Patent ID: 6471213
Filing Date: 2002-10-29
Classification: F01D,F16J

Abstract:
A seal structure for a gas turbine comprising:a seal ring holding ring supported on an inner shroud of a stationary blade; a circular seal portion supported by said seal ring holding ring and surrounding a periphery of a rotor, said circular seal portion including a brush seal disposed at an upstream side of the inner shroud with respect to a main current gas flow, and a labyrinth seal disposed at a downstream side of the inner shroud with respect to the main current gas flow, wherein each of said brush seal and said labyrinth seal is formed of a plurality of sections, and each of said sections of said brush seal and said labyrinth seal has opposite end portions that are each defined by rectangular cut surfaces that oppose and contact adjacent rectangular cut surfaces of adjacent ones of said sections, wherein a predetermined gap is provided between said adjacent ends of said sections to account for thermal expansion of said brush seal and said labyrinth seal, and each of said contacting adjacent rectangular cut surfaces of said sections defines a non-linear path, defined by two axially extending segments interconnected by a radially extending segment, so as to reduce the amount of sealing air leaking through said gap, wherein said radially extending segment is longer than said axially extending segments, and at least one of said axially extending segments extends through a majority of the axial length of said respective section.