摘要
文章基于某小型涡喷发动机,开展了小型涡轮冲压组合发动机性能计算与匹配性分析。给出了涡轮冲压组合发动机详细的性能计算流程、设计点参数确定准则和涡轮冲压组合发动机模态转换过程参数计算方法。根据涡喷发动机压气机进口、涡轮出口的总静压参数沿飞行轨迹的变化规律,确定了涡轮模态向冲压模态转换的合理区间。根据冲压发动机燃烧室进口参数和静压平衡等约束条件,确定了小型涡轮冲压组合发动机关键截面几何参数。分析了不同的流量调节阀开度对模态转换过程参数变化规律的影响。按照模态转换过程保持流量连续的准则,确定了模态转换过程流量调节阀开度随马赫数的变化规律。最后给出了沿飞行轨迹的涡轮冲压组合发动机推力、比冲和喷管喉道面积的变化。
Aim.In our opinion,when we use TRE for long-distance and hypersonic flight,the effect of closing off the turbojet engine for protecting it from the high Mach airflow and the matching of the performance of a turbojet engine with that of a ramjet engine around the mode transition range are important areas of interest that need to be but have not yet been evaluated.Section 1 of the full paper explains our method of evaluation.The core of subsection 1.1 is that it presents the flow chart for computing the performance parameters and thermodynamic parameters of a certain type of small TRE and gives the criteria of determining the design parameters of the TRE.The core of subsection 1.2 is that it optimizes the reasonable mode transition range according to the computed performance parameters and thermodynamic parameters along the flight trajectory and design limits such as the Mach number at the entrance of a ramjet burner which should be less than 0.3.The core of subsection 1.3 is that it analyzes the effect of the opening area of a mode transition valve on the thermodynamic parameters,especially the relationship between the total pressure of the mixer inlet of TRE and its static pressure.Section 2 presents the calculation results,given in Figs.3 through 6 and 8 through 12,and their analysis for a certain type of small TRE;in particular,the analysis determines the optimal mode transition range of this type of small TRE.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2010年第2期234-239,共6页
Journal of Northwestern Polytechnical University
基金
教育部新世纪优秀人才支持计划(NCET-06-0884)资助
