Design and performance analysis of turbine based combined cycle inlet operation with Mach 0~4
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摘要: 从TBCC推进系统总体性能需求出发，给出了TBCC进气道捕获面积以及模态转换马赫数确定过程。在此基础上开展基于平动式模态转换装置的马赫数0~4内并联TBCC进气道气动方案设计，给出了进气道单自由度几何调节机构方案及其几何调节规律。通过对涡轮通道典型几何参数的规律化研究，结果表明：方转圆段几何长度、中心点ym值以及面积变化规律对进气道出口总压恢复系数及马赫数影响较小，对进气道出口流场的均匀度影响较大；就研究的进气道而言，选取方转圆段几何长度为3m，中心控制点ym=1.5，沿程截面面积变化规律为"先急后缓"的设计较为适宜；Ma=4.0时，设计的TBCC变几何进气道总压恢复系数为0.45，Ma=2.2时，总压恢复系数和畸变分别为0.79和0.15。
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关键词:
- 涡轮基组合循环推进系统 /
- TBCC进气道 /
- 变几何机构 /
- 平动式模态转换 /
- 方转圆扩压段
Abstract: The turbine based combined cycle (TBCC) inlet was designed based on the thrust and mass-flow requirement of the TBCC propulsion system. The design points parameters of TBCC inlet, namely the captured area and the mode transition Mach number from turbine mode to ramjet mode were investigated through one-dimensional analysis of turbine engine and ramjet engine in this paper. Then the TBCC inlet scheme which can operate from Ma 0 to 4 was designed and its mode transition device was designed based on the translation scheme. The variable scheme of the TBCC inlet can be achieved through the single degree of freedom mechanism and the profile of the inlet operating at different Mach numbers was given. After the investigation of the length, control point values and the area diffusing rules of rectangular-to-circular shape diffuser of turbine flowpath, the numerical simulation results indicate that the diffuser length, control point values and the area diffusing rules have mild effects on the total pressure recovery and Mach number at the exit of the turbine flowpath, but control point values have significant effects on the distortion index. According to the results above, the diffuser length is chosen to be 3m, the value of the control point to be 1.5 and the area changing rule along the diffuser is chosen as a rapid turning at the entrance. The total pressure recovery of the TBCC inlet is 0.45 at Ma4.0 and 0.79 at Ma2.2, the distortion index is 0.15 at Ma2.2. -
图 2 冲压模态下的需求推力及飞行器重量
Figure 2. The required thrust and the weight of aircraft at ramjet mode
图 3 冲压模态不同化学恰当比下的捕获面积及流量
Figure 3. The captured area and massflow at different stoichiometric ratio of ramjet mode
图 4 发动机需求流量与进气道捕获流量对比
Figure 4. The comparison between massflow required by engine and captured by inlet
图 6 沿飞行轨迹涡喷/冲压发动机推力及耗油率变化规律
Figure 6. The thrust and SFC of TBCC propulsion system along the flying trajectory
图 7 Ma0~4 TBCC变几何进气道型面及控制规律
Figure 7. The scheme of Ma0~4 TBCC variable geometry inlet
图 8 Ma0~4 TBCC变几何进气道机构简图
Figure 8. The framework of Ma0~4 TBCC variable geometry inlet
图 10 涡轮流道进气道出口性能随扩压段长度的变化曲线
Figure 10. The performance of inlet at different length of turbine diffuser
图 11 不同ym值下，涡轮发动机流道方转圆扩压段几何造型
Figure 11. The profile of turbine diffuser at different ym values
图 12 不同ym下，涡轮流道方转圆扩压段出口总压恢复系数等值图
Figure 12. The total pressure contour of turbine diffuser exit section at different ym values
图 13 涡轮通道出口性能随方转圆扩压段中心点ym的变化曲线
Figure 13. The performance of turbine diffuser at different ymvalues
图 14 Ma1.5~4.0 TBCC进气道马赫数云图
Figure 14. The Mach number contour of TBCC inlet from Ma1.5 to 4.0
表 1 不同方转圆沿程截面面积变化规律下涡轮流道进气道出口气动性能
Table 1. The parameters of ramjet engine at design point
Area Mae σ DC60 Δσ/% Rapid turning at the exit 0.4043 0.7868 0.1444 1.4115 Modest turning 0.4020 0.7861 0.1584 1.5452 Rapid turning at the entrance 0.4002 0.7855 0.1331 1.2929 
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