Compressor casing treatment for gas turbine engine

摘要

An axial flow compressor for a gas turbine engine is disclosed having a casing treatment that includes a shrouded rotor and an airflow member disposed in a passage between a casing and the shrouded rotor. In one form the airflow member is stationary with the casing and in another the airflow member is coupled to rotate with the shrouded rotor. The airflow member can have an airfoil shape in some embodiments. A passage inlet that extracts working fluid and provides it to the passage can be formed between a leading edge of the rotor and a trailing edge. A passage outlet can be formed upstream of the leading edge of the rotor.

主权项

1. An apparatus comprising:
a gas turbine engine compressor having a bladed rotor enclosed by an annular shroud and disposed within a portion of a compressor casing section, the bladed rotor having an upstream side and a downstream side, the annular shroud having an upstream end and a downstream end as referenced relative to a flow stream through the bladed rotor; an airflow passage formed between the compressor casing section and the annular shroud, the airflow passage having an inlet defined by the downstream end of the annular shroud and an outlet defined by the upstream end of the annular shroud such that the inlet is located downstream to the outlet as referenced by the flow stream through the bladed rotor; and an airfoil-shaped airflow member attached to the shroud and disposed within the airflow passage, the airfoil-shaped airflow member oriented transverse to the bladed rotor thereby forming an angle between the airfoil-shaped airflow member and a neighboring blade of the bladed rotor such that as air enters from the inlet is turned to reduce an absolute tangential velocity of the air across the airfoil-shaped airflow member.