Influence of the turbine guide vane adjustment on the film holes outflow in whole engine environment
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摘要:
针对变循环发动机低压涡轮导叶调节导致涡轮叶片气膜孔流量分配显著改变的问题，通过建立压气机级间变引气模块和涡轮变导叶角度冷气掺混模块，实现了考虑涡轮导叶角度调节的主流道气路与空气系统气路之间的数据交互和模块化耦合求解。以带核心风扇的双外涵变循环发动机（CDFS VCE）为对象，研究了整机环境下低压涡轮导叶调节对涡轮叶片气膜孔出流流量的影响规律。研究表明：考虑压气机变引气和涡轮变导叶角度掺混不会显著影响导向器叶片和转子叶片冷却气流量占核心机进口流量的比例，但是造成了导向器和转子叶片冷却气在不同位置气膜孔间分配关系的显著非均衡响应。导叶角度在−3°～4°的调节范围内，导叶吸力面气膜孔冷却气比例降低可达20%，动叶压力面气膜孔冷却气比例降低约6%。
Abstract:To investigate the influence of low-pressure turbine guide vane adjustments on film hole flow distribution in variable cycle engines, a variable inter-stage bleed module for the compressor and a turbine mixing module with adjustable vane angles were developed. These modules enabled modular coupling and data exchange between the main flow and secondary air systems. Using a core-driven fan stage variable cycle engine (CDFS VCE) as the test case, the study analyzed the impact of guide vane adjustments on film hole outflow across the engine. The research indicates that considering the variable inter-stage bleeding for the compressor and mixing with adjustable guide vane angles does not significantly affect the proportion of cooling air from the guide vanes and rotor blades to the core engine inlet flow, but causes a significantly unbalanced response in the distribution of cooling air among film holes at different positions of the guide vanes and rotor blades. Within the adjustment range of the guide vane angle from −3° to 4°, the flow rate ratio of the film holes on the suction side of the guide vane decreases by up to 20%, while the flow rate ratio of the film holes on the pressure side of the rotor blade decreases by approximately 6%.
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图 1 压气机级间引气模块基本架构
Figure 1. Basic architecture for compressor inter-stage bleeding module
图 2 带级间引气的高压压气机特性
Figure 2. Characteristic of high-pressure compressor with inter-stage bleeding
图 3 不同导叶角度下动叶前缘气膜孔相对压比特性
Figure 3. Relative pressure characteristics of leading edge film holes under different turbine guide vane angle
图 4 变导叶调节对涡轮临界截面的影响
Figure 4. Influence of variable guide vane regulation on turbine critical section
图 5 CDFS VCE原理构型及空气系统主要流路示意图
Figure 5. Configuration and main flow path of the secondary air system of the CDFS VCE
图 6 CDFS VCE性能与低压涡轮冷却流路一体化耦合模型
Figure 6. Integrated coupling model of the CDFS VCE performance and low-pressure turbine （LPT） cooling flow path
图 8 导叶角度对涡轮导叶冷却气流量的影响
Figure 8. Influence of guide vane angle on the cooling air flow of the turbine guide vane
图 9 导叶角度对涡轮导叶气膜孔流量分布的影响
Figure 9. Influence of guide vane angle on the flow distribution of the film holes in turbine guide vane
图 10 低压涡轮导叶角度对引气边界的影响
Figure 10. Influence of LPT guide vane angle on the bleeding boundary
图 11 低压涡轮导叶角度对低压涡轮进口总压的影响
Figure 11. Influence of guide vane angle on the inlet total pressure of LPT
图 12 导叶角度调节过程低压涡轮导叶气膜孔相对压比的变化规律
Figure 12. Variation of relative pressure ratio of the film hole in LPT guide vane during the guide vane angle adjustment
图 13 导叶角度对涡轮动叶冷却气流量的影响
Figure 13. Influence of guide vane angle on the cooling air flow of the turbine rotor blade
图 14 导叶角度对涡轮动叶气膜孔流量分布的影响
Figure 14. Influence of guide vane angle on the flow distribution of the film holes in turbine rotor blade
图 15 导叶角度调节过程低压涡轮动叶气膜孔相对压比的变化规律
Figure 15. Variation of relative pressure ratio of the film hole in LPT rotor blade during the guide vane angle adjustment
表 1 CDFS VCE设计状态主要循环参数
Table 1. Primary cycle parameters of the CDFS VCE in the design condition
循环参数 数值 风扇压比 4.5 核心风扇压比 1.35 高压压气机压比 4 第一外涵涵道比 0.2 第二外涵涵道比 0.15 涡轮前温度/K 1 849 
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表 2 涡轮导叶调节过程导叶气膜孔落压比相对变化
Table 2. Relative variation in pressure ratio of the guide vane film holes during the turbine guide vane adjustment
调节范围/（°） 气膜孔位置/% 前缘 压力面 吸力面 尾缘 −3～0 7.4 8.3 11.4 16.2 0～4 2.4 13.6 −31.2 −17.5
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表 3 涡轮导叶调节过程动叶气膜孔落压比相对变化
Table 3. Relative variation in pressure ratio of the rotor balde film holes during the turbine guide vane adjustment
调节范围/（°） 气膜孔位置/% 前缘 压力面 吸力面 尾缘 −3～0 −10.3 −28.5 4.1 0.6 0～4 0.6 −31.5 −3.8 −7.9
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