Patents by Inventor John H. R. Sadler

John H. R. Sadler 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: 5192186
    Abstract: A shroud ring suitable for the turbine of a gas turbine engine comprises an annular heat pipe with radially inwardly directed flanges which are bridged by a plurality of abutting tiles so that together they define an annular chamber. The annular chamber serves to provide a thermal barrier between the tiles and a major portion of the heat pipe. The operating temperature of the shroud ring is thus reduced thereby ensuring reduced radial expansion.
    Type: Grant
    Filed: November 20, 1984
    Date of Patent: March 9, 1993
    Assignee: Rolls-Royce plc
    Inventor: John H. R. Sadler
  • Patent number: 5031288
    Abstract: A compressor rotor structure for a gas turbine engine is made by linear friction bonding stub rooted blades and separate platform pieces, to lands between slots in a compressor disc periphery. These results an integral structure in which the periphery of the disc has had metal removed so as to form the slots and the disc is thus lightened, and the stub roots and platform pieces cooperate to form the airflow inner annulus wall.
    Type: Grant
    Filed: October 1, 1990
    Date of Patent: July 16, 1991
    Assignee: Rolls-Royce, plc
    Inventor: John H. R. Sadler
  • Patent number: 4484859
    Abstract: In order to damp possible vibration of a rotor blade for a gas turbine engine, the blade has a hollow tip portion with an internal surface extending across the direction of the centrifugal field on the blade. A weight comprising e.g. Silicon Nitride or Carbide is caused by centrifugal force to bear on this surface. Relative motion and hence friction between the weight and the surface serves to damp vibration of the blade.
    Type: Grant
    Filed: December 13, 1982
    Date of Patent: November 27, 1984
    Assignee: Rolls-Royce Limited
    Inventors: George Pask, John H. R. Sadler, John F. Coplin
  • Patent number: 4441859
    Abstract: A rotor blade for a gas turbine engine is provided with an internal tip damper comprising a damper weight which rotates under centrifugal load to cam itself into engagement between two components of the aerofoil, in particular the interior surface of the hollow aerofoil and the tip of a cooling air entry tube. By altering the degree of offset between the center of gravity of the weight and its support the frictional engagement may be varied.
    Type: Grant
    Filed: January 20, 1982
    Date of Patent: April 10, 1984
    Assignee: Rolls-Royce Limited
    Inventor: John H. R. Sadler
  • Patent number: 4422229
    Abstract: An aerofoil member such as a blade or vane for a gas turbine engine comprises a hollow aerofoil with a plug of porous material filling a region of the hollow interior. The porous material forms at least part of the external surface of the aerofoil so that cooling fluid can flow from the interior of the aerofoil through the plug to the external surface of the aerofoil. The plug is preferably at the leading or trailing edge of the aerofoil. Methods of making the member include investment casting using a porous ceramic core to form the porous plug, or using sintered particulate material to form the porous plug.
    Type: Grant
    Filed: December 16, 1981
    Date of Patent: December 27, 1983
    Assignee: Rolls-Royce Limited
    Inventors: John H. R. Sadler, George Pask, Wilfred H. Wilkinson
  • Patent number: 4419044
    Abstract: A gas turbine engine has a turbine which includes an annular array of rotary aerofoil blades surrounded by an annular shroud member. All or a major portion of the annular shroud member is constituted by a heat pipe. A distance measuring device is provided to measure the clearance between the tips of the rotary aerofoil blades and the shroud member and its output is monitored by a control unit. The control unit is adapted to control a valve which regulates the flow rate of cooling air directed onto the heat pipe. The arrangement is such that the temperature of the heat pipe is maintained at a level which is consistent with the clearance between the rotary aerofoil blade tips and the annular shroud member being within a predetermined range of values.
    Type: Grant
    Filed: November 6, 1981
    Date of Patent: December 6, 1983
    Assignee: Rolls-Royce Limited
    Inventors: Brian Barry, John H. R. Sadler, Susan M. Allen, David W. Artt