Patents Assigned to Florida Turbine Technologies, Inc.
  • Turbine blade with impingement cooling cavities and platform cooling channels connected in series
    Patent number: 8734108
    Abstract: A turbine rotor blade with impingement cooling cavities for the airfoil and serpentine flow cooling channels for the platform of the blade. Two impingement cavities provide cooling for the forward section of the airfoil while another two impingement cavities provide cooling for the aft section of the airfoil. Both impingement cavity cooling circuits are connected in series to platform cooling channels that use the same cooling air to cool the platform. The spent cooling air from the platform cooling channels is discharged into a dead rim cavity as purge air for the blade. The blade with the impingement cavities and the platform serpentine flow cooling channels are all formed as a single piece from a metal printing process.
    Type: Grant
    Filed: November 22, 2011
    Date of Patent: May 27, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine vane with leading edge fillet region cooling
    Patent number: 8727725
    Abstract: A turbine vane for use in a gas turbine engine, the vane including an airfoil portion and an endwall in which fillets extend around the airfoil at the junction to the endwall. A row of film cooling holes that connects to a cooling air supply cavity on the outer side of the endwall and open into breakout holes that are located in the fillets discharge film cooling air into the fillet. The breakout holes extend around the leading edge in the fillet and extend along the pressure side fillet and the suction side fillet just past the leading edge region to discharge film cooling air into the fillets. The film cooling holes are straight holes and are aligned with the curvature of the fillet at the midpoint height of the fillet.
    Type: Grant
    Filed: January 22, 2009
    Date of Patent: May 20, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Multiple staged compressor with last stage airfoil cooling
    Patent number: 8721265
    Abstract: A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by passing cooling air through the airfoils without discharging film cooling air. A portion of the compressed air from the discharge of the compressor is bled off and passed through a heat exchanger to preheat a fuel and to cool the compressed air. The cooled compressed air is then passed through the last stage airfoil of the compressor to provide cooling. The cooling air is then reintroduced back into the compressor at an earlier stage or passed through an airfoil in the turbine to provide cooling.
    Type: Grant
    Filed: July 19, 2013
    Date of Patent: May 13, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Joseph D Brostmeyer, John E Ryznic
  • Turbine rotor blade with multi-vortex tip cooling channels
    Patent number: 8708645
    Abstract: A turbine rotor blade with a tip section having a pressure side and suction side tip rail that forms a squealer pocket. A number of chordwise extending ribs formed within the squealer pocket form vortex cooling channels that extend from the leading edge region and open along the pressure side tip peripheral wall. A row of tip cooling holes opens into each of the vortex cooling channels to discharge cooling air and form a vortex flow within the channels that provides both sealing and cooling for the blade tip.
    Type: Grant
    Filed: October 24, 2011
    Date of Patent: April 29, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine stator vane
    Patent number: 8702375
    Abstract: A stator vane for an industrial turbine, the vane includes a serpentine flow cooling circuit for cooling of the airfoil, and two separate purge air channels to supply air to the rim cavities. The purge channels are formed as separate channels from the serpentine flow channels so that the purge air is not heated by the hot metal and has smooth surfaces so that pressure losses is minimal.
    Type: Grant
    Filed: May 19, 2011
    Date of Patent: April 22, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Sequential cooling insert for turbine stator vane
    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
  • Turbine blade with near wall cooling channels
    Patent number: 8678766
    Abstract: A turbine rotor blade with a low flow cooling circuit that includes a number of upward flowing and downward flowing near wall cooling channels connected by tip floor near wall cooling channels to provide cooling for the walls of the blade. Cooling air is supplied from the root supply cavity and flows through the near wall channels and then discharges into a collector cavity formed within the airfoil walls. The spent cooling air is then discharged through trailing edge exit holes to cool the trailing edge region.
    Type: Grant
    Filed: July 2, 2012
    Date of Patent: March 25, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Tip cap for a turbine rotor blade
    Patent number: 8678764
    Abstract: A turbine rotor blade with a spar and shell construction, and a tip cap that includes a row of lugs extending from a bottom side that form dovetail grooves that engage with similar shaped lugs and grooves on a tip end of the spar to secure the tip cap to the spar against radial displacement. The lug on the trailing edge end of the tip cap is aligned perpendicular to a chordwise line of the blade in the trailing edge region in order to minimize stress due to the lugs wanting to bend under high centrifugal loads. A two piece tip cap with lugs at different angles will reduce the bending stress even more.
    Type: Grant
    Filed: October 27, 2009
    Date of Patent: March 25, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Keith D Kimmel
  • Mini sized combined cycle power plant
    Patent number: 8640437
    Abstract: A mini combined cycle power plant with a mini gas turbine engine that operates at around 20,000 to 30,000 rpm and is connected to an electric generator through a speed reduction gear box, a low pressure steam turbine connected directly to the gas turbine engine, a high pressure steam turbine connected to the low pressure steam turbine through a smaller gear box so that the high pressure steam turbine can operate at around 70,000 to 100,000 rpm, and a heat recovery steam generator to use the turbine exhaust to produce high pressure steam for the two steam turbines. Leftover heat from the HRSG is used to heat homes or buildings in the local area to the power plant to improve the overall efficiency of the plant.
    Type: Grant
    Filed: February 24, 2011
    Date of Patent: February 4, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Joseph D Brostmeyer
  • Industrial turbine blade with platform cooling
    Patent number: 8641377
    Abstract: A turbine rotor blade for an industrial gas turbine engine with a platform cooling circuit that flows from the suction side of the platform and around both the leading edge and trailing edge of the platform, and then along the pressure side platform to cover the entire platform surface. The cooling air flows along smaller diameter cooling holes that cover substantially the entire pressure side platform surface and is then discharged out through openings onto the pressure side mate-face.
    Type: Grant
    Filed: February 23, 2011
    Date of Patent: February 4, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Industrial turbine blade with platform cooling
    Patent number: 8641368
    Abstract: A turbine rotor blade with a platform hot spot cooling circuit that includes a bracket occupying a space below the platform on the pressure side of the blade neck and forming a cooling air supply hole connected to the blade cooling air supply channel and opening into an impingement cavity located below a hot spot location on the pressure side platform surface. A number of film cooling holes are connected to the impingement cavity and open onto the platform surface to cool the hot spot location.
    Type: Grant
    Filed: January 25, 2011
    Date of Patent: February 4, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine exhaust cylinder and strut cooling
    Patent number: 8641362
    Abstract: A turbine exhaust cylinder for an industrial gas turbine engine with an external blower that delivers cooling air to an inner space of the exhaust cylinder that provides cooling for the struts that support the exhaust cylinder. The cooling air passes over the bearing housing and then up through a space formed between a fairing and the strut. The cooling air is then discharged through a cover plate.
    Type: Grant
    Filed: September 26, 2011
    Date of Patent: February 4, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine vane with endwall cooling
    Patent number: 8632298
    Abstract: A turbine stator vane with an endwall cooling circuit that includes a first ten-pass serpentine flow cooling circuit and a second ten-pass serpentine flow cooling circuit. Each serpentine circuit is connected to cooling air feed holes supplied from an endwall impingement cavity, where cooling air serpentines along the leading edge section of the endwall, along the two mate faces, and then serpentines along the trailing edge section where the cooling air is discharged from exit holes spaced along the trailing edge side of the endwall.
    Type: Grant
    Filed: March 21, 2011
    Date of Patent: January 21, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine rotor blade with serpentine cooling
    Patent number: 8628298
    Abstract: A turbine rotor blade has a number of serpentine flow cooling circuits to provide cooling to forward and aft sections of the airfoil and to upper span and lower span sections of the airfoil in order to provide specific cooling to directed sections of the airfoil. A common cooling air supply channel extends the entire spanwise length of the airfoil and supplies cooling air to each of the serpentine flow cooling circuits.
    Type: Grant
    Filed: July 22, 2011
    Date of Patent: January 14, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine stator vane with purge air channel
    Patent number: 8628294
    Abstract: A stator vane for an industrial turbine, the vane includes a serpentine flow cooling circuit for cooling of the airfoil, and a separate purge air channel to supply purge air to the rim cavities. The purge channel is formed as a separate channel from the serpentine flow channels so that the purge air is not heated by the hot metal and has smooth surfaces so that pressure losses is minimal.
    Type: Grant
    Filed: May 19, 2011
    Date of Patent: January 14, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine blade platform with impingement cooling
    Patent number: 8622701
    Abstract: A turbine rotor disk with rotor blades secured within slots, where the rotor disk includes a radial extension that occupies a space where a dead rim cavity would be formed, and in which the radial extension includes a cooling air chamber with impingement cooling air holes directed to discharge impingement cooling air to a backside surface of the platforms of the blades.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: January 7, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine blade with cooling air inlet holes
    Patent number: 8622702
    Abstract: A turbine rotor blade with a root section having a cooling air feed hole opening onto a bottom surface of the root section of the blade. The feed hole includes a clam shell shape with a forward side wider than an aft side of the feed hole, and the feed hole is sloped upward from the forward side to the aft side to form a scoop so that cooling air flowing along a live rim cavity in a rotor disk will more easily flow into the feed holes with less loss of pressure.
    Type: Grant
    Filed: April 21, 2010
    Date of Patent: January 7, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Inter-propellant thrust seal
    Patent number: 8622690
    Abstract: An inter-propellant thrust seal for a rocket engine with purge fluid introduced into purge chambers to prevent mixing of reactive fluids located outside of bearings, and where one of the purge chambers is formed by an axial thrust piston on the rotor shaft so that the purge fluid in that chamber will also produce axial thrust on the rotor shaft.
    Type: Grant
    Filed: December 1, 2010
    Date of Patent: January 7, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Andrew P Wall
  • High temperature turbine stator vane
    Patent number: 8622692
    Abstract: A high temperature resistant turbine stator vane with an airfoil section made from oxide dispersion strengthened (ODS) material extruded through a die, an internal cooling circuit is machined into the airfoil section after the extrusion, and then two endwalls are formed separately and then secured to the airfoil section ends to form the stator vane. Film cooling holes can be drilled into the airfoil section and the endwalls.
    Type: Grant
    Filed: December 13, 2010
    Date of Patent: January 7, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Turbine blade with tip cooling circuit
    Patent number: 8616845
    Abstract: A turbine rotor blade with a forward flowing serpentine flow cooling circuit in the airfoil and a serpentine flow cooling circuit formed within the blade tip formed in series to provide cooling air flow through the airfoil and then through the blade tip. Cooling air from the airfoil serpentine circuit is bled off to provide cooling of the trailing edge region through T/E exit slots. The tip serpentine cooling circuit includes legs on the pressure and suction side walls with tip edge cooling holes to provide layers of film cooling air for the blade tip rails. A separate cooling air circuit is used in the leading edge region to provide convection cooling, impingement cooling and film cooling for the leading edge region.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: December 31, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang