TURBINE SECTION WITH TIP FLOW VANES

摘要

A turbine section of a gas turbine engine comprises a gas path having an outer boundary wall. A circumferential array of turbine blades projects radially into the gas path. Each turbine blade extends in span from a hub to a tip and in chord from a leading edge to a trailing edge. A circumferential array of tip flow vanes extends radially inward from the outer boundary wall with a span corresponding generally to a radial depth of a tip leakage flow region of the turbine blades. The tip flow vanes are disposed downstream of the circumferential array of turbine blades adjacent to the trailing edge of the turbine blades.

主权项

1. A turbine section of a gas turbine engine, the turbine section comprising: a gas path having an outer boundary wall, a turbine rotor having a circumferential array of turbine blades projecting radially into the gas path, each turbine blade extending in span from a hub to a tip and extending in chord from a leading edge to a trailing edge, a circumferential array of tip flow vanes extending radially inward from the outer boundary wall with a span corresponding generally to a radial depth (h) of a tip leakage flow region of the turbine blades, the tip flow vanes being disposed downstream of the circumferential array of turbine blades and at a short axial distance therefrom to catch a tip leakage flow before it starts mixing with a mainstream flow coming from the turbine blades.