Abstract
Tandem blade technology has become an effective method to break the load limit of conventional aerodynamic configurations. To expand the application range of tandem blades, the supersonic tandem blade flow characteristic was studied and an optimal design was conducted by using a computational fluid dynamics (CFD) solver, with an inflow Mach number of 1.2. The main conclusions follow: (1) the tandem blade loss is difficult to control because of the complicated flow structures with supersonic inflow; (2) the forward blade loss dominates the tandem blade overall loss in the whole operating conditions; and (3) the tandem blade profile was optimized by considering the aerodynamic interaction between forward and aft blade. The numerical simulation results show that the total pressure loss declines by 20% at the design point, and the incidence range increases by about 0.5°.
Highlights
Increasing the aerodynamic loading of the compressor is of great significance for shortening the axial length of the aero-engine and reducing the weight of the structure
The tandem blade technology has become an effective method to break the load limit of conventional aerodynamic configurations, and it is of wide interest by researchers
Based on the discussion above, this paper tries to reveal the flow characteristic and conducts an optimal design in supersonic tandem blade with an inflow Mach number of 1.2, which is the typical optimal design in supersonic tandem blade with an inflow Mach number of 1.2, which is the typical value of a transonic tandem rotor tip
Summary
Increasing the aerodynamic loading of the compressor is of great significance for shortening the axial length of the aero-engine and reducing the weight of the structure. Based on the discussion above, this paper tries to reveal the flow characteristic and conducts an optimal design in supersonic tandem blade with an inflow Mach number of 1.2, which is the typical optimal design in supersonic tandem blade with an inflow Mach number of 1.2, which is the typical value of a transonic tandem rotor tip. It is mainly carried out from the following two aspects: firstly, the flow mechanism in tandem blade was studied with an inflow Mach number of 1.2; secondly, the supersonic tandem blade was optimized on the condition that considers the aerodynamic interaction between a forward and aft blade
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