Rotating, Oscillating, Or Reciprocating Patents (Class 60/39.78)
  • Patent number: 8925296
    Abstract: The invention relates to a jet engine (1), in particular an aircraft jet engine, including at least one combustion chamber (3). The combustion chamber (3) is connected to at least one compressed gas intake (4) and to at least one burnt gas outlet (5). Said burnt gas outlet(s) (5) include an exhaust valve. The exhaust valve includes two rotary parts (7), referred to as rotary exhaust parts, the rotary exhaust parts (7) including curved walls (8) and intermediate walls (9) connecting the curved walls (8), and rotating in a coordinated, continuous fashion such that said valve is in a closed position in order to block the gas during at least one combustion step, and in an open position in order to define a space (10) through which the gas flows out from the combustion chamber (3) during at least one expansion step.
    Type: Grant
    Filed: January 15, 2010
    Date of Patent: January 6, 2015
    Inventor: Michel Aguilar
  • Patent number: 8813474
    Abstract: An engine including a means for supplying fuel to the combustion chamber of the fire tube, that includes a variable-volume transfer chamber for receiving fuel, a fuel transfer means from the tank of the engine towards the transfer chamber, and injection means for injecting fuel into the combustion chamber from the transfer chamber. The engine further includes an elastic return at least partially defined by the fuel contained in the transfer chamber.
    Type: Grant
    Filed: June 4, 2009
    Date of Patent: August 26, 2014
    Assignee: MBDA France
    Inventors: Emeric Daniau, Fran├žois Falempin, Etienne Bobo, Jean-Pierre Minard
  • Patent number: 8555612
    Abstract: A constant volume combustor device includes, in one form, a detonative combustion. The apparatus includes inlet and outlet ports that interface with a plurality of fluid flow passageways on a rotor. A buffer gas is routed through some of the inlet and outlet ports and into and out of the plurality of fluid flow passageways. One of the inlet ports is a buffer gas inlet port that when placed in registry with a fluid flow passageway allows the flow of buffer gas into the respective passageway. Fuel is delivered into the buffer gas proximate the buffer gas inlet port so that only a portion of the buffer gas inlet port receives any fuel. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings.
    Type: Grant
    Filed: February 21, 2012
    Date of Patent: October 15, 2013
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Philip H. Snyder, Calvin W. Emmerson
  • Patent number: 8375722
    Abstract: An apparatus and method for inducing waves within a container arranged to permit a through-flow of fluid flowing generally from an inlet of the container to an exit of the container, wherein the container has wave inducing means located at the exit of the container, the wave inducing means being operable to vary the area of the exit thereby inducing waves within the container. The apparatus may form part of a combustor test rig.
    Type: Grant
    Filed: July 3, 2007
    Date of Patent: February 19, 2013
    Assignee: Rolls-Royce plc
    Inventors: Nickolaos Pilatis, Arthur L Rowe
  • Publication number: 20110214407
    Abstract: In one embodiment, a pulse detonation system includes a pulse detonation tube including a base tube and a thermally protective layer disposed adjacent to an inner surface of the base tube. The thermally protective layer is configured to limit temperature fluctuations at the inner surface of the base tube to less than approximately 20 degrees Celsius during operation of the pulse detonation system, and the thermally protective layer does not comprise a ceramic coating.
    Type: Application
    Filed: March 4, 2010
    Publication date: September 8, 2011
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Brian Gene Brzek, Adam Rasheed, Narendra Digamber Joshi
  • Publication number: 20110088370
    Abstract: According to the invention, the engine (I) includes a means for supplying fuel to the combustion chamber (7) of the fire tube (2), that comprises a variable-volume transfer chamber (9) for receiving fuel, a fuel transfer means (10) from the tank (4) of the engine (I) towards the transfer chamber (9), and injection means (11) for injecting fuel into the combustion chamber (7) from the transfer chamber (9). The engine further includes an elastic return means at least partially defined by the fuel contained in the transfer chamber (9).
    Type: Application
    Filed: June 4, 2009
    Publication date: April 21, 2011
    Inventors: Emeric Daniau, Francois Falempin, Etienne Bobo, Jean-Pierre Minard
  • Publication number: 20090193786
    Abstract: A continuous detonation system, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel. In this way, a mixture of the fuel and air is continuously detonated within each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature.
    Type: Application
    Filed: February 1, 2008
    Publication date: August 6, 2009
    Applicant: General Electric Company
    Inventors: Kurt David Murrow, Lawrence Butler
  • Patent number: 7328570
    Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of the fan section, the booster compressor including a first compressor blade row and a second compressor blade row connected to a second drive shaft and interdigitated with the first compressor blade row; and, a pulse detonation system for powering the first and second drive shafts. The pulse detonation system powers only the second drive shaft during a first designated condition of the gas turbine engine and both the first drive shaft and the second drive shaft during a second designated condition of the gas turbine engine. The first and second drive shafts are powered independently of each other by the pulse detonation system.
    Type: Grant
    Filed: September 1, 2004
    Date of Patent: February 12, 2008
    Assignee: General Electric Company
    Inventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, James Paul Davidson
  • Patent number: 7251928
    Abstract: Pressure and density of a gaseous mixture are increased in the process of introducing the gaseous mixture into the combustor of an air-breathing pulse detonation engine employing atmospheric oxygen as an oxidizer. The exit valve 20 able to be opened and closed is provided at the outlet of the combustor 15, an air cooler 12 is provided in the exit of the intake, and density is increased by exchange of heat of the air received at the intake with a coolant in the air cooler 12. Furthermore, by closing the exit valve 20 provided in the outlet of the combustor during the process of loading the gaseous mixture, transition to the detonation process is possible without expansion of the high-pressure high density air obtained by ram-compression at the intake.
    Type: Grant
    Filed: February 18, 2005
    Date of Patent: August 7, 2007
    Assignee: Japanese Aerospace Exploration Agency
    Inventors: Takayuki Kojima, Tetsuya Sato, Hiroaki Kobayashi
  • Patent number: 7124573
    Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough. The pulse detonation system includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages are disposed therethrough.
    Type: Grant
    Filed: March 18, 2004
    Date of Patent: October 24, 2006
    Assignee: General Electric Company
    Inventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, Ching-Pang Lee
  • Patent number: 7062901
    Abstract: The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled to the at least one periodic combustion chamber. The supersonic exhaust nozzle is configured with a variable exhaust expansion ratio.
    Type: Grant
    Filed: July 15, 2005
    Date of Patent: June 20, 2006
    Assignee: Sierra Engineering Incorporated
    Inventor: Curtis William Johnson
  • Patent number: 6981365
    Abstract: The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled to the at least one periodic combustion chamber. The supersonic exhaust nozzle is configured with a variable exhaust expansion ratio.
    Type: Grant
    Filed: December 26, 2002
    Date of Patent: January 3, 2006
    Assignee: Sierra Engineering Incorporated
    Inventor: Curtis William Johnson
  • Patent number: 6901738
    Abstract: A turbine engine has a circumferential array of combustion chamber conduits downstream of the compressor and upstream of the turbine. Means are provided for directing oxygen-containing gas from the compressor to the conduits so as to cyclically feed a gas charge into each conduit through its first port and permit discharge of combustion products of the charge and fuel through both the first and second ports.
    Type: Grant
    Filed: June 26, 2003
    Date of Patent: June 7, 2005
    Assignee: United Technologies Corporation
    Inventors: Bradley C. Sammann, Wendell V. Twelves, Jr., Gary D. Jones
  • Patent number: 6889505
    Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation chambers is disposed therein. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement around the forward surface, the aft surface, and the outer circumferential surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein which sequentially align with the detonation chambers as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation chambers of each detonation stage so that reaction forces induced by the detonation cycles create a torque which causes the cylindrical member to rotate.
    Type: Grant
    Filed: April 2, 2003
    Date of Patent: May 10, 2005
    Assignee: General Electric Company
    Inventors: Lawrence Butler, Kattalaicheri Srinivasan Venkataramani, Kurt David Murrow, Ivett Alejandra Leyva
  • Publication number: 20030154707
    Abstract: A rotary inlet flow controller, with one or more open ducts extending therethrough, aerodynamically controls the amount and velocity of the flow of air to combustion chambers of pulse detonation engines, or other engines, without imposing large cyclic airflow transients in the diffuser of the air intake. The ducted rotary inlet flow controller supplies airflow and sealing in synchronization with the cycles of the engine: airflow and fueling supply, sealing, combustion, and re-opening for additional airflow. This controller will supply near-uniform, continuous airflow to the engine. The preferred controller has one or more propeller-like blades that are designed to cyclically and sequentially duct incoming flow to the inlet ports of the combustion chambers, while also providing the capability of sealing the ports during combustion.
    Type: Application
    Filed: September 7, 2001
    Publication date: August 21, 2003
    Inventors: Bobby W. Sanders, Lois J. Weir
  • Patent number: 6464490
    Abstract: A pulsating combustor has a plurality of annular plate elements (12), which are stacked in spaced vertical alignment so as to define a central space (14). There is a plurality of slot-like passages (18), one such passage between each adjacent pair of elements. There is at least one combustion chamber (21) in communication with at least one slot-like passage. Fuel and combustion air are fed into the combustion chambers. There is a spark plug for igniting a fuel-air mixture in the combustion chamber. Preferably there is a first housing (24) defining the combustion chamber and another housing defining a collection chamber for combustion gases emerging from the passages.
    Type: Grant
    Filed: April 27, 2001
    Date of Patent: October 15, 2002
    Assignee: Clean Energy Combustion Systems, Inc.
    Inventor: John D. Chato
  • Patent number: 6439503
    Abstract: A pulse detonation cluster includes a cluster housing and a plurality of pulse detonation engines mounted within the housing. Each pulse detonation engine has an inner tubular housing rigidly and concentrically mounted within a cylindrical bore of an outer tubular housing. The inner housing has a plurality of inner housing ports, and the outer housing has a plurality of outer housing ports. A detonation chamber is formed in the annulus between the inner housing and the outer housing. An outer valve sleeve is rotatably mounted to the outer housing for selectively allowing air to enter the detonation chamber through the outer housing ports. A fuel delivery member is aligned with each inner housing port to deliver fuel to the detonation chamber through the inner housing ports. An inner sleeve is mounted to the inner housing to protect the fuel delivery members during detonation. The air and fuel mixture is detonated by several igniters located in the detonation chamber.
    Type: Grant
    Filed: July 10, 2000
    Date of Patent: August 27, 2002
    Assignee: Lockheed Martin Corporation
    Inventors: Don D. Winfree, Louis G. Hunter, Jr., Billy D. Couch
  • Patent number: 6381947
    Abstract: In a staged gas turbine combustion engine, each combustion chamber of an annular array of chambers includes at least a pilot and a main combustion stage each having an fuel injection nozzle; the method includes feeding fuel continuously in operation to the pilot stage nozzle and controlling the fuel flow to the main stage nozzle through a pulsing and dosing valve to control the fuel flow delivered to the main stage fuel nozzle.
    Type: Grant
    Filed: May 10, 2001
    Date of Patent: May 7, 2002
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: F. Richard Emmons
  • Patent number: 6212875
    Abstract: An air compressor device and method for producing compressed air. The device comprises a rotatable cylinder assembly having a drive shaft extending along a central axis and three equally sized combustion chambers extending parallel to the center axis. The drive shaft is connected to a turbine or other drive means which provides rotational movement to the drive shaft and cylinder assembly. Two circular end plates are concentrically positioned with the central axis on each end of the cylinder assembly. The end plates are stationary with respect to the rotatable cylinder assembly and comprise an intake plate and an outlet plate. Openings are provided on the end plates to allow for communication of a gas into and out of the combustion chambers at designated times during operation of the compressor. A fuel injector is positioned upon the intake plate along with an ignition means. The device operates on a modified Schmidt-type pulsejet cycle. Fresh air is received in each of the chambers and compressed.
    Type: Grant
    Filed: April 7, 1999
    Date of Patent: April 10, 2001
    Inventor: Brian F. Lewis