Chordally bifurcated turbine blade
First Claim
1. A gas engine turbine blade comprising:
- a dovetail for joining said blade to a rotor disk;
an airfoil including;
a pressure side and a suction side joined together at a leading edge and a trailing edge, and extending longitudinally from a root to a tip, said root being integrally joined with said dovetail;
a chordal line extending between said pressure and suction sides from said leading edge to said trailing edge; and
a longitudinally extending flow channel including a chordally extending, imperforate septum diving said flow channel into a first chamber disposed adjacent to said pressure side and a second flow chamber spaced laterally from said first chamber and disposed adjacent to said suction said; and
a supply manifold for receiving compressed air at a single pressure, and disposed in flow communication with both said first and second chambers for channeling thereto first and second portions of said compressed air, respectively.
1 Assignment
0 Petitions
Accused Products
Abstract
A gas turbine engine turbine blade includes an airfoil having pressure and suction sides joined together at leading and trailing edges and extending from a root to a tip. The airfoil also includes a longitudinally extending flow channel for receiving compressed air, with the flow channel including a chordally extending, imperforate septum dividing the flow channel into first and second laterally spaced apart flow chambers. The blade further includes a supply manifold for receiving the compressed air at a single pressure which is disposed in flow communication with both the first and second chambers for channeling thereto respective first and second portions of the compressed air. The septum is used to reduce or eliminate radial velocity distortion, or blowoff of film cooling air from the suction side.
174 Citations
10 Claims
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1. A gas engine turbine blade comprising:
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a dovetail for joining said blade to a rotor disk; an airfoil including; a pressure side and a suction side joined together at a leading edge and a trailing edge, and extending longitudinally from a root to a tip, said root being integrally joined with said dovetail; a chordal line extending between said pressure and suction sides from said leading edge to said trailing edge; and a longitudinally extending flow channel including a chordally extending, imperforate septum diving said flow channel into a first chamber disposed adjacent to said pressure side and a second flow chamber spaced laterally from said first chamber and disposed adjacent to said suction said; and a supply manifold for receiving compressed air at a single pressure, and disposed in flow communication with both said first and second chambers for channeling thereto first and second portions of said compressed air, respectively. - View Dependent Claims (2, 3, 4, 5, 6)
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7. A turbine blade comprising:
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a dovetail for joining said blade to a rotor disk; a airfoil including; a pressure side and suction side joined together at a leading edge and a trailing edge, and extending longitudinally from a root to a tip, said root being integrally joined with said dovetail; a chordal line extending between said pressure and suction sides from said leading edge to said trailing edge; and a longitudinally extending flow channel including a chordally extending, imperforate septum dividing said flow channel into a first chamber disposed adjacent to said pressure side and a second flow chamber spaced laterally from said first chamber and disposed adjacent to said suction side; and a supply manifold for receiving compressed air at a single pressure, and disposed in flow communication with both said first and second chambers for channeling thereto first and second portions of said compressed air, respectively; and
whereinsaid airfoil pressure side adjacent said first chamber includes a plurality of longitudinally spaced apart film cooling holes extending therethrough in flow communication with said first chamber for receiving therefrom said compressed air first portion for film cooling said airfoil pressure side adjacent said first chamber; said flow channel is a leading edge channel extending longitudinally adjacent to said leading edge; said film cooling holes extending through said first chamber are leading edge, pressure side film cooling holes; and said airfoil further includes leading edge, suction side film cooling holes extending through said suction side in flow communication with said second chamber. - View Dependent Claims (8)
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9. A turbine blade comprising:
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a dovetail for joining said blade to a rotor disk; an airfoil including; a pressure side and a suction side joined together at a leading edge and a trailing edge, and extending longitudinally from a root to a tip, said root being integrally joined with said dovetail; a chordal line extending between said pressure and suction sides from said leading edge to said trailing edge; and two longitudinally extending flow channels including a leading edge channel having a chordally extending, imperforate septum dividing said leading edge channel into a first chamber disposed adjacent to said pressure side and second flow chamber spaced laterally from said first chamber and disposed adjacent to said suction side, said first and second chambers extending longitudinally adjacent to said leading edge; and
a mid-chord channel having a chordally extending, imperforate septum dividing said mid-chord channel into a first chamber disposed adjacent to said pressure side and a second flow chamber spaced laterally from said mid-chord first chamber and disposed adjacent to said suction side, said mid-chord first and second chambers being spaced between said leading edge channel and said trailing edge; andtwo supply manifolds including an inlet supply manifold disposed in said dovetail for receiving compressed air at a single pressure and disposed in flow communication with both said first and second chambers of said mid-chord channel for receiving compressed air at a single pressure, and disposed in flow communication with both said first and second chambers of said leading edge channel for channeling thereto respective portions of said compressed air; and
whereinsaid airfoil pressure side adjacent said mid-chord first chamber includes a plurality of longitudinally spaced apart mid-chord, pressure side film cooling holes disposed in flow communication with said mid-chord first chamber; and said airfoil pressure side adjacent said leading edge first chamber includes a plurality of longitudinally spaced apart leading edge, pressure side film cooling holes disposed in flow communication with said leading edge first chamber; said airfoil suction side adjacent said mid-chord second chamber is imperforate for preventing flow of said compressed air second portion from being discharged from said mid-chord second chamber directly through said airfoil suction side; and said airfoil further includes leading edge, suction side film cooling holes extending through said suction side in flow communication with said leading edge second chamber. - View Dependent Claims (10)
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Specification