TURBINE SHROUD SECTION, TURBINE ENGINE AND METHOD FOR COOLING TURBINE SHROUD

摘要

PROBLEM TO BE SOLVED: To provide a shroud section including a cooling passage minimizing loss of kinetic momentum of high temperature gas flow. SOLUTION: Part of gas flow 26 flowing through a gas turbine engine moves inside of a turbine in a circumference direction. A cooling passage 36 of the shroud section 30 provided along the outer circumference of the turbine is aligned to an estimated circumference flow direction 41 and is inclined to the circumference direction to discharge cooling air toward a discharge direction 42 The discharge direction 42 is aligned with the flow direction 41 and includes circumference direction component 47 perpendicular to a center axis A. The flow direction 41 has anglesαin relation to the discharge direction 42. It is preferable to keep anglesαclose to 0°to minimize loss of kinetic momentum of the gas flow 26. Cooling air is discharged in the discharge direction 49 aligning with a flow direction 41' at a rear edge part 44. Kinetic momentum of high temperature gas flow 26 is increased by this invention, and turbine efficiency is improved. COPYRIGHT: (C)2007,JPO&INPIT