GAS TURBINE ENGINE

摘要

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.

主权项

1. A gas turbine engine comprising a plurality of shrouds that are arranged facing the tip of a turbine rotor blade,
wherein each one of the shrouds comprises a groove portion that is provided in a surface facing the turbine rotor blade, and a plurality of film cooling holes that open to a bottom portion of the groove portion.