Overall performance of different heating configurations of turbojet engines
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摘要:
为了研究不同加热构型涡喷发动机总体性能差异，利用Visual C++（VC）平台，采用部件级建模法，分别建立了两种加热构型涡喷发动机变比热仿真计算模型，并通过仿真对比分析了两种涡喷发动机在不同工作循环参数匹配条件下的性能差异，结果表明：当级间燃烧涡喷发动机有效效率高于加力燃烧涡喷发动机7%时，级间燃烧涡喷发动机所选压气机总增压高于加力燃烧涡喷发动机25.07%，级间燃烧涡喷发动机需选取较高压气机增压比。在节流特性方面，级间燃烧全开状态发动机油耗相较于全开加力状态降低33.33%；在高度与速度特性方面，级间燃烧涡喷发动机性能受飞行工况变化的影响程度低于加力燃烧涡喷发动机与常规循环涡喷发动机。
Abstract:In order to study the overall performance differences of two heating configurations of turbojet engines, the Visual C++ (VC) platform was employed, and a component-level modeling method was utilized. Simulation models for the two heating configurations of the turbojet engines were established, and a comparative analysis was conducted through simulation to evaluate their performance under different operational parameters. The results indicated that when the interstage turbine burner turbojet engine’s effective efficiency exceeded that of the afterburner turbojet engine by 7%, the total pressure ratio of the interstage turbine burner turbojet engine’s selected compressor was higher than that of the afterburner turbojet engine by 25.07%. The interstage turbine burner turbojet engine required a higher compressor pressure ratio to be selected. Regarding throttling characteristics, the fuel consumption of the interstage turbine burner turbojet engine in the fully open state was reduced by 33.33% compared with the fully open afterburner state. In terms of altitude and speed characteristics, the performance of the interstage turbine burner turbojet engine was less affected by changes in flight conditions compared with the afterburner cycle turbojet engine and conventional cycle turbojet engine.
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图 1 级间燃烧涡喷发动机模型站位图
Figure 1. Schematic diagram of interstage turbine burner turbojet engine model label
图 2 加力燃烧涡喷发动机模型站位图
Figure 2. Schematic diagram of afterburner turbojet engine model label
图 3 两种循环参数共同作用下设计点性能的变化情况
Figure 3. Variation of design point performance under the combined influence of two cycle parameters
图 4 加力燃烧涡喷发动机有效效率随循环参数变化情况
Figure 4. Variation of afterburner turbojet engine effective efficiency with cycle parameter changes
图 5 级间燃烧涡喷发动机有效效率随循环参数变化情况
Figure 5. Variation of interstage turbine burner turbojet engine effective efficiency with cycle parameter changes
图 6 加力燃烧与级间燃烧涡喷发动机节流特性对比
Figure 6. Comparison of throttle characteristic between afterburner and interstage turbine burner turbojet engines
图 7 加力燃烧与级间燃烧涡喷发动机效率对比
Figure 7. Comparison of the efficiency of afterburner and interstage turbine burner turbojet engines
图 8 3种不同循环涡喷发动机高度特性对比
Figure 8. Comparison of altitude characteristics for three different cycle turbojet engines
图 9 3种不同循环涡喷发动机有效效率与推进效率随飞行高度的变化对比
Figure 9. Comparison of effective efficiency and propulsive efficiency with changing flight altitude for three different cycle turbojet engines
图 10 3种不同循环涡喷发动机总效率随飞行高度的变化对比
Figure 10. Comparison of overall efficiency with changing flight altitude of three different cycle turbojet engines
图 11 3种不同循环涡喷发动机速度特性对比
Figure 11. Comparison of velocity characteristics of three different cycle turbojet engines
图 12 3种不同循环涡喷发动机有效效率与推进效率随飞行马赫数的变化对比
Figure 12. Comparison of effective efficiency and propulsive efficiency with changing flight Mach number of three different cycle turbojet engines
图 13 3种不同循环涡喷发动机总效率随飞行马赫数的变化对比
Figure 13. Comparison of overall efficiency with changing flight Mach number for three different cycle turbojet engines
表 1 模型站位标号
Table 1. Model station label
项目 站位 远前方气流截面 0 进气道入口截面 1 进气道出口截面 2 低压压气机出口截面 24 高压压气机进口截面 25 高压压气机出口截面 3 燃烧室出口截面 4 高压涡轮出口截面 45 级间燃烧室出口截面 47 低压涡轮出口截面 5 加力燃烧室出口截面 7 拉瓦尔尾喷管喉道截面 8 拉瓦尔尾喷管出口截面 9 
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表 2 部分模型计算输入参数
Table 2. Partial model calculation input parameters
项目 数值 发动机进口换算流量/（kg/s） 65.1514 进气道总压恢复系数 0.99 低压压气机增压比 2.05 高压压气机增压比 4.20 燃烧室出口总温/K 1225 高压涡轮等熵效率 0.90 低压涡轮等熵效率 0.92 燃烧室总压恢复系数 0.98 低压压气机等熵效率 0.85 高压压气机等熵效率 0.86 级间燃烧室总压恢复系数 0.98 加力燃烧室总压恢复系数 0.98
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表 3 加力燃烧涡喷发动机仿真程序计算结果验证
Table 3. Validation of simulation program results for afterburner turbojet engine
状态 参数 GasTurb VC程序 相对误差/% 设计点 净推力/（daN） 6908 6916 0.12 耗油率/（kg/（（daN∙h）） 1.7859 1.7903 0.25 非设计点 净推力/（（daN） 6908 6916 0.12 耗油率/（kg/（（daN∙h）） 1.7850 1.7902 0.29
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表 4 两种不同加热构型涡喷发动机设计点性能对比
Table 4. Comparison of the performance at the design point of two turbojet engines with different heating configurations
参数 加力燃烧 级间燃烧 变化率/% 净推力/（daN） 6916 5307 −23.26 燃油消耗率/（kg/（（daN∙h）） 1.790276 1.032980 −42.30
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表 5 两种不同加热构型涡喷发动机热效率对比
Table 5. Comparison of thermal efficiency of two turbojet engines with different heating configurations
参数 加力燃烧 级间燃烧 热效率增加量 热效率/% 22.65 31.89 9.24
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表 6 两种加热构型涡喷发动机调节循环参数后性能对比
Table 6. Comparison of performance after adjusting cycle parameters in two different heating configurations turbojet engines
项目 压气机
增压比净推力/
daN耗油率/
（kg/（（daN∙h））有效
效率/%加力燃烧 34.34 8723.71 1.42029 36 级间燃烧 42.95 7700.84 1.09043 43
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