Patent ID: 9115594
Filing Date: 2015-08-25
Classification: F01D,F04D,F05D,Y10T

Abstract:
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.