Patent ID: 9441540
Filing Date: 2016-09-13
CPC Classification: F01D,F02C,F04D

Claim Text:
1. An inducer assembly for use with a gas turbine engine having one or more turbine blades, comprising: a discharge casing; a swirl cavity; an inducer disposed between and in fluid communication with the discharge casing and the swirl cavity, wherein the inducer comprises an inlet at the discharge casing and an outlet at the swirl cavity, wherein the outlet comprises a tangential exit angle into the swirl cavity, wherein the inducer tangentially accelerates and directs a flow of discharge air from the discharge casing tangentially into the swirl cavity to drive the discharge air within the swirl cavity in a swirling manner; and at least one guide vane disposed on a wall within the swirl cavity adjacent to and upstream of the inducer outlet to reduce a pressure loss due to the tangential exit angle in a region where an airflow from the inducer merges with the swirling airflow within the swirl cavity.