Axial Flow Runner With Blades Extending Radially Inward And Outward From Common Annulus Patents (Class 415/77)
  • Patent number: 11905853
    Abstract: An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.
    Type: Grant
    Filed: April 13, 2021
    Date of Patent: February 20, 2024
    Assignee: GE AVIO S.r.l.
    Inventors: Alberto Buonvino, Luca Giacobone, Daniele Coutandin, Ernesto Sozio, Francesco Bertini
  • Patent number: 11661943
    Abstract: A counter-rotating fan, comprising two impellers and a motor. The motor is used for driving the two impellers to rotate. The two impellers are axially spaced apart from each other, and are divided into a first-stage impeller and a second-stage impeller. When the counter-rotating fan operates, airflow is blown to the direction of the second-stage impeller by means of the first-stage impeller. At least one impeller has turns of blades arranged in the radial direction of the impeller. Blades of each turn are spaced apart from each other around a hub of the impeller, and a spacer ring is connected between two adjacent turns of blades. The counter-rotating fan is stable in rotation and good in cooling effect, it is not easy to deform, and the wind is strong in the center.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: May 30, 2023
    Inventors: Xiaowen Hu, Site Hu, Hui Zhang, Rong Yi
  • Patent number: 10774741
    Abstract: An aeronautical propulsion system including a turbine engine having a fan and an electric motor drivingly coupled to at least one of the fan or the turbine engine. The aeronautical propulsion system additionally includes a fuel cell for providing electrical energy to the electric motor, the fuel cell generating water as a byproduct. The aeronautical portion system directs the water generated by the fuel cell to the turbine engine during operation to improve an efficiency of the aeronautical propulsion system.
    Type: Grant
    Filed: January 26, 2016
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventor: Mohammed El Hacin Sennoun
  • Patent number: 10619483
    Abstract: An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.
    Type: Grant
    Filed: November 21, 2017
    Date of Patent: April 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Dmytro Mykolayovych Voytovych, Alexander Staroselsky, Om P. Sharma, Gabriel L. Suciu, Brian Merry, Ioannis Alvanos
  • Patent number: 9926883
    Abstract: A gas turbine engine for a small aircraft such as a UAV having a bypass flow with a variable area bypass nozzle located at an outlet of the bypass channel, the nozzle having one position with a maximum flow area and a second position with a minimal flow area. The compressor is a twin stream compressor with an inner flow path for compressed air to the combustor and an outer flow path for the bypass channel. A fan stage can be used in front of the compressor.
    Type: Grant
    Filed: May 17, 2017
    Date of Patent: March 27, 2018
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Robert A. Ress
  • Patent number: 9856740
    Abstract: An integrally bladed rotor for a gas turbine engine includes a hub, a plurality of blades radially extending from the hub and being integrally formed therewith. The hub having a rim from which the blades project and a pair of axially opposed split hub members extending at least radially inward from the rim. Each of the split hub members has a radially outer flex arm portion extending form the hub and a radially inner moment flange portion. At least one moment inducing element separately formed from the hub is mounted axially between the opposed split hub members and acts on the moment flange portions of the opposed split hub members to generate an inward bending moment on the flex arm portions of the opposed split hub members during rotation of the rotor, thereby deflecting the rim and the blades of the rotor radially inwardly.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: January 2, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Alexandre Ayers
  • Patent number: 9850794
    Abstract: A power generation system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; an airflow generation system coupled to an expander shaft downstream of the gas turbine system for drawing in a flow of ambient air through an air intake section; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; a flow directing system for directing the flow of ambient air generated by the airflow generation system to the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.
    Type: Grant
    Filed: June 29, 2015
    Date of Patent: December 26, 2017
    Assignee: General Electric Company
    Inventors: Parag Prakash Kulkarni, Lewis Berkley Davis, Jr., Robert Joseph Reed
  • Patent number: 8985967
    Abstract: A rotor is provided. The rotor comprises external blades for use in causing rotation of the rotor, and internal blades for use in propelling a fluid through the rotor during rotation of the rotor.
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: March 24, 2015
    Assignee: Vetco Gray Controls Limited
    Inventor: Gopalakrishna Gudivada
  • Patent number: 8770917
    Abstract: A wind power generation system with turbofans includes an air supply system, a composite structure with a turbofan, several generator components, a control device, and an air passage well. The air supply system is configured to rise the wind which enters into the wind power generation system, and further wind which is raised drives the composite structure with a turbofan to rotate; an operating gear ring connected to the composite structure with the turbofan rotates with it, and then the rotating turbofan drives a small gear in a generator component which engages with the operating gear ring to rotate with high speed. The generator begins to generate electricity when a required rotary speed of an electric generating set is achieved.
    Type: Grant
    Filed: July 10, 2013
    Date of Patent: July 8, 2014
    Assignee: Beijing Xiangtian Huachuang Aerodynamic Force Technology Research Institute Company Limited
    Inventors: Dengrong Zhou, Jian Zhou
  • Patent number: 8672614
    Abstract: Exhaust apparatus for exhausting “dirty” exhaust gases accept a core flow of such exhaust gases and combine that with an annularly-surrounding “rooftop” flow of ambient air for diluting the exhaust gases as well as expelling the diluted flow in a forcibly expelled plume in order to ensure that the “effective” expulsion distance of the expelled diluted flow is at least the physical length of the exhaust apparatus plus the gains gotten from efflux velocity and flowrate.
    Type: Grant
    Filed: February 2, 2009
    Date of Patent: March 18, 2014
    Assignee: Loren Cook Company
    Inventor: Erich R. Fitzpatrick
  • Patent number: 8556585
    Abstract: A cooling fan for cooling a mechanical section of a driving device attached to a rotary shaft including a plurality of blades configured to generate an airflow toward an outside of the rotary shaft in directions along radius directions of the rotary shaft with rotation of the rotary shaft, and a plurality of ribs that have widths in directions crossing the blades, extend toward outsides along the radius directions with respect to a center axis of the rotary shaft, reinforce the corresponding plurality of blades, and are directed on a side of the mechanical section at tips of the plurality of ribs, wherein at least parts of the blades exist inside the ribs along the radius directions of the ribs.
    Type: Grant
    Filed: May 21, 2012
    Date of Patent: October 15, 2013
    Assignee: Sumitomo Heavy Industries, Ltd.
    Inventors: Kazuhisa Abe, Shnsuke Miwa
  • Publication number: 20120076638
    Abstract: An axial turbomachine including a rotor-blade cascade is provided. The turbomachine includes a casing in which the cascade is installed and a guide-blade carrier which encloses the cascade and is integrated into the inner side of the housing. The guide-blade carrier is arranged immediately adjacently to the blade tips faulting a radial gap, wherein the guide-blade carrier is mounted in the housing, such that it may be displaced parallel to the axis of the axial turbomachine, and includes an adjusting ring which is supported on contact surfaces on the housing and guide-blade carrier and may be rotated about the axis, wherein the contact surfaces of the adjusting ring and of the housing and/or of the guide-blade carrier are set with respect to a plane perpendicular to the axis, so that, when the adjusting ring is rotated about the axis, the guide-blade carrier is displaced axially by the adjusting ring.
    Type: Application
    Filed: March 22, 2010
    Publication date: March 29, 2012
    Inventors: Francois Benkler, Andreas Böttcher, Uwe Kahlstorf, Torsten Matthias, Dieter Minninger, Oliver Schneider, Peter Schröder, Vyacheslav Veitsman
  • Patent number: 8128342
    Abstract: Exemplary embodiments provide an information system adapted to focus a plurality of audio messages to a plurality of different locations. As a consumer passes a display, their attention is attracted based on the series of messages. Further, a consumer can obtain more and different information as they change their position. Exemplary embodiments may also display a different image to the consumer depending on the position of the consumer relative to the display. Further embodiments may utilize touch-screen technology to allow a user to select an icon from the screen and obtain further information either through additional messages, video, or both.
    Type: Grant
    Filed: October 9, 2008
    Date of Patent: March 6, 2012
    Assignee: Manufacturing Resources International, Inc.
    Inventors: William Dunn, David Williams, Jerry Fraschilla
  • Patent number: 8104265
    Abstract: An representative gas turbine includes: a first annular gas flow path; a second annular gas flow path located radially outwardly from the first gas flow path; in series order, a multi-stage fan, radially inboard portions of a first set of high pressure compressor blades, a second set of high pressure compressor blades, a combustion section and a high pressure turbine, positioned along the first gas flow path; and in series order, the multi-stage fan and radially outboard portions of the first set of high pressure compressor blades, positioned along the second gas flow path such that the inboard portions of the first set of high pressure compressor blades, the second set of high pressure compressor blades, the combustion section and the high pressure turbine are not positioned along the second gas flow path.
    Type: Grant
    Filed: June 28, 2007
    Date of Patent: January 31, 2012
    Assignee: United Technologies Corporation
    Inventor: Daniel B. Kupratis
  • Patent number: 8037686
    Abstract: The invention is for a continuous-combustion, closed-cycle, gas turbine engine with a regenerator and a displacer. It has embodiments that remove heater and cooler interior volumes during gas compression, which enable it to scale well to very large sizes. Low combustion temperatures insure very low emissions. The displacer levitated by an integral gas bearing and small clearance seal and given oscillatory translational motion by electromagnetic forces operates without surface wear. The turbine blades, subjected only to warm gases, are durable and inexpensive. Thus, this engine has a very long, continuous, maintenance-free service life. This gas turbine engine also operates without back work allowing high efficiency for both low and rated output. Pressurized encapsulation permits use of low-cost ceramics for high temperature components. The invention includes a unique monolithic ceramic heater, a compact high-capacity regenerator and a constant-power gas turbine.
    Type: Grant
    Filed: July 3, 2007
    Date of Patent: October 18, 2011
    Inventor: George Lasker
  • Patent number: 7988407
    Abstract: An axial fan is provided. The axial fan includes a base, a rotor, a guide and a plurality of blades. The guide connects to a guide tube to provide airflow. Each blade has a passive part and an active part, wherein the passive part is driven by the airflow from the guide to rotate the active part synchronously. The axial fan increases air quantity and decreases air pressure to provide efficient heat dissipation.
    Type: Grant
    Filed: March 31, 2006
    Date of Patent: August 2, 2011
    Assignee: Delta Electronics Inc.
    Inventors: Wei-Chun Hsu, Shun-Chen Chang, Wen-Shi Huang
  • Patent number: 7921635
    Abstract: A tip turbine engine (40) provides a peripheral combustor (30) with a more efficient combustion path through the combustor and through the tip turbine blades (34). In the combustor, the core airflow is received generally axially from compressor chambers in hollow fan blades (28) and then turned radially outwardly into a combustion chamber (112), where it is then mixed with the fuel and ignited. The combustor has a combustion path extending axially from a forward end of its combustion chamber through a combustion chamber outlet (122) and through a turbine (32) mounted to the fan. Thus, when the core airflow begins to expand in a high-energy gas stream, it has a substantially axial path from the combustion chamber through the turbine.
    Type: Grant
    Filed: December 1, 2004
    Date of Patent: April 12, 2011
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, James W. Norris, Craig A. Nordeen, Brian Merry
  • Fan
    Publication number: 20100290890
    Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.
    Type: Application
    Filed: October 6, 2008
    Publication date: November 18, 2010
    Applicant: BRONSWERK HEAT TRANSFER B.V.
    Inventor: Augustinus Wilhelmus Maria Bertels
  • Patent number: 7828511
    Abstract: An axial tip turbine driven pump in which a first fluid pumped by an inducer is driven by a second fluid that reacts with a turbine blade extending from a shroud on the inducer. The inducer includes a set of screw thread blades and a second set of partial blades that are covered by a shroud in the aft section of the inducer. A row of turbine blades extends from the shroud and into a manifold that forms the outer casing for the pump. The fluid flow through the manifold reacts with the turbine blades and drives the inducer to pump the fluid from the inlet and through guide vanes downstream from the inducer. The fluid passing through the turbine blades is collected in an outlet collector manifold and discharged into the fluid flowing through the guide vanes. The inducer with the turbine blades is rotatably supported within the housing formed by the guide vane support member and the manifold casing. The swirl flow direction of the turbine blades is opposite to that of the swirl flow in the inducer.
    Type: Grant
    Filed: March 18, 2008
    Date of Patent: November 9, 2010
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Alex Pinera, Frank W Huber
  • Patent number: 7758303
    Abstract: A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges.
    Type: Grant
    Filed: July 31, 2006
    Date of Patent: July 20, 2010
    Assignee: General Electric Company
    Inventors: Aspi Rustom Wadia, Alan Glen Turner, Aaron Michael Dziech, Peter Nicholas Szucs, John Jared Decker
  • Patent number: 7686579
    Abstract: A ducted fan includes a fan that generates an airflow that flows substantially parallel with the axis of the rotating shaft of the fan; a duct, arranged around the fan, that extends in the direction of the rotating shaft of the fan and includes an airflow inlet defined by the upstream end and an airflow outlet defined by the downstream end, and that has a ramp portion formed in the inner face of the airflow inlet; an airflow guide portion, provided at the airflow outlet, that introduces air from outside of the duct to a position downstream of the airflow outlet; and a negative-pressure forming portion, provided at the downstream end of the airflow guide portion. The negative-pressure forming portion generates a negative pressure near the downstream end of the airflow guide portion when air passes by the negative-pressure forming portion.
    Type: Grant
    Filed: August 2, 2006
    Date of Patent: March 30, 2010
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventor: Masatsugu Ishiba
  • Patent number: 7618232
    Abstract: This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F1) and a secondary flow (F2). This volume (V) comprises a plurality of annular segments in the form of cells separated in pairs by blades of a first fan, these blades passing through both the primary flow (F1) and the secondary flow (F2). These cells are fixed to an upstream annular collar and a downstream annular collar driven rotationally by the aforementioned blades.
    Type: Grant
    Filed: August 21, 2006
    Date of Patent: November 17, 2009
    Assignee: Snecma
    Inventors: Eric Stephan Bil, Gilles Alain Marie Charier
  • Patent number: 7603839
    Abstract: The pump system extracts motive power from oil in the pressurized oil circuit to power a scavenge pump mounted on a scavenge oil circuit.
    Type: Grant
    Filed: December 22, 2005
    Date of Patent: October 20, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Kevin Allan Dooley
  • Publication number: 20090246003
    Abstract: A turbocharger having a sliding piston for regulating exhaust gas flow into the turbine wheel includes a set of first vanes mounted on a fixed first wall of the turbine nozzle and projecting axially toward an opposite second wall of the nozzle, and/or a set of second vanes mounted on the end of the piston and projecting in an opposite axial direction toward the first wall of the nozzle. For the/each set of vanes, there are leakage dams formed on the wall that is adjacent the vane tips when the piston is closed. The leakage dams are closely adjacent the vane tips and discourage exhaust gas from leaking in a generally radial direction past the vane tips as the piston just begins to open from its fully closed position.
    Type: Application
    Filed: March 28, 2008
    Publication date: October 1, 2009
    Inventors: Quentin Roberts, Ahmed Alnega
  • Patent number: 7500352
    Abstract: A gas turbine engine (2) comprises a fan unit (4,18,36,42,44,46) in flow relationship with an engine core and a bypass duct, of which said engine core and bypass duct (16) are in parallel flow relationship with each other. The engine core comprises a compressor (6), a combustor (8) and a turbine (10), with an inner casing (12) provided around said engine core which defines the engine core intake (32). The bypass duct (16) is defined by an outer casing (14) radially spaced apart from the fan unit (4,18,36,42,44,46) and the inner casing (12) along at least part of the length of the gas turbine engine (2). Bypass air compression means (28) are provided such that, under substantially all engine power conditions, air at exit from the bypass duct (16) is at a greater pressure than air delivered to the engine core intake (32).
    Type: Grant
    Filed: May 23, 2005
    Date of Patent: March 10, 2009
    Assignee: Rolls-Royce PLC
    Inventor: Stephen J. Bradbrook
  • Patent number: 7484929
    Abstract: Exhaust apparatus for exhausting “dirty” exhaust gases accept a core flow of such exhaust gases and combine that with an annularly-surrounding “rooftop” flow of ambient air for diluting the exhaust gases as well as expelling the diluted flow in a forcibly expelled plume in order to ensure that the “effective” expulsion distance of the expelled diluted flow is at least the physical length of the exhaust apparatus plus the gains gotten from efflux velocity and flowrate.
    Type: Grant
    Filed: July 11, 2005
    Date of Patent: February 3, 2009
    Assignee: Loren Cook Company
    Inventor: Erich R. Fitzpatrick
  • Patent number: 7470105
    Abstract: A cylindrical rotor with internal blades, configured by a ring of variable diameter and length according to necessity, as well as the blade quantity, pitch, surface and angle in its interior, being the assembly made of different materials.
    Type: Grant
    Filed: August 23, 2005
    Date of Patent: December 30, 2008
    Inventor: João Bosco de Oliveira
  • Patent number: 7120019
    Abstract: A structure for cooling an electronic component includes a heat sink attached to the component, an inner air duct extending into a central portion of the heat sink, and an outer air duct extending into an outer portion of the heat sink. In inner fan, within the inner air duct, moves air in one direction, while an outer fan, in the outer air duct, moves air in the other direction. The fans may be built as separate rotors, or as separate portions of a single rotor.
    Type: Grant
    Filed: August 18, 2004
    Date of Patent: October 10, 2006
    Assignee: International Business Machines Corporation
    Inventors: Jimmy Grant Foster, Sr., Michael Sean June, Albert Vincent Makley, Jason Aaron Matteson
  • Patent number: 7037089
    Abstract: A cooling fan with dual blade sets has an impeller formed by a rotatable hub, a stator assembly, and a shell. A plurality of mini blades and a plurality of guide blades are respectively formed on a bottom surface and an external surface of the rotatable hub. The impeller has a plurality of holes defined on the bottom surface being arranged in a circle adjacent to the mini blades. Therefore when the impeller rotates, the mini blades are able to drive out the heat in an inner space between the impeller and the shell through the holes to outside.
    Type: Grant
    Filed: May 25, 2004
    Date of Patent: May 2, 2006
    Inventor: Hsin-Mao Hsieh
  • Publication number: 20020182053
    Abstract: A low-noise axial fan is provided with whining sound minimized. The axial fan includes a plurality of blades arranged around a rotation axis at predetermined layout pitches. The blades are arranged at varied layout pitches. For instance, the layout pitch between the two adjacent blades may be different from the layout pitch between the remaining blades. This arrangement controls the whirring sound of the fan, which would be high in level if the blades were arranged at an equal layout pitch. A low-noise axial fan thus results.
    Type: Application
    Filed: January 26, 2001
    Publication date: December 5, 2002
    Inventor: Atsushi Miyazawa
  • Patent number: 4969326
    Abstract: An axial flow compressor for a bypass type jet engine has a low pressure stage which includes a one-piece, annular hoop shroud mounted to the airfoil of each of the rotor blades in the low pressure stage to divide the airflow entering the compressor into an outer, bypass airflow path and an inner airflow path directed to the higher pressure stages of the compressor. The hoop shroud is formed of circumferentially wound, parallel fibers such as silicone carbide fibers embedded in a metal matrix material such as titanium, wherein the volume ratio of the hoop shroud is approximately one-third fibers and two-thirds metal matrix material.
    Type: Grant
    Filed: August 15, 1988
    Date of Patent: November 13, 1990
    Assignee: General Electric Company
    Inventors: William D. Blessing, Richard W. Stickles
  • Patent number: 4846261
    Abstract: The present invention relates to a heat exchange machine for removing the excess of the heat during the summer period and the excess of humidity during the cold period. The machine comprises two tubes, one inside the other, an intermediate frame with two sets of blades attached to the frame from inside and outside thereof and driven by a common reversible motor in the same direction. One of these sets is the set of blades rigidly fixed to and the other one is swingingly mounted in the frame, so that the change of the direction of the fixed set of blades induces the change of the direction of the air flow in one of the tubes, meanwhile the direction of the air flow along the other tube induced by the other set of swingable blades remains the same regardless of the direction of rotation of this set.
    Type: Grant
    Filed: November 18, 1987
    Date of Patent: July 11, 1989
    Assignee: Karjasuo Oy
    Inventor: Ilmari Kittila
  • Patent number: 4826403
    Abstract: A power turbine (12) comprises alternate annular arrays of contra-rotatable turbine blades. Two arrays of turbine blades (30) and (47) have annular arrays of aerofoil propulsion blades (17,18) respectively attached thereto. Alternate arrays of turbine blades are attached to a primary drum member (55) in such a manner that below normal operating temperatures, limited relative radial movement is permitted between them. However when the normal operating temperature is reached, the relative radial movement is inhibited in such a manner that the rigidity of the power turbine (12) enhanced.
    Type: Grant
    Filed: May 14, 1987
    Date of Patent: May 2, 1989
    Assignee: Rolls-Royce plc
    Inventor: Ronald Catlow
  • Patent number: 4734008
    Abstract: An open-vane regenerative impeller for a fuel pump. The impeller has a ring-like body portion from which a plurality of open-vane impeller vanes extend radially out and a plurality of fan blades extend radially in. The impeller is disposed in a closed cavity between two pump bodies with the vanes in an annular pumping chamber and the fan blades in a cylindrical vapor collection chamber radially inboard of the pumping chamber. The fan blades operate to blow vapor out of the vapor collection chamber through a vapor discharge slot in one of the pump bodies when rotation of the impeller commences thereby to enhance the initial vacuum at the inlet port to the pumping chamber.
    Type: Grant
    Filed: June 20, 1986
    Date of Patent: March 29, 1988
    Assignee: General Motors Corporation
    Inventor: Robert A. Roth
  • Patent number: 4724670
    Abstract: A turbine engine includes an elongated motor having a power source and a drive shaft. A first compressor connected to a fuel inlet, and a second compressor having an air inlet are coaxially mounted for rotation upon the motor. An elongated casing for the second compressor terminates in an intermediate casing which defines a pair of diffuser chambers, and terminates in a turbine casing having a converging exhaust outlet. Pressurized high velocity vaporized fuel and compressed air are delivered into the diffuser chambers and through a plurality of fuel injectors to continuously feed air and combustible fuel into an elongated combustion chamber member which is rotatably mounted within the turbine casing. One end of the combustion chamber member extends into and is journaled upon the intermediate casing.
    Type: Grant
    Filed: December 17, 1984
    Date of Patent: February 16, 1988
    Assignee: Josie M. Greer, administratrix
    Inventor: David Greer
  • Patent number: 4288983
    Abstract: A turbofan configuration for a gas turbine engine is disclosed. Various construction details which improve engine performance by supercharging working medium gases to the engine core are discussed. Engines configured in accordance with the present invention include an island splitter which is disposed across the fan flow path. The island splitter is spaced apart from the core engine case. A supercharging, compression stage is driven commonly with the fan stage and extends outwardly into proximity with the core case.
    Type: Grant
    Filed: October 19, 1978
    Date of Patent: September 15, 1981
    Assignee: United Technologies Corporation
    Inventor: Thomas E. O'Rourke, Jr.
  • Patent number: 4165949
    Abstract: In a turbine for a compressible fluid in which the fluid flow leaving the tepenultimate stage is separated into two coaxial flows, the inner flow passes through both the penultimate and the final stages of the turbine while the outer flow passes through the final stage only. This high efficiency arrangement for the last stages of a high power turbine exploits the advantages made available by using titanium as the blade material.
    Type: Grant
    Filed: August 4, 1977
    Date of Patent: August 28, 1979
    Assignee: Groupe Europeen pour la Technique des Turbines a Vapeur G.E.T.T.
    Inventor: Gilbert Riollet
  • Patent number: 4055949
    Abstract: A dual-flow or multiflow gas turbine power plant comprising a jet pipe, at east two separate flow-ducts each opening into the jet pipe, namely a first flow-duct through which passes, in operation, a first gas flow and which contains a gas generator of the gas turbine type and an expansion-turbine located downstream of the gas generator, and a second flow-duct through which passes, in operation, a second gas flow and a mixer device in which the first gas flow leaving the expansion turbine, and the second gas flow, are arranged to be mixed prior to entering the jet pipe, the plant further comprising a recompressor located downstream of the mixer device, in which the mixture of the two gas flows is arranged to be recompressed before entering the jet pipe.
    Type: Grant
    Filed: May 3, 1976
    Date of Patent: November 1, 1977
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation
    Inventor: Serge Boudigues
  • Patent number: 4055042
    Abstract: A gas turbine engine has a core engine which drives a fan, the fan comprising a main rotor stage and a stub rotor stage whose blades have a smaller radial extent than those of the main rotor stage. The main and stub stages of the fan both compress air to form a main fan airflow and a stub stage airflow respectively, the stub stage airflow being divided into two portions one of which rejoins the main fan airflow and one of which enters the core engine intake. In order to match the flow angles of the various flows, the stub stage has inner and outer outlet guide vanes which give different degrees of deflection to the two component portions of the stub stage airflow.
    Type: Grant
    Filed: July 8, 1976
    Date of Patent: October 25, 1977
    Assignee: Rolls-Royce Limited
    Inventor: Rowan Herbert Colley
  • Patent number: 3968647
    Abstract: A dual-flow or multiflow gas turbine power plant comprising a jet pipe, at east two separate flow-ducts each opening into the jet pipe, namely a first flow-ducts through which passes, in operation, a first gas flow and which contains a gas generator of the gas turbine type and an expansion-turbine located downstream of the gas generator, and a second flow-ducts through which passes, in operation, a second gas flow and a mixer device in which the first gas flow leaving the expansion turbine, and the second gas flow, are arranged to be mixed prior to entering the jet pipe, the plant further comprising a recompressor located downstream of the mixer device, in which the mixture of the two gas flows is arranged to be recompressed before entering the jet pipe.
    Type: Grant
    Filed: May 7, 1974
    Date of Patent: July 13, 1976
    Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation
    Inventor: Serge Boudigues