دانلود مقاله یک تحلیل تطبیقی و بهینه سازی دو SOFC ترکیبی مافوق صوت
چکیده
مقدمه
توصیف سیستم
مدل ریاضی
اعتبار سنجی
نتایج
نتیجه گیری
منابع
Abstract
Introduction
System description
Mathematical model
Validation
Results
Conclusion
References
چکیده
در این مطالعه، ما دو نوع مختلف از سیستم‌های محرکه را برای یک هواپیمای بدون سرنشین مافوق صوت (پهپاد) که با سرعت 1.8 ماخ پرواز می‌کند، مقایسه کردیم که از دو نوع سوخت مختلف برای تعیین ویژگی‌ها و مزایای آنها استفاده می‌کنند. همچنین تأثیر عوامل مختلف از جمله ارتفاع و پارامترهای کلیدی طراحی پیشرانه را بر بازده و مدت پرواز بررسی می کند. این سیستم‌های پیشرانه پیشنهادی از یک پیل سوختی اکسید جامد (SOFC) برای تولید گرمای مورد نیاز برای عملکرد توربین و تولید نیروی رانش استفاده می‌کنند. هیدروژن برای SOFC یا در مخزن ذخیره می شود یا از طریق اصلاح داخلی متان در داخل پیل سوختی تولید می شود. ما اثرات چندین پارامتر طراحی کلیدی برای این موتورها را در شرایط پرواز و ارتفاعات مختلف مطالعه کردیم. انجام یک بهینه سازی چند هدفه برای هر سیستم محرکه پیشنهادی برای به حداکثر رساندن نیروی رانش موتور در حالی که مصرف سوخت را در حداقل نرخ برای دستیابی به طولانی ترین مدت پرواز حفظ می کند. سپس بهترین شرایط را تعیین کردیم که رانش قابل قبول با مدت زمان پرواز معقول همراه باشد. نتایج نشان داد که راندمان و توان تولیدی پیشرانه با افزایش ارتفاع پرواز یا نسبت فشار کمپرسور افزایش می‌یابد. همچنین، به دلیل چرخش مجدد سوخت در آند SOFC، در مقایسه با استفاده از هیدروژن، بازده بالاتری را مشاهده کردیم. زیرا چرخش آند باعث مصرف بیشتر سوخت می شود. نتیجه بهینه سازی نشان می دهد که راندمان و مصرف سوخت برای سیستم سوخت هیدروژنی برای موتور با سوخت متان به ترتیب 48.7% و 0.0024 kg/s و 67.9% و 0.0066 کیلوگرم بر ثانیه است.
توجه! این متن ترجمه ماشینی بوده و توسط مترجمین ای ترجمه، ترجمه نشده است.
Abstract
In this study, we compared two different types of propulsion systems for a supersonic unmanned aerial vehicle (UAV) flying at Mach 1.8, which are using two different types of fuel to determine their characteristics and advantages. Also, investigate the effect of various factors such as altitudes and key design parameters of the propulsion system on efficiency and flight duration. These proposed propulsion systems are using a solid oxide fuel cell (SOFC) to generate the heat required for the operation of the turbine and generate thrust. The hydrogen for SOFC is either stored in the tank or generated by the internal reformation of methane inside the fuel cell. We studied the effects of several key design parameters for these engines in different flight conditions and altitudes; carrying out a multi-objective optimization for each proposed propulsion system to maximize the thrust of the engine while keeping the fuel consumption at a minimum rate to achieve the longest flight duration. Then we determined the best conditions where the acceptable thrust is accompanied by reasonable flight duration. Results indicated that the efficiency and generated power of the propulsion system will increase by higher flight altitude or compressor pressure ratio. Also, due to the recirculation of fuel in the SOFC’s anode, we observed higher efficiency in comparison when hydrogen is used; since anode-recirculation causes higher fuel utilization. The optimization result shows that the efficiency and fuel consumption for the hydrogen-fueled system is 48.7% and 0.0024 kg/s, respectively, and 67.9% and 0.0066 kg/s. for the methane-fueled engine.
Introduction
SOFCs, facilities with considerable capability of conserving energy have been investigated from different aspects as the experimental study cases and numerical simulation attempts. Stambouli et al. [1] has outlined the global population growth and the growing need for energy and its environmental impacts. Zhang et al. [2] has reviewed the different concepts and strategies for overcoming climate change and energy security challenges by using the SOFC integrated systems. Buonomano et al. [3] has reviewed the SOFC-GT integrated systems that use alternative fuels like coal and biomass. Bae et al. [4] has investigated a dynamic model of the SOFC under electrical load change. The results have shown that the overall behavior is mostly related to the diffusion in the anode. As an innovative power source for portable application in vehicles, the SOFCs was subjected to many analyses incorporated with many commercial projects. STALKER-XE as a SOFC-powered UAV was experimentally applied by the Advanced Research Projects Agency [5]. They concluded considerable endurance for UAVs with the SOFC power resource in comparison with battery-powered ones. Volvo [6] completed the process of production and testing diesel heavy-duty truck which uses SOFC as an auxiliary power unit (APU). Their results introduced SOFC APU as an important facility in the body of the power generation system in their truck.
Conclusion
In the case of comparing the performance of two hybrid turbine-less configurations of the supersonic power unit in this study with hydrogen and methane as different types of fuel, a numerical simulation of the operating condition is performed. The thermodynamic parameters of both systems are studied under the condition of supersonic flight mode with the Mach number equal to 1.8. Finally, the generated thrust and consumed fuel as the key parameters of the flight were optimized by the Genetic algorithm and TOPSIS method. The main results of this study are shown as follow:
1. The efficiency and generated power of the propulsion system by increasing flight altitude increase in the case of the methane-fuel system.
2. Low temperature at high altitude flight levels in case of fixed Mach number and compressors pressure ratio leads to increment in intake air mass flow rate of the system.