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首页> 外文会议>Mechanical properties and performance of engineering ceramics and composites VII >EXPERIMENTAL AND NUMERICAL STUDY ON APPLICATION OF A CMC NOZZLE FOR HIGH TEMPERATURE GAS TURBINE
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EXPERIMENTAL AND NUMERICAL STUDY ON APPLICATION OF A CMC NOZZLE FOR HIGH TEMPERATURE GAS TURBINE

机译：CMC喷嘴在高温燃气轮机上应用的实验与数值研究

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摘要

Ceramic_Matrix Composites (CMC) is the promising material because its allowable temperature is by 200degC higher than those of conventional Ni-base super alloys. A lot of attempts to apply this ceramic for a hot section of advanced gas turbine engines have been done. However in order to gain full performance benefits from this advanced material, many things to be confirmed are remained. In this study, a thermal shock test using a nozzle cascade rig and numerical thermal stress analyses have been conducted under an engine emergency shutdown (thermal shock) condition, which is the most severe condition of any gas turbine engine operations. In the thermal shock test, gas temperature dropped immediately to idle condition within a few second by fuel cut-off and the temperature fields of the CMC nozzle surface were measured by using infrared (IR) cameras. Important dimensionless numbers, such as Reynolds number of main gas flow, are approximately equivalent to those of typical gas turbine engines. The numerical thermal stress analyses are conducted at the actual thermal distribution to calculate the locations where a high thermal stress is generated. Experimental and numerical results are described and discussed in detail in this paper.
机译：Ceramic_Matrix复合材料（CMC）是有前途的材料，因为其允许温度比传统的Ni基超级合金高200℃。已经进行了许多尝试将这种陶瓷应用于高级燃气涡轮发动机的高温部分。但是，为了从这种先进的材料中获得全部的性能优势，还有许多事情需要确认。在这项研究中，已经在发动机紧急停机（热冲击）条件下使用喷嘴级联钻机进行了热冲击试验，并进行了数值热应力分析，这是任何燃气涡轮发动机运行中最严重的条件。在热冲击试验中，通过切断燃料，气体温度在几秒钟内立即下降到空转状态，并且使用红外（IR）摄像机测量了CMC喷嘴表面的温度场。重要的无量纲数（例如主气流的雷诺数）大约等于典型的燃气涡轮发动机的无量纲数。在实际的热分布上进行数值热应力分析，以计算产生高热应力的位置。本文对实验和数值结果进行了详细描述和讨论。

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  • 会议地点 Daytona Beach FL(US);Daytona Beach FL(US);Daytona Beach FL(US)
  • 作者

    Kozo Nita; Yoji Okita; Chiyuki Nakamata;

  • 作者单位

    Advanced Technology Department, Research Engineering Division, Aero-Engine Space Operations, IHI Corporation 229, Tonogaya, Mizuho-machi, Nishitama-gun, Tokyo, 190-1297, JAPAN;

    Advanced Technology Department, Research Engineering Division, Aero-Engine Space Operations, IHI Corporation 229, Tonogaya, Mizuho-machi, Nishitama-gun, Tokyo, 190-1297, JAPAN;

    Advanced Technology Department, Research Engineering Division, Aero-Engine Space Operations, IHI Corporation 229, Tonogaya, Mizuho-machi, Nishitama-gun, Tokyo, 190-1297, JAPAN;

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