Patents by Inventor David M Beaven

David M Beaven has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 11585278
    Abstract: A method of determining one or more fuel characteristics of an aviation fuel for powering a gas turbine engine of an aircraft includes: measuring one or more trace substance parameters of the fuel, the one or more trace substance parameters each associated with a respective trace substance in the fuel; and determining one or more fuel characteristics of the fuel based on the one or more trace substance parameters. Further, a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.
    Type: Grant
    Filed: June 29, 2022
    Date of Patent: February 21, 2023
    Assignee: ROLLS-ROYCE plc
    Inventors: Peter Swann, David M Beaven, Craig W Bemment, Alastair G Hobday, Benjamin J Keeler, Christopher P Madden, Martin K Yates
  • Patent number: 9145776
    Abstract: A blade assembly including: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device having a root part and a hub part, the root part being located radially inwards of the hub part in a retention cavity in use, wherein at least a portion of the root part enters the retention cavity via an interlock which prevents radial separation of the root and hub in the event of a primary retention device failure.
    Type: Grant
    Filed: May 30, 2012
    Date of Patent: September 29, 2015
    Assignee: ROLLS-ROYCE plc
    Inventors: Kenneth J Mackie, David M Beaven
  • Patent number: 8453458
    Abstract: Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped centre fairing is associated with an exit nozzle and a bypass duct such that channels between the fairing, nozzle exit and duct can be adjusted to change the available areas. Such variation is achieved by relative axial displacement, typically of the exit nozzle using an appropriate mechanism.
    Type: Grant
    Filed: January 23, 2007
    Date of Patent: June 4, 2013
    Assignee: Rolls-Royce PLC
    Inventors: John R Whurr, Richard G Stretton, David M Beaven, Nicholas Howarth
  • Publication number: 20120321476
    Abstract: A blade assembly including: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device having a root part and a hub part, the root part being located radially inwards of the hub part in a retention cavity in use, wherein at least a portion of the root part enters the retention cavity via an interlock which prevents radial separation of the root and hub in the event of a primary retention device failure.
    Type: Application
    Filed: May 30, 2012
    Publication date: December 20, 2012
    Applicant: ROLLS-ROYCE PLC
    Inventors: Kenneth J. MACKIE, David M. BEAVEN
  • Patent number: 7850417
    Abstract: In a contra rotating propeller engine propeller blade assemblies are provided which rotate in opposite directions as a result of association with an epicyclic gear assembly acting as a differential gearbox. A carrier is provided to drive one propeller blade assembly. Actuators are provided to cause pitch angle adjustment of the respective propeller blades of the assemblies. These actuators, are secured upon a stationary structure and act through actuator rods and appropriate mechanisms to cause such angular pitch adjustment. Rotational de-couplers are provided to rotationally isolate the actuators while an actuator rod part acts across the assemblies and a rotational de-coupler to de-couple contra rotation between the assemblies while still allowing axial displacement for adjustment of the other propeller blade assembly.
    Type: Grant
    Filed: June 22, 2007
    Date of Patent: December 14, 2010
    Assignee: Rolls-Royce PLC
    Inventor: David M. Beaven
  • Publication number: 20090158704
    Abstract: Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped centre fairing is associated with an exit nozzle and a bypass duct such that channels between the fairing, nozzle exit and duct can be adjusted to change the available areas. Such variation is achieved by relative axial displacement, typically of the exit nozzle using an appropriate mechanism.
    Type: Application
    Filed: January 23, 2007
    Publication date: June 25, 2009
    Applicant: ROLLS-ROYCE PLC
    Inventors: John R. Whurr, Richard G. Stretton, David M. Beaven, Nicholas Howarth
  • Publication number: 20080020891
    Abstract: In a contra rotating propeller engine propeller blade assemblies are provided which rotate in opposite directions as a result of association with an epicyclic gear assembly acting as a differential gearbox. A carrier is provided to drive one propeller blade assembly. Actuators are provided to cause pitch angle adjustment of the respective propeller blades of the assemblies. These actuators, are secured upon a stationary structure and act through actuator rods and appropriate mechanisms to cause such angular pitch adjustment. Rotational de-couplers are provided to rotationally isolate the actuators whilst an actuator rod part acts across the assemblies and a rotational de-coupler to de-couple contra rotation between the assemblies whilst still allowing axial displacement for adjustment of the other propeller blade assembly.
    Type: Application
    Filed: June 22, 2007
    Publication date: January 24, 2008
    Applicant: ROLLS-ROYCE PLC
    Inventor: David M. Beaven
  • Patent number: 7296414
    Abstract: A mounting assembly (10) for mounting a gas turbine engine on an aircraft. The assembly (10) comprising four equispaced hydraulic piston and cylinder thrust links (16) connecting between the engine fan case (12) and the air intake (14), which intake (14) is mounted to the airframe.
    Type: Grant
    Filed: October 1, 2004
    Date of Patent: November 20, 2007
    Assignee: Rolls-Royce plc
    Inventors: Richard G Stretton, Peter K Beardsley, David M Beaven
  • Patent number: 6098399
    Abstract: A ducted fan gas turbine has a fan shaft which is supported at its upstream end by a bearing. In the event of damage to the engine's fan, frangible bolts fracture to permit radial movement of the shaft. That movement is limited by the sequential engagement of the outer race of the bearing with first and second movement limiting portions on fixed structure of the engine. This alters the natural frequency of vibration of the fan, so permitting the fan to windmill without excessive vibration.
    Type: Grant
    Filed: February 10, 1998
    Date of Patent: August 8, 2000
    Assignee: Rolls-Royce plc
    Inventors: Martyn Richards, John W Allen, Kenneth F Udall, David M Beaven
  • Patent number: 6073439
    Abstract: A ducted fan gas turbine engine is provided with a fan which is carried by a shaft. Frangible fuse pins maintain the shaft carrying the fan coaxial with the engine longitudinal axis. In the event of severe fan damage, the fuse pins fracture and the fan shaft orbits about the engine longitudinal axis. An annular resilient member is provided to exert a radially inward restoration force upon the fan shaft following such an event in order to reduce vibration.
    Type: Grant
    Filed: March 4, 1998
    Date of Patent: June 13, 2000
    Assignee: Rolls-Royce plc
    Inventors: David M Beaven, Kenneth F Udall
  • Patent number: 6009701
    Abstract: A ducted fan gas turbine engine is provided with a fan which is carried by a shaft. A frangible fuse ring maintains the shaft carrying the fan coaxial with the engine longitudinal axis. In the event of severe fan damage, the fuse ring (28) fractures and the fan shaft orbits about the engine longitudinal axis. A pair of threaded members (39, 41), one of which is of generally frusto-conical configuration, cooperate as a result of the orbiting motion to restore the coaxial relationship between the fan shaft and the engine longitudinal axis.
    Type: Grant
    Filed: December 19, 1997
    Date of Patent: January 4, 2000
    Assignee: Rolls-Royce, PLC
    Inventors: Christopher Freeman, Peter G G Farrar, Martyn Richards, John W Allen, Kenneth F Udall, David M Beaven