Gas turbine engine with air and steam cooled turbine
AssigneeROLLS-ROYCE plc
InventorsAllan J. Salt, Alan Cash, Carlton Smith
Life of this patent
Estimating the term…
Abstract
In a gas turbine engine including a turbine which has a closed cycle steam cooling system and an open cycle gas cooling system sealing arrangements are provided between adjacent pairs of turbine rotor stages. The sealing arrangement has axially extending passages to supply cooling gas from one of the turbine rotor stages to the cooling gas passages in the turbine rotor blades. Each sealing arrangement comprises a pair of sealing formations each made up of a plurality of sealing segments. Also the sealing arrangement has axially extending passages to supply steam from one of the turbine rotor stages to the steam cooling passages in the turbine rotor blades.
Claims19
A gas turbine engine including a multi-stage turbine having a first cooling system and a second cooling system, said engine comprising a first rotor stage having a plurality of first turbine rotor blades, each first turbine rotor blade having a first passage for the flow of a first cooling fluid and a second passage for the flow of a second cooling fluid, a second rotor stage having a plurality of second turbine rotor blades, each second turbine rotor blade having a third passage for the flow of the first cooling fluid and a fourth passage for the flow of the second cooling fluid, a first sealing arrangement extending axially between the first and second rotor stages, a first chamber formed between the first and second rotor stages and the first sealing arrangement, the first sealing arrangement having at least one passage extending axially between the first and second rotor stages to supply the first cooling fluid between the first and second rotor stages, the first cooling system being arranged to supply first cooling fluid to the first passages in the first turbine rotor blades and being arranged to supply first cooling fluid through the at least one passage extending axially through the first sealing arrangement to the third passages in the second turbine rotor blades.
A gas turbine engine including a multi-stage turbine having a closed cycle steam cooling system and an open cycle gas cooling system, said engine comprising a first rotor stage having a plurality of first turbine rotor blades, each first turbine rotor blade having a first closed passage for the flow of steam and a second passage for the flow of gas, each first turbine blade having a trailing edge which is open to discharge the gas from the second passage through the trailing edge of the first turbine rotor blade, a second rotor stage having a plurality of second turbine rotor blades, each second turbine rotor blade having a third closed passage for the flow of steam and a fourth passage for the flow of gas, each second turbine blade having a trailing edge which is open to discharge the gas from the fourth passage through the trailing edge of the second turbine rotor blade, a first sealing arrangement extending axially between the first and second rotor stages, the first sealing arrangement having at least one passage extending axially between the first and second rotor stages, a first chamber formed between the first and second rotor stages and the first sealing arrangement, means to supply cooling gas to the second passages in the first turbine rotor blades and the at least one passage in the first sealing arrangement, said at least one passage in the first sealing arrangement being arranged to supply cooling gas to the fourth passages in the second turbine rotor blades, means to supply steam to the first passages in the first turbine rotor blades and the first passages being arranged to supply steam to the first chamber.
Dependencies are inferred from the claim text.