فناوری در مهندسی هوافضا

فناوری در مهندسی هوافضا

اثر پوشش محافظ گرمایی بر روی عملکرد حرارتی پره توربین گازی

نوع مقاله : علمی پژوهشی

نویسندگان
1 دانشجوی کارشناسی‌ارشد، گروه مهندسی مکانیک، دانشگاه شهید مدنی آذربایجان، تبریز، ایران
2 دانشیار، گروه مهندسی مکانیک، دانشگاه شهید مدنی آذربایجان، تبریز، ایران
3 استادیار، گروه مهندسی مکانیک، دانشگاه شهید مدنی آذربایجان، تبریز، ایران
چکیده
با توجه به اهمیت بسیار بالای توربین گازی در تولید برق و همچنین توسعه روزافزون آن، از جمله‌­ی مهم­ترین روش­‌ها برای افزایش کارایی پره­‌های توربین گازی، افزودن پوشش محافظ گرمایی به سطح خارجی آنهاست. این پوشش­‌ها اینکه باعث بهبود خنک­‌کاری پره توربین گازی می‌­شوند، ولی معایبی نیز دارند که از جمله­ معایب آنها زبر نمودن سطح پره‌­ها است که ناخواسته منجر به جدایش­‌های جریان سیال داغ اطراف توربین گازی می‌­شوند، لذا سطوح زبر پوشش­‌های محافظ گرمایی می­‌بایست به طور بهینه و هدف­دار مورد استفاده قرار گیرند. در این تحقیق، با استفاده از نرم افزار تجاری فلوئنت به بررسی و تحلیل این نوع پوشش­‌ها، برای یافتن مناسب­‌ترین حالت ممکن جهت استفاده از آن پرداخته شده‌است. تاثیر پارامترهای زبری سطح، ضخامت و جنس پوشش­‌های محافظ گرمایی مورد بررسی قرار گرفته و بهینه‌ترین حالت برای پارامترهای مذکور، به ترتیب 1/0 م م، 38/0 م م و 7/2 وات بر متر در کلوین بدست آمده‌است.
کلیدواژه‌ها
موضوعات

عنوان مقاله English

The Effect of Thermal Barrier Coating on the Thermal Performance of a Gas Turbine Blade

نویسندگان English

Ali Hajizadeh 1
Mir Yoseph Hashemi 2
Ali ziaie Asl 3
1 M. Sc. Student, Department of Mechanical Engineering, Azarbaijan Shahid Madani University, Tabriz, Iran
2 Associate Professor, Department of Mechanical Engineering, Azarbaijan Shahid Madani University, Tabriz, Iran
3 Assistant Professor, Department of Mechanical Engineering, Azarbaijan Shahid Madani University, Tabriz, Iran
چکیده English

Due to the very high importance of gas turbines in electricity production and also its increasing development in the electricity industry, one of the essential methods to increase the efficiency of gas turbine blades is to add thermal barrier coating to their outer surface. These coatings improve the cooling of gas turbine blades, but they also have disadvantages, such as the roughness of their surface causing the separation of the hot fluid flow around the turbine blades. The rough surfaces of thermal barrier coatings should be used optimally and purposefully. In this research, using the commercial software of Fluent, this type of coating has been investigated and analyzed to find the most optimal possible mode for its use. The influence of surface parameters such as roughness, thickness, and material of thermal barrier coatings have been investigated. The most optimal state for the mentioned parameters is 0.1 mm, 0.38 mm, and 2.7 W/m.K, respectively.

کلیدواژه‌ها English

Thermal Barrier Coating
Gas Turbine
Roughness
Numerical Simulations
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  • تاریخ دریافت 28 فروردین 1402
  • تاریخ بازنگری 19 مرداد 1402
  • تاریخ پذیرش 01 مهر 1402
  • تاریخ اولین انتشار 08 آبان 1402