極超音速空気吸い込み式エンジン用予冷却器(プリクーラ)の開発研究  [in Japanese] Development Study on a Precooler for the Hypersonic Air-Breathing Engine  [in Japanese]

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Abstract

Here is presented an experimental and analytical study on a precooler for hypersonic air-breathing engines. Precooling of the incoming air breathed by an air-inlet gives extension of the flight envelope and improvement of the thrust and specific impulse. Three precooler models were installed into an air-turbo ramjet engine and tested under the sea level static condition. When the fan inlet temperature was down to 180K, the engine thrust and specific impulse increased by 2.0 and 1.2 times respectively. Thick frost formed on the tube surfaces at the entrance part of the precooler blocked the air-flow passage. On the other hand, very thin frost formed at the exit part because the water vapor included in the air was changed to mist particles due to the low temperature of the air in this part. Parametric studies on the precooler design values and a sizing analysis were also performed. Decrease of tube outer diameters on the precooler is only way to increase heat exchange rates without increase of its weight and pressure loss.

Journal

  • JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 50(580), 196-203, 2002-05-05

    THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

References:  6

Cited by:  4

Codes

  • NII Article ID (NAID)
    10008213696
  • NII NACSIS-CAT ID (NCID)
    AA11307372
  • Text Lang
    JPN
  • Article Type
    Journal Article
  • ISSN
    13446460
  • NDL Article ID
    6170727
  • NDL Call No.
    Z74-B503
  • Data Source
    CJP  CJPref  NDL  J-STAGE 
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