Patents by Inventor Colin E Scrase

Colin E Scrase 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).

  • Gas turbine engine
    Patent number: 7448845
    Abstract: A turbofan gas turbine engine (10) comprises a fan rotor and a compressor rotor (62). The fan rotor (24) carries a plurality of circumferentially spaced radially outwardly extending fan blades (26). The compressor rotor carries a plurality of circumferentially spaced radially outwardly extending compressor blades (64). The fan rotor (24) is mounted on a fan shaft (38) and the compressor rotor (62) is mounted on a compressor shaft (68). The compressor shaft (68) is arranged around the fan shaft (38). The fan rotor (24) is rotatably mounted on a support structure (40) by a first bearing (50) and the compres˜sor rotor (62) is rotatably mounted on the support structure (40) by a second bearing (58) spaced axially from the first bearing (50). The fan and compressor rotors (24,62) are normally arranged coaxially with each other and with the support structure (40).
    Type: Grant
    Filed: May 16, 2006
    Date of Patent: November 11, 2008
    Assignee: Rolls-Royce plc
    Inventors: Nigel D. Stephenson, Colin E. Scrase
  • Gas turbine engine
    Patent number: 7153091
    Abstract: A turbofan gas turbine engine (10) comprises a fan rotor and a compressor rotor (62). The fan rotor (24) carries a plurality of circumferentially spaced radially outwardly extending fan blades (26). The compressor rotor carries a plurality of circumferentially spaced radially outwardly extending compressor blades (64). The fan rotor (24) is mounted on a fan shaft (38) and the compressor rotor (62) is mounted on a compressor shaft (68). The compressor shaft (68) is arranged around the fan shaft (38). The fan rotor (24) is rotatably mounted on a support structure (40) by a first bearing (50) and the compressor rotor (62) is rotatably mounted on the support structure (40) by a second bearing (58) spaced axially from the first bearing (50). The fan and compressor rotors (24, 62) are normally arranged coaxially with each other and with the support structure (40).
    Type: Grant
    Filed: April 27, 2004
    Date of Patent: December 26, 2006
    Assignee: Rolls-Royce plc
    Inventors: Nigel D Stephenson, Colin E Scrase
  • Gas turbine engine
    Publication number: 20040240985
    Abstract: A turbofan gas turbine engine (10) comprises a fan rotor and a compressor rotor (62). The fan rotor (24) carries a plurality of circumferentially spaced radially outwardly extending fan blades (26). The compressor rotor carries a plurality of circumferentially spaced radially outwardly extending compressor blades (64). The fan rotor (24) is mounted on a fan shaft (38) and the compressor rotor (62) is mounted on a compressor shaft (68). The compressor shaft (68) is arranged around the fan shaft (38). The fan rotor (24) is rotatably mounted on a support structure (40) by a first bearing (50) and the compressor rotor (62) is rotatably mounted on the support structure (40) by a second bearing (58) spaced axially from the first bearing (50). The fan and compressor rotors (24, 62) are normally arranged coaxially with each other and with the support structure (40).
    Type: Application
    Filed: April 27, 2004
    Publication date: December 2, 2004
    Inventors: Nigel D. Stephenson, Colin E. Scrase