Patent ID: 9359958
Filing Date: 2016-06-07
CPC Classification: F01D,F02C,F05D

Claim Text:
1. A seal mechanism for a turbine rotor in a gas turbine engine, comprising: a labyrinth seal defined by wherein the inner ring member has an outer periphery, the outer periphery including grooves extending in a direction parallel to the longitudinal axis of the turbine rotor formed on the outer periphery and spaced at intervals in a peripheral direction of the ring member, the outer ring member includes pins extending parallel to the longitudinal axis of the turbine rotor, and the pins are engaged in the grooves so that the inner member is movable in the radial direction of the turbine rotor but immovable in a peripheral direction of the turbine rotor relative to the outer ring member, wherein the inner and outer ring members are made of different materials and a coefficient of thermal expansion of the material of the inner member is greater than that of the outer member.