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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.3 pt.A; 20050606-09; Reno-Tahoe,NV(US) >THE EFFECTS OF VARYING THE COMBUSTOR-TURBINE GAP
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THE EFFECTS OF VARYING THE COMBUSTOR-TURBINE GAP

机译：改变燃气轮机间隙的影响

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摘要

To protect hot turbine components, cooler air is bled from the high pressure section of the compressor and routed around the combustor where it is then injected through the turbine surfaces. Some of this high pressure air also leaks through the mating gaps formed between assembled turbine components where these components experience expansions and contractions as the turbine goes through operational cycles. This study presents endwall adiabatic effectiveness levels measured using a scaled up, two-passage turbine vane cascade. The focus of this study is evaluating the effects of thermal expansion and contraction for the combustor-turbine interface. Increasing the mass flow rate for the slot leakage between the combustor and turbine showed increased local adiabatic effectiveness levels while increasing the momentum flux ratio for the slot leakage dictated the coverage area for the cooling. With the mass flow held constant, decreasing the combustor-turbine interface width caused an increase in uniformity of coolant exiting the slot, particularly across the pressure side endwall surface. Increasing the width of the interface had the opposite effect thereby reducing coolant coverage on the endwall surface.
机译：为了保护热的涡轮机部件，较冷的空气从压缩机的高压部分排出，并绕过燃烧器，然后再通过涡轮机表面注入。这些高压空气中的一些也会通过组装的涡轮机部件之间形成的配合间隙泄漏，在这些间隙中，随着涡轮机的运行，这些部件会发生膨胀和收缩。这项研究提出了使用按比例放大的两通道涡轮叶片级联测量的端壁绝热有效性水平。这项研究的重点是评估燃烧器-涡轮界面的热膨胀和收缩的影响。燃烧器和涡轮之间的缝隙泄漏的质量流量的增加显示出局部绝热有效性水平的提高，而缝隙泄漏的动量通量比的增加决定了冷却的覆盖面积。在质量流量保持恒定的情况下，减小燃烧室/涡轮机界面的宽度会导致离开槽（尤其是在压力侧端壁表面）的冷却剂均匀性增加。增大界面的宽度具有相反的效果，从而减少了冷却剂在端壁表面上的覆盖。

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