Sealing and cooling arrangement for combustor vane interface

Power plants – Combustion products used as motive fluid – Combustion products generator

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60 3983, 415175, F02C 100

Patent

active

048215228

ABSTRACT:
A seal assembly secured to the downstream end of a gas turbine engine combustor liner forms a gas path seal at the upstream facing platforms of turbine inlet guide vanes and also cools the vane platforms. The seal assembly includes an annular coolant compartment which feeds cooling air to a plurality of circumferentially spaced apart, axially extending open-ended channels formed between a conical portion of the downstream-most combustor liner and an annular baffle member disposed on the non-gas path side of the conical liner. The seal assembly is supported and axially located on a cylindrical surface which permits locating the seal assembly such that the downstream end of the conical liner is closely spaced from the turbine inlet guide vane platforms to reduce leakage from the gas path. The open-ended channels are also closely spaced from the vane platforms and located to direct high velocity coolant fluid against the upstream facing surfaces of the platforms at circumferential locations where the pressure in the gas path is highest, thereby further reducing leakage from the gas path.

REFERENCES:
patent: 3186168 (1965-06-01), Ormerod et al.
patent: 3307354 (1967-03-01), Macaulay et al.
patent: 3527053 (1970-09-01), Horn
patent: 3565545 (1971-02-01), Bobo et al.
patent: 3670497 (1972-06-01), Sheldon
patent: 3965066 (1976-06-01), Sherman et al.
patent: 4025226 (1977-05-01), Hovan

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