Invention Grant
US08167559B2 Turbine vane for a gas turbine engine having serpentine cooling channels within the outer wall 有权
用于在外壁内具有蛇形冷却通道的燃气涡轮发动机的涡轮叶片

  • Patent Title: Turbine vane for a gas turbine engine having serpentine cooling channels within the outer wall
  • Patent Title (中): 用于在外壁内具有蛇形冷却通道的燃气涡轮发动机的涡轮叶片
  • Application No.: US12396660
    Application Date: 2009-03-03
  • Publication No.: US08167559B2
    Publication Date: 2012-05-01
  • 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: F01D5/14
  • IPC: F01D5/14
Turbine vane for a gas turbine engine having serpentine cooling channels within the outer wall
Abstract:
A turbine vane for a gas turbine engine having an outer wall containing a plurality of serpentine cooling channels. The serpentine cooling channels may be configured to receive cooling fluids from internal cooling fluids supply channels. The serpentine cooling channels may be positioned in the pressure side and suction side outer walls and configured such that a first pass is positioned radially outward from an internal chamber a greater distance than a second pass. As such, cooling fluids are first passed proximate to an outer surface where the fluids are heated and then passed proximate to an inner surface, thereby establishing a smaller thermal gradient than typically found in conventional turbine blade outer walls.
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