Patents by Inventor Russell B. Jones

Russell B. Jones 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: 20210299419
    Abstract: Ingestible devices with a relatively large payload volume or sample volume, as well as related components, systems and methods, are disclosed.
    Type: Application
    Filed: June 14, 2021
    Publication date: September 30, 2021
    Inventors: Mitchell Lawrence Jones, Russell B. Ford, Edward G. Solomon, Jeffrey A. Shimizu
  • Patent number: 11041436
    Abstract: A process for retrofitting an industrial gas turbine engine of a power plant where an old industrial engine with a high spool has a new low spool with a low pressure turbine that drives a low pressure compressor using exhaust gas from the high pressure turbine, and where the new low pressure compressor delivers compressed air through a new compressed air line to the high pressure compressor through a new inlet added to the high pressure compressor. The old electric generator is replaced with a new generator having around twice the electrical power production. One or more stages of vanes and blades are removed from the high pressure compressor to optimally match a pressure ratio split. Closed loop cooling of one or more new stages of vanes and blades in the high pressure turbine is added and the spent cooling air is discharged into the combustor.
    Type: Grant
    Filed: May 15, 2017
    Date of Patent: June 22, 2021
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B. Jones, Joseph D. Brostmeyer, Justin T. Cejka, John E. Ryznic
  • Patent number: 11028698
    Abstract: A small gas turbine engine with a ceramic turbine to allow for higher turbine inlet temperatures, where a metallic compressor is secured to a ceramic shaft extending from a ceramic turbine to form a single piece ceramic shaft and turbine, where a threaded nut secures a split ring retainer on the compressor end of the ceramic shaft. A hollow thrust runner is compressed between the compressor disk and the turbine disk by the threaded nut to secure rotor together. A centering spring forms a tight fit between the metallic thrust runner and the ceramic shaft on the turbine side.
    Type: Grant
    Filed: June 20, 2019
    Date of Patent: June 8, 2021
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B Jones, Edwin L Kite
  • 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: 10739233
    Abstract: A system and method for testing a combustor or other component of a large industrial gas turbine engine. A test facility for testing a gas turbine engine component includes a storage reservoir, a heat exchanger (13) with a first fluid flow passage connected to the storage reservoir and a second fluid flow passage, a combustor (18) connected to the second fluid flow passage of the heat exchanger (13), a hot gas stream from the combustor flowing within the second fluid flow passage, and a test component of a gas turbine engine connected to the second fluid flow passage of the heat exchanger (13). The compressed air from the storage reservoir (11) passes through the heat exchanger (13) first fluid flow passage and is preheated from the hot gas stream passing through the second fluid flow passage, and the preheated compressed air from the heat exchanger (13) passes into the test component for testing.
    Type: Grant
    Filed: September 26, 2016
    Date of Patent: August 11, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Joseph D. Brostmeyer, Russell B. Jones, James P. Downs
  • Patent number: 10641177
    Abstract: A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines.
    Type: Grant
    Filed: March 23, 2016
    Date of Patent: May 5, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Joseph D. Brostmeyer, Russell B. Jones, Justin T. Cejka, John A. Orosa, John E. Ryznic
  • Patent number: 10557497
    Abstract: An axial thrust load sensor for an axial thrust foil bearing used in a small gas turbine engine, the axial thrust load sensor having a axial thrust foil bearing plate and an intermediate washer plate and a load sensor plate arranged face to face to form the load sensor. The load sensor plate has three pedestals on a front side and three pedestals on a back side so that all six pedestals alternate at equal spacing. Next to each pedestal is a strain gauge connected to a controller. The controller regulates a supply of cooling air to the axial thrust bearing in order to control a thrust balance.
    Type: Grant
    Filed: June 20, 2019
    Date of Patent: February 11, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Russell B Jones
  • Publication number: 20200003115
    Abstract: A turbocharged gas turbine engine with an electric generator to provide electrical power for an aircraft (e.g., UAV) with multiple propulsor fans each driven by an electric motor, where the engine includes a low spool that drives a main fan and a high spool that drives a high speed electric generator. The low pressure compressor supplies low pressure air to an inlet of the high pressure compressor. A row of stator vanes in the high pressure turbine is cooled using cooling air bled off from the low pressure compressor outlet that is passed through an intercooler and a boost compressor, where the spent vane cooling air is discharged into the combustor. The low pressure turbine and the two compressors each include a variable inlet guide vane to control the power level of the engine. Bypass flow from the main fan is used to cool hot parts of the engine.
    Type: Application
    Filed: January 29, 2018
    Publication date: January 2, 2020
    Inventors: Russell B. Jones, Robert A. Ress, JR.
  • Publication number: 20190178160
    Abstract: A process for retrofitting an industrial gas turbine engine of a power plant where an old industrial engine with a high spool has a new low spool with a low pressure turbine that drives a low pressure compressor using exhaust gas from the high pressure turbine, and where the new low pressure compressor delivers compressed air through a new compressed air line to the high pressure compressor through a new inlet added to the high pressure compressor. The old electric generator is replaced with a new generator having around twice the electrical power production. One or more stages of vanes and blades are removed from the high pressure compressor to optimally match a pressure ratio split. Closed loop cooling of one or more new stages of vanes and blades in the high pressure turbine is added and the spent cooling air is discharged into the combustor.
    Type: Application
    Filed: May 15, 2017
    Publication date: June 13, 2019
    Inventors: Russell B. JONES, Joseph D. BROSTMEYER, Justin T. CEJKA, John E. RYZNIC
  • Publication number: 20190145314
    Abstract: An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.
    Type: Application
    Filed: April 24, 2017
    Publication date: May 16, 2019
    Inventors: John A OROSA, Joseph D BROSTMEYER, Russell B JONES, Justin T CEJKA
  • Patent number: 10208619
    Abstract: A turbine with a variable inlet guide vane assembly in which the vane airfoils extend between inner and outer buttons, and in which a center of rotation of the airfoil is located aft of an aerodynamic center of pressure of the airfoil. The trailing edge of the airfoil extends into both of the buttons such that no gap is formed between the airfoil trailing edge region and a static part of the turbine during movement of the airfoil from an opened position to a closed position.
    Type: Grant
    Filed: June 6, 2016
    Date of Patent: February 19, 2019
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B Jones, Barry J Brown, Stephen E Murray
  • Publication number: 20190041293
    Abstract: A system and method for testing a combustor or other component of a large industrial gas turbine engine. A test facility for testing a gas turbine engine component includes a storage reservoir, a heat exchanger (13) with a first fluid flow passage connected to the storage reservoir and a second fluid flow passage, a combustor (18) connected to the second fluid flow passage of the heat exchanger (13), a hot gas stream from the combustor flowing within the second fluid flow passage, and a test component of a gas turbine engine connected to the second fluid flow passage of the heat exchanger (13). The compressed air from the storage reservoir (11) passes through the heat exchanger (13) first fluid flow passage and is preheated from the hot gas stream passing through the second fluid flow passage, and the preheated compressed air from the heat exchanger (13) passes into the test component for testing.
    Type: Application
    Filed: September 26, 2016
    Publication date: February 7, 2019
    Applicant: Florida Turbine Technologies, Inc.
    Inventors: Joseph D. BROSTMEYER, Russell B. JONES, James P. DOWNS
  • Patent number: 10151211
    Abstract: An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.
    Type: Grant
    Filed: September 15, 2015
    Date of Patent: December 11, 2018
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Joseph D Brostmeyer, Russell B Jones
  • Publication number: 20180245512
    Abstract: An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.
    Type: Application
    Filed: February 28, 2017
    Publication date: August 30, 2018
    Inventors: Joseph D. Brostmeyer, Russell B. Jones, John A. Orosa
  • Patent number: 10053746
    Abstract: A method of repairing a worn carburized surface on a sprag clutch comprising the steps of: grinding the worn carburized surface of the sprag clutch to prepare the surface for metallurgical bonding; place the worn carburized surface in a PVD Cathodic Arc chamber; preheat the worn carburized surface to remove moisture and provide for a good metallurgical bonding surface; reverse sputter clean the surface to remove any surface oxide; apply a first coating layer using the PVD process to a maximum thickness; change the coating macro topology by polishing the coated surface; apply a second coating layer using the PVD process to a maximum thickness; and, grind or polish the coating to a desired dimension.
    Type: Grant
    Filed: October 31, 2016
    Date of Patent: August 21, 2018
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC.
    Inventors: Russell B Jones, Robert J. Wright
  • Publication number: 20180230815
    Abstract: A cooling circuit for a trailing edge region of a turbine airfoil where the trailing edge is relatively thin, the cooling circuit having a series of aftward flowing channels alternating with a series of forward flowing cooling channels, and a turn channel at the trailing edge of the airfoil where the aftward flowing channels flow into the forward flowing channels in order to keep the airfoil thin and to provide cooling to the thin trailing edge. Spanwise extending cooling supply channels and cooling return channels are connected to the aftward and forward flowing channels and positioned to allow for a thinner airfoil.
    Type: Application
    Filed: February 15, 2017
    Publication date: August 16, 2018
    Inventor: Russell B. Jones
  • Patent number: 10006293
    Abstract: A part formed using an metal additive manufacturing process such as a turbine airfoil with an oversized feature such as an oversized hole, where the oversized hole is filled with a preform having a shape of a normal sized hole and secured within the part using a braze or weld material, and where the preform is removed to leave within the part the normal sized hole. The preform is made of a refractory material that can be removed from the part by exposure to oxygen.
    Type: Grant
    Filed: July 22, 2015
    Date of Patent: June 26, 2018
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Russell B Jones
  • Patent number: 9964040
    Abstract: A spiral cooling system for cooling an aft turbine casing of a gas turbine engine. The gas turbine engine includes a turbine casing having a fore end and an aft end, a star bearing support member supporting a bearing housing and including a plurality of struts each mounted to an aft flange at the aft end of the turbine casing. The turbine casing includes an outer casing wall and an inner casing wall at the aft end defining an airflow plenum therebetween that receives cooling air at an input end opposite to the aft flange. The spiral cooling system includes a plurality of fins secured to an inside surface of the outer wall and being spaced from the inner wall that directs the airflow from the input end in a circular manner around the plenum to an output end of the plenum.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: May 8, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Russell B. Jones, Ross Peterson
  • Publication number: 20180066586
    Abstract: A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines.
    Type: Application
    Filed: March 23, 2016
    Publication date: March 8, 2018
    Inventors: Joseph D. BROSTMEYER, Russell B. JONES, Justin T. CEJKA, John A. OROSA, John E. Ryznic
  • Publication number: 20180010476
    Abstract: An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.
    Type: Application
    Filed: September 15, 2015
    Publication date: January 11, 2018
    Inventors: Joseph D. Brostmeyer, Russell B. Jones