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Technique to Predict Stage-by-Stage, Pre-Stall Compressor Performance Characteristics Using a Streamline Curvature Code With Loss and Deviation Correlations

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Master's thesis

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Because of the complex flow fields and component interaction in a modem gas turbine engine, these engines require extensive testing to validate performance and stability. The testing process can become expensive and complex. Modeling and simulation of gas turbine engines is one way to reduce testing costs, provide fidelity, and enhance the quality of essential testing. Several numerical simulations for gas turbine engines have been developed at Arnold Engineering Development Center to simulate gas turbine engines and their various components. Compressor performance characteristics are needed in these codes to provide turbomachinery source terms. These terms are currently provided by experimental data. A technique to analytically create these characteristics would greatly enhance the quality and value of the codes in existence. Therefore, a technique to create 1-D and 2-D compressor performance characteristics with specifications of only annulus geometry, blade geometry, and loss and deviation correlations has been developed. This method uses a previously developed streamline curvature code SLCC with open literature loss and deviation correlations to provide on and off design stage performance. Data reduction techniques are then used to convert the predicted flow field behavior in the bladed regions into stage by stage performance characteristics of the compressor.

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  • Jet and Gas Turbine Engines

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