Diffuser insert for high pressure compressor of e.g. jet engine, has inner blade support shell with multiple orifices whose side wall has four blade positioning bosses defining blade support points contacting surfaces of outer wall of blade

摘要

The insert has an outer blade support shell, an inner blade support shell (4), and multiple blades (6), where the shell (4) has multiple orifices. A side wall of the orifices has four blade positioning bosses (22). Each boss defines a blade support point. The points are disposed to contact two aerodynamic surfaces (26, 28) of an outer wall of the blade, near their upstream and downstream ends, respectively. An independent claim is also included for a blade support shell for diffuser insert of a compressor of a turbomachine.