating is used.
    Type: Grant
    Filed: January 26, 2007
    Date of Patent: February 9, 2010
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Cheryl A. Schopf, Jack W. Wilson, Jr.
  • Patent number: 6805533
    Abstract: A cooled fluid flow component for a combustion engine which employs internal impingement and exterior surface film cooling is disclosed. The fluid flow component has improved tolerance to assembly and manufacturing variations. The fluid flow component includes at least one interior cavity having an associated impingement sleeve. An impingement annulus surrounding the impingement sleeve is divided into more than one region, with each region forced to have a pressure equal, pressure, with the pressure induced being sufficient to provide adequate backflow margin. The external cooling holes are shaped to address possible overflow tendencies, and the impingement holes are adapted to reduce or eliminate possible losses of impingement cooling effectiveness.
    Type: Grant
    Filed: September 27, 2002
    Date of Patent: October 19, 2004
    Assignee: Siemens Westinghouse Power Corporation
    Inventor: Cheryl A. Schopf
  • Publication number: 20040062649
    Abstract: A cooled fluid flow component for a combustion engine which employs internal impingement and exterior surface film cooling is disclosed. The fluid flow component has improved tolerance to assembly and manufacturing variations. The fluid flow component includes at least one interior cavity having an associated impingement sleeve. An impingement annulus surrounding the impingement sleeve is divided into more than one region, with each region forced to have a pressure equal, pressure, with the pressure induced being sufficient to provide adequate backflow margin. The external cooling holes are shaped to address possible overflow tendencies, and the impingement holes are adapted to reduce or eliminate possible losses of impingement cooling effectiveness.
    Type: Application
    Filed: September 27, 2002
    Publication date: April 1, 2004
    Applicant: Siemens Westinghouse Power Corporation
    Inventor: Cheryl A. Schopf