Interrelated Reaction Motors Patents (Class 60/224)
  • Patent number: 10378379
    Abstract: A spoolie manifold including two or more spaced apart caps including outlets and one pair of caps connected together in flow communication by a jumper tube assembly. Jumper tube assembly including a jumper tube having first and second spoolies attached to opposite ends of the jumper tube. Ends may be welded into counterbores of the spoolies having spherical spoolie ends press-fitted into first and second sleeves in bores in pair of the caps and sleeves retained in bores with retainer clips. A duct connected in flow communication to an inlet of one of the caps. Spoolie manifold may include three spaced apart caps including a distributor cap between two port caps connected in flow communication to distributor cap by jumper tube assembly. Cap outlets may be feed strut ports in casing of turbine frame including hub spaced inwardly from casing and having spaced apart hollow struts with strut ports.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: John Alan Manteiga, Sydney Michelle Wright, Christopher Richard Koss, Tod Kenneth Bosel
  • Patent number: 10309310
    Abstract: In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.
    Type: Grant
    Filed: May 10, 2013
    Date of Patent: June 4, 2019
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Wesley K. Lord
  • Patent number: 10190506
    Abstract: An exemplary turbomachine exhaust flow diverting assembly includes an outer flow diverter distributed about a rotational axis of a turbomachine. The outer flow diverter moveable between a first position and a second position. The outer flow diverter in the first position permits more flow through a main bypass flow passage and less flow through a third stream bypass flow passage. The outer flow diverter in the second position permits more flow through the third stream bypass flow passage and less flow through the main bypass flow passage.
    Type: Grant
    Filed: November 30, 2015
    Date of Patent: January 29, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Jose E. Ruberte Sanchez
  • Patent number: 10161316
    Abstract: Aspects of the disclosure are directed to an engine of an aircraft. The engine may include a first fan configured to output a first air flow, a second fan configured to receive a first portion of the first air flow and output a second air flow, a core configured to receive a first portion of the second air flow and generate a first stream, and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream based on at least one of the first air flow and the second air flow.
    Type: Grant
    Filed: April 13, 2015
    Date of Patent: December 25, 2018
    Assignee: United Technologies Corporation
    Inventors: Daniel B. Kupratis, Christopher J. Hanlon, Walter A. Ledwith, Jr.
  • Patent number: 10001063
    Abstract: A propulsion system for an aircraft includes first and second turbine engines mounted within a fuselage of the aircraft. The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor axis. The second turbine engine includes a second engine core and a second propulsor disposed about a second propulsor axis parallel to the first propulsor axis. The first engine core and the second engine core are mounted at an angle relative to corresponding ones of the first and second propulsor axes.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: June 19, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler
  • Patent number: 9951721
    Abstract: A gas turbine engine includes an auxiliary airflow control system to provide selective communication of a portion of a second stream from a second stream flow path into a third stream flow path, the auxiliary airflow control system in communication with a high temperature flow sourced from the turbine section.
    Type: Grant
    Filed: October 21, 2014
    Date of Patent: April 24, 2018
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Walter A Ledwith, Jr., Christopher J Hanlon
  • Patent number: 9926885
    Abstract: A gas turbine engine includes a bypass flow passage that has an inlet and defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is arranged within the bypass flow passage. A first turbine is a 5-stage turbine and is coupled with a first shaft, which is coupled with the fan. A first compressor is coupled with the first shaft and is a 3-stage compressor. A second turbine is coupled with a second shaft and is a 2-stage turbine. The fan includes a row of fan blades that extend from a hub. The row includes a number (N) of the fan blades, a solidity value (R) at tips of the fab blades, and a ratio of N/R that is from 14 to 16.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: March 27, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Byron R. Monzon
  • Patent number: 9915201
    Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.
    Type: Grant
    Filed: December 26, 2013
    Date of Patent: March 13, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Michael Abraham Karam, Craig Heathco, Andrew Eifert
  • Patent number: 9845768
    Abstract: An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: December 19, 2017
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Kenneth M. Pesyna, Anthony F. Pierluissi, Bryan H. Lerg, Justin N. Moore
  • Patent number: 9822731
    Abstract: A method to reduce aerodynamic drag of a engine exhaust/engine nozzle includes collecting data that is indicative of an instant flight condition, entering the data into a decision algorithm that, based on the data, outputs at least first and second drag control parameters corresponding, respectively, to an angle of one or more variable area turbines of a turbine engine and a position of a variable area exhaust nozzle of the turbine engine, and adjusting the angle of the one or more variable area turbines and the position of the variable area exhaust nozzle according to, respectively, the first and second drag control parameters to reduce aerodynamic drag of an engine exhaust/engine nozzle of the turbine engine.
    Type: Grant
    Filed: March 27, 2015
    Date of Patent: November 21, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Adam Joseph Suydam, Christopher G. Hugill
  • Patent number: 9771897
    Abstract: A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.
    Type: Grant
    Filed: October 8, 2012
    Date of Patent: September 26, 2017
    Assignee: SNECMA
    Inventors: Nicolas Soulier, Bruno Brochard, Jean-Michel Sannino
  • Patent number: 9725182
    Abstract: An aeroengine control device including a mount and having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel. Each lever is movable between a rest position and a maximum actuation position. The secondary lever is mounted to pivot on the main lever. Cam paths are mounted on the code wheel and on the mount in such a manner that the main lever can move the code wheel when the main lever is moved while the secondary lever is in the rest position. The secondary lever can move the code wheel when the secondary lever is moved while the main lever is in the rest position, with movement of either lever being prevented when the other lever is clearly away from its rest position.
    Type: Grant
    Filed: September 30, 2013
    Date of Patent: August 8, 2017
    Assignee: Safran Electronics & Defense
    Inventors: Hafid Elabellaoui, Jean-Eric Besold, Sebastien Pautard, Thierry Cartry, David Engler, Etienne Merlet
  • Patent number: 9650954
    Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.
    Type: Grant
    Filed: January 15, 2015
    Date of Patent: May 16, 2017
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Michael E. McCune, Jesse M. Chandler, Alan H. Epstein, Steven M. O'Flarity, Christopher J. Hanlon, William F. Schneider, Joseph B. Staubach, James A. Kenyon
  • Patent number: 9555903
    Abstract: A method of diagnosing a bleed air system fault, where the method includes receiving a sensor signal from the at least one of the bleed air system sensor to define a sensor output, comparing the sensor output to a reference value, and diagnosing a fault in the bleed air system based on the comparison.
    Type: Grant
    Filed: May 13, 2014
    Date of Patent: January 31, 2017
    Assignee: GE AVIATION SYSTEMS LIMITED
    Inventor: Julia Ann Howard
  • Patent number: 9115648
    Abstract: The subject application involves a method of controlling operation of a gas turbine. The method includes determining a first temperature associated with a portion of the gas turbine during operation of said gas turbine, and sensing an operational parameter of the gas turbine during operation of the gas turbine. An ambient pressure in an ambient environment of the gas turbine is also sensed, and the operational parameter corrected using the ambient pressure sensed in the ambient environment of the gas turbine to establish a corrected operational parameter. A threshold temperature is determined based at least in part on the corrected operational parameter, and a backup routine is initiated to limit operation of the gas turbine when the temperature associated with the gas turbine is greater than or equal to the threshold temperature.
    Type: Grant
    Filed: April 10, 2009
    Date of Patent: August 25, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: James Henahan, Harold Lamar Jordan, David Ewens
  • Patent number: 9057328
    Abstract: A gas turbine engine includes a combustor section, a fan section forward of the combustor section, a low pressure turbine section along the combustor section, and an intercooling turbine section aft of the fan section and forward of the combustor section. The intercooling turbine section includes upstream and downstream intercooling turbine variable vanes. The intercooling turbine section is situated in an intermediate flow path that is inboard of an outer bypass flow path. The intermediate flow path splits downstream from the intercooling turbine section to a second stream bypass flow path and a core flow path. The second stream bypass flow path is inboard of the outer bypass flow path and extends to an exhaust nozzle. The exhaust nozzle is located aft of the low pressure turbine section and inboard of the outer bypass flow path.
    Type: Grant
    Filed: November 1, 2011
    Date of Patent: June 16, 2015
    Assignee: United Technologies Corporation
    Inventor: Daniel B. Kupratis
  • Patent number: 8955304
    Abstract: A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed.
    Type: Grant
    Filed: February 10, 2012
    Date of Patent: February 17, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Joseph B. Staubach, Christopher M. Dye
  • Patent number: 8950172
    Abstract: The jet (40) has an air-fuel combustion chamber (42) and a plurality of rocket engines (11) arranged upstream from the combustion chamber (42), each rocket engine having its own combustion chamber with the wall thereof being cooled by lateral injection of fuel through said wall.
    Type: Grant
    Filed: July 10, 2009
    Date of Patent: February 10, 2015
    Assignee: Snecma
    Inventors: Daniel Peyrisse, Jean-Marie Conrardy
  • Publication number: 20150013306
    Abstract: A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes. Electromotive force is used in lieu of hot section power turbines to achieve engine air compression or alternately perform thrust work at low velocities.
    Type: Application
    Filed: January 10, 2014
    Publication date: January 15, 2015
    Inventor: Rudolph Allen Shelley
  • 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: 8884202
    Abstract: A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks.
    Type: Grant
    Filed: March 9, 2011
    Date of Patent: November 11, 2014
    Assignee: United Launch Alliance, LLC
    Inventor: Frank C. Zeglar
  • Publication number: 20140260182
    Abstract: A gas turbine engine has a fairing and an air intake that includes an air inlet embedded within the fairing for supplying free stream atmospheric air to a gas generator.
    Type: Application
    Filed: December 30, 2013
    Publication date: September 18, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Steven H. Zysman
  • Publication number: 20140250862
    Abstract: A gas turbine engine has a propulsor including a fan and a power turbine, an engine core aerodynamically connected to the propulsor by a transition duct, and a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.
    Type: Application
    Filed: February 26, 2014
    Publication date: September 11, 2014
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • Patent number: 8789354
    Abstract: A gas turbine engine includes a propulsion unit mounted to rotate about a first axis, and a core engine mounted to rotate about a second axis, and wherein the first and second axes are non-parallel. A gas turbine engine includes a propulsion unit driven by a free turbine which is adjacent to the propulsion unit and an associated fan, and having a gas generator core engine including a compressor, combustor and turbine section. A method is also disclosed.
    Type: Grant
    Filed: February 10, 2012
    Date of Patent: July 29, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Wesley K. Lord, Christopher M. Dye
  • Publication number: 20140196436
    Abstract: An object of the present invention is to provide a technique of enlarging a stable operating range of an intake in accordance with an operating condition of an engine without using a complicated control system so that a wide operating range of the engine can be covered. In an operation stabilization method for a supersonic intake according to the present invention, an enlarged duct between a cowl and a ramp of the intake is divided by a splitter plate such that an opening angle of the enlarged duct decreases. Further, in the operation stabilization method for a supersonic intake according to the present invention, when the duct is divided by the splitter plate, the splitter plate is disposed such that, from among a cowl side duct and a ramp side duct, cross-section variation in one duct, in which an effect of a flow is larger, is reduced within an allowable range of total pressure loss in the other duct.
    Type: Application
    Filed: January 15, 2014
    Publication date: July 17, 2014
    Applicant: JAPAN AEROSPACE EXPLORATION AGENCY
    Inventor: Yasushi Watanabe
  • Publication number: 20140137538
    Abstract: A gas turbine engine has a compressor, a fan for delivering air into the compressor and into a bypass duct, a combustion section and a turbine section. A control for the gas turbine engine is programmed to change a fueling level and position at least one effector that may be moved to unique positions in a coordinated fashion upon receipt of a command to change thrust. The thrust provided by the engine is changed without a reduction in an airflow stability margin compared to a thrust change commanded only by a fueling change. Some aspects of the positioning are transitory.
    Type: Application
    Filed: November 16, 2012
    Publication date: May 22, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Patent number: 8590288
    Abstract: A fan control apparatus includes a fan, two engine+compressor combinations, two air supply systems, and an FCC. When an abnormality occurs in one of the air supply systems and one of the engine+compressor combinations, the FCC maintains the flow rate of the normally operating air supply system and then increases the flow rate. As a result, the normally operating drive source is prevented from overloading. In another embodiment, a fan control apparatus includes a fan, an air source, two air supply systems, and a bypass channel. The air is caused to flow through the bypass channel when an abnormality occurs in one of the air supply systems. As a result, the time that elapses till the fluid can be supplied at a necessary flow rate is shortened.
    Type: Grant
    Filed: March 28, 2008
    Date of Patent: November 26, 2013
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventor: Masatsugu Ishiba
  • Patent number: 8528341
    Abstract: The present invention provides a regenerative superheater system for an ejector ramjet engine. The invention includes a superheater in thermal communication with the combustion chamber of the ramjet engine. The superheater transfers thermal energy from combustion chamber to an ejectant which is then redirected upstream to the ramjet ejector. In one embodiment of the invention the temperature of the ejectant is modulated by a variable geometry cooler that controls the amount of thermal energy removed from the superheater system by ambient air. In an alternate embodiment of the invention, the temperature of the ejectant is modulated by a variable geometry superheater that controls the amount of thermal energy added to the superheater system through combustion gas.
    Type: Grant
    Filed: January 24, 2013
    Date of Patent: September 10, 2013
    Assignee: Grossi Aerospace, Inc.
    Inventor: Fabio G. Grossi
  • Publication number: 20130227930
    Abstract: Gas turbine engine frames are disclosed. An example gas turbine engine frame may include a generally annular outer casing disposed coaxially about a hub; a plurality of circumferentially spaced apart struts joined to the hub and the outer casing, individual struts extending radially outwardly from the hub to the outer casing; and a stiffening rail monolithically formed with the outer casing circumferentially between two of the struts. The stiffening rail may extend radially inward beyond the inner surface of the outer casing between the struts.
    Type: Application
    Filed: March 5, 2012
    Publication date: September 5, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Courtland Earl Pegan, JR., Kurt Thomas Hildebrand, Scott Patrick Ryczek, Derek Thomas Dreischarf
  • Publication number: 20130199156
    Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique variable cycle gas turbine engine. Another embodiment is a unique adaptive fan system for a variable cycle turbofan engine having at least one turbine. Another embodiment is a unique method for operating a variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and related systems.
    Type: Application
    Filed: March 27, 2011
    Publication date: August 8, 2013
    Inventors: Robert A. Ress, JR., Steve Stratton, Matthew J. Starr
  • Publication number: 20130186060
    Abstract: A two-spool turbojet built up of major bladed components first developped for unrelated turbofan engine types. The high pressure (“HP”) spool comes from a turbofan which powered a large airliner carrying 300 or more passengers across a continent or an ocean. The low pressure (“LP”) compressor is the fan from a military aircraft's engine or a smaller airliner turbofan, or both. The object is that all the LP compressor output goes into the HP compressor, making a turbojet from existing turbofan components. This saves development costs, and creates an engine for propelling a large aircraft at supersonic speeds more efficiently than by an afterburning turbofan. In the preferred embodiment, the number of stages in the HP spool is halved, saving weight for the addition of a remote fan (known elsewhere) which doubles the air mass flow. That increases propulsive efficiency during subsonic cruise.
    Type: Application
    Filed: January 20, 2012
    Publication date: July 25, 2013
    Inventor: Patrick A. Kosheleff
  • Patent number: 8453428
    Abstract: A number of engines usable alone or in combination are taught herein. One engine comprises a housing, a drive shaft mounted within the housing, a first impeller and a second impeller mounted on the drive shaft for movement, and a combustion mediating hub between the second impeller and the first impeller and mounted for movement in both a clockwise and counter-clockwise direction with respect to the drive shaft, where the hub includes an annular plate, a first plurality of blades mounted on a first surface of the annular plate and facing the second impeller and a second plurality of blades mounted on a second, opposing surface of annular plate and facing the first impeller. An ignition source and a fuel source extend through the housing into an area between an outer peripheral wall of the annular plate and an inner wall of the housing.
    Type: Grant
    Filed: May 6, 2011
    Date of Patent: June 4, 2013
    Inventor: Ronald August Kinde, Sr.
  • 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: 8403841
    Abstract: A surgical access system including a tissue distraction assembly and a tissue refraction assembly, both of which may be equipped with one or more electrodes for use in detecting the existence of (and optionally the distance and/or direction to) neural structures before, during, and after the establishment of an operative corridor to a surgical target site.
    Type: Grant
    Filed: December 14, 2009
    Date of Patent: March 26, 2013
    Assignee: NuVasive, Inc.
    Inventors: Patrick Miles, Scot Martinelli, Eric Finley, James Gharib, Allen Farquhar, Norbert Kaula, Goretti Medeiros
  • Patent number: 8297039
    Abstract: A propulsion engine (100) for an aircraft, the propulsion engine comprising: one or more fans (110, 120); driving means (132) arranged to drive the one or more fans; and power transfer means (134) connected to the one or more fans and arranged to selectively transfer a variable amount of power to or from the one or more fans so as to control the rotational speed of the one or more fans.
    Type: Grant
    Filed: September 15, 2010
    Date of Patent: October 30, 2012
    Assignee: Rolls-Royce plc
    Inventor: David P. Scothern
  • Patent number: 8256203
    Abstract: The present disclosure generally pertains to rocket based combined cycle (RBCC) propulsion units. In one exemplary embodiment, at least one rocket thruster is integrated with a jet engine but is external to the flow path of the jet engine, forming an altitude compensating plug nozzle. Since the rocket thruster is external to such flow path, the rocket flow from the rocket thruster interacts with the jet flow from the jet engine aft of the nozzle of the jet engine. Such interaction occurs without a significant performance penalty in the operation of the jet engine. In fact, it is possible that the interaction of the rocket flow with the jet flow may actually improve the efficiency of the jet engine under some conditions. Moreover, having the rocket thrusters positioned external to the flow path of the jet engine helps to avoid many of the problems plaguing conventional RBCC propulsion units.
    Type: Grant
    Filed: January 28, 2008
    Date of Patent: September 4, 2012
    Assignee: The University of Alabama in Huntsville
    Inventors: James B. Blackmon, David B. Landrum, Sean Entrekin
  • Patent number: 8242422
    Abstract: There is disclosed a vehicle and methods for maneuvering the vehicle. The vehicle may include a plurality of multiple-impulse rocket motors, each of which comprises a plurality of independently ignitable solid fuel propellant charges, and a processor that generates at least one command to ignite at least one solid fuel propellant charge of at least one of the plurality of multiple-impulse rocket motors.
    Type: Grant
    Filed: June 15, 2009
    Date of Patent: August 14, 2012
    Assignee: Raytheon Company
    Inventors: Thomas A. Olden, Robert J. Cavalleri
  • Patent number: 8127528
    Abstract: A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the stream of pressurized air to generate streams of combustion air and supercharged auxiliary air. A peripheral case surrounds the engine case to form a peripheral duct. An auxiliary combustor and propulsor are positioned within the peripheral duct. A bleed duct extends from the high pressure spool to the auxiliary combustor. Variable ductwork directs airflow through the bleed duct and peripheral duct in two modes. A first mode comprises directing the stream of auxiliary air to the auxiliary combustor, and directing stream of inlet air through the peripheral duct. A second mode comprises directing the stream of auxiliary air into the stream of bypass air, and preventing inlet air from entering the peripheral duct.
    Type: Grant
    Filed: February 26, 2008
    Date of Patent: March 6, 2012
    Assignee: United Technologies Corporation
    Inventor: Gary D. Roberge
  • Patent number: 8127527
    Abstract: A method and system for operating a gas turbine engine is provided. The system includes in serial flow arrangement, at least one compressor, a combustor, and at least one turbine. The method includes compressing atmospheric air in the gas turbine engine, channeling at least a portion of the compressed air from the turbine engine flowpath to an oxidizer supply system, and channeling an oxygen-depleted flow of the compressed air from the oxidizer supply system to the gas turbine engine flowpath.
    Type: Grant
    Filed: November 22, 2004
    Date of Patent: March 6, 2012
    Assignee: General Electric Company
    Inventor: Rollin George Giffin
  • Patent number: 8117827
    Abstract: A gas turbine engine assembly includes at least one propelling gas turbine engine and an auxiliary engine used for generating power. The propelling gas turbine engine includes a fan assembly and a core engine downstream from said fan assembly. The core engine includes a compressor, a high pressure turbine, a low pressure turbine, and a booster turbine coupled together in serial-flow arrangement such that the booster turbine is rotatably coupled between the high and low pressure turbines. The auxiliary engine includes at least one turbine and an inlet. The inlet is upstream from the high pressure turbine and is in flow communication with the propelling gas turbine engine core engine, such that a portion of airflow entering the propelling engine is extracted for use by the auxiliary engine.
    Type: Grant
    Filed: March 16, 2009
    Date of Patent: February 21, 2012
    Assignee: General Electric Company
    Inventors: Gary Craig Wollenweber, John B. Turco
  • Publication number: 20120023899
    Abstract: Provided is a turbofan engine capable of effectively using the air flowing through the inner diameter side area of a fan that is disposed at the front end side. The turbofan engine in which the fan is disposed at the front end side is equipped with a first low-pressure compressor at the upstream side and on the inner diameter side of the fan. Accordingly, the first low-pressure compressor can be operated by effectively using the air flowing through the rotation center portion of the fan, so that the air can be efficiently used and the output of the engine can be increased.
    Type: Application
    Filed: February 6, 2009
    Publication date: February 2, 2012
    Inventor: Shoji Yasuda
  • Publication number: 20110277447
    Abstract: An engine for an aircraft flying in a cruise flight direction comprises at least one rotor having a plurality of rotor blades. The at least one rotor is driven about a rotor axis at a rotational frequency. The rotor axis is oriented in the cruise flight direction of the aircraft, and at least one geometric parameter of the rotor blades that influences the propulsion characteristics of the rotor is variable. The engine further comprises a controller which periodically varies the geometric parameter of the rotor blades at at least one frequency that is at least as high as the rotational frequency of the rotor.
    Type: Application
    Filed: July 26, 2011
    Publication date: November 17, 2011
    Applicant: Deutsches Zentrum fur Luft- und Raumfahrt e.V.
    Inventor: Arne Stürmer
  • Patent number: 8015795
    Abstract: An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being a plurality of air transfer ducts each extending from a different location in the gas turbine engine so as to be capable to provide air in each of those air transfer ducts at one end thereof at pressures differing from one another and connected at the other end of each to the air intake to transfer air thereto.
    Type: Grant
    Filed: May 18, 2007
    Date of Patent: September 13, 2011
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Brian M. Fentress
  • Publication number: 20110179767
    Abstract: The invention relates to an aircraft propeller (1) comprising a turbomachine (8) housed in a nacelle (10) and a cooler (45) capable of being traversed by a hot fluid, which is to be cooled by thermal exchange with cold air external to the cooler. The propeller (1) comprises an air stream (13) (13b) capable of directing pressurized air towards an air duct (20) realized between an outer wall (6) and an inner wall (60) of the nacelle (10). The cooler comprises volumetric cooling means (14) located in the air duct (20) and surface cooling means (15), unrelated to said volumetric cooling means, located at an outside wall (6, 101) of the aircraft.
    Type: Application
    Filed: January 25, 2011
    Publication date: July 28, 2011
    Applicant: AIRBUS OPERATIONS (S.A.S)
    Inventors: Christelle RINJONNEAU, Pierre GUILLAUME
  • Publication number: 20110146228
    Abstract: A power extraction system is disclosed having a forward fan stage configured to pressurize an airflow, an aft fan stage having a tip-fan configured to pressurize a first portion of a pressurized air flow from the forward fan stage wherein the aft fan stage is driven by a second portion of the pressurized airflow, and a power drive system adapted to supply power from the aft fan stage.
    Type: Application
    Filed: September 2, 2010
    Publication date: June 23, 2011
    Inventor: JOHN LEWIS BAUGHMAN
  • Publication number: 20110107738
    Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.
    Type: Application
    Filed: January 19, 2011
    Publication date: May 12, 2011
    Applicant: Aerojet-General Corporation
    Inventor: Melvin J. Bulman
  • Patent number: 7937945
    Abstract: Units of engines are described herein. The units contain a unique combined-cycle (deflagration-detonation) “contra-rotation, anti-gyration, gyroscopic,” turbine fan-jet/free-piston engine configuration for induced air supercharging that boosts the performance of novel Ramjet engines or Ramjet engine configurations by improving internal air-stream dynamics. These dynamics are the result of co-operative air stream intermixing through convergent, supercharge-attenuated, inducted, compressed, tuned, pre-heated ambient air. Results are achieved through the varying of the geometric structural form and the utilization of unique engines and air induction and propulsion conformations, aided with supplemental air, fuel, oxygen and optional water and electrolyte charging.
    Type: Grant
    Filed: February 5, 2007
    Date of Patent: May 10, 2011
    Inventor: Ronald August Kinde, Sr.
  • Publication number: 20100327110
    Abstract: The invention relates to a nacelle (100) for the turbojet of an aircraft that comprises a downstream structure including: an outer structure (106), a concentric inner structure (109) surrounding a downstream portion (111) of the turbojet and including an upstream section having a relatively small diameter (113) and a downstream section having a relatively large diameter (114), wherein said inner structure (109) defines together with the outer structure (106) an annular flow channel (108); and a guiding system (140) for connecting the inner structure (109) and the downstream portion (111) of the turbojet engine or a portion of a suspension mast; characterised in that the guiding system (140) includes a means for combining a translation and rotation movement of at least a portion of said inner structure (109) between a working position, in which the inner structure (109) is used as a cowling for the turbojet downstream portion (111), and a maintenance position in which the inner structure (109) exposes said tur
    Type: Application
    Filed: January 21, 2009
    Publication date: December 30, 2010
    Applicant: AIRCELLE
    Inventors: Pierre Caruel, Jean-Philippe Joret, Peter Segat
  • Publication number: 20100223904
    Abstract: A gas turbine engine comprising an intermediate compressor and two shafts connecting respective high and low pressure turbines and compressors respectively is characterised by the intermediate pressure compressor connecting to either the high pressure shaft or the low pressure shaft via a gearbox.
    Type: Application
    Filed: February 12, 2010
    Publication date: September 9, 2010
    Applicant: ROLLS-ROYCE PLC
    Inventor: David A. EDWARDS
  • Patent number: 7762056
    Abstract: A gas turbine engine with a turbine with an exhaust manifold thereabout from which fluids can be transferred to the turbine and an air compressor having an air transfer duct extending therefrom so as to be capable to provide compressed air in that air transfer duct at one end thereof to the air intake of an internal combustion engine provided as an intermittent combustion engine. The air intake and an exhaust outlet are each coupled to combustion chambers therein and a rotatable output shaft is also coupled to those combustion chambers for generating force. The exhaust outlet has an exhaust transfer duct extending therefrom so as to have the intermittent combustion engine be capable to provide exhaust therefrom in that exhaust transfer duct at one end thereof, and the exhaust transfer duct being connected at an opposite end thereof to the exhaust manifold to be capable of transferring intermittent combustion engine exhaust thereto.
    Type: Grant
    Filed: May 15, 2007
    Date of Patent: July 27, 2010
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Brian M. Fentress, Charles E Lents