Patents Assigned to Florida Turbine Technologies, Inc.
  • Patent number: 10801338
    Abstract: An air cooled integrally bladed rotor with single crystals turbine rotor blades having cooling air passages formed into an equiax rotor disk, where a mold having expendable Molybdenum tooling and reusable molybdenum tooling is used to form the IBR. An annular blade ring with openings is used to secure the single crystal rotor blades within the mold, and a number of tube tools are inserted into a bottom end of each blade that forms a cooling air supply passage within the rotor disk. Two molybdenum circular shaped hubs are used to secure a bottom end of the tube tools with the mold. The mold is filled with metal powder and high pressure is used to solidify the powder to form the IBR. Expendable tooling is removed using sublimation when exposed to oxygen. Reusable tooling is reused to form additional IBRs.
    Type: Grant
    Filed: July 18, 2018
    Date of Patent: October 13, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Robert L Memmen
  • Patent number: 10794190
    Abstract: An air cooled integrally bladed rotor with bore entry cooling holes for a small gas turbine engine cast using a ceramic core having an axial bore forming piece with a plurality of radial extending spokes that end in an annular ring to form cooling air supply passages for air cooled turbine blades. Bulbous chambers are formed in a circumferential cooling air supply channel formed below each blade, where cooling air holes are drilled from a tip of each blade and into the bulbous chambers. The radial spokes have an elliptical cross sectional shape with a major axis perpendicular to a rotational axis of the central bore of the IBR. A spacing of the inlet openings in the bore are minimized to reduce stress.
    Type: Grant
    Filed: July 30, 2018
    Date of Patent: October 6, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Robert L Memmen, William L Plank
  • 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: 10731485
    Abstract: An air cooled integrally bladed rotor with single crystals turbine rotor blades having cooling air passages formed into an equiax rotor disk, where a mold having expendable Molybdenum tooling and reusable molybdenum tooling is used to form the IBR. An annular blade ring with openings is used to secure the single crystal rotor blades within the mold, and a number of tube tools are inserted into a bottom end of each blade that forms a cooling air supply passage within the rotor disk. Two molybdenum circular shaped hubs are used to secure a bottom end of the tube tools with the mold. The mold is filled with metal powder and high pressure is used to solidify the powder to form the IBR. Expendable tooling is removed using sublimation when exposed to oxygen. Reusable tooling is reused to form additional IBRs.
    Type: Grant
    Filed: February 4, 2020
    Date of Patent: August 4, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Robert L Memmen
  • Patent number: 10704391
    Abstract: A small aero gas turbine engine with an axial thrust limiter device that uses compressed air acting on a rotating disk extending from a rotor of the engine in which a forward pressure chamber and an aft pressure chamber applies a pressure to both sides of the rotating disk. When rotor is shifted, one side of the rotating disk has an increase in pressure acting on it to shift the rotor in an axial direction. Each pressure chamber includes an upper variable restriction and a lower variable restriction in which the restriction varies due to axial movement of the rotor. A forward and an aft foil bearing can also be used in addition to axial balance the rotor when not enough pressure is available such as at engine startup.
    Type: Grant
    Filed: May 24, 2017
    Date of Patent: July 7, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Joseph Brostmeyer
  • 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: 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: 10634153
    Abstract: A turbopump is formed from a metal additive manufacturing process in which both the housing and the impeller are formed as a single piece with the impeller trapped within the single piece housing. The impeller is formed with an axial bore and a shaft is secured by a tie bolt on one end to secure forward and aft bearings within the housing after the impeller and housing have been formed.
    Type: Grant
    Filed: June 6, 2016
    Date of Patent: April 28, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Alex Pinera, Stephen M Brooks, Timothy J Miller
  • Patent number: 10584795
    Abstract: An axial assembled interlocking labyrinth seal with a rotor and a stator each having a series of separate spiral shaped teeth with a gap formed on each of the separate teeth, so that the rotor can be rotated within the stator and axially advanced by aligning the gaps of the teeth on the rotor with gaps on the stator so that the axial labyrinth seal can be assembled.
    Type: Grant
    Filed: March 29, 2017
    Date of Patent: March 10, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Ross H Peterson
  • Patent number: 10578159
    Abstract: A self-metering hydrostatic thrust bearing for a small gas turbine engine. The thrust bearing can provide thrust capacity in the fore and aft directions of a hydrostatic thrust bearing using a single source of air. The air supply is directed towards the loaded bearing and away from the unloaded bearing by the self-metering mechanism operated by the thrust load.
    Type: Grant
    Filed: April 5, 2019
    Date of Patent: March 3, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Stephen M Brooks
  • Patent number: 10570758
    Abstract: An aero gas turbine engine with a last stage turbine disc of a solid bore design. The solid bore turbine disc includes a center tie bolt that attaches to an upstream face of the solid bore disc. The attachment location is under the bore of the upstream stage. The aft side of the solid disc creates a stub shaft upon which a bearing is directly mounted. No fasteners pass through the solid bore disc. Omission of outboard fasteners allow for ease of assembly, reduced cost, reduced weight, and a reduced part count.
    Type: Grant
    Filed: May 18, 2018
    Date of Patent: February 25, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Andrew P Wall, Edwin L Kite, Alex Pinera
  • 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
  • Patent number: 10533610
    Abstract: An aero gas turbine engine with a fan stage and a bearing rotatably supporting the fan stage, where the bearing is cooled by passing cooling air through the bearing, and the spent bearing cooling air is re-injected into the air flow path at a location where the effect is minimalized. The location is just downstream from a leading edge of a stator vane and along a pressure side surface of the vane. A fine mist of oil can be discharged into the bearing cooling air to also lubricate the bearing, where both the oil and the spent cooling air is reintroduced into the air flow path.
    Type: Grant
    Filed: May 1, 2018
    Date of Patent: January 14, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Ross H Peterson, John A Orosa, Robert A Ress, Jr.
  • Patent number: 10436209
    Abstract: A turbomachine such as a turbocharger with an air journal bearing and an air thrust bearing arrangement with a fixed air journal bearing connected in series with a floating air journal bearing connected by a hollow spring to supply compressed air from the fixed air journal bearing to the floating air journal bearing, and a forward air thrust bearing and an aft air thrust bearing connected in parallel to a source of compressed air. An air vent cavity is formed between the forward bearing and the aft bearing in which compressed air from all four bearings can be collected and discharged from a housing. Some of the compressed air from the forward thrust bearing is discharged with a compressor outlet, and some of the compressed air from the aft thrust bearing is discharged into a turbine inlet.
    Type: Grant
    Filed: February 10, 2017
    Date of Patent: October 8, 2019
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC.
    Inventors: Alex Pinera, Stephen M Brooks
  • Patent number: 10288520
    Abstract: An apparatus and a process for testing a large combustor or a high Mach aero vehicle in a wind tunnel, where liquid air stored in a tank is pumped to a high pressure above 1,500 psi, then vaporized to produce gaseous air at the same high pressure, where the high pressure gaseous air is then heated to a high temperature and then passed into a combustor for testing or passed through a converging diverging nozzle and then into a wind tunnel to produce a non-vitiated gaseous air flow of at least Mach 5 for testing of an aero vehicle. Water can be added to the high pressure liquid air to produce an air flow having a normal water content.
    Type: Grant
    Filed: May 23, 2017
    Date of Patent: May 14, 2019
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC
    Inventors: Timothy J Miller, John E Ryznic
  • Patent number: 10233768
    Abstract: A power plant for an aircraft such as an unmanned aero vehicle in which a gas turbine engine drives an electric generator to produce electrical power for a system load of the aircraft. An engine control unit monitors engine performance and regulates engine power output through fuel flow control to a combustor. A power control module regulates power output of the generator to the system load and to a battery through a bus. A pulse width modulation is used between the power control module and the bus to optimize performance of the gas turbine engine instead of adjusting fuel flow to the combustor.
    Type: Grant
    Filed: March 22, 2018
    Date of Patent: March 19, 2019
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Oran A. Watts, III, John W Polywoda, III
  • 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
  • Patent number: 10209146
    Abstract: An apparatus and a process for experimentally determining a heat transfer coefficient of a surface which includes a duct having an outer passage for water flow and an inner passage for air flow, the two passages separated by a thin wall membrane such that the water flow establishes a datum temperature on the thin wall membrane, and where air flowing through the second passage and over the thin wall membrane surface which can include heat transfer enhancements features will be heated by the features, and where the heat transfer coefficient can be determined from the surface temperature of the thin wall membrane and the change in temperature of the air flow. The duct with the thin wall membrane and heat transfer enhancement features is produced using a plastic or metallic additive manufacture process for low cost and quit turnaround time.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: February 19, 2019
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC
    Inventors: Christopher K Rawlings, Phillip M Redman, Bryan C Bernier, James P Downs
  • 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