Invention Grant
US08096770B2 Trailing edge cooling for turbine blade airfoil 有权
涡轮叶片翼型的后缘冷却

  • Patent Title: Trailing edge cooling for turbine blade airfoil
  • Patent Title (中): 涡轮叶片翼型的后缘冷却
  • Application No.: US12396629
    Application Date: 2009-03-03
  • Publication No.: US08096770B2
    Publication Date: 2012-01-17
  • Inventor: George Liang
  • Applicant: George Liang
  • Applicant Address: US FL Orlando
  • Assignee: Siemens Energy, Inc.
  • Current Assignee: Siemens Energy, Inc.
  • Current Assignee Address: US FL Orlando
  • Main IPC: F01D5/18
  • IPC: F01D5/18
Trailing edge cooling for turbine blade airfoil
Abstract:
A gas turbine engine hollow turbine airfoil having chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between the leading edge and the trailing edge. A trailing edge rib extends from the trailing edge toward the leading edge, and forms a solid member between the pressure and suction sidewalls. A cooling fluid channel extends in the spanwise direction through the airfoil adjacent to the trailing edge rib. A plurality of fluid chambers are formed in the trailing edge rib. Film cooling holes extend from the fluid chambers to the pressure and suction sidewalls, and trailing edge discharge holes extend from the fluid chambers to the trailing edge. A metering hole is associated with each of the fluid chambers to define a flow restriction connecting the cooling fluid channel to a respective fluid chamber.
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