| 主权项 |
1. A system, comprising:
a gas turbine engine, comprising:
a combustion section;a turbine section coupled to the combustion section, wherein the turbine section comprises a turbine stage having a plurality of turbine blades, each blade of the plurality of turbine blades having a blade end at a first end and a second end coupled to a rotor, and a stationary shroud disposed about the plurality of turbine blades that defines a clearance between each blade end of the plurality of turbine blades and an innermost surface of the stationary shroud that is disposed at an oblique angle relative to a rotational axis of the plurality of turbine blades; anda diffuser section coupled to the turbine section, wherein the diffuser section comprises an outer wall defining an expanding flow path downstream from the plurality of turbine blades, the outer wall comprises a first wall portion that contacts and extends from the stationary shroud, the first wall portion having a first angle relative to the rotational axis of the plurality of turbine blades, the first angle is between 16 and 40 degrees, and when over tip leakage flow flows through the clearance between each blade end and the innermost surface of the stationary shroud, the over tip leakage flow energizes and maintains a boundary layer along the outer wall. |
