Patent ID: 7037067

Claim:
A gas turbine engine, comprising: a compressor compressing air; a combustor to burn fuel in the compressed air compressed by the compressor; a turbine operated by expansion of combustion gas from the combustor, the turbine operating the compressor in association; and a cooling plate provided on a stationary section in the vicinity of a turbine disc in the turbine, the cooling plate extending in a radial direction of the turbine disc so as to be opposed to a side surface of a rim of the turbine disc in a manner such that the opposing surface of the cooling plate is close to the side surface of the rim, wherein a cooling passage is formed between the opposing surface of the cooling plate and the side surface of the rim wherein a portion of the compressed air can flow as cooling air through the cooling passage, wherein the turbine includes a stator and a rotor and wherein, when a distance between said turbine stator and said turbine rotor both constituting the turbine in an axial direction thereof is defined as S and a distance between the turbine rotor and the cooling plate in the axial direction of the turbine is defined as Sc, the relation between the distances is established as: Sc/S= 0.1 to 0.2.