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STUDY ON SYSTEM PERFORMANCE OF LIQUIEFIED AIR CYCLE ENGINE

液化空气循环发动机系统性能研究

基本信息

批准号：
11450374
负责人：
KAMIJO Kenjiro
金额：
$ 9.41万
依托单位：
TOHOKU UNIVERSITY
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (B)
财政年份：
1999
资助国家：
日本
起止时间：
1999 至 2001
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-11450374/
关键词：
AIR LIQUEFACATION ROCKET ENGINE HEAT EXCHANGER LIQUID HYDROGEN TWO-PHASE FLOW LIQUID AIR

项目摘要

Based on the experimental results, an analytical method of estimating a liquefaction (mass of liquefied air cooled by 1 kg of liquid hydrogen), and an outlet temperature of liquid hydrogen of the heat exchanger was established, by which we easily evaluate the performance of the heat exchanger cooled by liquid hydrogen. Using this analytical method, we will be able to easily improve the performance of heat exchanger. The specific impulse of LACE was estimated using the above -mentioned method. More than 1,000 second of the specific impulse was calculated even in a simple LACE system. The higher specific impulse will be able to obtain by improvement of the heat exchanger, selection of the optimum LACE system, the selection of the optimum delivery pressure of liquid hydrogen pump, etc. Judging from the mentioned above performance of the present LACE engine, it will be considered that the LACE engine would be a one of the candidates of a rocket based combined cycle engine for a future reusable launch vehicle. The effect of the flight trajectory on the LACE engine was numerically investigated. The numerical results showed that the specific impulse of the present LACE system was smaller than that expected in the low flight Mach number. Therefore, some means, for instance the use of subcooled liquid hydrogen, will be required which enhance the performance of the LACE engine in the low flight Mach number.

基于实验结果，建立了估算液化量（1kg液氢冷却液化空气的质量）和换热器液氢出口温度的解析方法，从而可以方便地评价液氢冷却换热器的性能。利用这种分析方法，我们将能够很容易地改善换热器的性能。用上述方法估算了LACE的比冲.即使在简单的LACE系统中也计算出超过1，000秒的比冲。通过改进热交换器、选择最佳的LACE系统、选择最佳的液氢泵输出压力等，可以获得较高的比冲。从现有LACE发动机的上述性能来看，LACE发动机是未来可重复使用运载器火箭基组合循环发动机的候选者之一。数值研究了飞行轨迹对LACE发动机的影响。数值计算结果表明，在低飞行马赫数下，本LACE系统的比冲小于预期值。因此，需要采取一些措施，例如使用过冷液氢，以提高LACE发动机在低飞行马赫数下的性能。