Gas turbine engine cooling system

Claim 2

A cooling system for a turbine of a gas turbine engine, said system comprising a turbine rotor with blades extending therefrom: a plurality of circumferentially closely spaced pre-swirl nozzles defining a substantially continuous annular outlet flow area through which flows, in operation, a cooling fluid; and a plurality of circumferentially spaced pitot receivers projecting from the blades of the turbine in a direction towards the pre-swirl nozzles and terminating at their free open inlet ends in closely spaced relation to the nozzles with the ends being substantially perpendicular to the relative approach vector of the fluid from the nozzles, the pitot receivers being sized and positioned to collect a portion only of the pre-swirled cooling fluid from the nozzles and to direct it to a portion only of the interior of each of the blades of the turbine.

Claim 3

A cooling system as claimed in claim 1 and in which each turbine blade of the turbine is provided with a pitot receiver on a root portion thereof.

Claim 4

A cooling system as claimed in claim 1 and in which each pitot receiver supplies cooling fluid to a leading edge cooling fluid passage in the respective blade.

Claim 5

A cooling system for a turbine of a gas turbine engine comprising a turbine rotor with blades extending therefrom, a circumferentially extending array of pre-swirl nozzles arranged to provide a substantially continuous annular outlet flow area through which passes, in operation, a flow of cooling fluid, and a circumferential array of individual pitot receivers projecting from the blades of the turbine towards the pre-swirl nozzles and disposed on the turbine downstream of the pre-swirl nozzles, the pitot receivers being sized and positioned to collect a portion only of the pre-swirled cooling fluid from the nozzles and to direct it to a portion only of the interior of each of the blades of the turbine, each pitot receiver being disposed with its inlet normal to the relative approach vector of the fluid from the pre-swirl nozzles.

Claim 6

A cooling system for a turbine of a gas turbine engine comprising a turbine rotor with blades extending therefrom, a circumferentially extending array of pre-swirl nozzles arranged to provide a substantially continuous annular outlet flow area through which passes, in operation, a flow of cooling fluid, and a circumferential array of individual pitot receivers projecting from the blades of the turbine towards the pre-swirl nozzles and disposed on the turbine downstream of the pre-swirl nozzles, the pitot receivers being sized and positioned to collect a portion only of the pre-swirled cooling fluid from the nozzles and to direct it to a portion only of the interior of each of the blades of the turbine, each pitot receiver being disposed with its inlet normal to the relative approach vector of the fluid from the pre-swirl nozzles.

Claim 7

A cooling system for a turbine of a gas turbine engine comprising a turbine rotor with blades extending therefrom, a circumferentially extending array of pre-swirl nozzles arranged to provide a substantially continuous annular outlet flow area through which passes, in operation, a flow of cooling fluid, and a circumferential array of individual pitot receivers projecting from the blades of the turbine towards the pre-swirl nozzles and disposed on the turbine downstream of the pre-swirl nozzles, the pitot receivers being sized and positioned to collect a portion only of the pre-swirled cooling fluid from the nozzles and to direct it to a portion only of the interior of each of the blades of the turbine, and each blade has more than one cooling fluid passage in the interior thereof and the pitot receivers are arranged with their inlets normal to the relative approach vector of the fluid from the pre-swirl nozzles to supply cooling fluid to at least one, but not all, of the passages, further cooling fluid receivers being disposed on the turbine to collect a further portion of the cooling fluid from the nozzles and to direct it to any remaining passage in the blade.

Claim 8

A cooling system for a turbine of a gas turbine engine comprising a turbine rotor with blades extending therefrom, a circumferentially extending array of pre-swirl nozzles arranged to provide a substantially continuous annular outlet flow area through which passes, in operation, a flow of cooling fluid, and a circumferential array of individual pitot receivers projecting from the blades of the turbine towards the pre-swirl nozzles and disposed on the turbine downstream of the pre-swirl nozzles, the pitot receivers being sized and positioned to collect a portion only of the pre-swirled cooling fluid from the nozzles and to direct it to a portion only of the interior of each of the blades of the turbine, and each blade has more than one cooling fluid passage in the interior thereof and the pitot receivers are arranged with their inlets normal to the relative approach vector of the fluid from the pre-swirl nozzles to supply cooling fluid to at least one, but not all, of the passages, further cooling fluid receivers being disposed on the turbine to collect a further portion of the cooling fluid from the nozzles and to direct it to any remaining passage in the blade.

Claim 9

A cooling system as claimed in claim 5 and in which each turbine blade of the turbine is provided with a pitot receiver on a root portion thereof.

Claim 10

A cooling system as claimed in claim 5 and in which the further cooling fluid receivers direct the cooling fluid received therein to diffusing chambers in the root portion of each blade with which the remaining cooling fluid passage or passages in the blade communicate.