Air-ingestion Rotor Tip Unit Patents (Class 416/22)
  • Patent number: 9732700
    Abstract: A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.
    Type: Grant
    Filed: September 25, 2014
    Date of Patent: August 15, 2017
    Assignee: The Boeing Company
    Inventors: David F. Cerra, Robert H. Willie, Alvaro Prieto
  • Patent number: 9546618
    Abstract: A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.
    Type: Grant
    Filed: October 24, 2013
    Date of Patent: January 17, 2017
    Assignee: THE BOEING COMPANY
    Inventors: Robert H. Willie, David F. Cerra, Leonard J. Hebert
  • Patent number: 9085354
    Abstract: Systems and methods for vertical takeoff and/or landing are disclosed herein. An aerial vehicle may include a first propulsion unit and a second propulsion each rotatably connected to a body. The aerial vehicle may include a first wing and a second wing each rotatably connected to the body. And the aerial vehicle may include a control system configured to: position the first propulsion unit, the second propulsion unit, the first wing, and the second wing; operate the first propulsion unit and the second propulsion unit; and rotate the first propulsion unit, the second propulsion unit, the first wing, and the second wing.
    Type: Grant
    Filed: April 23, 2013
    Date of Patent: July 21, 2015
    Assignee: Google Inc.
    Inventors: Eric Peeters, William Graham Patrick
  • Publication number: 20130142650
    Abstract: A turbine device, including: a turbine housing including an inlet, a flow channel, an outlet, a middle partition, an arced partition; a turbine impeller; a gas outlet; and an exhaust manifold. The turbine impeller and the gas outlet are arranged inside the turbine housing. The exhaust manifold is connected to the inlet. The flow channel is arranged inside the turbine housing. The outlet is arranged on the flow channel close to the turbine impeller. The middle partition is disposed inside the flow channel and divides the flow channel into a left flow channel and a right flow channel. The arced partition is arranged in both the left and right flow channels. One end of the arced partition is in a rigid connection with the middle partition, and the other end of the arced partition is close to the outlet of the turbine housing.
    Type: Application
    Filed: February 3, 2013
    Publication date: June 6, 2013
    Applicant: KANGYUE TECHNOLOGY CO., LTD.
    Inventor: KANGYUE TECHNOLOGY CO., LTD.
  • Patent number: 7334990
    Abstract: A gas compressor based on the use of a driven rotor having an axially oriented compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which forms a supersonic shockwave axially, between adjacent strakes. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the gas compression ramp on a strake, the shock capture lip on the adjacent strake, and captures the resultant pressure within the stationary external housing while providing a diffuser downstream of the compression ramp.
    Type: Grant
    Filed: March 28, 2005
    Date of Patent: February 26, 2008
    Assignee: Ramgen Power Systems, Inc.
    Inventors: Shawn P. Lawlor, Mark A. Novaresi, Charles C. Cornelius
  • Patent number: 6510683
    Abstract: An apparatus (100) for generation of mechanical and electrical power. Ramjet type thrust modules (102a, 102b) operate at supersonic speeds (preferably Mach 3 to 4) at the distal or tip ends (116a, 116b) of a low aerodynamic drag rotor (106). Rotor (106) is affixed at a hub means (114) to a power output means including central rotating upper (104a) and lower (104b) shaft portions. Rotor (106) is a structural member which transmits the thrust generated by the thrust modules (102a, 102b) to the shaft portions (104a, 104b). The ramjet thrust modules (102a, 102b) capture and compress a supplied free air stream, which is mixed with and oxidizes a convenient liquid or gaseous fuel such as natural gas from fuel supply means (103). Combustion gases expand to create thrust to rotate the thrust modules (102a, 102b), which are constrained by the rotor (106), to rotates about the axis defined by the shaft (104a, 104b) at supersonic thrust module velocities, producing shaft energy.
    Type: Grant
    Filed: March 14, 1994
    Date of Patent: January 28, 2003
    Assignee: Ramgen Power Systems, Inc.
    Inventor: Shawn P. Lawlor
  • Patent number: 6250069
    Abstract: An apparatus (100) for generation of mechanical and electrical power. Ramjet type thrust modules (102a, 102b) operate at supersonic speeds (preferably Mach 3 to 4) at the distal or tip ends (116a, 116b) of a low aerodynamic drag rotor (106). Rotor (106) is affixed at a hub means (114) to a power output means including central rotating upper (104a) and lower (104b) shaft portions. Rotor (106) is a structural member which transmits the thrust generated by the thrust modules (102a, 102b) to the shaft portions (104a, 104b). The ramjet thrust modules (102a, 102b) capture and compress a supplied free air stream, which is mixed with and oxidizes a convenient liquid or gaseous fuel such as natural gas from fuel supply means (103). Combustion gases expand to create thrust to rotate the thrust modules (102a, 102b), which are constrained by the rotor (106), to rotates about the axis defined by the shaft (104a, 104b) at supersonic thrust module velocities, producing shaft energy.
    Type: Grant
    Filed: March 14, 1994
    Date of Patent: June 26, 2001
    Assignee: Ramgen Power Systems, Inc.
    Inventor: Shawn P. Lawlor
  • Patent number: 5984635
    Abstract: A helicopter aircraft with an upper hollow center circular plenum in gaseous communication with a plurality of hollow hinged attached rotor blades. Below the plenum and in gaseous communication with it are two fan jet engines whose gaseous output can be inputted to the plenum and their attached hollow rotor blades through a operator controlled valve system. This same valve system can be adjusted to completely or partially by-pass the plenum and discharge the jet engines' gas to a common rear rudder located on the aircraft's to provide directional control to the aircraft when in flight. The plenum is shaped lenticular in cross section similar to an airplane wing to provide a lifting body when the helicopter is in forward flight.
    Type: Grant
    Filed: August 24, 1998
    Date of Patent: November 16, 1999
    Inventor: Merrill Manson Keller
  • Patent number: 5934873
    Abstract: A helicopter includes a rotor tip jet engine which combines ram compression and centrifugal compression to increase the thrust. A first flow of fuel is dispersed in the ram air and is carried into a combustion area of the engine. A separate flow of fuel is injected into the centrifugally compressed air before the fuel air mixture enters the combustion area. For helicopters and other applications, the ram jet engine combines ram air and a separate mass of compressed air which is directed into the combustion area for increased thrust. A regulator or control mechanism is also provided for regulating the quantity of compressed air which is added. The regulator or control mechanism may also be used to cut off or stop the addition of the separate mass of compressed air.
    Type: Grant
    Filed: September 29, 1997
    Date of Patent: August 10, 1999
    Assignee: Safe Flight Instrument Corporation
    Inventor: Leonard M. Greene
  • Patent number: 5709076
    Abstract: Novel power generation method and apparatus. At least partially unshrouded type supersonic ramjet thrust module(s) are provided at the periphery of a low aerodynamic drag tapered disc rotor. The rotor is affixed at a central hub to a shaft, and rotates about an axis defined by the shaft. The rotor acts as a structural member which transmits to the shaft the thrust generated by the ramjets. In the preferred embodiment, an unshrouded ramjet inlet captures and compresses an impinging inlet air stream by utilizing the thrust module inlet structures and an adjacent housing sidewall. The compressed air inlet stream provides oxygen for mixing with a fuel such as natural gas which is injected into the through flow air stream upwind of the ramjet thrust modules. Fuel is oxidized in the ramjet thrust module(s) to produce expanding combustion gases.
    Type: Grant
    Filed: June 7, 1995
    Date of Patent: January 20, 1998
    Inventor: Shawn P. Lawlor
  • Patent number: 5372005
    Abstract: Thrust modules are provided at the distal ends of a low aerodynamic drag rotor. The rotor is affixed at a central hub to a shaft, and rotates about an axis defined by the shaft. In the preferred embodiment the thrust modules are ramjet engines, and the ramjet inlet captures and compresses an impinging inlet air stream. The compressed air stream thus provides oxygen for mixing with a fuel which is supplied to the ramjet thrust modules from a convenient fuel source such as natural gas. The fuel is oxidized in the thrust modules to produce combustion gases. The gases expand, and the exhaust flow creates thrust which is substantially tangential to the circumference defined by the distal end of the rotor. The gases expand to motivate the ramjet engine to rotate about the shaft at supersonic thrust module velocities, producing shaft energy.
    Type: Grant
    Filed: September 14, 1992
    Date of Patent: December 13, 1994
    Inventor: Shawn P. Lawler
  • Patent number: 4702437
    Abstract: A helicopter has a low profile electric motor mounted in each of the rotor blades to drive a cross-flow fan which draws air in through a slot at the leading edge of the blade and forces it out through an opposing slot adjacent the trailing edge of the blade to provide the thrust for rotating the rotor blade. An engine is located in the fuselage of the helicopter for driving an electric generator to produce the electricity supplied to the motors mounted in the blades. In addition, yaw control is achieved without the necessity of tail structure or a tail rotor using a small electric motor driving or absorbing power from the main rotor shaft. Both the yaw control motor and the main rotor shaft tilt together as a rigid unit. Pitch and roll control is achieved without the necessity of aerodynamic surfaces by movement of the main rotor support mast about a gimbal bearing support located above the center of gravity of the helicopter.
    Type: Grant
    Filed: February 7, 1985
    Date of Patent: October 27, 1987
    Inventor: Hoyt A. Stearns, Jr.
  • Patent number: 4010919
    Abstract: This invention relates to an improved design for autogyros. It involves a more desirable layout of cockpit/engine placement than heretofore thought of. It provides for improved efficiency, visibility and balance and solves some of the problems of recent autogyros. Further, it provides for an improved and simplified rotor spin up mechanism.
    Type: Grant
    Filed: December 5, 1975
    Date of Patent: March 8, 1977
    Inventor: Gerald L. Breuner