초록 ▼

A seal ring separating surface for a gas turbine, which sets a shape of an end portion in the separation surface to a cutting surface and reduces the leaking amount of sealing air. A seal ring holding ring (1) fixes brush seals (3, 4) on an upstream side of a stationary blade by bolts (5, 6) respect

A seal ring separating surface for a gas turbine, which sets a shape of an end portion in the separation surface to a cutting surface and reduces the leaking amount of sealing air. A seal ring holding ring (1) fixes brush seals (3, 4) on an upstream side of a stationary blade by bolts (5, 6) respectively, so as to form a seal with respect to a rotor disc (69). Further, the seal ring holding ring (1) fixes and supports a seal ring (2) on a downstream side by a bolt (7) so as to form a seal with respect to a seal portion (8) on the disc (69) side. The brush seals (3, 4) and the seal ring (2) are structured so as to have a circular ring shape and a separation construction, and each of the separation pieces has a gap, so that sealing air can leak to a downstream side from an upstream side through the gap. However, since the separation piece end portion is formed in a cutting surface and the shape of the gap is formed in a bypass passage, the resistance of an air flow passage is increased and the amount of leaking air amount is reduced.

대표청구항 ▼

1. 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 upst

1. 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.