GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE CONFIGURATION
First Claim
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1. A component for a gas turbine engine comprising:
- an exterior surface providing pressure and suction sides, a cooling passage in the component includes a serpentine passageway having first and second passes respectively configured to provide fluid flow in opposite directions from one another, the first pass includes first and second portions nested relative to one another and overlapping in a thickness direction, the first and second portions adjacent to one another by sharing a common wall, the first portion provided on the suction side, and the second portion provided on the pressure side.
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Abstract
A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another. The first pass includes first and second portions nested relative to one another and overlapping in a thickness direction. The first and second portions are adjacent to one another by sharing a common wall. The first portion is provided on the suction side. The second portion is provided on the pressure side.
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Citations
20 Claims
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1. A component for a gas turbine engine comprising:
an exterior surface providing pressure and suction sides, a cooling passage in the component includes a serpentine passageway having first and second passes respectively configured to provide fluid flow in opposite directions from one another, the first pass includes first and second portions nested relative to one another and overlapping in a thickness direction, the first and second portions adjacent to one another by sharing a common wall, the first portion provided on the suction side, and the second portion provided on the pressure side. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A gas turbine engine comprising:
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compressor and turbine sections; and an airfoil provided in one of the compressor and turbine sections, the airfoil including an exterior surface providing pressure and suction sides, a cooling passage in the airfoil includes a serpentine passageway having first and second passes respectively configured to provide fluid flow in opposite directions from one another, the first pass includes first and second portions nested relative to one another and overlapping in a thickness direction, the first and second portions adjacent to one another by sharing a common wall, the first portion provided on the suction side, and the second portion provided on the pressure side. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18, 19, 20)
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Specification