Slinger Type Patents (Class 60/745)
  • Patent number: 10578116
    Abstract: A rotational body 1 includes a rotational shaft 2, an impeller 3, and a nut 6. The impeller includes a hub portion 4 having a peripheral surface 4s inclined to the axial direction of the rotational shaft and having an insert hole 4h in which the rotational shaft is inserted, and a blade portion 5. At least one of the rotational shaft or the insert hole of the hub portion has an interference fit portion 10 for fit between the rotational shaft and the impeller, where the outside diameter of the rotational shaft is larger than the inside diameter of the insert hole of the hub portion. The interference fit portion is formed in a region which does not include the largest outside diameter portion 4B where the hub portion has a largest outside diameter, with the rotational shaft and the impeller mating with each other.
    Type: Grant
    Filed: December 11, 2013
    Date of Patent: March 3, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Noriyuki Hayashi, Makoto Ozaki, Nariaki Seike, Hiroshi Kanki, Hiroshi Suzuki
  • Patent number: 10443847
    Abstract: A sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing dilution air to hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow direction. The mixer guides combustion gases in a hot gas flow path extending from the first combustion chamber. The second burner including a duct having an inlet for connection to the first combustion chamber and an outlet for connection to the second burner. The mixer includes injection pipes pointing inwards from the side walls for admixing the dilution air to cool the hot gases leaving the first combustion chamber. The injection pipes are distributed circumferentially along the side wall of the mixer. The injection pipes have a conical or quasi-conical shape addressed to the center of the mixer.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: October 15, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Andrea Ciani, Adnan Eroglu
  • Patent number: 9464527
    Abstract: Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade. A blade outlet duct provides for fluid communication between the forward hollow interior portion and a forward cavity of the bladed rotor, and a rotor outlet duct provides for discharging the fuel from a radially-inboard portion of the forward cavity.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: October 11, 2016
    Assignee: Williams International Co., LLC
    Inventors: Robert S. Thompson, Jr., Gregg G. Williams, David W. Jarrell, Curtis E. Lynch, Mark E. Suchezky
  • Publication number: 20140260296
    Abstract: A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion chamber has a fuel atomization zone extending radially outwardly from the fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone. A plurality of nozzle air inlets are defined in the fuel atomization zone of the combustor shell. The nozzle air inlets have a nozzle axis intersecting the stream of fuel and a tangential component in a direction of rotation of the fuel slinger. A plurality of dilution holes are defined in the combustor shell and have a dilution axis intersecting the combustion zone. The dilution axis of at least some of the dilution holes has a tangential component opposite to the direction of rotation of the fuel slinger.
    Type: Application
    Filed: March 12, 2013
    Publication date: September 18, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: PRATT & WHITNEY CANADA CORP.
  • Patent number: 8820092
    Abstract: Fuel (12) is supplied to a rotatable portion (118) of a gas turbine engine (10) comprising a rotor (24) and at least one blade (26, 26.1) operatively coupled thereto, so as to provide for cooling at least one of the rotor (24) or the at least one blade (26, 26.1) by transforming the fuel (12) to a vapor or gaseous state. The fuel (12) is discharged in a vapor or gaseous state from the rotatable portion (118) directly into a combustion chamber (16) of the gas turbine engine (10).
    Type: Grant
    Filed: April 9, 2009
    Date of Patent: September 2, 2014
    Assignee: Williams International Co., L.L.C.
    Inventors: Robert S. Thompson, Jr., Gregg Williams, David W. Jarrell, Curtis E. Lynch, Mark E. Suchezky
  • Patent number: 8776525
    Abstract: The present invention provides in one embodiment a unique gas turbine engine. Another embodiment is a unique gas turbine engine combustion system. Still another embodiment is a unique gas turbine engine combustor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine combustion systems and combustors.
    Type: Grant
    Filed: December 22, 2010
    Date of Patent: July 15, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Victor L. Oechsle
  • Patent number: 8677728
    Abstract: A gas turbine engine (10) comprises a diffuser (14) and a nozzle (16) affixed to an annular housing (12), a bearing assembly including first and second bearings (24,26) mounted on a support tube (28) affixed at one end (28a) in cantilever fashion to a radially inner portion (16c) of the nozzle, a compressor (18) and a turbine (20) affixed to axially spaced apart ends of a shaft (22) rotatably mounted in the bearings, and an annular combustor (32) disposed between the compressor and turbine and concentric to the shaft. The diffuser is adjustably attached to the housing external threads (14e) on an outer annular surface of the diffuser and received in internal threads (12e) in an internal annular surface of the housing. An electric generator (42) is disposed radially inward of the annular combustor axially between the diffuser and nozzle. A fuel slinger (30), affixed to the shaft, receives fuel from an air/fuel annulus (88) defined by a stator (44) and a rotor (46) of the generator.
    Type: Grant
    Filed: March 4, 2004
    Date of Patent: March 25, 2014
    Assignee: Technical Directions, Inc
    Inventors: Joseph J. Kovasity, Vern E. Brooks
  • Patent number: 8677731
    Abstract: A hybrid combustor combines two distinct fuel injection sources to spray fuel in the combustor. The combustor combines a rotary fuel slinger for spraying fuel in a first combustion zone during high power level and cruise conditions and a set of fuel nozzles for spraying fuel in a second combustion zone during lower power level and starting conditions.
    Type: Grant
    Filed: June 12, 2013
    Date of Patent: March 25, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Patent number: 8666632
    Abstract: A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering module per stage of the multistage combustor. Each fuel metering module includes a pump, a flow meter, a pressure sensor, a controller, and a motor, which work together to control fuel output.
    Type: Grant
    Filed: April 20, 2011
    Date of Patent: March 4, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Thaddeus J. Zebrowski, Richard E. Versailles
  • Patent number: 8479492
    Abstract: A hybrid combustor combines two distinct fuel injection sources to spray fuel in the combustor. The combustor combines a rotary fuel slinger for spraying fuel in a first combustion zone during high power level and cruise conditions and a set of fuel nozzles for spraying fuel in a second combustion zone during lower power level and starting conditions.
    Type: Grant
    Filed: March 25, 2011
    Date of Patent: July 9, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Patent number: 8327644
    Abstract: A micro gas turbine engine for use in a turbo heater or co-generation application is described. The micro gas turbine engine includes a fuel delivery system which minimizes the development of deposits in the air-fuel passageway. To this end, a fuel delivery channel formed between a fuel deflector and a slinger body is formed with a contoured or undulating surface. A fuel deflector ring is interposed between the fuel delivery channel and the slinger impeller to facilitate the flow of the air-fuel mixture into the combustion chamber.
    Type: Grant
    Filed: November 6, 2009
    Date of Patent: December 11, 2012
    Assignee: JHRG Inc.
    Inventors: Richard W. Gordon, Nancy Ann Gordon, legal representative
  • Patent number: 8276388
    Abstract: An annular expansion ring centered on a main axis and suitable for being mounted on a fuel injector coaxial with the ring is disclosed. The ring presents holes that are distributed around the main axis and open out into its upstream face to enable air to pass towards the zone that is downstream from the ring. The ring includes a conical annular groove that converges downstream, that is open downstream, and that has the holes opening out into the upstream portion thereof. The axis of each of the holes makes an angle relative to the main axis that is strictly greater than the angle between the generator line of the cone defining the annular groove and the main axis, such that the air exiting from the holes impacts against the inner wall of the annular groove, i.e. its wall that is closer to the main axis.
    Type: Grant
    Filed: July 1, 2008
    Date of Patent: October 2, 2012
    Assignee: Snecma
    Inventors: Alain Cayre, Christophe Pieussergues, Jackie Raymond Julien Prouteau, Denis Jean Maurice Sandelis
  • Publication number: 20120240588
    Abstract: A hybrid combustor combines two distinct fuel injection sources to spray fuel in the combustor. The combustor combines a rotary fuel slinger for spraying fuel in a first combustion zone during high power level and cruise conditions and a set of fuel nozzles for spraying fuel in a second combustion zone during lower power level and starting conditions.
    Type: Application
    Filed: March 25, 2011
    Publication date: September 27, 2012
    Inventors: Bhawan B. PATEL, Oleg MORENKO
  • Patent number: 8006500
    Abstract: A combustor for a small gas turbine engine in which a compressor discharges a swirling air flow into the combustor, and a fuel impeller is rotatably connected to the compressor and slings atomized fuel into the combustor in a direction to produce a stagnation zone within the combustor. A plurality of fuel injectors delivers fuel to the inlet end of the fuel impeller. The combustor outlet is a nozzle shape that produces a high enough pressure level in the swirl air flow such that the cooler air flows along the inner combustor wall to form an insulation layer from the hot combustor gas flow within the combustor. The fuel impeller produces a very fine mist of fuel and the stagnation zone produced results in easy starting of the engine and stable combustor burning.
    Type: Grant
    Filed: January 29, 2008
    Date of Patent: August 30, 2011
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Jack W. Wilson, III
  • Patent number: 7942006
    Abstract: A combustion system includes a combustor having a forward annular liner having a first plurality of effusion holes, and an aft annular liner having a second plurality of effusion holes and forming a combustion chamber with the forward annular liner. The first plurality of effusion holes and the second plurality of effusion holes are adapted to receive compressed air from a compressor and contribute to a single toroidal recirculation air flow pattern in the combustion chamber. The combustion system further includes a rotary fuel slinger further adapted to receive a flow of fuel from a fuel source and to centrifuge the received fuel into the combustion chamber; and an igniter extending at least partially into the combustion chamber to ignite the fuel and compressed air in the combustion chamber, to thereby generate combusted gas.
    Type: Grant
    Filed: March 26, 2007
    Date of Patent: May 17, 2011
    Assignee: Honeywell International Inc.
    Inventors: Ian L. Critchley, Frank J. Zupanc
  • Patent number: 7762072
    Abstract: A combustion system includes a fuel manifold adapted to receive a flow of fuel from a fuel source, the fuel manifold including at least one orifice from which the received fuel is discharged. The combustion system further includes a rotary fuel slinger disposed adjacent to the fuel manifold. The rotary fuel slinger includes a coupler shaft and a slinger disc coupled to the coupler shaft. The slinger disc includes a first portion disposed generally perpendicular to the coupler shaft and a second portion disposed at an angle to the first portion. The fuel manifold is positioned relative to the rotary fuel slinger such that the discharged fuel impinges on the second portion. The rotary fuel slinger is configured to rotate such that the flow of fuel is centrifuged radially outwardly from the second portion onto the first portion and subsequently off the rotary fuel slinger to atomize the received fuel.
    Type: Grant
    Filed: January 16, 2007
    Date of Patent: July 27, 2010
    Assignee: Honeywell International Inc.
    Inventors: Ian L. Critchley, Paul R. Yankowich, Kenneth R. Tyrer
  • Patent number: 7685822
    Abstract: A rotary cup fuel injector for use in a gas turbine engine, the rotary cup injector being rotatably secured to the rotor shaft and positioned radially inward of the combustor, the rotary cup injector having a front face with a parabolic shape and a rear face with a slanted and flat shape. The front and rear faces of the injector form a thin film of fuel on the surfaces and—because of the high rotational speed—produce fine droplet's of fuel to be injected into a combustion chamber. The two faces inject fuel into two combustion zones of the combustor.
    Type: Grant
    Filed: November 9, 2005
    Date of Patent: March 30, 2010
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Mark M. Harris
  • Publication number: 20090071161
    Abstract: A combustion system includes a combustor having a forward annular liner having a first plurality of effusion holes, and an aft annular liner having a second plurality of effusion holes and forming a combustion chamber with the forward annular liner. The first plurality of effusion holes and the second plurality of effusion holes are adapted to receive compressed air from a compressor and contribute to a single toroidal recirculation air flow pattern in the combustion chamber. The combustion system further includes a rotary fuel slinger further adapted to receive a flow of fuel from a fuel source and to centrifuge the received fuel into the combustion chamber; and an igniter extending at least partially into the combustion chamber to ignite the fuel and compressed air in the combustion chamber, to thereby generate combusted gas.
    Type: Application
    Filed: March 26, 2007
    Publication date: March 19, 2009
    Applicant: HONEYWELL INTERNATIONAL, INC.
    Inventors: Ian L. Critchley, Frank J. Zupanc
  • Publication number: 20080184707
    Abstract: A fuel manifold is provided for receiving a flow of fuel from a fuel source and delivering the flow of fuel to a rotary fuel slinger. The fuel manifold can include a housing having an end face and defining a cavity for receiving the flow of fuel; at least one exit orifice formed in the housing end face and in fluid communication with the cavity; and a fuel drip guide extending from the end face.
    Type: Application
    Filed: October 27, 2006
    Publication date: August 7, 2008
    Inventors: Frank J. Zupanc, Ian L. Critchley
  • Patent number: 7036321
    Abstract: An auxiliary power unit (APU) includes a rotary fuel slinger, and a single-spool, two-stage turbine. The rotary fuel slinger receives a rotational drive force from the turbine, and a supply of fuel from a fuel source. The rotary fuel slinger injects the fuel into a combustor as a continuous “fuel sheet.” As a result, fuel mixing and atomization inside the combustor is improved, which reduces emissions and pattern factor, which in turn increases turbine life.
    Type: Grant
    Filed: April 30, 2004
    Date of Patent: May 2, 2006
    Assignee: Honeywell International, Inc.
    Inventors: Rodolphe Dudebout, David H. Edmonds, Frank J. Zupanc, Roger J. DeRudder, Mario Scaini, Victor M. Reyes
  • Patent number: 6983606
    Abstract: An integrated gas turbine compressor and rotary fuel injector is provided which includes a rotary cup combustor having an atomizing element for dispersal and distribution of fuel throughout the combustor. The combustor is positioned in close proximity to the compressor impeller of a gas turbine engine having a centrifugal compressor. The rear face of the impeller, or the rear face of an attachment to the impeller, is contoured to receive the fuel supply. The contour terminates at a lip disposed at a larger radius from the centerline shaft than conventional shaft-mounted slingers. The larger radius of fuel release provides better fuel atomization due to larger rim speeds, thereby improving combustor performance.
    Type: Grant
    Filed: September 9, 2003
    Date of Patent: January 10, 2006
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Wesley Brown
  • Patent number: 6925812
    Abstract: A radially-extending arm is adapted to rotate within a stream of first fluid flowing thereacross. In one embodiment, the arm comprises a plurality of lands located at different radial distances from the axis of rotation, and a port located on each land is operatively coupled to a source of a second fluid. The second fluid is sprayed from the rotating arm into the stream of first fluid that flows across the lands, and is thereby atomized. In another embodiment, the arm comprises a land stepped into the trailing edge thereof, and a port for injecting the second fluid is located on the land. In another embodiment, the land comprises a groove located between the port and an associated riser surface stepped into the trailing edge. In another embodiment, the arm comprises a port in the trailing edge thereof from which the second fluid is injected, and a groove is located on the trailing edge in a radially increasing direction from the port.
    Type: Grant
    Filed: May 22, 2003
    Date of Patent: August 9, 2005
    Assignee: Williams International Co., L.L.C.
    Inventors: Jamey J. Condevaux, Guido J. Defever
  • Patent number: 5526640
    Abstract: A gas turbine engine (20) comprises a diffuser (24) and a nozzle (26) affixed to a cylindrical housing member (22), a bearing assembly (34) including a support tube (36) affixed at one end (36a) in cantilever fashion to a radially inner portion (26c) of the nozzle, a compressor (28) and a turbine (30) affixed to axially spaced apart ends of a shaft (32) rotatably mounted therebetween in the support tube by antifriction bearings, and an annular combustion chamber (40) disposed between the compressor and turbine and concentric to the shaft. A fuel slinger (38), affixed to the shaft, receives fuel from an air/fuel annulus (96) defined by the support tube and shaft. An air/fuel mixture in the annulus also lubricates the bearings and cools a hub portion (30a) of the turbine. Movement of the mixture through the air/fuel annulus is enhanced by pumps (38c, 102, 104 and 312).
    Type: Grant
    Filed: May 16, 1994
    Date of Patent: June 18, 1996
    Assignee: Technical Directions, Inc.
    Inventors: Vern E. Brooks, Richard Chute
  • Patent number: 5323602
    Abstract: An annular combustor for a gas turbine engine having a rotatable fuel slinger has a first plurality of effusion cooling holes for directing air flow radially inwardly toward said fuel slinger and circumferentially in the direction of rotation of the fuel slinger and a second plurality of effusion cooling holes on the opposite side of the fuel slinger for directing air radially inwardly and circumferentially in the direction of rotation of the fuel slinger, thereby to produce a pair of annular axially spaced helical air flow patterns having a confluence in the direction of fuel flow radially outwardly from the fuel slinger.
    Type: Grant
    Filed: May 6, 1993
    Date of Patent: June 28, 1994
    Assignee: Williams International Corporation
    Inventor: Guido J. Defever
  • Patent number: 5224339
    Abstract: A small gas turbine engine for generating thrust and shaft horsepower is provided. The engine is comprised in a flow series arrangement of an inlet, a diffuser, a single stage compressor, a fuel slinger combustor, a single stage turbine, and an exhaust nozzle. The compressor circumscribes the turbine and is mounted on the same rotating wheel so that the flow of air in the compressor is in the direction opposite to the direction of hot gas flow in the turbine. Accordingly, both the compressor and turbine are on the same side of the combustor and hence only a single bearing support structure is required.
    Type: Grant
    Filed: December 19, 1990
    Date of Patent: July 6, 1993
    Assignee: Allied-Signal Inc.
    Inventor: Jeffrey M. Hayes
  • Patent number: 5042256
    Abstract: A fuel pump within the main shaft of a turbine engine comprises a fuel tube extending axially through the shaft, a first shaft wall and the second shaft wall spaced apart from each other at one end of the tube to define a flow passage therebetween, a plurality of substantially radially aligned vanes extending across the passageway, an annular cavity in fluid communication with the outlet of the vaned passageway and a plurality of circumferentially spaced injector nozzles in fluid communication with the annular cavity and opening into the combustion chamber of turbine engine. The pump vanes impart sufficient energy to the fuel to overcome friction losses in the injector nozzles and to overcome the pressure within the combustor chamber. In addition, the energy imparted to the fuel forms a fuel barrier which separates the combustor chamber pressure from pressure within the fuel tube.
    Type: Grant
    Filed: July 28, 1986
    Date of Patent: August 27, 1991
    Assignee: Teledyne Industries, Inc.
    Inventor: Raymond Smith
  • Patent number: 4870825
    Abstract: A fuel slinger for a gas turbine is provided with a hydraulic fuel trap within the U-shaped cross section thereof to inject fuel metered by a low pressure fuel system into a combustion chamber at relatively higher pressure.
    Type: Grant
    Filed: June 9, 1988
    Date of Patent: October 3, 1989
    Assignee: Williams International Corporation
    Inventor: William I. Chapman
  • Patent number: 4819424
    Abstract: A ramjet combustor operates on a slurry fuel that is atomized to 25 microns or less droplet size. A ram air turbine drives a fuel slinger which injects the fuel into the swirl stabilized ramjet combustor.
    Type: Grant
    Filed: September 16, 1987
    Date of Patent: April 11, 1989
    Assignee: Williams International Corporation
    Inventor: Michael J. Bak
  • Patent number: 4769996
    Abstract: A fuel pumping and transfer system for a multiple concentric shaft gas turbine engine which has the capability to handle contaminated or slurry fuels. The fuel is introduced into the innermost shaft at any desired low pressure thereby eliminating the need for a high pressure fuel pump. Fuel is introduced through a rotating fuel tube disposed within the inner shaft of the engine. The centrifugal force caused by rotation of the shafts causes the fuel to be collected against the inner wall of the shaft creating a centrifugal pressure dam. As the fuel passes from one collection region to the next the differential pressure between the inner shaft region and the combustor increases sufficiently to provide proper combustion.
    Type: Grant
    Filed: January 27, 1987
    Date of Patent: September 13, 1988
    Assignee: Teledyne Industries, Inc.
    Inventor: Dennis E. Barbeau
  • Patent number: 4598544
    Abstract: A medium bypass turbofan engine including a fan mounted on a low pressure shaft and positioned at the inlet of the engine; an intermediate pressure single-stage axial compressor carried by the low pressure shaft and positioned to receive a working airstream portion of the air discharged by the fan; a single-stage high pressure centrifugal compressor positioned to receive the output of the intermediate pressure compressor and carried by a high pressure shaft received telescopically over the low pressure shaft; an annular burner positioned to receive the output of the high pressure compressor; an annular slinger carried by the low pressure shaft and arranged to inject fuel into the burner; a high pressure single-stage axial turbine positioned to receive the output of the burner and carried by the high pressure shaft; and a low pressure multi-stage axial turbine positioned to receive the output of the high pressure turbine and carried by the low pressure shaft.
    Type: Grant
    Filed: April 28, 1983
    Date of Patent: July 8, 1986
    Assignee: Williams International Corporation
    Inventors: Sam B. Williams, John F. Jones, David K. Dorer
  • Patent number: 4429527
    Abstract: A turbine engine having a combustor premix system for mixing fuel and air to provide increased efficiency by reducing temperature peaks in the combustor. The system includes a primary mixing chamber for mixing compressed air and atomized fuel and a secondary mixing chamber located between the primary mixing chamber and the combustor for mixing additional compressed air to the fuel-air mixture. The secondary mixing chamber comprises a plurality of tubes with air metering ports in the walls thereof and a control assembly to vary the air flow to the ports for off design engine operating conditions, and optimizes fuel-air mixtures for the combustor at all engine operating speeds improving fuel economy and exhaust pollution control. The primary mixing chamber is located adjacent to and between the compressor for the air and the combustor so that the fuel-air mixture flowing therethrough tends to cool the compressor and the chamber itself shields the compressor from radiant heat from the combustor.
    Type: Grant
    Filed: June 19, 1981
    Date of Patent: February 7, 1984
    Inventor: J. Michael Teets
  • Patent number: 4257236
    Abstract: A liquid atomizing device comprises a nozzle emitting the liquid to be atomized, and a hollow cylindrical atomizing member secured at one end to a rotary shaft coaxially therewith for rotation about its own axis. The atomizing member has a circular cylindrical inner surface coaxially encircling the rotary shaft. According to one embodiment, the inner surface has a uniform diameter, while it is of dual diameter according to another embodiment. The nozzle faces the inner surface of the atomizing member to direct a jet of liquid thereagainst. The atomizing member is provided at another end thereof, which is open and defines an outlet for the atomizing member, with a plurality of radially inwardly projecting arcuate rims which are circumferentially equally spaced apart from one another to define an arcuate recess between each adjoining pair of rims.
    Type: Grant
    Filed: March 16, 1979
    Date of Patent: March 24, 1981
    Assignee: Toyota Jidosha Kogyo Kabushiki Kaisha
    Inventor: Teru Morishita
  • Patent number: 4255935
    Abstract: A liquid atomizing device comprises a cylindrical body provided with an inner cylinder having a cylindrical inner peripheral surface and an outer cylinder secured to the front end of said inner cylinder and having a cylindrical inner peripheral surface concentric with the inner peripheral surface of the inner cylinder. The inner peripheral surface of the outer cylinder has a larger diameter than that of the inner cylinder. The device includes a nozzle injecting a liquid against the inner peripheral surface of the inner cylinder during rotation of both of said cylinders at a high speed.
    Type: Grant
    Filed: October 23, 1978
    Date of Patent: March 17, 1981
    Assignee: Toyoto Jidosha Kogyo Kabushiki Kaisha
    Inventor: Teru Morishita
  • Patent number: 4232526
    Abstract: A rotating slinger fuel injector for turbine engines is provided with a plurality of radial holes for distributing and mixing fuel and air throughout the combustor. Fuel is supplied from a stationary fuel manifold through fuel ports in a rotating slinger which distributes the fuel in a plurality of planes throughout the combustor. Air is channeled from the compressor rotor through radially and axially angled air ports provided in the slinger so as to distribute air in a plurality of planes which intersect the planes of distributed fuel at various points throughout the interior combustor. Thus the combustion intensity and efficiency is greatly increased.
    Type: Grant
    Filed: December 26, 1978
    Date of Patent: November 11, 1980
    Assignee: Teledyne Industries, Inc.
    Inventor: Dennis E. Barbeau
  • Patent number: 4188780
    Abstract: A fuel system particularly for a gas turbine engine in which a tubular shaft rotatable during operation of the engine at engine speed or at a speed proportional thereto has a fuel inlet through which liquid fuel is introduced into the interior of the shaft, the peripheral wall of the shaft having at least one port therein communicating externally of the shaft with a combustion region of the engine and comprising a first resiliently-supported valve member mounted on the outside of the peripheral wall of the shaft in registration with the port to move away from the shaft centrifugally as the speed of rotation of the shaft increases, thereby to open the port and thus to allow fuel to flow through the port to the combustion region.
    Type: Grant
    Filed: October 20, 1977
    Date of Patent: February 19, 1980
    Assignee: Noel Penny Turbines Limited
    Inventor: Robert N. Penny