FIELD: machine building.
SUBSTANCE: invention relates to a seal assembly for use in a gas turbine engine. Seal assembly between a disc cavity and a turbine section hot gas path includes stationary vane 14 assembly 12 and rotating blade 20 assembly 18 downstream from vane assembly 12. Blades 20 are supported on platform 28 and rotate with a turbine rotor and platform 28 during operation of engine 10. Platform 28 includes radially outwardly facing first surface 40, radially inwardly facing second surface 46, third surface 48 and a plurality of grooves 60 extending into third surface 48. Grooves 60 are arranged such that a space is defined between adjacent grooves 60. Grooves 60 are tapered from entrances thereof located distal from first surface 40 to exits thereof located proximate to first surface 40 such that the entrances are wider than the exits.
EFFECT: invention is aimed at prolonging the life and increasing efficiency of the engine.
11 cl, 10 dwg
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