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A gas turbine cooling system efficiently cools a first-stage turbine wheel and attachment portions of first-stage turbine blades. The gas turbine cooling system includes a group of impingement cooling holes provided in a partition wall as a stationary component that separates an exit space of a comp

A gas turbine cooling system efficiently cools a first-stage turbine wheel and attachment portions of first-stage turbine blades. The gas turbine cooling system includes a group of impingement cooling holes provided in a partition wall as a stationary component that separates an exit space of a compressor and a wheel space located upstream of a turbine wheel for ejecting compressed air in the exit space toward the turbine wheel and attachment portions of the turbine blades.

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1. A cooling system for a gas turbine, the gas turbine comprising: a compressor for compressing air;a combustor for combusting the air compressed by the compressor with fuel; anda turbine driven by a combustion gas generated by the combustor, the turbine including at least one turbine wheel having t

1. A cooling system for a gas turbine, the gas turbine comprising: a compressor for compressing air;a combustor for combusting the air compressed by the compressor with fuel; anda turbine driven by a combustion gas generated by the combustor, the turbine including at least one turbine wheel having turbine blades on an outer circumferential section thereof, the turbine blades of the at least one turbine wheel each having an attachment portion to be connected to the at least one turbine wheel,the cooling system comprising at least one group of impingement cooling holes provided in a local portion of a partition wall as a stationary component that separates an exit space of the compressor from a wheel space located upstream of the at least one turbine wheel for allowing the compressed air in the exit space of the compressor to impinge on the at least one turbine wheel and the respective attachment portions of the turbine blades of the at least one turbine wheel, andan orifice plate configured to be inserted and removably detached by fasteners on an upstream side of the stationary component and insertable into a hole in the stationary component to introduce impingement cooling air on the at least one turbine wheel downstream of the stationary component. 2. The cooling system of claim 1, wherein the at least one group of impingement cooling holes comprise a plurality of groups of impingement cooling holes, the plurality of groups of impingement cooling holes being arranged in a circumferential direction of the partition wall. 3. The cooling system of claim 1, wherein the cooling system further comprises at least one adjusting unit, disposed detachably on an upstream side of the group of impingement cooling holes in the partition wall, for adjusting a flow rate or a pressure of the compressed air flowing into the at least one group of impingement cooling holes. 4. A cooling system for a gas turbine, the gas turbine comprising: a compressor for compressing air;a combustor for combusting the air compressed by the compressor with fuel; anda turbine driven by a combustion gas generated by the combustor, the turbine including at least one turbine wheel having turbine blades on an outer circumferential section thereof, the turbine blades of the at least one turbine wheel each having an attachment portion to be connected to the at least one turbine wheel,the cooling system further comprising:at least one installation hole formed in a partition wall as a stationary component that separates an exit space of the compressor from a wheel space located upstream of the at least one turbine wheel such that the at least one installation hole connects the exit space and the wheel space; andat least one cartridge detachably installed into the at least one installation hole, the at least one cartridge having a group of impingement cooling holes for allowing the compressed air in the exit space of the compressor to impinge on the at least one turbine wheel and the respective attachment portions of the turbine blades of the at least one turbine wheel;the at least one cartridge configured to be inserted and removably detached by fasteners on an upstream side of the stationary component and insertable to introduce impingement cooling air on the at least one turbine wheel downstream of the stationary component. 5. The cooling system of claim 4, wherein the at least one installation hole comprises a plurality of installation holes,the at least one cartridge comprises a plurality of cartridges,the plurality of installation holes and the plurality of cartridges being arranged in a circumferential direction of the partition wall. 6. The cooling system of claim 5, wherein each of the plurality of cartridges can independently be attached into and detached from each of the plurality of installation holes. 7. The cooling system of claim 4, wherein the at least one cartridge includes: a body having an opening into which the compressed air in the exit space of the compressor flows and the group of impingement cooling holes; andan adjusting unit, attached to the opening, for adjusting a flow rate or a pressure of the compressed air flowing into the group of impingement cooling holes. 8. The cooling system of claim 4, wherein the cooling system further comprises at least one adjusting unit disposed on a compressed-air-intake side of the at least one installation hole for adjusting a flow rate or a pressure of the compressed air flowing into the group of impingement cooling holes.