초록 ▼

A blade or vane for a gas turbine engine includes a primary cooling system (42) with a series of medial passages (44, 46a, 46b, 46c, 48) and an auxiliary cooling system (92) with a series of cooling conduits (94). The conduits of the auxiliary cooling system are parallel to and radially coextensive

A blade or vane for a gas turbine engine includes a primary cooling system (42) with a series of medial passages (44, 46a, 46b, 46c, 48) and an auxiliary cooling system (92) with a series of cooling conduits (94). The conduits of the auxiliary cooling system are parallel to and radially coextensive with the medial passages and are disposed in the peripheral wall (16) of the airfoil between the medial passages and the airfoil external surface (28). The conduits are chordwisely situated in a zone of high heat load (104, 106) so that their effectiveness is optimized. The conduits may also be chordwisely coextensive with some of the medial passages so that coolant in the medial passages is protected from excessive temperature rise. The chordwise dimension C of the conduits is limited so that potentially damaging temperature gradients do not develop in the airfoil wall (16).

대표청구항 ▼

[ We claim:] [1.] A coolable airfoil, comprising:a peripheral wall having an external surface comprised of a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from an airfoil root t

[ We claim:] [1.] A coolable airfoil, comprising:a peripheral wall having an external surface comprised of a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from an airfoil root to an airfoil tip;a primary cooling system comprised of at least one radially extending medial passage bounded at least in part by the peripheral wall; andan auxiliary cooling system comprised of at least one cooling conduit substantially parallel to and radially coextensive with the medial passage, the conduit disposed in the wall between the medial passage and the external surface and chordwisely situated exclusively within a zone of high heat load, the high heat load zone being from about 0% to 20% of the chordwise distance from the leading edge to the trailing edge along the suction surface and about 10% to 75% of the chordwise distance from the leading edge to the trailing edge along the pressure surface, the airfoil wall chordwisely outside the high heat load zone being devoid of the cooling conduits.