Gas turbine engine and a rotor for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorAlan R Jones
Life of this patent
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Abstract
A rotor (38) for a gas turbine engine (10) has a low emissivity surface finish, or high emissivity surface finish (44), on at least a portion of its surface (42) to reduce temperature differentials between an upper portion and a lower portion of the rotor (38). This reduces bowing of the rotor (38) to allow the gas turbine engine (10) to be started without harmful vibrations of the rotor (38).
Claims22
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.
A rotor for a gas turbine engine having an upper portion, a lower portion, a radially inner surface and a radially outer surface, the rotor having a high emissivity surface finish on at least a portion of its radially inner surface and a high emissivity surface finish on at least a portion of its radially outer surface to reduce temperature differentials between the upper portion and the lower portion of said rotor.
A rotor for a gas turbine engine having an upper portion, a lower portion, a radially inner surface and a radially outer surface, the rotor having a low emissivity surface finish on at least a portion of its radially inner surface and a low emissivity surface finish on at least a portion of its radially outer surface to reduce temperature differentials between the upper portion and the lower portion of the at least one rotor.
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 low-pressure rotor having a high emissivity surface finish on at least a portion of its radially outer surface, the high-pressure rotor having a high emissivity surface finish on at least a portion of its radially outer surface and a high emissivity surface 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.
A gas turbine engine comprising at least one rotor and at least one casing arranged coaxially around the at least one rotor, the rotor having an upper portion, a lower portion, a radially inner surface and a radially outer surface, the at least one casing having a radially inner surface and a radially outer surface, the at least one rotor having a low emissivity surface finish on at least a portion of its radially inner surface and a low emissivity surface finish on at least a portion of its radially outer surface to reduce temperature differentials between the upper portion and the lower portion of the at least one rotor.
Dependencies are inferred from the claim text.