초록 ▼

A gas turbine vane having an inner shroud that is cooled by a portion of the cooling air directed to a cavity between two adjacent rows of discs. A portion of the cooling air in the cavity flows through impingement plates and impinges on the inner surface of the inner shroud. Another portion of the

A gas turbine vane having an inner shroud that is cooled by a portion of the cooling air directed to a cavity between two adjacent rows of discs. A portion of the cooling air in the cavity flows through impingement plates and impinges on the inner surface of the inner shroud. Another portion of the cooling air flows through a passage in the leading edge of the inner shroud that has a pin fin array for enhanced cooling. The impingement plates form chambers that collect both the impingement air and the pin fin passage air and direct it through holes in the trailing edge of the inner shroud for cooling of the trailing edge. Longitudinal passages along the side of the inner shroud direct the cooling air from the pin fin passage tot the trailing edge.

대표청구항 ▼

A gas turbine comprising: a) a compressor for producing compressed air; b) a combustor for heating at least a portion of said compressed air, thereby producing a hot compressed gas; and c) a turbine for expanding said hot compressed gas so as to produce shaft power, said turbine further comprising:

A gas turbine comprising: a) a compressor for producing compressed air; b) a combustor for heating at least a portion of said compressed air, thereby producing a hot compressed gas; and c) a turbine for expanding said hot compressed gas so as to produce shaft power, said turbine further comprising: i) a rotor centrally disposed therein; ii) a generally hollow stationary vane disposed therein that is exposed to said hot compressed gas, said stationary vane having an outer shroud portion, an inner shroud portion and an airfoil portion disposed therebetween, said outer shroud portion being in flow communication with a flow of cooling air formed by a second portion of said compressed air, said cooling air passing through said outer shroud portion and said airfoil portion; iii) a cavity being formed between said inner shroud portion and said rotor, said cavity receiving said flow of cooling air after passing through said inner shroud portion; iv) said inner shroud portion having a first passage formed therein, said first passage being in flow communication with said cavity, whereby said first passage receives at least a first portion of said cooling air, an array of pin fins disposed in said first passage and substantially radially oriented therein for increasing heat transfer from said inner shroud to said first portion of said cooling air; and wherein said inner shroud further comprises: a) leading and trailing edges, said first passage being formed in a portion of said inner shroud adjacent said leading edge; b) a chamber formed therein, said first passage in flow communication with said chamber, whereby said chamber receives at least a portion of said cooling air received by said first passage; and c) a plurality of second passages formed in said trailing edge portion, said second passages in flow communication with said chamber, wherein said second passages receive at least a portion of said cooling air received by said chamber.