火箭推进

针对空气涡轮火箭冲压发动机马赫数1.5～4.5工作范围的设计要求,提出了一种唇口平移的曲面轴对称进气道变几何方案及其新型调节机构,并通过数值仿真方法对其总体性能和流动特性进行研究。结果表明:采用曲面压缩的轴对称变几何进气道总体性能较高,尤其是流量捕获能力良好,可以满足整个工作范围的需求。此外,新型调节机构简单可行,利于工程实现。

In view of the design requirements for the air turbine-rocket and ramjet(ATRR)engines with Mach number from 1.5 to 4.5, a variable geometry scheme of curved symmetrical inlet with cowl translation is proposed as well as its new adjustment mechanism. The overall performances and flow characteristics are studied by numerical simulation. The results show that overall performances of the axisymmetric variable-geometric inlet with curved surface compression is high, especially the flow capture ability is good, which can meet requirements of the entire operating range. In addition, the new mechanism is simple and feasible, which is beneficial to the engineering realization.

引言
1 基准轴对称进气道设计
2 基准进气道的数值结果分析
3 进气道变几何方案分析
4 唇口平移方案的调节机构
5 结论

图1 基准进气道三维构型(Inlet1)<br/>Fig.1 3D configuration of reference inlet(Inlet1)

图1 基准进气道三维构型(Inlet1)
Fig.1 3D configuration of reference inlet(Inlet1)

图2 基准进气道的流量系数与目标值的对比<br/>Fig.2 Comparison of flow coefficient for reference inlet with the target value

图2 基准进气道的流量系数与目标值的对比
Fig.2 Comparison of flow coefficient for reference inlet with the target value

图3 典型来流马赫数时基准进气道的马赫数分布<br/>Fig.3 Mach number distribution of reference inlet at typical Mach number

图3 典型来流马赫数时基准进气道的马赫数分布
Fig.3 Mach number distribution of reference inlet at typical Mach number

图4 变几何进气道的流量系数与目标值的对比<br/>Fig.4 Comparison of flow coefficient for variable geometry inlet with the target value

图4 变几何进气道的流量系数与目标值的对比
Fig.4 Comparison of flow coefficient for variable geometry inlet with the target value

图5 基准进气道和变几何进气道性能变化曲线<br/>Fig.5 Performance curves of reference inlet and variable geometry inlet

图5 基准进气道和变几何进气道性能变化曲线
Fig.5 Performance curves of reference inlet and variable geometry inlet

图6 基准进气道和变几何进气道喉道和出口的马赫数变化曲线<br/>Fig.6 Mach number curves of throat and exit plane for reference inlet and variable geometry inlet

图6 基准进气道和变几何进气道喉道和出口的马赫数变化曲线
Fig.6 Mach number curves of throat and exit plane for reference inlet and variable geometry inlet

图7 典型来流马赫数时变几何进气道的马赫数分布<br/>Fig.7 Mach number distribution of variable geometry inlet at typical Mach number

图7 典型来流马赫数时变几何进气道的马赫数分布
Fig.7 Mach number distribution of variable geometry inlet at typical Mach number

图8 轴对称变几何进气道的调节机构示意图<br/>Fig.8 Schematic diagram of adjustment mechanism for axisymmetric variable geometric inlet

图8 轴对称变几何进气道的调节机构示意图
Fig.8 Schematic diagram of adjustment mechanism for axisymmetric variable geometric inlet

[1] EHRLICH C F. Early studies of RBCC applications and lessons learned for today, AIAA 2000-3105 [R]. USA: AIAA, 2000.
[2] SNYDER L E,ESCHER D W. Turbine based combination cycle(TBCC)propulsion subsystem integration, AIAA 2004-3649[R]. USA: AIAA, 2004.
[3] 南向谊, 王拴虎, 李平. 空气涡轮火箭发动机研究的进展及展望[J]. 火箭推进,2008,34(6): 31-35.
[4] LONGSTAFF R,BOND A. The SKYLON project, AIAA 2011-2244[R]. USA: AIAA, 2011.
[5] SIEBENHAAR A, J BOGAR T J. Integration and vehicle performance assessment of the aerojet “Trijet” combined-cycle engine, AIAA 2009-7420[R]. USA: AIAA, 2009.
[6] 韦宝禧, 凌文辉, 江强, 等. TRRE发动机关键技术分析及推进性能探索研究[J]. 推进技术, 2017, 38(2): 298-305.
[7] 张华军, 郭荣伟, 李博.TBCC进气道研究现状及其关键技术[J]. 空气动力学学报,2010, 28(5): 613-621.
[8] CONNORS J F, WOOLLEN R R. Performance characteristics of several types of axially symmetric nose inlets at Mach number 3.85, NACA RM E52115[R]. USA: AIAA, 1952.
[9] LEZBERG E A, METZLER A J, PACK W D. Instream measurements of combustion during Mach 5 to 7 tests of the hypersonic research engine(HRE), AIAA 1993-2324[R]. USA: AIAA, 1993.
[10] VOLAND R T, AUSLENDE A H, SMART M K. CIAM/NASA Mach 6.5 scramjet flight and ground test, AIAA 1999-4848[R]. USA: AIAA, 1999.
[11] SORENSEN N E,LATHAM E A. Variable geometry for supersonic mixed compression inlets, AIAA 1974-1172[R].USA: AIAA, 1974.
[12] STEPHEN C, BRADFORD A N, TIMOTHY R M. Flight testing the linear aero spike SR-71 experiment(LASRD), NASA TM 1988-206567[R].USA: AIAA,,1988.
[13] COLVILLE J R,LEWIS M J. An aerodynamic redesign of the sr-71 inlet with applications to turbine based combined cycle engines, AIAA 2004-3481 [R]. USA: AIAA, 2004.
[14] KOBAYASHI H, TANATSUGU N, TETSUYA S T, et al. Experimental study of multi-row disk inlets for hypersonic air breathing propulsion, AIAA 2004-861, [R]. USA: AIAA, 2004.
[15] 滕健, 袁化成. 一种轴对称变几何进气道设计方法[J]. 航空动力学报, 2013,28(1):96-103.
[16] 王亚岗, 袁化成, 郭荣伟. TBCC 用轴对称进气道流量控制技术研究[J]. 推进技术,2013,34(12):1606-1615.
[17] 向有志, 张堃元, 王磊, 等. 壁面压升可控的高超轴对称进气道优化设计[J]. 航空动力学报, 2011,26(10):2193-2199.
[18] 李永洲, 张堃元. 基于马赫数分布可控曲面外内锥形基准流场的前体进气道一体化设计[J]. 航空学报, 2015,36(1): 289-301.

备注

引言

1 基准轴对称进气道设计

2 基准进气道的数值结果分析

3 进气道变几何方案分析

4 唇口平移方案的调节机构

5 结论

期刊信息