• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>ASME turbo expo: turbomachinery technical conference and exposition >TURBINE VANE ENDWALL FILM COOLING COMPARISON FROM FIVE FILM-HOLE DESIGN PATTERNS AND THREE UPSTREAM LEAKAGE INJECTION ANGLES
【24h】

TURBINE VANE ENDWALL FILM COOLING COMPARISON FROM FIVE FILM-HOLE DESIGN PATTERNS AND THREE UPSTREAM LEAKAGE INJECTION ANGLES

机译：五个膜孔设计图案和三个上游泄漏注射角度的涡轮叶片端墙膜冷却比较

获取原文
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

The effects of upstream leakage injection angle on film cooling effectiveness of a turbine vane endwall with various endwall film-hole designs were examined by applying PSP measurement technique. As the leakage flow from the slot between the combustor and the turbine vane is not considered an active source to protect the vane endwall in certain engine designs, discrete cylindrical holes are implemented near the slot to create additional controllable upstream leakage flow to cool the vane endwall. Three potential leakage injection angles were studied: 30°, 40°, and 50°. To explore the optimum endwall cooling design, five different film-hole patterns were tested: axial row, cross row, cluster, mid-chord row, and downstream row. Experiments were conducted in a four-passage linear cascade facility in a blowdown wind tunnel at the exit isentropic Mach number of 0.5 corresponding to inlet Reynolds number of 380,000 based on turbine vane axial chord length. A freestream turbulence intensity of 19% with an integral length scale of 1.7 cm was generated at the cascade inlet plane. Detailed film cooling effectiveness for each design was analyzed and compared at the design operation conditions (coolant mass flow ratio 1% and density ratio 1.5). The results are presented in terms of high-fidelity film effectiveness contours and laterally (spanwise) averaged effectiveness. This paper will provide the gas turbine designers valuable information on how to select the best endwall cooling pattern with minimum cooling air consumption over a range of upstream leakage injection angle.
机译：通过应用PSP测量技术，研究了上游泄漏喷射角对具有各种端壁膜孔设计的涡轮叶片端壁的膜冷却效率的影响。由于在某些发动机设计中，燃烧室和涡轮机叶片之间的缝隙泄漏流不被认为是保护叶片端壁的有效来源，因此在该缝隙附近设置了离散的圆柱孔，以产生额外的可控上游泄漏流来冷却叶片端壁。 。研究了三个潜在的泄漏注入角：30°，40°和50°。为了探索最佳的端壁冷却设计，测试了五种不同的膜孔样式：轴向排，横排，簇，中弦排和下游排。实验是在排污风洞的四通道线性叶栅设施中进行的，出口等熵马赫数为0.5，对应于基于涡轮叶片轴向弦长的雷诺数为380,000。在叶栅入口平面处产生了19％的自由流湍流强度，整体长度尺度为1.7 cm。在设计操作条件下（冷却剂质量流量比为1％，密度比为1.5），对每种设计的详细薄膜冷却效率进行了分析和比较。结果以高保真胶片效果轮廓和横向（跨度）平均效果表示。本文将为燃气轮机设计人员提供宝贵的信息，说明如何在上游泄漏喷射角度范围内选择最佳的端壁冷却方式并以最少的冷却空气消耗。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号