高通流大负荷微型向心涡轮设计及试验技术研究
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摘要
微型涡轮发动机具有高能量密度和高推重比优势，是满足先进低成本微小型空中武器系统推进动力需求的先进动力装置。微型向心涡轮作为其主要核心部件，高通流能力与高单级负荷是其未来发展的方向，开展高通流大负荷微型向心涡轮设计技术研究，对提高涡轮级性能乃至微型发动机整机性能均具有重要意义。本文采用数值模拟与试验相结合的手段针对高通流大负荷微型向心涡轮设计技术展开研究，主要有以下几方面工作：
1、开展了厘米级微型向心涡轮与轴流涡轮综合性能对比研究，基于MTE-D微型发动机对比了单级微型轴流涡轮和向心涡轮在大流量、高功率状态下的气动性能及尺寸差异，针对当前微发部件设计水平，总结了微型发动机涡轮选型的规律，可作为厘米级微型发动机涡轮选型依据。
2、初步构建了高通流、大负荷微型向心涡轮转子叶轮的设计框架，针对叶轮直径30~100mm量级的微型向心涡轮转子，研究了叶片角分布、轮径比、进口斜流角、叶轮轴向宽度等设计参数对叶轮流场性能的影响，初步总结了各参数的设计原则和选取规律，同时完成了MTE-D微发原理样机向心涡轮转子的方案设计，数值模拟结果表明该叶轮设计点性能为：落压比2.25，流量0.42kg/s，效率0.82。
3、基于MTE-D微发原理样机研究并完善了整体叶片式导向器设计技术，针对叶片角分布规律、子午流道形状及叶片数等关键设计因素对导向器性能的影响进行了研究，确定了较佳的叶片角分布规律，明确了子午流道形状的设计原则，针对MTE-D原理样机整机环境优选出最佳的相对轴向宽度和叶片数，同时完成了MTE-D原理样机整体叶片式导向器的方案设计，数值模拟结果表明该导向器设计点流量0.4kg/s，总压恢复系数0.97。
4、完成了国内首座厘米级微型压气机/涡轮联合试验台的搭建，该试验台具备厘米级离心压气机全转速部件测试以及厘米级向心涡轮长周期热态性能测试功能。本试验台采用共轴分流路结构，具有独立的压气机气路和涡轮气路，可分别调节压气机和涡轮工况，便捷地实现两者在不同转速、流量工况下的功率匹配，满足测试叶轮等转速特性测试的需求。为了精确测量叶轮效率，为该试验台设计了测量精度可达1%的光电式扭矩传感器。
5、采用自建的微型压气机/涡轮联合试验台，针对本文所设计的MTE-D原理样机直径78mm微型向心涡轮开展了冷、热态部件性能测试研究，获得了该叶轮的部分叶轮特性，试验结果验证了数值模拟的准确性。同时将本文所设计的向心涡轮及整体叶片式导向器应用到MTE-D微发原理样机中，针对该样机开展了地面台架试车，成功运转至设计转速，推力超过120N，进一步验证了本文研究所获得的微型向心涡轮技术的成效。
Micro turbine engine can be used as propulsion system of low-cost micro aerial weaponsplatform because of its high power density and high thrust-weight ratio. Micro radial inflow turbine isthe core component of micro turbine engine. The high flow capacity and high single-stage load is thefuture developmental direction. The design technique research on micro radial inflow turbine withhigh flow capacity and single-stage load is important to improve the turbine performance and microengine performance. This paper studied the design techniques of micro turbine engine by numericalsimulation and experimental means, including the following aspects:
1. The comprehensive performance comparison between micro radial turbine and axial turbinewas carried out. Based on the MTE-D micro turbine engine environment, the aerodynamicperformance and size differences of single-stage micro axial turbine and radial turbine was comparied,under the high flow rate and high power state. Based on the current design technique level of microengine components, the micro turbine type selection rule was summaried, which could be used toguide the turbine type selection for centimeter-level micro turbine engine.
2. The design framework of micro radial inflow turbine rotor with high flow and high load wasbuilt. For the radial turbine rotor with the dimameter of30~100mm, the influences of leaf angledistribution, wheel diameter ratio, import flow angle, and impeller axial width on turbine performancewere studied. The preliminary design principles and selection laws of these design parameters weresummaried. The micro radial turbine rotor of MTE-D micro engine was designed. At the design point,the turbine drop pressure ratio was2.25, the flow rate was0.42kg/s, and the efficiency was0.82.
3. Based on the MTE-D micro engine, the design techniques of micro vane nozzle wasresearched and improved. The influences of leaf angle distribution, meridional channel shape, bladenumber and other key design factors on nozzle performance were studied. The research determined abetter leaf angle distribution, defined the design principles of the meridional channel shape, andchoiced the best relative axial width and blade number. The design of micro vane nozzle for MTE-Dmicro engine was completed. Its flow rate was0.4kg/s, and the total pressure recovery coefficient was0.97.
4. A new test facility for centimeter-level micro compressor and turbine was built. The test rigcould be used for full speed test of centrifugal compressor and long duration thermal test of radialinflow turbine. The facility had separate compressor path and turbine path. The power match at different speed and flow conditions could be achieved easily by adjusting compressor and turbineoperating condition individually to meet the need of impeller characteristics. In order to accuratelymeasure the impeller efficiency, the optical torque sensor with measurement accuracy of1%wasdesigned.
5. By this self-built test rig for micro compressor and turbine, the cold and thermal tests of amicro radial turbine rotor designed in this paper with a diameter of78mm were completed, and partimpeller characteristics of this turbine were obtained. The test results verified the accuracy of thenumerical simulation. The micro radial turbine rotor and micro vane nozzle designed in this paperwere used in MTE-D micro turbine engine, and the engine ground test was completed. The engineachieved the design speed, and the thrust was more than120N. The ground test results furtherverificated the design technology for micro radial inflow turbine obtained by this paper.
1、开展了厘米级微型向心涡轮与轴流涡轮综合性能对比研究，基于MTE-D微型发动机对比了单级微型轴流涡轮和向心涡轮在大流量、高功率状态下的气动性能及尺寸差异，针对当前微发部件设计水平，总结了微型发动机涡轮选型的规律，可作为厘米级微型发动机涡轮选型依据。
2、初步构建了高通流、大负荷微型向心涡轮转子叶轮的设计框架，针对叶轮直径30~100mm量级的微型向心涡轮转子，研究了叶片角分布、轮径比、进口斜流角、叶轮轴向宽度等设计参数对叶轮流场性能的影响，初步总结了各参数的设计原则和选取规律，同时完成了MTE-D微发原理样机向心涡轮转子的方案设计，数值模拟结果表明该叶轮设计点性能为：落压比2.25，流量0.42kg/s，效率0.82。
3、基于MTE-D微发原理样机研究并完善了整体叶片式导向器设计技术，针对叶片角分布规律、子午流道形状及叶片数等关键设计因素对导向器性能的影响进行了研究，确定了较佳的叶片角分布规律，明确了子午流道形状的设计原则，针对MTE-D原理样机整机环境优选出最佳的相对轴向宽度和叶片数，同时完成了MTE-D原理样机整体叶片式导向器的方案设计，数值模拟结果表明该导向器设计点流量0.4kg/s，总压恢复系数0.97。
4、完成了国内首座厘米级微型压气机/涡轮联合试验台的搭建，该试验台具备厘米级离心压气机全转速部件测试以及厘米级向心涡轮长周期热态性能测试功能。本试验台采用共轴分流路结构，具有独立的压气机气路和涡轮气路，可分别调节压气机和涡轮工况，便捷地实现两者在不同转速、流量工况下的功率匹配，满足测试叶轮等转速特性测试的需求。为了精确测量叶轮效率，为该试验台设计了测量精度可达1%的光电式扭矩传感器。
5、采用自建的微型压气机/涡轮联合试验台，针对本文所设计的MTE-D原理样机直径78mm微型向心涡轮开展了冷、热态部件性能测试研究，获得了该叶轮的部分叶轮特性，试验结果验证了数值模拟的准确性。同时将本文所设计的向心涡轮及整体叶片式导向器应用到MTE-D微发原理样机中，针对该样机开展了地面台架试车，成功运转至设计转速，推力超过120N，进一步验证了本文研究所获得的微型向心涡轮技术的成效。
Micro turbine engine can be used as propulsion system of low-cost micro aerial weaponsplatform because of its high power density and high thrust-weight ratio. Micro radial inflow turbine isthe core component of micro turbine engine. The high flow capacity and high single-stage load is thefuture developmental direction. The design technique research on micro radial inflow turbine withhigh flow capacity and single-stage load is important to improve the turbine performance and microengine performance. This paper studied the design techniques of micro turbine engine by numericalsimulation and experimental means, including the following aspects:
1. The comprehensive performance comparison between micro radial turbine and axial turbinewas carried out. Based on the MTE-D micro turbine engine environment, the aerodynamicperformance and size differences of single-stage micro axial turbine and radial turbine was comparied,under the high flow rate and high power state. Based on the current design technique level of microengine components, the micro turbine type selection rule was summaried, which could be used toguide the turbine type selection for centimeter-level micro turbine engine.
2. The design framework of micro radial inflow turbine rotor with high flow and high load wasbuilt. For the radial turbine rotor with the dimameter of30~100mm, the influences of leaf angledistribution, wheel diameter ratio, import flow angle, and impeller axial width on turbine performancewere studied. The preliminary design principles and selection laws of these design parameters weresummaried. The micro radial turbine rotor of MTE-D micro engine was designed. At the design point,the turbine drop pressure ratio was2.25, the flow rate was0.42kg/s, and the efficiency was0.82.
3. Based on the MTE-D micro engine, the design techniques of micro vane nozzle wasresearched and improved. The influences of leaf angle distribution, meridional channel shape, bladenumber and other key design factors on nozzle performance were studied. The research determined abetter leaf angle distribution, defined the design principles of the meridional channel shape, andchoiced the best relative axial width and blade number. The design of micro vane nozzle for MTE-Dmicro engine was completed. Its flow rate was0.4kg/s, and the total pressure recovery coefficient was0.97.
4. A new test facility for centimeter-level micro compressor and turbine was built. The test rigcould be used for full speed test of centrifugal compressor and long duration thermal test of radialinflow turbine. The facility had separate compressor path and turbine path. The power match at different speed and flow conditions could be achieved easily by adjusting compressor and turbineoperating condition individually to meet the need of impeller characteristics. In order to accuratelymeasure the impeller efficiency, the optical torque sensor with measurement accuracy of1%wasdesigned.
5. By this self-built test rig for micro compressor and turbine, the cold and thermal tests of amicro radial turbine rotor designed in this paper with a diameter of78mm were completed, and partimpeller characteristics of this turbine were obtained. The test results verified the accuracy of thenumerical simulation. The micro radial turbine rotor and micro vane nozzle designed in this paperwere used in MTE-D micro turbine engine, and the engine ground test was completed. The engineachieved the design speed, and the thrust was more than120N. The ground test results furtherverificated the design technology for micro radial inflow turbine obtained by this paper.
引文
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