الفهرس 
Tandem BladeOnly 14 pages are availabe for public view
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Abstract
Since the implementation of the gas turbine engines for the purpose of aircraft propulsion and power generation, continuous progress has been made in their performance and efficiency. However, there remains a continuing need for continued improvement with regard to its noise, efficiency, power and weight. In response to the demand for improved gas turbine engine performance, a great deal of research has focused on enhancing the design of axial-flow compressors.
There are two available means in evaluating new compressor designs these are experimental and computational. The advantage of experimental testing is that it gives more accurate and reliable results. While, 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.
Computational fluid dynamic (CFD) codes are highly sophisticated and require a great deal of computation time. Consequently, less complex reliable codes were used in the design; analysis, blade selection and optimization in the present study.