首页> 外文会议>ASME turbo expo: turbine technical conference and exposition >THE EFFECT OF AREA RATIO CHANGE VIA INCREASED HOLE LENGTH FOR SHAPED FILM COOLING HOLES WITH CONSTANT EXPANSION ANGLES
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THE EFFECT OF AREA RATIO CHANGE VIA INCREASED HOLE LENGTH FOR SHAPED FILM COOLING HOLES WITH CONSTANT EXPANSION ANGLES

机译:恒定膨胀角的异型膜冷却孔的开孔面积变化对长径比的影响

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Shaped film cooling holes are used as a cooling technology in gas turbines to reduce metal temperatures and improve durability, and they generally consist of a small metering section connected to a diffuser that expands in one or more directions. The area ratio of these holes is defined as the area at the exit of the diffuser, divided by the area at the metering section. A larger area ratio increases the diffusion of the coolant momentum, leading to lower average momentum of the coolant jet at the exit of the hole and generally better cooling performance. Cooling holes with larger area ratios are also more tolerant of high blowing ratio conditions, and the increased coolant diffusion typically better prevents jet liftoff from occurring. Higher area ratios have traditionally been accomplished by increasing the expansion angle of the diffuser while keeping the overall length of the hole constant. The present study maintains the diffuser expansion angles and instead increases the length of the diffuser, which results in longer holes. Various area ratios have been examined for two shaped holes: one with forward and lateral expansion angles of 7° (7-7-7 hole) and one with forward and lateral expansion angles of 12° (12-12-12 hole). Each hole shape was tested at numerous blowing ratios to capture trends across various flow rates. Adiabatic effectiveness measurements indicate that for the baseline 7-7-7 hole, a larger area ratio provides higher effectiveness, especially at higher blowing ratios. Measurements also indicate that for the 12-12-12 hole, a larger area ratio performs better at high blowing ratios but the hole experiences ingestion at low blowing ratios. Steady RANS simulations did not accurately predict the levels of adiabatic effectiveness, but did predict the trend of improving effectiveness with increasing area ratio for both hole shapes. Flowfield measurements with PIV were also performed at one downstream plane for a low and high area ratio case, and the results indicate an expected decrease in jet velocity due to a larger diffuser.
机译:异型膜冷却孔在燃气轮机中用作冷却技术,以降低金属温度并提高耐用性,并且通常由连接到沿一个或多个方向扩展的扩散器的小计量部分组成。这些孔的面积比定义为扩散器出口处的面积除以计量部分的面积。较大的面积比会增加冷却剂动量的扩散,从而导致孔出口处的冷却剂射流的平均动量降低,并且冷却性能通常会更好。具有较大面积比的冷却孔还可以更好地承受高吹风比条件,并且增加的冷却剂扩散通常可以更好地防止喷射升空的发生。传统上,通过在保持孔的总长度恒定的同时增加扩散器的膨胀角来实现更高的面积比。本研究保持了扩压器的膨胀角,而增加了扩压器的长度,从而导致了更长的孔。已经检查了两个异形孔的各种面积比:一个具有7°(7-7-7孔)的正向和横向膨胀角,另一个具有12°(12-12-12孔)的正向和横向膨胀角。每个孔的形状都以多种吹塑比进行了测试,以捕获各种流速下的趋势。绝热效果测量表明,对于基线7-7-7孔,较大的面积比可提供更高的效果,尤其是在较高的吹塑比下。测量还表明,对于12-12-12孔,较大的面积比在高吹塑比下表现更好,但孔在低吹塑比下会被吸食。稳定的RANS模拟不能准确预测绝热效果的水平,但是可以预测随着两种孔形状的面积比增加而提高效果的趋势。在低面积比和高面积比的情况下,在一个下游平面上也进行了PIV流场测量,结果表明由于较大的扩散器,射流速度有望降低。

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