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The SLCC Compressor Performance Analysis Code (CPAC) was originally developed by Hearsey (1970) and later modified by Hale (1996). CPAC has the ability to use correlations to obtain stage-by-stage characteristics, which for an axial-flow flow compressor are the pressure ratio and the efficiency with respect to corrected mass flow rates at various speeds. These correlations specify blade total pressure loss and flow deviation from the blade exit geometry, which encompass the physical phenomena that the blade geometry imposes on the flow field. Loss and deviation correlations implement theory from geometric effects, boundary layers, and shocks in an effort to match the empirical results. Current correlations in CPAC are inaccurate for high-speed transonic axial-flow flow compressors. The correlations used in industry are likely to be more accurate but are usually proprietary. However, additional correlations are available in the open literature. The primary goal of the present correlation studies was to obtain accurate loss and deviation models for use in an SLCC. Due to the complexity of this task, the effort was divided into parts. The logical method for this breakdown was to use a 1-D compressible flow code to investigate loss correlations along a solitary streamline as opposed to attempting an entire spanwise flow prediction. The streamline chosen for this initial investigation was that located at the mid-span of the blade, often referred to as the meanline. The purpose of the meanline analysis was to provide a simple method of gathering insights on the behavior and quality of the correlations. In addition, losses due to hub and casing boundary layers are negligible at the meanline, as are many secondary flow effects. It is also beneficial that because radial effects can be neglected, the radius of the meanline streamline remains relatively constant as opposed to the radii of hub and tip streamlines. It is hypothesized that the correlations which best represent the data at the meanline will also perform adequately for the majority of the remainder of the flowfield. This is due to the fact that loss and deviation at the meanline are functions of the behavior of the flowfield along the entire span of the blade. 2PDF Image | Gas Turbine Design Axial Flow Compressors
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