MIXED FLOW AND CENTRIFUGAL COMPRESSOR FOR GAS TURBINE ENGINE

摘要

A two stage compressor with a mixed flow first stage, a centrifugal second stage, and an intermediate duct. The centrifugal rotor (2) has a circumferential array of radially extending centrifugal flow blades (16) between the centrifugal flow hub and an associated centrifugal flow shroud. An intermediate duct (3) has an inner duct wall (20) defining an axially curvilinear transition surface of revolution between anoutlet end of the mix ed flow hub and an inlet end of the centrifugal flow hub and an outer duct wall (21) defining an axially curvilinear transition surface of revolution betwee n an outlet end of the mixed flow shroud and an inlet end of the centrifugal flow shroud.