Airfoil with improved internal cooling channel pedestals
First Claim
1. An airfoil for a turbine engine, the airfoil comprising:
- a first side wall;
a second side wall spaced apart from the first side wall;
an internal cooling channel formed between the first side wall and the second side wall, the internal cooling channel comprising;
at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall;
a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and
a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end;
wherein at least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end, further wherein the profile is a simple curve described at any point around the periphery of the corresponding pedestal end by a radius of curvature at a point;
the profile at a first point includes a first local maximum value of the radius of curvature;
the first point being a point around the periphery nearest a leading edge of the airfoil;
a trailing edge;
a pressure side wall connecting the leading edge and the trailing edge; and
a suction side wall spaced apart from the pressure side wall, the suction side wall connecting the leading edge and the trailing edge;
wherein the pressure side wall is the first side wall and the suction side wall is the second side wall.
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Accused Products
Abstract
An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.
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Citations
19 Claims
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1. An airfoil for a turbine engine, the airfoil comprising:
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a first side wall; a second side wall spaced apart from the first side wall; an internal cooling channel formed between the first side wall and the second side wall, the internal cooling channel comprising; at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall; a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end; wherein at least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end, further wherein the profile is a simple curve described at any point around the periphery of the corresponding pedestal end by a radius of curvature at a point;
the profile at a first point includes a first local maximum value of the radius of curvature;
the first point being a point around the periphery nearest a leading edge of the airfoil;a trailing edge; a pressure side wall connecting the leading edge and the trailing edge; and a suction side wall spaced apart from the pressure side wall, the suction side wall connecting the leading edge and the trailing edge;
wherein the pressure side wall is the first side wall and the suction side wall is the second side wall. - 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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a compressor section; a combustor section; and a turbine including; a plurality of airfoils, at least one of the plurality of airfoils including; a first side wall; a second side wall spaced apart from the first side wall; an internal cooling channel formed between the first side wall and the second side wall, the internal cooling channel comprising; at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall; a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end; wherein at least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end, further wherein the profile is a simple curve described at any point around the periphery of the corresponding pedestal end by a radius of curvature at a point;
the profile at a first point includes a first local maximum value of the radius of curvature;
the first point being a point around the periphery nearest a leading edge of the airfoil;a trailing edge; a pressure side wall connecting the leading edge and the trailing edge; and a suction side wall spaced apart from the pressure side wall, the suction side wall connecting the leading edge and the trailing edge;
wherein the pressure side wall is the first side wall and the suction side wall is the second side wall. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18)
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19. A method for providing enhanced gas turbine engine airfoil durability, the method comprising:
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introducing cooling air into an internal cooling channel within the airfoil; flowing the cooling air through the internal cooling channel past pedestals connected to walls of the airfoil;
the internal cooling channel including fillets at pedestal ends, at least some of the fillets including a profile that is non-uniform around the periphery of the corresponding pedestal end, wherein the profile is a simple curve described at any point around the periphery of the corresponding pedestal end by a radius of curvature at a point;
the profile at a first point includes a first local maximum value of the radius of curvature;
the first point being a point around the periphery nearest a leading edge of the airfoil; andexhausting cooling air through trailing edge cooling slots.
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Specification