火箭冲压组合发动机部件缩尺关系理论初探  

Theoretical analysis on scaling relation of components for rocket ramjet combined engine

作　　者：杜泉[1,2] 付秀文 DU Quan;FU Xiuwen(Xi＇an Aerospace Propulsion Institute, Xi＇an 710100, China;Science and Technology on Liquid Rocket Engine Laboratary, Xi＇an 710100, China)

机构地区：[1]西安航天动力研究所,陕西西安710100 [2]液体火箭发动机技术重点试验室,陕西西安710100

出　　处：《火箭推进》2018年第2期18-22,共5页Journal of Rocket Propulsion

基　　金：国家863项目(2014AA7023026)

摘　　要：为了使小尺度火箭冲压组合发动机的试验结果支撑中大尺度发动机的研制,从火箭冲压组合发动机各个部件的工作原理出发,理论分析了火箭冲压组合发动机部件缩尺关系,构建了小尺度发动机部件与中大尺度发动机部件之间的缩尺关系。研究表明:液态碳氢燃料火箭冲压组合发动机缩尺关系区别于氢燃料超燃冲压发动机的"压力-长度"缩尺关系;发动机各部件的缩尺关系差异明显;进排气系统可采用几何缩尺关系;隔离段、燃料喷注器、火焰稳定装置遵循不同的缩尺关系;燃料穿透深度与发动机尺寸呈线性关系,而蒸发和雾化与发动机尺度无关;火箭推力室缩尺可按照缩尺因子改变火箭推力室的数量实现。Based on the operating principle of each component for rocket ramjet combined engine, the scaling relation of components for rocket ramjet combined engine was theoretically analyzed, and the scaling relation between the components of small size engine and midsize engine or large size engine was established to make the test results of small size rocket ramjet combined engine support the development of large size engine. The analysis results show that the scaling relation of the hydrocarbon fueled rocket ramiet combined engine is different from the pressure-length scaling relation of hydrogen fueled scramjet engine ; the scaling relation of all the components for the two kinds of engines is obviously different ; geo- metric scaling relation can be adopted for the intake and exhaust system; the scaling of isolator, fuel in- jectors and flame stabilizing device abides by different scaling relation ; the penetration depth of liquid fu- el is linear relation with engine size, but the atomization and evaporation of liquid fuel has no relation with engine size ; the scaling of thrust chamber can be realized by changing the number of thrust chambers according to the scale factor.

关 键 词：火箭冲压组合发动机 缩尺关系 碳氢燃料 发动机尺度 

分 类 号：V430-34[航空宇航科学与技术—航空宇航推进理论与工程]