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Gas Turbine Design Axial Flow Compressors

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Gas Turbine Design Axial Flow Compressors ( gas-turbine-design-axial-flow-compressors )

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Chapter 1.0 Introduction Since the implementation of gas turbine engines for the purpose of aircraft propulsion, continuous progress has been made in their performance, reliability, and efficiency. However, there remains a continuing need for continued improvement with regard to noise, cost, efficiency, power, safety, and weight. Unfortunately, an improvement in any one of these areas will often lead to detrimental effects in another area. Therefore, different types of aircraft have specific engine design criteria which are optimized for the particular application. In response to the demand for improved aircraft gas turbine engine performance, a great deal of research has focused on enhancing the design of axial-flow compressors. The two available means of evaluating new compressor designs are experimental and computational. The advantages of experimental testing are more accurate and reliable results. Therefore, physical experimental testing is required prior to implementation of a new design. The advantages of computational simulation are speed, reduced cost, more data, and rapid design modifications. Due to time and cost considerations involved in experimental testing of new compressors, computational simulations have been used more extensively in recent years. Through the use of advanced and accurate computer simulations, much of the preliminary experimental testing may be eliminated. Three-dimensional computational fluid dynamic (CFD) codes are highly sophisticated and require a great deal of computation time. In addition, 3-D CFD codes require accurate turbulence models which are currently unavailable. As a result of these limitations, less complex psuedo-3-D Streamline Curvature Codes (SLCC), which provide a spanwise prediction of thermodynamic and other flow variables, are still widely used (Cetin, 1987). 1

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