Patent ID: 6575699
Filing Date: 2003-06-10
Classification: F01D,F02C,F04D,F05D

Abstract:
A gas turbine engine comprising a low-pressure rotor, a high-pressure rotor and at least one casing, the high-pressure rotor being arranged coaxially around the low-pressure rotor, the at least one casing being arranged coaxially around the high-pressure rotor, the high-pressure rotor having a radially inner surface, a radially outer surface, an upper portion and a lower portion, the low-pressure rotor having a radially inner surface, a radially outer surface, an upper portion and a lower portion, the at least one casing having a radially inner surface and a radially outer surface, the high-pressure rotor having a high emissivity surface finish on at least a portion of its radially inner surface, the low-pressure rotor having a high emissivity surface finish on at least a portion of its radially outer surface and a high emissivity surface finish on at least a portion of its radially inner surface to reduce temperature differentials between the upper portion and the lower portion of the high-pressure rotor and the upper portion and the lower portion of the low-pressure rotor.