Serving as a key component of the core engine, high-load axial compressor is expected to have high performance, which determines several critical parameter levels aero-engine. The unsteady effect on performance induced by interaction among different rotors should not be ignored during design compressor. between R1 (the first rotor row) and R2 second transonic was measured in detail using high-f...

The hub and casing walls of axial compressors are often modeled as smooth continuous surfaces in CFD simulations, but real geometries, non-smooth pinches, steps leakage cavities may exist. In the GPPS first Turbomachinery Workshop, a comprehensive validation verification campaign RANS flow solvers was conducted, all simulation results consistently over-predicted total pressure ratio at rotor ex...

This paper covers the development of stage-by-stage and parallel flow path compressor modeling approaches for a Variable Cycle Engine. The stage-by-stage compressor modeling approach is an extension of a technique for lumped volume dynamics and performance characteristic modeling. It was developed to improve the accuracy of axial compressor dynamics over lumped volume dynamics modeling. The sta...

Usually, the first stage of a compressor of a gas turbine works in the region of transonic flow, so that the designer has to take into account a lot of flow details like shocks, boundary layer separation and their interaction, when a new machine is defined. Beside other problems the choice of the blade geometry and profile family is one important consideration. For the design of the blades anal...