DOUBLE WALL AIRFOIL COOLING CONFIGURATION FOR GAS TURBINE ENGINE
First Claim
1. An airfoil comprising:
- pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls extending in a radial direction to provide an exterior airfoil surface, a core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip, an outer cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core cooling passage, the core cooling passage and the outer cooling passage, and a cooling hole fluidly interconnects the core and outer cooling passages, the cold side wall has a first thickness and a protrusion extending from the cold side wall beyond the first thickness to a second thickness, the cooling hole arranged at least partially in the protrusion.
3 Assignments
0 Petitions
Accused Products
Abstract
An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. An outer cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core cooling passage. The core cooling passage, the outer cooling passage and a cooling hole fluidly interconnects the core and outer cooling passages. The cold side wall has a first thickness and a protrusion that extends from the cold side wall beyond the first thickness to a second thickness. The cooling hole is arranged at least partially in the protrusion.
18 Citations
20 Claims
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1. An airfoil comprising:
pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls extending in a radial direction to provide an exterior airfoil surface, a core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip, an outer cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core cooling passage, the core cooling passage and the outer cooling passage, and a cooling hole fluidly interconnects the core and outer cooling passages, the cold side wall has a first thickness and a protrusion extending from the cold side wall beyond the first thickness to a second thickness, the cooling hole arranged at least partially in the protrusion. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. A gas turbine engine comprising:
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a combustor section arranged fluidly between compressor and turbine sections; and an airfoil arranged in the turbine section, the airfoil including pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls extending in a radial direction to provide an exterior airfoil surface, a core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip, an outer cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core cooling passage, the core cooling passage and the outer cooling passage, and a cooling hole fluidly interconnects the core and outer cooling passages, the cold side wall has a first thickness and a protrusion extending from the cold side wall beyond the first thickness to a second thickness, the cooling hole arranged at least partially in the protrusion. - View Dependent Claims (14, 15, 16, 17, 18, 19)
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20. A casting mold for an airfoil comprising:
a shell and a core assembly together defining pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls extending in a radial direction to provide an exterior airfoil surface, a core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip, an outer cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core cooling passage, the core cooling passage and the outer cooling passage, and a cooling hole fluidly interconnects the core and outer cooling passages, the cold side wall has a first thickness and a protrusion extending from the cold side wall beyond the first thickness to a second thickness, the cooling hole arranged at least partially in the protrusion.
Specification