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      |本期目錄/Table of Contents|

      [1]李繼宸,朱惠人,陳大為,等.尾跡影響下有復合角扇形孔渦輪葉片表面的氣膜冷卻效率實驗研究[J].西安交通大學學報,2019,53(09):167-175.[doi:10.7652/xjtuxb201909022]
       LI Jichen,ZHU Huiren,CHEN Dawei,et al.Experimental Study on Film Cooling Effectiveness of the Turbine Blade with Compound-Angled Fan-Shaped Holes under Wake Influence[J].Journal of Xi'an Jiaotong University,2019,53(09):167-175.[doi:10.7652/xjtuxb201909022]
      點擊復制

      尾跡影響下有復合角扇形孔渦輪葉片表面的氣膜冷卻效率實驗研究(PDF)

      《西安交通大學學報》[ISSN:0253-987X/CN:61-1069/T]

      卷:
      53
      期數:
      2019年第09期
      頁碼:
      167-175
      欄目:
      出版日期:
      2019-09-10

      文章信息/Info

      Title:
      Experimental Study on Film Cooling Effectiveness of the Turbine Blade with Compound-Angled Fan-Shaped Holes under Wake Influence
      作者:
      李繼宸1 朱惠人1 陳大為1 陳剛2 周道恩1
      1.西北工業大學動力與能源學院, 710072, 西安; 2.中國航發沈陽發動機研究所, 110015, 沈陽
      Author(s):
      LI Jichen1 ZHU Huiren1 CHEN Dawei1 CHEN Gang2 ZHOU Daoen1
      1.School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China; 2.AECC Shenyang Engine Institute, Shenyang 110015, China
      關鍵詞:
      復合角扇形孔 尾跡 氣膜冷卻效率 壓敏漆 渦輪葉片
      Keywords:
      compound-angled fan-shaped hole wake film cooling effectiveness pressure sensitive paint turbine blade
      分類號:
      V231.1
      DOI:
      10.7652/xjtuxb201909022
      摘要:
      為研究尾跡影響下帶有復合角扇形孔的渦輪葉片的氣膜冷卻效率變化規律,利用壓敏漆技術獲得了不同質量流量比、不同尾跡斯特勞哈爾數(0、0.12、0.36)下的渦輪葉片表面氣膜冷卻效率分布。研究結果表明:氣膜孔復合角有利于射流的橫向擴散,孔下游射流的覆蓋面積較大; 在無尾跡條件下,質量流量比的增加使得帶有復合角氣膜孔的渦輪葉片前緣與壓力面大部分區域的氣膜冷卻效率提高,使得吸力面氣膜冷卻效率下降,吸力面靠近葉頂的低氣膜冷卻效率區域面積變小; 在尾跡條件下,質量流量比的增加使得前緣、壓力面以及吸力面靠近尾緣區域的氣膜冷卻效率提高,使得吸力面其他區域的氣膜冷卻效率降低; 尾跡會使葉片表面氣膜冷卻效率顯著降低,在尾跡斯特勞哈爾數為0.36的條件下,小質量流量比時葉片表面氣膜冷卻效率的平均降幅為35%,大質量流量比時平均降幅為26%,氣膜冷卻效率的下降幅度減小。
      Abstract:
      The film cooling effectiveness of the turbine blade with compound-angled fan-shaped holes was measured by the pressure sensitive paint technique.The wake's Strouhal number was varied from 0 to 0.36 and three mass flux ratios were determined.Results show that the compound-angled holes can enhance the lateral spreading of coolant, and the injection has a wider coverage area without wakes.The increase of the mass flux ratio causes an increase in the film cooling effectiveness over the leading edge and most area of the pressure surface with compound-angled holes, but a decrease on the suction surface.The increase of mass flux ratio also reduces the area near the tip on the suction side, where the film coverage is insufficient under wake influence, and causes an increase in the film cooling effectiveness over the leading edge, the pressure surface and the suction surface near the trailing edge, but decreases this effectiveness on the mid-chord region of the suction surface.The wake causes a remarkable decrease in the film cooling effectiveness over the blade surface.In the case that wake's Strouhal number is 0.36, the average film cooling effectiveness over the blade is decreased by 35% under the condition of low mass flux ratio, and decreased by 26% under the condition of high mass flux ratio.

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      備注/Memo

      備注/Memo:
      收稿日期: 2019-03-28。作者簡介: 李繼宸(1996—),男,碩士生; 朱惠人(通信作者),男,教授,博士生導師;痦椖: 國家重點基礎研究發展規劃資助項目(2013CB035702)。
      更新日期/Last Update: 2019-09-04
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