Multidisciplinary Design of a Three Stage High Speed Booster

Abstract

The paper describes a multidisciplinary conceptual design of an axial compressor, targeting a three stage, high speed, high efficiency booster with a design pressure ratio of 2.8. The paper is outlined in a step wise manner starting from basic aircraft and engine thrust requirements, establishing the definition of the high speed booster interface points and its location in the engine. Thereafter, the aerodynamic 1D/2D design is carried out using the commercial throughflow tool SC90C. A number of design aspects are described, and the steps necessary to arrive at the final design are outlined. The SC90C based design is then carried over to a CFD based conceptual design tool AxCent, in which a first profiling is carried out based on a multiple circular arc blade definition. The design obtained at this point is referred to as the VINK compressor. The first stage of the compressor is then optimized using an in-house optimization tool, where the objective functions are evaluated from detailed CFD calculations. The design is improved in terms of efficiency and in terms of meeting the design criteria put on the stage in the earlier design phases. Finally, some aeromechanical design aspects of the first stage are considered. The geometry and inlet boundary conditions of the compressor are shared with the turbomachinery community on a public server. This is intended to be used as a test case for further optimization and analysis.

Design of Chalmers new low-pressure compressor test facility for low-speed testing of cryo-engine applications

“…The 2.5 low-speed axial compressor is designed to accurately replicate the final stages of a modern high-speed LPC in the virtual engine VINK, Lejon et al [2017]. The components in the compressor following the flow directions are: adjustable inlet guide vanes (IGV); first rotor (r1); a stator row (s1); second rotor (r2); and finally the outlet guide vane (OGV).…”

Numerical Investigation on the Pressure Perturbation of a Transonic Aeroelastic Compressor Rig

“…The blade profile is based on the first rotor of the VINK-6 compressor, designed and optimized by Lejon [5]. Figure 1 and Table 1 show the detailed information of the linear cascade.…”

Numerical Sensitivity Study on the Design of a Transonic Aeroelastic Compressor Rig

“…The blade profile is based on the first rotor of the VINK-6 compressor, designed and optimized by Lejon [13]. Due to the diffusion of the shroud, the pitch to chord ratio varies from 0.7179 at the leading edge to 0.7259 at the trailing edge.…”