TURBINE AIRFOIL WITH SINGLE AFT FLOWING THREE PASS SERPENTINE COOLING CIRCUIT
First Claim
1. A gas turbine engine airfoil comprising:
- an airfoil outer wall having width wise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base to a radially outer airfoil tip, a plurality of radially extending internal ribs extending width wise between said pressure and suction side walls;
an internal single three pass serpentine cooling circuit having radially extending first, second, and third serpentine channels between, in axially aft succession, first, second, third, and fourth ribs of said radially extending internal ribs;
said first, second, and third serpentine channels bounded by said first, second, third, and fourth ribs of said plurality of radially extending internal ribs and said pressure and suction side walls;
said serpentine cooling circuit including an entrance and a terminal end wherein said terminal end is positioned aft of said entrance so as to have a chordal flow direction aftwards from said leading edge to said trailing edge within said serpentine circuit;
a straight through single pass leading edge cooling channel located between said first rib, said leading edge, and said outer wall; and
said first serpentine channel and said leading edge cooling channel extending radially through said the base.
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Accused Products
Abstract
A gas turbine engine hollow airfoil includes an airfoil outer wall having width wise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of the airfoil and extending radially outward from a base to a tip. The airfoil includes a single three pass aft flowing serpentine cooling circuit and a straight through leading edge cooling channel extending radially through the airfoil and bounded in part by the leading edge. The exemplary embodiment includes a trailing edge cooling plenum and a straight through single pass trailing edge feed channel for providing cooling air to the trailing edge cooling plenum.
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Citations
14 Claims
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1. A gas turbine engine airfoil comprising:
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an airfoil outer wall having width wise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base to a radially outer airfoil tip, a plurality of radially extending internal ribs extending width wise between said pressure and suction side walls;
an internal single three pass serpentine cooling circuit having radially extending first, second, and third serpentine channels between, in axially aft succession, first, second, third, and fourth ribs of said radially extending internal ribs;
said first, second, and third serpentine channels bounded by said first, second, third, and fourth ribs of said plurality of radially extending internal ribs and said pressure and suction side walls;
said serpentine cooling circuit including an entrance and a terminal end wherein said terminal end is positioned aft of said entrance so as to have a chordal flow direction aftwards from said leading edge to said trailing edge within said serpentine circuit;
a straight through single pass leading edge cooling channel located between said first rib, said leading edge, and said outer wall; and
said first serpentine channel and said leading edge cooling channel extending radially through said the base. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A gas turbine engine blade comprising:
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a hollow airfoil extending radially outwardly from a root;
said airfoil comprising;
an airfoil outer wall having width wise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base to a radially outer airfoil tip, a plurality of radially extending internal ribs extending width wise between said pressure and suction side walls;
an internal single three pass serpentine cooling circuit having radially extending first, second, and third serpentine channels between, in axially aft succession, first, second, third, and fourth ribs of said radially extending internal ribs;
said first, second, and third serpentine channels bounded by said first, second, third, and fourth ribs of said plurality of radially extending internal ribs and said pressure and suction side walls;
said serpentine cooling circuit including an entrance and a terminal end wherein said terminal end is positioned aft of said entrance so as to have a chordal flow direction aftwards from said leading edge to said trailing edge within said serpentine circuit;
a straight through single pass leading edge cooling channel located between said first rib, said leading edge, and said outer wall; and
said first serpentine channel and said leading edge cooling channel extending radially through said base and root. - View Dependent Claims (9, 10, 11, 12, 13, 14)
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Specification