Initial Stage Sizing
TURBOdesign Pre was used to assess the performance potential of different stage pressure ratio split, different RPMs, shrouded or open impeller etc. A preliminary performance map prediction was also provided by TURBOdesign Pre analysis. Based on these the design RPM was selected and the optimum compromise betewen stage
A shrouded blade was chosen over an open impeller for the advantage on efficiency, which was also compatible with the customer’s manufacturability. During the meanline analysis phase, it also appeared that a splitter blade design could be necessary to reach the maximum capacity requirement.performance and overall operational range was determined.
3D Design and Optimization of Impeller and Vaneless Diffuser
By using the 3D blade Inverse Design software TURBOdesign1 with a simple blade loading an initial (full blade) impeller design was obtained to achieve the target pressure ratio and the maximum capacity at high RPM. The design was also modified to have a good compressor efficiency at 100% load COP evaluation. Following this initial design, an optimized design with the splitter blade was generated. Both the meridional profile and the blade loading distribution were optimized during the detailed design process. For the second stage inlet condition estimation, certain pipe loss was assumed and provided by the customer. Each stage compressor was designed to have a large operating range at design RPM. The other rating conditions or IPLV can be covered by varying the rotational speed and closing the IGV.
The optimized design was analysed using the commercial CFD code (Ansys CFX) across its operating range. The numerical prediction showed good efficiency levels at both design and off-design conditions. The performance at various RPMs were also checked against the targets. The analysis showed that with the help of IGV the compressor design can deliver reasonably good efficiency at load conditions. The maximum lift condition was also investigated numerically.
The required RPM and the pressure ratio split between the two stages for this condition was predicted. Meanwhile, the mechanical stress level on the blade was checked by FEA study. Some iterations were carried out between the aerodynamic design and the stress analysis. The blade thickness profile and the blade number were modified to reduce the stress level while maintaining the choke margin. The maximum stress at overspeed of the final design was controlled within the material limit. Furthermore, the power consumption for each compressor stage was extracted from the CFD analysis at the maximum lift condition and the near choke condition.