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: 20170342854
    Abstract: A large frame heavy duty industrial gas turbine engine that can produce twice the power as a conventional single spool industrial engine, and can operate at full power during a hot day. The industrial engine includes a high spool that directly drives an electric generator at a synchronous speed of the electric power grid, a low spool with a low pressure turbine that drives a low pressure compressor from the exhaust gas from the high pressure turbine, where the low pressure compressor supplies compressed air to the high pressure compressor. Variable inlet guide vane assemblies are used in the low pressure turbine and the low pressure compressor so that the high spool can operate at full power even during a hot day. The low spool is designed to operate at a higher speed than at the normal temperature conditions so that a high mass flow can be produced for the high spool during the hot day conditions.
    Type: Application
    Filed: April 25, 2016
    Publication date: November 30, 2017
    Inventors: Barry J. Brown, Joseph D. Brostmeyer, Justin T. Cejka, Russell B. Jones
  • Publication number: 20170298826
    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: April 18, 2016
    Publication date: October 19, 2017
    Inventors: John E. Ryznic, Russell B. Jones, Joseph D. Brostmeyer, Justin T. Cejka
  • Patent number: 9771821
    Abstract: An interstage seal for a turbine of a gas turbine engine, the interstage seal having a seal carrier with an axial extending seal tooth movable with a stator of the engine, and a rotor with a seal surface that forms the interstage seal with the seal tooth, where a magnetic force produced by two magnets and a gas force produced by a gas pressure acting on the seal carrier forms a balancing force to maintain a close clearance of the seal without the seal tooth contacting the rotor seal surfaces during engine operation. In other embodiments, two pairs of magnets produce first and second magnetic forces that balance the seal in the engine.
    Type: Grant
    Filed: June 15, 2015
    Date of Patent: September 26, 2017
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC.
    Inventors: Jacob A Mills, Russell B Jones, Thomas D Sexton
  • Publication number: 20170241336
    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 17, 2016
    Publication date: August 24, 2017
    Inventors: Russell B. Jones, Joseph D. Brostmeyer, Justin T. Cejka, John E. Ryznic
  • Publication number: 20170234226
    Abstract: A combustor of an industrial gas turbine engine having a combustor secured within a combustor casing with a combustor cavity surrounding the combustor, and a flow liner forming a cooling air space between the casing and the flow liner in which high pressure cooling air can be passed to provide insulation to the casing from the high temperature gas surround the combustor. The flow liner can include a TBC or a layer of insulation to limit heat buildup of the cooling air flowing through the space to further insulate the casing.
    Type: Application
    Filed: November 1, 2016
    Publication date: August 17, 2017
    Inventor: Russell B. Jones
  • Publication number: 20170234152
    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: Application
    Filed: June 6, 2016
    Publication date: August 17, 2017
    Inventors: Russell B Jones, Barry J Brown, Stephen E Murray
  • Patent number: 9683444
    Abstract: An air hot part of a gas turbine engine, the hot part having an isogrid formed on a cool surface opposite to a hot surface, where an impingement plate bonded over multiple impingement cooling surfaces of the airfoil, where the impingement plate forms a series of double or triple impingement cooling for separate surfaces of the airfoil. The impingement plate can be shaped and sized to fit over an airfoil surface that requires multiple impingement cooling.
    Type: Grant
    Filed: December 5, 2014
    Date of Patent: June 20, 2017
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Russell B Jones
  • Patent number: 9638047
    Abstract: An air cooled turbine airfoil with an impingement plate bonded over multiple impingement cooling surfaces of the airfoil, where the impingement plate forms a series of double or triple impingement cooling for separate surfaces of the airfoil. The impingement plate can be shaped and sized to fit over an airfoil surface that requires multiple impingement cooling.
    Type: Grant
    Filed: November 5, 2014
    Date of Patent: May 2, 2017
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Russell B Jones
  • Publication number: 20170089264
    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: Application
    Filed: September 30, 2015
    Publication date: March 30, 2017
    Inventors: Russell B. Jones, Ross Peterson
  • Patent number: 9581028
    Abstract: An air cooled turbine stator vane form a small gas turbine engine in which the vane has an airfoil of less than one inch in spanwise height, where the airfoil is a hollow airfoil having an insert that forms a sequential impingement cooling circuit for the pressure side wall and then the suction side wall. The insert includes a plurality of cooling air supply channels connected together by ribs where pressure side impingement holes are formed in the cooling air supply channels and suction side wall impingement cooling holes are formed in the ribs.
    Type: Grant
    Filed: May 30, 2014
    Date of Patent: February 28, 2017
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC.
    Inventors: Russell B Jones, Alex Pinera
  • Publication number: 20170022905
    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 25, 2016
    Publication date: January 26, 2017
    Inventors: John A. Orosa, Joseph D. Brostmeyer, Justin T. Cejka, Russell B. Jones
  • Publication number: 20160215694
    Abstract: An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, where the low pressure spool is operated at high electrical demand to supply compressed air to the high pressure compressor of the high pressure spool, and where turbine exhaust is used to drive a second electric generator from steam produced in a heat recovery steam generator. The power plant can operate at 25% of peak load while keeping the unused parts of the power plant hot for easy restart when high power output is required.
    Type: Application
    Filed: September 11, 2014
    Publication date: July 28, 2016
    Inventors: Joseph D. BROSTMEYER, Justin T. CEJKA, Russell B. JONES
  • Patent number: 9394799
    Abstract: An air riding seal between a rotor and a stator in a turbine of a gas turbine engine, where an annular piston is movable in an axial direction within a housing that extends from the stator, and a bellows is secured to the annular piston to form a flexible air passageway from a compressed air inlet through the annular piston and into a cushion cavity that forms an air riding seal between the annular piston and the rotor sealing surface. In another embodiment, a flexible seal secured to and extending from the annular piston forms a sealing surface between the annular piston chamber and the annular piston to provide a seal and allow for axial movement.
    Type: Grant
    Filed: July 9, 2015
    Date of Patent: July 19, 2016
    Assignee: S & J DESIGN LLC
    Inventors: Jacob A Mills, Wesley D Brown, Thomas D Sexton, Russell B Jones
  • Patent number: 9353687
    Abstract: A gas turbine engine with a closed-loop liquid metal cooling fluid system for cooling stator vanes within the turbine, in which the stator vanes are made of a metallic material that will not react with the liquid metal cooling fluid. The stator vane may be made from a typical metal material such as ferrous metal alloys, nickel alloys or cobalt (Co) alloys, and an insert or liner made of molybdenum or tantalum may be placed inside to protect the outer vane material from reacting with a liquid metal such as bismuth, lead (Pb), indium, or alloy mixtures of thereof. In the case where the liquid coolant is bismuth, the liquid bismuth must be purged from the cooling system before the fluid cools and solidifies so the solidified bismuth does not expand and break the vanes.
    Type: Grant
    Filed: August 4, 2014
    Date of Patent: May 31, 2016
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Joseph D Brostmeyer, John W Appleby, Jr., Russell B Jones
  • Patent number: 8684668
    Abstract: A sequential impingement cooling insert for a turbine stator vane that forms a double impingement for the pressure and suction sides of the vane or a triple impingement. The insert is formed from a sheet metal formed in a zigzag shape that forms a series of alternating impingement cooling channels with return air channels, where pressure side and suction side impingement cooling plates are secured over the zigzag shaped main piece. Another embodiment includes the insert formed from one or two blocks of material in which the impingement channels and return air channels are machined into each block.
    Type: Grant
    Filed: November 26, 2012
    Date of Patent: April 1, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B Jones, Judson J Krueger, William L Plank
  • Patent number: 8511999
    Abstract: A turbine rotor blade of the spar and shell construction, the spar including a tip end with a dovetail shaped groove extending from the top, and a tip cap includes a dovetail shaped slot that engages with the spar groove to retain the tip cap in place. A shell made from a high temperature resistant material is secured in place between the platform and the tip cap. The platform includes a core extending into a hollow space formed by the shell and discharges impingement cooling air against the backside wall of the shell. The spar and the platform include fir tree configurations so that an assembled blade can be inserted into a slot of a rotor disk.
    Type: Grant
    Filed: March 25, 2010
    Date of Patent: August 20, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Keith D Kimmel, Jack W. Wilson, Russell B Jones
  • Patent number: 8500405
    Abstract: A turbine stator vane for an industrial engine, the vane having two impingement cooling inserts that produce a series of impingement cooling from the pressure side to the suction side of the vane walls. Each insert includes a spar with a row of alternating impingement cooling channels and return air channels extending in a radial direction. Impingement cooling plates cover the two sides of the insert and having rows of impingement cooling holes aligned with the impingement cooling channels and return air openings aligned with the return air channel.
    Type: Grant
    Filed: September 20, 2012
    Date of Patent: August 6, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B Jones, John A Fedock, Gloria E Goebel, Judson J Krueger, Christopher K Rawlings, Robert L Memmen
  • Patent number: 8444389
    Abstract: A multiple piece turbine rotor blade with a shell having an airfoil shape and secured between a spar and a platform with the spar including a tip end piece. a snap ring fits around the spar and abuts against the spar tip end piece on a top side and abuts against a shell on the bottom side so that the centrifugal loads from the shell is passed through the snap ring and into the spar and not through a tip cap dovetail slot and projection structure.
    Type: Grant
    Filed: March 30, 2010
    Date of Patent: May 21, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B Jones, John A Fedock
  • Patent number: 5752802
    Abstract: An improved airfoil tip sealing apparatus is disclosed wherein brush seals are attached to airfoil tips with the distal ends of the brush seal fibers sealingly contacting opposing wall surfaces. Embodiments for variable vanes, stators and both cooled and uncooled turbine blade applications are disclosed.
    Type: Grant
    Filed: December 19, 1996
    Date of Patent: May 19, 1998
    Assignee: Solar Turbines Incorporated
    Inventor: Russell B. Jones
  • Patent number: 5653579
    Abstract: The present gas turbine engine (10) includes a disc assembly (64) defining a disc (66) having a plurality of blades (70) attached thereto. The disc (66) has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc (66). A shroud assembly (100) is attached to the gas turbine engine (10) and is spaced from the plurality of blades (70) a preestablished distance forming an interface (108) therebetween. Positioned in the interface is a seal (110) having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades (70).
    Type: Grant
    Filed: November 14, 1995
    Date of Patent: August 5, 1997
    Assignee: Solar Turbines Incorporated
    Inventors: Boris Glezer, Narender K. Bhardwaj, Russell B. Jones