Air cooled turbine airfoil
First Claim
1. An air cooled turbine airfoil comprising:
- a leading edge and a trailing edge;
a pressure side wall and a suction side wall;
a leading edge cavity formed in the leading edge region of the airfoil;
a mid-chord cavity located aft separated from the leading edge cavity by a rib; and
,a first baffle secured within the leading edge cavity, the first baffle forming a series of impingement compartments such that cooling air flows from one compartment to the next compartment, adjacent compartments being connected by a plurality of impingement holes and a spent air return hole.
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Accused Products
Abstract
A turbine airfoil with a multiple impingement cooling circuit to provide backside impingement cooling of the leading edge region and the pressure and suction side walls. A leading edge cavity and a mid-chord cavity are separated by a rib. A first baffle is secured within the leading edge cavity and forms a series of impingement compartments and impingement cooling holes to channel cooling air along the first baffle and provide impingement cooling along the backside wall of the leading edge region. A second baffle is secured within the mid-chord cavity and forms a series of pressure side and suction side impingement compartments and impingement cooling holes alternating from the pressure side wall to the suction side wall to channel cooling air along the second baffle and provide impingement cooling along the backside walls of the pressure and suction sides. A spent air collection channel extends along the trailing edge region and is connected to a row of exit cooling holes along the trailing edge of the airfoil. Cooling air from the first baffle flows into the second baffle, and from the second baffle into the spend air collection channel and out through the exit cooling holes.
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Citations
17 Claims
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1. An air cooled turbine airfoil comprising:
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a leading edge and a trailing edge; a pressure side wall and a suction side wall; a leading edge cavity formed in the leading edge region of the airfoil; a mid-chord cavity located aft separated from the leading edge cavity by a rib; and
,a first baffle secured within the leading edge cavity, the first baffle forming a series of impingement compartments such that cooling air flows from one compartment to the next compartment, adjacent compartments being connected by a plurality of impingement holes and a spent air return hole. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A process for cooling an airfoil used in a gas turbine engine, the process comprising the steps of:
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supplying pressurized cooling air to a first leading edge impingement compartment; impinging cooling air onto a first surface of the leading edge wall; collecting the first impinging cooling air into a second impingement compartment; impinging the cooling air from the second impingement compartment onto a second surface of the leading edge wall different from the first surface; collecting the second impinging air into a last impingement compartment; and
,impinging the cooling air from the last compartment onto a last surface of the leading edge wall different from the first and the second surfaces. - View Dependent Claims (12, 13, 14)
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15. An air cooled turbine airfoil comprising:
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a leading edge and a trailing edge; a pressure side wall and a suction side wall; a leading edge cavity extending along the spanwise length of the airfoil; a mid-chord cavity extending along the spanwise length of the airfoil; the leading edge cavity and the mid-chord cavity separated by a rib; a leading edge impingement baffle secured within the leading edge cavity, the leading edge impingement baffle forming a series of impingement compartments and impingement holes to channel cooling air along the airfoil and provide impingement cooling along the leading edge wall of the airfoil; a mid-chord impingement baffle secured within the mid-chord cavity, the mid-chord impingement baffle forming a series of pressure side and suction side impingement compartments and impingement holes to channel cooling air along the airfoil and provide impingement cooling along the pressure side and the suction side walls of the airfoil; and
,means to channel the cooling air from the outlet of the leading edge baffle to the inlet of the mid-chord baffle. - View Dependent Claims (16, 17)
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Specification