Preliminary experimental study on solid-fuel rocket scramjet combustor

Abstract

Liquid or gaseous fuel scramjet technology has made great progress, and there has been some research attention to solid-fuel scramjet. A new scramjet configuration using solid fuel as propellant, namely solid-fuel rocket scramjet, is tested experimentally. It consists of two combustors. One is a rocket combustor used as gas generator, and the other is a supersonic combustor used for secondary combustion. The experiment simulates a flight Mach number of 4 at high altitude (stagnation temperature and pressure are 1170 K and 1.16 MPa, respectively), and metalized solid fuel is used as propellant. The results reveal that fuel-rich gas from the gas generator can burn with air in the supersonic combustor. Preliminary evaluation results show that the combustion efficiency of the propellant is about 90%, and the total pressure recovery coefficient in the supersonic combustor is about 0.6. These results indicate that the configuration of solid-fuel rocket scramjet is feasible.

摘要

目的

通过发动机直连式实验,验证燃气发生器产生的 富燃燃气可以在超声速气流中二次燃烧,进而证 明固体火箭超燃冲压发动机方案的可行性,并初 步评估固体火箭超燃冲压发动机燃烧室的工作 性能。

创新点

1. 提出固体火箭超燃冲压发动机构型方案,并开 展固体火箭超燃冲压发动机燃烧室直连式实验 研究;2. 验证了固体火箭超燃冲压发动机构型可 行;3. 初步评估了固体火箭超燃冲压发动机燃烧 室的工作性能。

方法

1. 通过直连式实验测定固体火箭超燃冲压发动机 燃烧室的工作参数(图2、3 和4);2. 通过实验 现象(图8)和数据处理,确定燃气发生器产生 的富燃燃气可以在超声速燃烧室中燃烧,进而确 定固体火箭超燃冲压发动机方案的可行性;3. 初 步确定发动机燃烧室的工作性能(公式(6)和 (7))

结论

1. 燃气发生器中产生的富燃燃气可以在超声速燃 烧室中燃烧,固体火箭超燃冲压发动机构型方案 可行;2. 初步评估了固体火箭超燃冲压发动机燃 烧室的工作性能,总压恢复系数约为0.6,燃烧 效率约为90%;3.燃气发生器产生的部分一次燃 气沉积于燃气发生器喉部,使燃气发生器的工作 压力增加,进而引起富燃燃气质量流量的增加; 4. 燃烧室中的总压损失主要集中在富燃燃气入 口处,总压损失主要由射流引起的激波和燃气二次燃烧引起。