To reduce the negative impacts of stall and surge on compressor performance, a novel combined casing treatment (CCT) structure with axial skewed slots injection groove is proposed in this paper. The aerodynamic as well mechanisms loss generation, transonic NASA Rotor 67 are investigated numerically. simulation results indicate that, compared individual method, CCT works effectively regard to op...

To reveal the mechanisms underlying effect of self-circulating casing treatment with different circumferential coverage ratios on stability axial compressor, a three-dimensional unsteady numerical was hereby conducted Rotor 35. The 20%, 40%, 60%, and 80% were designed, respectively. calculated results point out that all schemes effectively expand stable working range compressor expansion is pos...

This paper presents the application of a viscous adjoint method to the multi-objective design optimization of a transonic compressor rotor blade row. The adjoint method requires about twice the computation effort of flow calculation to obtain the complete gradient information for each cost function, regardless of the number of design parameters. NASA Rotor 67 is redesigned to maximize the total...

Axial flow compressors are required to operate over a wide range of mass flow rate and rotational speeds at high efficiency in industrial gas turbines. However, the useful range of operation of the axial compressor is limited by the onset of two instabilities known as surge and rotating stall. To resolve these problems, variable stator blades or VGVs are considered by optimising the blade setti...

The relationship between tolerances of statically measured geometric parameters and the aerodynamic performance of a sample of manufactured airfoils is investigated in this thesis. The objective is to determine which geometric parameters are the best discriminators of performance, and how these best discriminators are affected by changes in design methodology, manufacturing precision, and desir...