Invention Grant
US07938624B2 Cooling arrangement for a component of a gas turbine engine 有权
燃气涡轮发动机的部件的冷却装置

  • Patent Title: Cooling arrangement for a component of a gas turbine engine
  • Patent Title (中): 燃气涡轮发动机的部件的冷却装置
  • Application No.: US11889709
    Application Date: 2007-08-15
  • Publication No.: US07938624B2
    Publication Date: 2011-05-10
  • Inventor: Ian Tibbott
  • Applicant: Ian Tibbott
  • Applicant Address: GB London
  • Assignee: Rolls-Royce PLC
  • Current Assignee: Rolls-Royce PLC
  • Current Assignee Address: GB London
  • Agency: Oliff & Berridge, PLC
  • Priority: GB0617992.3 20060913
  • Main IPC: F01D25/12
  • IPC: F01D25/12
Cooling arrangement for a component of a gas turbine engine
Abstract:
A component, such as a blade, vane or combustor wall of a gas turbine engine comprises two walls defining a coolant passage and has an array of pedestals extending between the two walls for heat removal. Each pedestal changes in cross-section along its length. Alternate rows of pedestals are arranged such that their larger cross-sectional area is adjacent one wall then the other. When a coolant flows through the passage it is forced to flow between one wall and the other wall so as to increase turbulence and hence mixing for a more even coolant temperature. The array of pedestals can also be used to tailor the individual heat loads on each wall independently and has the ability to use differing levels of blockage to counter adverse pressure gradients along successive rows of pedestals.
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