Turbine airfoil with multiple near wall compartment cooling
First Claim
1. A turbine airfoil used in a gas turbine engine, the airfoil comprising:
- an airfoil main body having a shape of an airfoil with a pressure side and a suction side, and a leading edge and a trailing edge;
a forward cooling air supply channel formed within the airfoil main body;
a mid-chord cooling supply channel formed within the airfoil main body;
a spent air collector cavity formed within the airfoil main body and positioned between the forward and mid-chord cooling supply channels;
a first pressure side impingement channel in fluid communication with at least the forward cooling air supply channel and the spent air collector channel;
a first suction side impingement channel in fluid communication with the mid-chord cooling air supply channel and the spent air collector channel; and
,a first suction side film cooling hole in fluid communication with the spent air collector channel.
4 Assignments
0 Petitions
Accused Products
Abstract
The present invention is a turbine airfoil such as a rotor blade with a cooling circuit that provides convective cooling to the airfoil main body, and impingement cooling and film cooling to the outer wall of the airfoil in order to maximize the cooling while minimizing the amount of cooling air used. The blade main body includes walls of such thickness to provide sufficient structural strength to support the airfoil assembly. The blade main body includes a rib that separates a first or forward cooling air supply channel from a spent air collector cavity. Another rib separates the spent air collector cavity from a second or mid-chord cooling air supply channel. A leading edge cooling supply cavity is connected to the forward supply channel through metering and impingement holes. Film cooling holes forming a well known showerhead arrangement provides film cooling for the leading edge of the blade.
72 Citations
18 Claims
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1. A turbine airfoil used in a gas turbine engine, the airfoil comprising:
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an airfoil main body having a shape of an airfoil with a pressure side and a suction side, and a leading edge and a trailing edge; a forward cooling air supply channel formed within the airfoil main body; a mid-chord cooling supply channel formed within the airfoil main body; a spent air collector cavity formed within the airfoil main body and positioned between the forward and mid-chord cooling supply channels; a first pressure side impingement channel in fluid communication with at least the forward cooling air supply channel and the spent air collector channel; a first suction side impingement channel in fluid communication with the mid-chord cooling air supply channel and the spent air collector channel; and
,a first suction side film cooling hole in fluid communication with the spent air collector channel. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A turbine airfoil used in a gas turbine engine, the airfoil comprising:
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an airfoil main body having a shape of an airfoil with a pressure side and a suction side, and a leading edge and a trailing edge; a forward cooling air supply channel formed within the airfoil main body; a first pressure side impingement channel in fluid communication with the forward cooling air supply channel; a first suction side impingement channel in fluid communication with the forward cooling air supply channel; a first suction side film cooling hole in fluid communication with the first pressure side impingement channel; a second suction side film cooling hole in fluid communication with the first suction side impingement channel, the second suction side film cooling hole being located upstream from the first suction side film cooling hole; a leading edge cooling supply cavity in fluid communication with the forward cooling air supply channel; and
,a showerhead arrangement in fluid communication with the leading edge cooling air supply channel. - View Dependent Claims (13, 14, 15, 16, 17, 18)
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Specification