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Inlet film cooling of turbine end wall of a gas turbine engine
Inlet film cooling of turbine end wall of a gas turbine engine
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机译:燃气轮机涡轮端壁的进气膜冷却
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摘要
The disclosure provides a gas turbine engine having a plurality of nozzle vanes extending between an inner shroud wall and an outer shroud wall of the engine. Each of the vanes includes a leading edge and at least one cooling protrusion extending upstream from a center of the leading edge. A cooling system is provided that is operable to inject cooling air upstream from the vanes. The disclosure also provides a method of cooling a gas turbine engine. The method includes the steps of supplying cooling air to an engine nozzle upstream of a gas directing vane, and adjusting the flow of the cooling air with a cooling protrusion extending forward from a leading edge center of the vane.
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