Advances in the application of non-contact temperature measurement technology for aero-engine blade
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Abstract:
The advancement of the aviation sector has made the temperature measurement technology for aero-engine turbine blades essential for maintaining the engine’s safe and steady performance. The non-contact temperature measurement technology is a trending research focus in turbine blade temperature measurement due to its benefits of not requiring direct touch with the object being measured and its suitability for high-temperature and high-speed conditions. This paper provides a concise overview of various key non-contact temperature measurement methods for aero-engines, such as fluorescence temperature measurement, fiber-optic temperature measurement, and radiation temperature measurement. It discusses the temperature measurement principle, technical characteristics, and the current research status both domestically and internationally. Based on this, this Review further discusses the main challenges faced by the non-contact temperature measurement technology and the development trend of the future.Keywords:
Aero engine
يمكن لتوربينات الرياح المنتشرة في مزارع الرياح على نطاق المرافق أن تدعم تلبية رغبات الطاقة المستقبلية وتقليل انبعاثات ثاني أكسيد الكربون عن طريق تقليل متطلبات الطاقة من الوقود الأحفوري. مع ارتفاع درجة حرارة الهواء على مدار اليوم، تزداد سرعة الرياح بسبب تدرجات درجة الحرارة، والتي تنتج تدرجًا في الكثافة / الضغط، مما يؤدي إلى حركة الهواء التي تواجهها توربينات الرياح. اعتمادًا على تضاريس الأرض، يمكن أن تواجه الرياح وتوجه في الوديان بين التلال وفوقها حيث تتدفق وتتبع منحنيات الأرض. تنتج هذه التضاريس زيادة في سرعة الرياح في القمم والتلال. في هذا العمل، تم تصميم شفرة دوار توربينات الرياح الأفقية الصغيرة للعمل في ظل سرعة الرياح المنخفضة، باستخدام برنامج (Q-Blade). استنادًا إلى نظرية عنصر الشفرة (BEM). مع الجنيح NACA3712. تم استخدام دوار ثلاثي الشفرات ودوار بخمس شفرات بناءً على نوع التوربين وحجم الدوار لتوليد الطاقة الميكانيكية من طاقة الرياح. تم إجراء مقارنة وتحليل قوة التوربين ومعامل القدرة ومعامل عزم الدوران عند سرعة رياح منخفضة ((1m/s-8m/s وتم الحصول على نتائج دقيقة للغاية. وجد أن أفضل أداء يمكن أن يعمل فيه دوار توربيني ثلاثي الشفرات بقدرة توربينية تبلغ (955W) كما تم الحصول على قدرة التوربين ((582W للدوار خماسي الشفرات. وجد أن تصميم توربينة رياح أفقية صغيرة بخمس ريش أفضل من التوربين بثلاث ريش ومناسب للعمل في المناطق ذات سرعة الرياح المنخفضة وبكفاءة عالية مقارنة بحجم التوربين.
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In today's industrial scenario, Gas Turbine is one of the most important components of auxiliary power plant system.In order maximize the overall performance and efficiency of all modern turbines, which theoretically operate according to Brayton cycle, they are operated at a very high temperature.These temperatures are so high that, which may fall in the region of turbine blade material melting point temperatures.Due to such high temperatures there is a possibility that the turbine blades may get damaged due to produced thermal stresses and presents a possible threat to the turbine system as well as the operators.Hence to ensure safe and reliable working of the turbines an effective and reliable cooling system is necessary.Currently available methods for cooling of the turbine blades include film cooling with impingement cooling for the leading edge, rib turbulated cooling using serpentine passages for the middle portion of the blade and pin fin cooling for the trailing edge of the turbine blades.The cooling mechanism for turbine blades must include cooling for all possible regions which are exposed to hot gas flow.The turbine blade tip is one of the critical regions which are severely exposed to hot gas flow occurring due to the leakage of gases from the clearance gap between the turbine tip and the shroud.Hence the tip of the turbine blade must be cooled effectively to prevent thermal expansion of the turbine blade tip due to heating.This cooling will eventually help to avoid rubbing of blades to the shroud which may cause their wear.In this paper, we will be presenting the review of various efforts made by various authors towards the cooling of the turbine blade tip.The paper includes both, experimental methods developed as well as numerical efforts reported.Various experimental setups developed for turbine blade tip cooling includes the pioneer work of R. S. Bunker [1] to the recent efforts put by the Potdar et al.It has been noted that most of the authors had attempted this kind of problems experimentally only.They have found that the heat transfer can be improved by adding various types of protrusions on the flat plate surface.These added surface essentially help to produce vortex kind of structure and eventually increases the turbulence level near the tip surface.However it is also fact that to carry out the experimentations for various conditions is very costly due to the need of the today's sophisticated measuring devices required to understand and visualize the heat transfer phenomena.On the other hand numerical simulations will provide the detailed visualization and analysis of the heat transfer and flow characteristics for cooling of turbine blade tip.However producing the accurate and reliable results using available CFD software ANSYS-Fluent also need to be reviewedAn attempt here is to explore and present most of the recentcontributions presented by various authors.These reviews will help and provide the detailed guidelines for planned numerical and experimental investigations required for the cooling of turbine blade tip, which help to provide the feasible and practically usable solution for cooling turbine tip.
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