為了減緩科氏力作用對燃氣渦輪機轉子葉片冷卻性能的不利影響，採用帶有橫向排放的旋轉楔形衝擊噴柱和柱鰭陣列通道配置，產生軸向冷卻(軸流式)模式。並比較兩個軸向冷卻(軸流式)通道在旋轉下，由光滑和開槽噴嘴壁所產生的紐賽數分布、凡寧摩擦係數和空氣熱性能係數。對於帶有凹槽和不帶凹槽的衝擊和柱鰭陣列區域的旋轉迎風(背風)面上的平均紐賽數進行了修正，修正值分別為靜態通道參考值的1.2-2.1倍(1.31-2.18倍)和1.15-1.64倍(1.2-2.15)倍；而衝擊噴柱(柱鰭陣列)區域上的最小壁面紐賽數則分別降低到區域平均紐賽數的20-65% (25-55%) 和 20-65% (25-60%)。噴嘴壁上的凹槽削弱了噴流之間的約束，並導引冷卻側流向柱鰭通道區域，提高了衝擊噴柱(柱鰭陣列)區域旋轉迎風、背風面的區域平均紐賽數，提高至光滑噴嘴壁的1.11-1.39倍 (1.17-1.39倍) 和 1.12-1.56倍 (1.19-1.44倍)。旋轉靜態凡寧摩擦數比值介於1.06-1.21倍(1.03-1.16倍)之間，開槽(光滑)的通道API∞ 值達到15-19.8 (10.1-15)。制定了兩個旋轉通道的區域平均紐賽數和凡寧摩擦係數相關性以供相關應用使用。

For leading edge cooling of a gas turbine rotor blade, the cooling performances of two rotating wedge-shaped channels with impinging jet-array and pin-fin array in axial flow mode (AFC) are experimentally studied for recovering the unfavorable Coriolis-force effect that undermines the heat transfer performance on a stabilized rotating surface. The study measures the detailed endwall Nusselt number (Nu) distributions, the Fanning friction factors (f), and the aerothermal performance indices (API) for the two rotating channels equipped with the smooth- and grooved-nozzle walls. The endwall average Nusselt numbers over the leading (trailing) surfaces for the impingement and pin-fin regions with and without the grooved nozzle walls are raised to 1.2-2.1(1.31-2.18) and 1.15-1.64(1.2-2.15) times the Nusselt number levels in static conditions (Nu0). The minimum endwall Nusselt numbers on the impingement (pin-fin) areas respectively fall to 20-65% (25-55%) and 20-65% (25-60%) of the endwall-mean Nusselt numbers. The grooved nozzle wall weakens the confinements of jet-array and assist to guide the cold coolant flows laterally toward the pin-fin region. The endwall average Nusselt numbers on the leading and trailing surfaces of the impingement (pin-fin) region of the rotating channel with the grooved nozzle wall are raised to 1.11-1.39 (1.17-1.39) and 1.12-1.56 (1.19-1.44) times the Nusselt numbers with smooth nozzle-wall. The ratios of Fanning friction factor between the rotating and static channels are between 1.06-1.21 and (1.03-1.16); whereas the values of API∞ are elevated to 15-19.8 (10.1-15) for the test channels with the grooved (smooth) nozzle walls. The correlations of endwall average Nusselt number and channel Fanning friction factors are devised to assist the cooling design applications of a gas turbine rotor blade.

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