Abstract
Tandem blade technology has been developed for years due to its capacity to bear higher aerodynamics than conventional configurations. Even so, there is still the tough problem of how to design tandem blades effectively and further improve blade performance. This paper tries to further understand the flow characteristics of tandem blades in order to present a new method of designing them under subsonic inflow conditions. Firstly, efforts were made to reveal the aerodynamic interaction between the forward blade (FB) and the aft blade (AB). Secondly, considering this aerodynamic interaction, the design principles and the camber line modification method were put forward, with which typical controlled diffusion airfoil (CD airfoil) isentropic Mach number distributions can be achieved for both FB and AB. Lastly, the optimizations were conducted on a 2D tandem blade and a transonic compressor with a tandem blade, respectively. The computation fluid dynamic (CFD) results show that the optimized tandem blade achieves a significant improvement for both 2D blade performance and transonic compressor characteristics at low speeds.
Highlights
Increasing the compressor aerodynamic load is of great significance for shortening the axial length of the aero-engine and reducing the weight of the structure
Bammert [3,4] optimized the multistage axial compressor with tandem blades, and the results showed that blade loss decreased approximately
The total pressure loss at the DE point decreases by about 6%, and the incidence range extends 2° while maintaining the aerodynamic load
Summary
Increasing the compressor aerodynamic load is of great significance for shortening the axial length of the aero-engine and reducing the weight of the structure. Due to the potential to break the aerodynamic load limit, the tandem blade has been widely investigated. Earlier studies were launched to investigate the tandem blade potential performance advantages compared with conventional configurations. In the 1970s, high-loaded tandem blades were investigated by the Pratt and Whitney group using a single-stage test rig [1,2]. Bammert [3,4] optimized the multistage axial compressor with tandem blades, and the results showed that blade loss decreased approximately. The forward blade undertakes the whole incidence range and part of the aerodynamic load; the aft blade undertakes a higher load in a relatively stable operating condition
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