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題名 | The Influence of Rotation for Cooling Performance of Gas Turbine Rotor Blade=旋轉對燃氣渦輪機動葉冷卻性能影響之研究 |
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作者 | 顏克家; 張始偉; | 書刊名 | 國立高雄海專學報 |
卷期 | 11 1996.04[民85.04] |
頁次 | 頁35-50 |
分類號 | 446.0131 |
關鍵詞 | 旋轉; 燃氣渦輪機; 動葉冷卻性能; |
語文 | 英文(English) |
中文摘要 | 本文發表一項針對燃氣渦輪機旋轉對其動葉冷卻性能影響之理論及實驗研究。實 驗設計之熱傳通道為一薄壁圓管內配置有五個環狀之凸起物( Turbulence Promoter )。 此熱傳通道之設計係模擬新式燃氣渦輪機動葉內備有增強冷卻效能設計之通道。實驗熱傳通 道之旋轉方向與主流場流向垂直。實驗流場之雷諾數範圍為自 10,000( 2500 )至 15,000 並分別於轉速 0, 1000, 2000 rev/min 下進行測試。為研究浮力 於旋轉流體中對熱傳係數之影響,實驗管壁之溫度於各雷諾數 / 轉速測試時均加熱至 75 ℃,100 ℃、125 ℃,150 ℃及 180℃。實驗證明旋轉造成徑向之熱傳分佈。旋轉管後端( Trailing Edge )之熱傳係數一直高於其前端( Leading Edge )。 於旋轉管前端,其熱 傳係數會因旋轉而降低至大約 80% 之靜上管熱傳係數值。 若於設計燃氣渦機動葉時未考慮 旋轉對熱傳係數之影響,則於渦輪機運轉時會有過熱之現象。故此項實驗結果對於設計燃氣 渦輪機動葉十分重要。 |
英文摘要 | This paper presents the results of an experimental study aimed at investigating the effect of rotation on the heat transfer of a circular-sectioned test tube which rotates about an axis normal to the flow direction This test tube was internally fitted with five full circumferential transverse ribs in attempts to simulate the typically enhanced cooling geometry inside a gas turbine rotor blade for the advanced gas turbine engine. The program of tests undertaken involved three nominal Reynolds number values in the rev/min The air (coolant flow was channeled from the root section of the rotating test tube toward its tip end For each Reynolds/speed option, five different levels of heater power were used to raise the wall temperature to 75 ℃, 100 ℃, 125 ℃, 150 ℃ and 180 ℃ in order to investigate the effect of buoyancy on the heat transfer. It is demonstrated that the circumferential heat transfer variation was established within the ribbed test tube due to the rotation As a result, the heat transfer level on the trailing surface of the rotating test tube was consistently higher than its leading counterpart. On the leading surface, the rotational heat transfer could be reduced to the levels about 80% of the non-rotational heat transfer values. This observation is important for the leading surface of a gas turbine rotor blade if the over-heating situation could develop on the leading surface of a gas turbine rotor blade if the effect of rotation on the heat transfer is not adequately taken into account. |
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