Including Mechanical Air Compressor Or Air Flow Inducing Means Patents (Class 60/269)
  • Patent number: 10822103
    Abstract: An aircraft propulsor assembly includes a fan having a nacelle and plural fan blades radially disposed within the nacelle. The fan blades are configured to be rotated by torque generated by a turbine engine of an aircraft to generate thrust for propelling the aircraft. The assembly also includes an electric motor including a stator in the nacelle of the fan and a rotor in tips of two or more of the fan blades. The electric motor is configured to generate torque that also rotates the fan blades to generate thrust for propelling the aircraft. The assembly also includes a controller configured to reduce or prevent an increase in an operating temperature of the turbine engine of the aircraft by automatically supplanting at least some of the torque generated by the turbine engine with the torque generated by the electric motor.
    Type: Grant
    Filed: August 9, 2017
    Date of Patent: November 3, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Narendra Digamber Joshi, Michael Solomon Idelchik
  • Patent number: 10766628
    Abstract: This disclosure relates to an air inlet for an aircraft with an integrated hand hold. One innovative aspect of the subject matter described herein can be implemented as an air inlet on the exterior surface of a cowling for a rotorcraft, wherein the air inlet having a scoop that includes a bottom surface having a wide, flat, front edge that angles downward towards the back, an opening in the back for air to enter, and two lateral sides coupled to the bottom surface, where the two sides are planar on a top surface and become longer in height towards the opening in the back, and hand hold, where the hand hold is a trough or an indentation in the bottom surface of the scoop that extends along a side.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: September 8, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brent Scannell, Thomas Mast
  • Patent number: 10746188
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool. The LP spool has an LP shaft for transferring a torque from an LP turbine to an LP compressor. The HP spool has an HP shaft for transferring a torque from an HP turbine to an HP compressor. The LP shaft is coaxially mounted inside the HP shaft. An inter-shaft bearing is mounted radially between the LP shaft and the HP shaft. The inter-shaft bearing is disposed axially between the HP compressor and the LP compressor.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: August 18, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ian A. MacFarlane, Sean Powers, Martin Poulin, Jean-Jacques Forest
  • Patent number: 10539073
    Abstract: This invention performs the gas pressurization task of a centrifugal compressor gas turbine engine in a new way. In this invention gas compression takes place by using pinwheel-like thrusters to induce a very high velocity full forced vortex in the gas being compressed. Much higher “tip” velocities can be achieved because no strength-limited solid centrifugal impeller is required to spin up the gas. Due to the consequent very high vortex velocity a single stage pressure ratio of twenty five to one, or more, may be possible. Because there is no high pressure turbine, the gas pressure delivered to some downstream useful work device is much higher than is the case with conventional gas turbine engines. The invention's compressor requires no major moving parts except for the gas flow. The consequence is that the invention is predicted to have substantially better performance and general characteristics than conventional gas turbine engines.
    Type: Grant
    Filed: March 20, 2017
    Date of Patent: January 21, 2020
    Inventor: Chester L Richards, Jr.
  • Patent number: 10138940
    Abstract: A roller bearing cage that includes a cylindrical body including a plurality of pocket holes defined within and positioned circumferentially about the cylindrical body. Each pocket hole includes a pair of side portions and a pair of end portions meeting with the pair of side portions at a corner portion. The corner portion is contoured with a compound radius.
    Type: Grant
    Filed: August 9, 2016
    Date of Patent: November 27, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Fabio Nonato de Paula, Yi Han, Joseph Robert Dickman
  • Patent number: 9021784
    Abstract: The thermodynamic louvered jet engine is a jet engine having a central air inlet surrounded by an annular air inlet. Both inlets are adapted to receive relatively cool, low-pressure air and to convey the air to a combustion chamber to mix and combust with injected jet fuel. The annular inlet is provided with a louvered outlet for directing the air to the combustion chamber. A portion of the hot combustion gases produced in the combustion chamber is circulated from the combustion chamber to mix with the inlet air supplied via the annular air inlet. Also, the central air inlet is provided with structure that directs a portion of the air from the central air inlet to mix with the circulated combusted gases. This arrangement permits the engine to develop a high-pressure build-up of exhaust gases, producing superior thrust while the aircraft is setting and while the aircraft is in flight.
    Type: Grant
    Filed: February 12, 2014
    Date of Patent: May 5, 2015
    Inventor: Thomas H. Sharpe
  • Publication number: 20150000252
    Abstract: A propulsion system and methods are presented. A substantially tubular structure comprises a central axis through a longitudinal geometric center, and a first fan rotates around the central axis, and comprises a first fan hub and first fan blades. The fan hub is rotationally coupled to the substantially tubular structure, and the first fan blades are coupled to the first fan hub and increase in chord length with increasing distance from the first fan hub. A second fan is rotationally coupled to the substantially tubular structure and rotates around the central axis and contra-rotates relative to the first fan. Second fan blades are coupled to the second fan hub, and a nacelle circumscribing the first fan and the second fan is coupled to and rotates with the first fan.
    Type: Application
    Filed: November 12, 2012
    Publication date: January 1, 2015
    Inventors: Matthew D. Moore, Kelly L. Boren
  • Patent number: 8887488
    Abstract: A high efficiency power plant for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines to drive an output shaft. At low power operation, only the high pressure ratio engine is operated. At high power operation, both engines are operated where the exhaust from the high pressure ratio engine is used to drive a turbine of the low pressure ratio engine. A compressor of the low pressure ratio engine supplies compressed air to a combustor that produces a hot gas stream that is passed through the power turbine.
    Type: Grant
    Filed: April 12, 2011
    Date of Patent: November 18, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Jose R. Paulino
  • Patent number: 8813472
    Abstract: A system includes a controller configured to control a semi-closed power cycle system. The controller is configured to receive at least one of a first signal indicative of an oxygen concentration within a first gas flow through a primary compressor, a second signal indicative of power output by the semi-closed power cycle system, a third signal indicative of a temperature of a second gas flow through a turbine, and a fourth signal indicative of a mass flow balance within the semi-closed power cycle system. The controller is also configured to adjust at least one of the first gas flow through the primary compressor, a fuel flow into a combustor, a fraction of the first gas flow extracted from the primary compressor, and an air flow through a feed compressor based on the at least one of the first signal, the second signal, the third signal, and the fourth signal.
    Type: Grant
    Filed: October 21, 2010
    Date of Patent: August 26, 2014
    Assignee: General Electric Company
    Inventors: James Anthony West, Alan Meier Truesdale
  • Patent number: 8756911
    Abstract: A turbine exhaust cylinder for an industrial gas turbine engine with an external blower that delivers cooling air to a heat shield jacket surrounding an outer diameter cylinder to provide impingement cooling for the cylinder. Spent impingement cooling air is collected as passed through a space formed between a fairing and a strut to provide cooling to these parts. The cooling air then provides cooling for the inner diameter cylinder before being discharged into the turbine exhaust gas or out from the turbine exhaust cylinder.
    Type: Grant
    Filed: November 16, 2011
    Date of Patent: June 24, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Patent number: 8726635
    Abstract: The present invention provides a gas turbine engine having a combustion chamber section substantially forward of an axial compressor section. An example embodiment uses a centrifugal compressor section behind the axial compressor section to help route compressed air exiting the axial compressor section forward to the combustion chamber section.
    Type: Grant
    Filed: December 17, 2012
    Date of Patent: May 20, 2014
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: Mark R. Dale
  • Patent number: 8701385
    Abstract: A method and an apparatus is disclosed for the operation of a turboprop aircraft engine provided with pusher propellers. In order to reduce thermal loading of the pusher propellers impaired by the hot exhaust-gas flow of the engine and increase the service life of the pusher propellers, cold air from the environment outside of the aircraft engine is fed into, and mixed with, the hot exhaust-gas flow passing the pusher propellers and their connecting structure before the hot exhaust-gas flow reaches the pusher propellers.
    Type: Grant
    Filed: December 7, 2009
    Date of Patent: April 22, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Patent number: 8695321
    Abstract: A control apparatus for controlling a compressor driven by a driving unit generating driving power by a gas turbine and an electric motor includes: a temperature detection section for detecting an exhaust gas temperature of the gas turbine; and a control section for generating a motor torque instruction value for the electric motor based on the detected exhaust gas temperature. Such a control apparatus can realize a control so as not to distribute a load on the electric motor when the exhaust gas temperature of the gas turbine is low and a driving power is low. As a result, the operation efficiency can be enhanced.
    Type: Grant
    Filed: May 16, 2008
    Date of Patent: April 15, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Kazuhiro Takeda, Masahiro Kobayashi, Hideki Nagao, Yoshiyuki Okamoto
  • Publication number: 20140086739
    Abstract: A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.
    Type: Application
    Filed: September 21, 2012
    Publication date: March 27, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Joseph Machnaim, Brian David Keith, Scott Michael Carson
  • Publication number: 20140083081
    Abstract: The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.
    Type: Application
    Filed: August 20, 2012
    Publication date: March 27, 2014
    Inventor: PATRICK R.E. BAHN
  • Patent number: 8671692
    Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.
    Type: Grant
    Filed: October 3, 2011
    Date of Patent: March 18, 2014
    Assignee: United Technologies Corporation
    Inventors: Steven W. Burd, William Sowa, Albert K. Cheung, Stephen Karl Kramer, Reid Dyer Curtis Smith, James Hoke
  • Patent number: 8667774
    Abstract: Secondary air flow is provided for a ducted fan having an engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral secondary flow blades extending intermediate an inner hub and the outer hub. A nacelle provides a first flow duct for the thrust fan blades and a secondary flow duct carries flow from the integral secondary flow blades.
    Type: Grant
    Filed: August 5, 2009
    Date of Patent: March 11, 2014
    Assignee: The Boeing Company
    Inventors: Mark S. Kuehn, Daniel A. Nyhus, Timothy G. Brewer
  • Patent number: 8667775
    Abstract: Secondary air flow is provided for a ducted fan having a reverse flow turbine engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral secondary flow blades extending intermediate an inner hub and the outer hub. A nacelle provides an outer flow duct for the thrust fan blades and a secondary flow duct carries flow from the integral secondary flow blades as cooling air for components of the reverse flow turbine engine.
    Type: Grant
    Filed: August 5, 2009
    Date of Patent: March 11, 2014
    Assignee: The Boeing Company
    Inventors: Michael K. Kisska, Norman H. Princen, Mark S. Kuehn, Gary B. Cosentino
  • Publication number: 20130174535
    Abstract: A method and gas turbine are provided for the reliable purging of an exhaust gas recirculation line of the gas turbine with exhaust gas recirculation without the use of additional blow-off fans. A blow-off flow of the compressor is used for the purging of the exhaust gas recirculation line. The gas turbine can include at least one purging line which connects a compressor blow-off point to the exhaust gas recirculation line.
    Type: Application
    Filed: March 4, 2013
    Publication date: July 11, 2013
    Applicant: Alstom Technology Ltd.
    Inventor: Alstom Technology Ltd
  • Publication number: 20130152544
    Abstract: A reaction engine is disclosed mainly intended for aviation, but which as described herein can be adapted for an industrial engine, which makes use of spherical chambers and a pressure system in the blades of the rotor-stator unit which permits a perfect adjustment between said blades and the inner face of the stator, preventing pressure losses. While edges likewise articulated in the same way as the blades, execute a labyrinth seal.
    Type: Application
    Filed: December 13, 2012
    Publication date: June 20, 2013
    Inventor: José Ramón MARTÍNEZ CASAÑ
  • Patent number: 8453463
    Abstract: An anti-vortex device for use in a compressor rotor assembly of a gas turbine engine is described. Spaced-apart radial passageways extend from an axially extending passage provided in a central area of the device to an outer peripheral rim surface thereof. The radial passageways channel air from the primary gaspath about the rotor assembly to the axially extending passage where the air is directed into a central axial passage of the rotor assembly.
    Type: Grant
    Filed: May 27, 2009
    Date of Patent: June 4, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Daljit Singh Grewal, Alessandro Ciampa, Jean-Francois Caron
  • Patent number: 8402738
    Abstract: A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow. The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.
    Type: Grant
    Filed: July 2, 2009
    Date of Patent: March 26, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Philip P. Truax, Daniel N. Miller, Edward C. Ma
  • Patent number: 8402740
    Abstract: An aircraft propulsion unit includes a gas-turbine core engine 10 having at least one compressor, one combustion chamber and one turbine driving a main shaft 11. The main shaft 11 of the gas-turbine core engine 10 is operationally connected to at least two separate fans 6-9 via a mechanical drive connection, each of them being arranged beside the gas-turbine core engine 10.
    Type: Grant
    Filed: February 27, 2009
    Date of Patent: March 26, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • Patent number: 8371522
    Abstract: A device for cooling hot gas to be discharged from an aircraft includes a duct for leading the hot gas from a hot gas source which is connectable to the device to an outlet point, and a frame which surrounds the duct and serves for mounting the duct. The duct is formed from one or more pipe sections and has one or more cooling air inlet points which is connectable to one or more cooling air sources in order to mix the hot gas with cooling air. An outlet pipe section of the duct extends outwards beyond the aircraft outer skin to lead hot gas through and out of a flow boundary layer on the outer skin.
    Type: Grant
    Filed: November 24, 2008
    Date of Patent: February 12, 2013
    Assignee: Airbus Operations GmbH
    Inventor: Markus Piesker
  • Patent number: 8356469
    Abstract: The present invention provides a gas turbine engine including a first combustion chamber, a dual compression rotor positioned behind the combustion chamber, and a centrifugal compression rotor positioned behind the dual compression rotor.
    Type: Grant
    Filed: April 7, 2008
    Date of Patent: January 22, 2013
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: Mark R. Dale
  • Patent number: 8250854
    Abstract: The self-starting turbineless jet engine has fuel delivery, fuel combustion and airflow components, but it does not contain and therefore avoids the limitations associated with turbines or other moving parts other than those associated with the fuel delivery. The jet engine provides inlet louvers or vanes which direct air through an internal restriction to before mixing it with a fuel for combustion in a combustion chamber. While most of the combustion gases are exhausted through an outlet portion of the turbineless jet engine, a portion of the combustion gases are mixed with air received from an aft inlet duct in sixteen thermodynamic air compressors and back through a centrally located hot gas and fire pressure conduit where the gases are further redirected by a high temperature insulated nose cone back into the air flow received by the inlet louvers, thereby providing heat and air compression, even at zero airspeed.
    Type: Grant
    Filed: February 28, 2011
    Date of Patent: August 28, 2012
    Inventor: Thomas H. Sharpe
  • Publication number: 20120131904
    Abstract: A power plant for a jet-type model airplanes and UAVs includes an electric motor and a cover. The cover receives a portion of the electric motor and a sleeve into which the electric motor is inserted. The sleeve has a plurality of fins to dissipate heat and create openings into the cover. Air from the fan rotor passes through the openings to cool an electronic speed control member and exits a rear opening in the cover. The cover may also have additional openings for air to enter into the cover.
    Type: Application
    Filed: September 25, 2011
    Publication date: May 31, 2012
    Inventor: Robert S. Violett
  • Patent number: 8181624
    Abstract: A Brayton cycle internal combustion engine of the open, or constant pressure type, in which rotary power is produced by the pressure of hot gasses against confined, rotor protrusions.
    Type: Grant
    Filed: May 17, 2007
    Date of Patent: May 22, 2012
    Inventor: Terry Michael Van Blaricom
  • Patent number: 8028528
    Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.
    Type: Grant
    Filed: October 17, 2005
    Date of Patent: October 4, 2011
    Assignee: United Technologies Corporation
    Inventors: Steven W. Burd, William Sowa, Albert K. Cheung, Stephen Karl Kramer, Reid Dyer Curtis Smith, James Hoke
  • Patent number: 8025546
    Abstract: A ducted fan assembly includes a housing unit, a motor, and a propeller. The housing unit includes a duct member, and a hollow seat member disposed in the duct member. The motor is mounted to an exterior of the seat member, and includes a power cord extending through the seat member. The propeller is mounted to the motor and is driven thereby to generate an airflow that flows through the duct member and that acts on the motor.
    Type: Grant
    Filed: July 9, 2008
    Date of Patent: September 27, 2011
    Assignee: EPF Hobby Co., Ltd.
    Inventor: Li-Hua Yen
  • Patent number: 8001764
    Abstract: A vibration isolation engine mount system and method for ducted fan aircraft, such as ducted fan vertical takeoff and landing (VTOL) aircraft, includes an engine for driving the ducted fan. The system includes an engine support structure for supporting the engine within the ducted fan. A rotor of the ducted fan is coupled to an engine shaft of the engine via a rotor hub. The system includes a plurality of vibration isolators configured to mount the engine to the engine support structure. Each of the plurality of vibration isolators is substantially concentrically oriented along a surface of a sphere. A center of the sphere is located at a center of the rotor hub.
    Type: Grant
    Filed: September 19, 2005
    Date of Patent: August 23, 2011
    Assignee: Aurora Flight Sciences Corporation
    Inventors: Robert Parks, Jean-Charles Ledé
  • Publication number: 20110083420
    Abstract: A ramjet engine (3, 4, 5), flying at Mach 3 has 64% efficiency, and at Mach 4 has 76% efficiency. Ramjet engines are currently only used for supersonic flight and have not been used as stationary engines with mechanical output. The present invention, in addition to subsonic flight, can be operated as a stationary engine, and can expand the use of the ramjet engine for mechanical output in vehicles, power plants, and in generator sets for large buildings, homes, and industry. The present invention provides the means to use ramjet engines as stationary engines by building nearly adiabatic compressors (1, 2, 12, 13, 14, 15) and expanders (6, 7, 8, 9, 10, 11) capable of (de-)compression ratios up to about 92:1 to supply the high energy gas/air required by ramjet engines, and shows how to replace de Laval nozzles with sonic converters (49, 50, 51) that convert supersonic to subsonic flow and sonic convertors (45, 46, 47) that convert subsonic to supersonic flow without having choke areas.
    Type: Application
    Filed: March 25, 2009
    Publication date: April 14, 2011
    Inventors: Rufus G. Clay, Robert Hockaday
  • 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
  • Patent number: 7823375
    Abstract: An InfraRed Suppression System includes a high aspect ratio exhaust duct which vectors a high temperature engine exhaust flow.
    Type: Grant
    Filed: August 1, 2005
    Date of Patent: November 2, 2010
    Assignee: Sikorsky Aircraft Corporation
    Inventors: David W. Zack, John Chapkovich, Richard A. Fitts
  • Patent number: 7765790
    Abstract: A ramjet engine (3, 4, 5), flying at Mach 3 has 64% efficiency, and at Mach 4 has 76% efficiency. Ramjet engines are currently only used for supersonic flight and have not been used as stationary engines with mechanical output. The present invention, in addition to subsonic flight, can be operated as a stationary engine, and can expand the use of the ramjet engine for mechanical output in vehicles, power plants, and in generator sets for large buildings, homes, and industry. The present invention provides the means to use ramjet engines as stationary engines by building nearly adiabatic compressors (1, 2, 12, 13, 14, 15) and expanders (6, 7, 8, 9, 10, 11) capable of (de-)compression ratios up to about 92:1 to supply the high energy gas/air required by ramjet engines, and shows how to replace de Laval nozzles with sonic converters (49, 50, 51) that convert supersonic to subsonic flow and sonic converters (45, 46, 47) that convert subsonic to supersonic flow without having choke areas.
    Type: Grant
    Filed: March 25, 2009
    Date of Patent: August 3, 2010
    Assignee: Amicable Inventions LLC
    Inventors: Rufus G. Clay, Robert G. Hockaday
  • Patent number: 7699975
    Abstract: In at least one embodiment of the present invention, a method of heating a FCC unit having a regenerator and a reactor for over CO2 reduction is provided. The method comprises compressing syngas to define compressed syngas. CO2 is separated from the compressed syngas to provide a first stream of gas comprising CO2. The first stream of gas is expanded with a second stream of gas comprising O2 to define a feed gas. The feed gas and an injected hydrocarbon feed are introduced to the regenerator having spent catalyst from the reactor. The regenerator is at gasification conditions to burn the injected hydrocarbon feed and coke from the spent catalyst producing the syngas and heat for operating the reactor at reaction temperatures.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: April 20, 2010
    Assignees: UOP LLC, BP Corporation North America Inc.
    Inventor: Brian W. Hedrick
  • Patent number: 7699974
    Abstract: In at least one embodiment of the present invention, a method of heating a FCC unit having a regenerator and a reactor having overall CO2 reduction is provided. The method comprises compressing syngas to define compressed syngas. Separating a first stream of gas comprising CO2 from the compressed syngas. A second stream of gas comprising O2 is expanded with the first stream of gas to produce a feed gas. The feed gas is introduced to the regenerator at gasification conditions to burn coke from coke heavy spent catalyst advanced from the reactor, producing syngas and heat for operating the reactor at reaction temperatures.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: April 20, 2010
    Assignees: UOP LLC, BP Corporation North America Inc.
    Inventor: Brian W. Hedrick
  • Patent number: 7685804
    Abstract: A device is provided. The device is configured to introduce a pressurized flow along a Coanda profile and to entrain additional fluid flow to create a high velocity fluid flow; wherein the high velocity fluid flow is directed to an end use system through a flow path in flow communication with the device.
    Type: Grant
    Filed: September 8, 2006
    Date of Patent: March 30, 2010
    Assignee: General Electric Company
    Inventor: Andrei Tristan Evulet
  • Publication number: 20100071345
    Abstract: According to the present invention, a blade with lift-to-drag ratio greater than one can generate a lift force greater than the drag force on the blade when a fluid flows across the blade. The blade can be positioned within an enclosed engine to produce a force greater than the force required to move the fluid across the blade, thereby creating a thrust for the enclosed engine. The direction and the magnitude of the thrust may be controlled by controlling the direction of fluid flow. According to the present invention, fluid flowing inside a thrust engine may be gaseous or liquid. A thrust engine of the present invention uses one or more wings in a configurable environment to create a directional force.
    Type: Application
    Filed: September 22, 2008
    Publication date: March 25, 2010
    Inventors: Guy Silver, Juinerong Wa
  • Patent number: 7617670
    Abstract: A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow, The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.
    Type: Grant
    Filed: May 4, 2006
    Date of Patent: November 17, 2009
    Assignee: Lockheed Martin Corporation
    Inventors: Philip P. Truax, Daniel N. Miller, Edward C. Ma
  • Publication number: 20090158705
    Abstract: The present invention provides a hypermixing fluid ejector. The ejector includes a reservoir containing a primary fluid and an ejector nozzle with a trailing-edge array of rectilinear orifices. The primary fluid is ejected through these orifices to entrain a secondary fluid, thereby creating a mixed fluid flow. A dividing line is defined on the trailing surface of the nozzle that is orthogonal to the linear axis of the ejector, and the orifices alternate above and below this dividing line in an abutting, offset manner. The orifices are geometrically inclined to produce spray cones that are convergent relative to this dividing line, resulting in convergent helical hypermixing of the primary fluid with the secondary fluid.
    Type: Application
    Filed: February 1, 2008
    Publication date: June 25, 2009
    Inventor: Fabio G. Grossi
  • Patent number: 7500353
    Abstract: A system is provided in an aircraft that includes a power unit and an eductor. The power unit has a nozzle, and is configured to exhaust gas, a portion of which flows in a swirling motion, through the nozzle. The eductor communicates with the power unit and includes a housing and a plurality of flow straighteners. The housing has an inlet, an outlet, and an inner peripheral surface that defines a flow passage. The inlet is configured to surround at least a portion of the nozzle and to receive the gas, and the outlet is configured to exhaust the gas. The plurality of flow straighteners extend radially inwardly from the housing inner surface into the flow passage and are configured to reduce swirl motion of the gas that flows therethrough. The power unit may be an auxiliary power unit or a turboshaft engine.
    Type: Grant
    Filed: October 25, 2005
    Date of Patent: March 10, 2009
    Assignee: Honeywell International Inc.
    Inventor: Morris G. Anderson
  • Patent number: 7500351
    Abstract: A gas turbine powerplant for a V/STOL aircraft in which a vectorable exhaust nozzle at a forward part (eg. nose) of the aircraft selectably receives a supply of cold fan air through a duct leading from the fan through a passageway (28) coaxial with the engine axis and located within the hub of the fan (12), with the aid of controllable flaps and diverters (26, 30).
    Type: Grant
    Filed: November 29, 1995
    Date of Patent: March 10, 2009
    Assignee: BAE Systems plc
    Inventors: Keith Martin Rogers, George Mansfield Appleyard
  • Publication number: 20080256926
    Abstract: A diffuser for a centrifugal compressor in a gas turbine engine, the diffuser including a diffuser ring having a series of bores defined therethrough to receive and direct air exiting the compressor, each bore being defined by a respective bore surface including a boride layer protecting the bore surface from erosion damage.
    Type: Application
    Filed: April 20, 2007
    Publication date: October 23, 2008
    Inventors: Reza ZIAEI, Victor Salivon, Jaroslaw Wojcik
  • Publication number: 20080250772
    Abstract: Disclosed is a device for separating liquids from gases comprising a preseparator that separates an untreated gas region from a preseparator gas region, a main separator comprising a coalescing element for increasing the size of liquid droplets and a post-separator.
    Type: Application
    Filed: April 10, 2007
    Publication date: October 16, 2008
    Applicant: MANN & HUMMEL GmbH
    Inventors: Stefan Becker, Carsten Schippers, Wolfgang Heikamp, Tobias Neumann, Andreas Stephan, Jens Gutekunst, Peter Biebricher
  • Publication number: 20080245637
    Abstract: A drive through crankshaft assembly which selectively provides rotational power to a vehicle accessory while continuously providing rotational power to a second vehicle accessory. Rotational power is selectively provided using a cone clutch assembly that is modular. The cone clutch assembly provides power to the first vehicle accessory when it is in an engaged state. The first vehicle accessory is turned off by putting the cone clutch assembly into a disengaged state using a clutch control system.
    Type: Application
    Filed: April 5, 2007
    Publication date: October 9, 2008
    Inventors: Travis L. Fetter, Michael R. Jenkins
  • Patent number: 7117663
    Abstract: A hydrogen fueled jet engine for hypersonic aircraft. The compressor of the jet engine is driven directly by a dual-acting rotary piston engine. Heated, high pressure hydrogen is delivered to the rotary piston engine for expansion therein. The crankshaft of the rotary piston engine is attached directly to the air compressor of the jet engine. The power from the expanding hydrogen drives the air compressor of the jet engine. After the hydrogen is expanded to produce power, the hydrogen is burned as fuel.
    Type: Grant
    Filed: May 25, 2004
    Date of Patent: October 10, 2006
    Inventor: Jonathan Cleaveland Knapp
  • Patent number: 7111449
    Abstract: A new type of gas heat engine is described that has several features similar to a gas turbine or jet engine. The engine is developed in many different configurations, each yielding different theoretical advantages and degrees of freedom. All of this family of engines have no moving components, provide heat recovery and operate over a wide range of input gas velocities. The new engines can use higher combustion temperatures and consequently have the potential for improved efficiency over current technology. There are many theoretical and practical advantages to the new concepts, which give flexibility in both engine design and operating characteristics that are difficult to embody in current turbo jets. Among the most important is the potential for a thermodynamic efficiency which exceeds that of current open cycle gas heat engines at a given pressure ratio. A new term in the equation of the Enthalpy of a gas is described, which could be exploited in yet other variants of the engine.
    Type: Grant
    Filed: November 14, 2002
    Date of Patent: September 26, 2006
    Inventor: David W. Stebbings
  • Patent number: 7051659
    Abstract: A scramjet has a cowl, a center structure, and a plurality of wide pylons connecting the cowl to the center structure, with scramjet engines positioned between adjacent pylons. Leading surfaces of adjacent pylons converge to one another to provide side wall compression to air entering the engines. The center structure includes a fore body, a center body and an aft body that, with the pylons, define a basic structure either formed entirely from one piece or several securely connected pieces. A method of testing the scramjet projectile comprises using a gun to accelerate the scramjet projectile to the takeover velocity of the engines.
    Type: Grant
    Filed: June 10, 2002
    Date of Patent: May 30, 2006
    Assignee: Alliant Techsystems Inc.
    Inventors: Jason S. Tyll, Robert J. Bakos, Florin Girlea, Ralph Woelfel, Dean Modroukas, John I. Endos
  • Patent number: RE45397
    Abstract: A Brayton cycle internal combustion engine of the open, or constant pressure type, in which rotary power is produced by the pressure of hot gasses against confined, rotor protrusions.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: March 3, 2015
    Inventor: Terry Michael Van Blaricom