GAS TURBINE ENGINE
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United States of America Patent
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Aug 28, 2014
filing date -
Feb 29, 2012
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Abstract
In a gas turbine engine (1) that has a plurality shrouds (8c and 9c), in which each one of the shrouds (8c and 9c) are provided with a groove portion (20) that is provided in a surface facing a turbine rotor blade (8a and 9a) and a plurality of film cooling holes (21) that open to a bottom portion of the groove portion (20), blocking of the film cooling holes (21 and 22) is prevented.
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