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- Type of Document: M.Sc. Thesis
- Language: Farsi
- Document No: 55636 (08)
- University: Sharif University of Technology
- Department: Mechanical Engineering
- Advisor(s): Hajilouy Benisi, Ali
- Abstract:
- Improving compressor performance and arriving at better conditions has always been considered by researchers and industrialists. However axial compressor design process is time consuming, very costly, and involves uncertainties and iterations such that sometimes the preset targets are not achieved. Therefore it is required to be able to perform preliminary design and specify the compressor geometry and blade specifications and predict the performance characteristics with a fast, cheap method with required accuracy suitable for this step before detailed design and manufacture. Also some design methods need a primary geometry that is generated by these methods.In this work, towards achieving the aim of preliminary three design of a single stage axial compressor from hub to tip, first a loss-based one dimensional performance prediction program was written. Then the program was verified by modelling the axial compressor of the available gas turbine and comparing the results with experiments. The maximum relative difference of pressure ratios was 1.6%. Efficiency lies at a distance from experimental results but the difference reaches its minimum of 5% close to nominal condition.In the next step one dimensional preliminary design program was created and using the simple radial equilibrium equation together with a prescribed velocity distribution, the ability to specify blade specifications at all radii is added to the program. The Sharif University gas turbine axial compressor was redesigned with this program. Thereafter the effect of varying vortex distributions for three dimensional design on performance parameters was inspected. The comparison of results shows that in practice, a limited range of vortex distributions is suitable in design.The performance prediction program was used to calculate the new compressor performance characteristic curves and the result was compared with experimental data. The new compressor produces 3% higher pressure ratio at design speed and its length is 20% less than the available compressor. It seems the recent method has some performance and manufacturing imrovements in some aspects and lies along the general trend of current researches.
- Keywords:
- Axial Compressor ; Aerodynamic Design ; Modeling ; Radial Equilibrium ; Compressor Blade
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