نوع مقاله : مقاله پژوهشی
نویسندگان
دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران
چکیده
کلیدواژهها
موضوعات
عنوان مقاله [English]
نویسندگان [English]
Compressors, which are used to increase gas pressure, play a critical role in industry and may be utilized either as part of a larger machine, such as a gas turbine, or as a standalone machine in processing units. Given the widespread application of compressors, improving their performance and expanding their operating range is of great importance, leading to extensive studies on this subject and the factors affecting it. In this study, the effect of blade tip clearance on the performance of a transonic multistage compressor was investigated using numerical simulation. First, a baseline NASA compressor was simulated and validated using available data. Additionally, a single-stage simulation of each compressor stage was conducted and validated by comparison with multi-stage simulation results. Subsequently, the impact of increasing rotor clearances to 1.5 and 2 times the baseline level was examined in three different scenarios: increasing clearance for all rotors, only the first rotor, or only the second rotor. The results indicate that among these two rotors, the one with the larger clearance is the primary source of instability. Furthermore, the operating range of the compressor remains almost unchanged compared to the scenario where the clearance of all rotors is increased uniformly.
کلیدواژهها [English]
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