Abstract:

In order to simplify the aspirated structure and improve the engineering appliance of the aspirated compressor, a compound flow control method, composed of tandem cascade and endwall suction technology, is proposed. Effects of applying tandem cascade, endwall suction and compound flow control method on the flow structures and aerodynamic loss of a highly loaded outlet vane are investigated by numerical simulations. As a result, the control effect of the compound flow control method is advantageous over the single flow control method, the corner stall is depressed and the two-dimensional flow separation is alleviated effectively by using a smaller aspirated flow rate, moreover, the outlet flow parameters turn more evenly, the total pressure loss is reduced by 59% when 0.90% of inlet mass flow is sucked away.

Key words: boundary layer aspiration, compound flow control method, highly-loaded compressor, tandem cascade, aircraft engine