Inlet film cooling of turbine end wall of a gas turbine engine
OwnerLuzeng Zhang, Hee Mooninventors
Life of this patent
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Abstract
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.
Claims20
A gas turbine engine comprising:
- a plurality of nozzle vanes extending between an inner shroud wall and an outer shroud wall of said engine, each of said vanes including a leading edge;
- said vanes each including at least one cooling protrusion extending upstream from a center of said leading edge;
- and
- a cooling system operable to inject cooling air upstream from said vanes.
A gas turbine engine nozzle section comprising:
- a first shroud portion having an end wall;
- a second shroud portion;
- at least one vane connected between said first and second shroud portions, said at least one vane including an airfoil portion and a cooling protrusion disposed adjacent said end wall.
A method of cooling a gas turbine engine comprising 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.
Dependencies are inferred from the claim text.