Cooling scheme for combustor vane interface
This patent describes a gas turbine engine having a combustor, turbine vanes and a turbine axially spaced but adjacent to the turbine vanes, combustor includes louver liners configured to define an annular passageway for directing the products of combustion between the turbine vanes. Each of the turbine vanes includes an airfoil section having a stagnation point at the leading edge and a platform section at the root of the airfoil section, a support structure attached to the platform section supporting the louver liners, a sheath in cooperation with the support structure for defining therewith a passageway for leading cooling air onto the turbine vanes. The support structure and the sheath are configured into a generally sinusoidally shaped discharge end providing circumferentially spaced alternate closed and open-ended passages the open ended passages located in line with each of the vanes for directing the cool air at the junction of the leading edge of the airfoil section of the turbine vanes and the platform and adjacent the stagnation point of the combustion products ingressing between the turbine vanes.
- Assignee:
- United Technologies Corp., Hartford, CT
- Patent Number(s):
- US 4739621
- OSTI ID:
- 6953961
- Resource Relation:
- Patent File Date: Filed date 11 Oct 1984
- Country of Publication:
- United States
- Language:
- English
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