与涡扇发动机和涡喷发动机相比，涡轴发动机具有体积小、质量轻、轴系短等显著特点，且由于其良好的高空性能和较宽的功率范围，活塞发动机在无人直升机的应用中逐渐被涡轴发动机取代。但由于成本问题，在小型无人直升机上航空活塞发动机仍占有绝对优势，因此对小功率涡轴发动机的研究十分有必要。该文基于Gas Turb对300 kW级的涡轴发动机进行总体设计与性能计算，Gas Turb是一款能够快速分析燃气轮机性能的软件，可以用于燃气轮机的热力学设计和总体性能计算，此外，利用ANSYS的叶片造型模块对离心压气机的叶轮和叶片进行造型设计，进一步完成了离心压气机的三维数值模拟，验证了所设计的离心压气机模型的可行性。
Turboshaft engines are smaller, lighter and have shorter shafts than large turbofan and turbojet engines. Due to their good high altitude performance and wide power range, turboshaft engines have gradually replaced piston engines in unmanned helicopters. However, piston engines are less expensive, so they still have the absolute advantage in small unmanned helicopters. Further research is needed to develop economical low power turboshaft engines. This study analyzed the design of a 300 kW turboshaft engine using Gas Turb, a thermodynamic turbine analysis software, with the blade modeling module of ANSYS used to design the impeller and blades of the centrifugal compressor. Three-dimensional simulations of the centrifugal compressor verify the feasibility of this design.
[1] 《航空发动机设计手册》总编委员会. 航空发动机设计手册第6册:涡桨及涡轴发动机总体[M]. 北京:航空工业出版社, 2001.Editorial board of aeroengine design manual. Aeroengine design manual volume 6:Turboprop and turboshaft engine[M]. Beijing:Aviation Industry Press, 2001. (in Chinese)
[2] 柳子昂. 高压比离心压气机叶型优化与数值研究[D]. 南京:南京航空航天大学, 2013.LIU Z A. The profile optimization and numerical simulation of high pressure ratio centrifugal compressor[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2013. (in Chinese)
[3] 《航空发动机设计手册》总编委员会. 航空发动机设计手册第8册:压气机[M]. 北京:航空工业出版社, 2000.Editorial board of aeroengine design manual. Aeroengine design manual volume 8:Compressor[M]. Beijing:Aviation Industry Press, 2001. (in Chinese)
[4] BONAIUTI D, AMONE A, ERMINI M, et al. Analysis and optimization of transonic centrifugal compressor impellers using the design of experiments technique[J]. Journal of Turbomachinery, 2006, 128(4):786-797.
[5] MALIK A, ZHENG Q. Effect of double splitter blades position in centrifugal compressor impeller[J]. Proceedings of the Institution of Mechanical Engineers, Part A:Journal of Power and Energy, 2019, 233(6):689-701.
[6] 高井辉. 基于CFX的离心式压气机内部流场数值研究[D].大连:大连理工大学, 2011.GAO J H. Numerical investigation on centrifugal compressor based on CFX[D]. Dalian:Dalian University of Technology, 2011. (in Chinese)
[7] 冀国锋, 殷明霞, 桂幸民. 某小型离心压气机气动设计[J]. 航空动力学报, 2010, 25(3):557-564.JI G F, YIN M X, GUI X M. Aerodynamic design of a small centrifugal compressor[J]. Journal of Aerospace Power, 2010, 25(3):557-564. (in Chinese)
[8] 袁鹏. 涡轴发动机气动性能改进研究及离心叶轮改型设计[D]. 南京:南京航空航天大学, 2007.YUAN P. Research on the performance of a turboshaft engine and its centrifugal compressor impeller design[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2007. (in Chinese)
[9] YANG C, LI Z G, JIANG Z K, et al. Numerical investigation of a high-speed centrifugal compressor impeller[J]. Tsinghua Science and Technology, 1999, 4(4):1678-1682.
[10] 杨策, 马朝臣, 王憔, 等. 离心压气机的初步设计及其优化方法[J]. 内燃机学报, 2001(5):454-458.YANG C, MA C C, WANG Q, et al. Preliminary design and optimization of centrifugal compressor[J]. Transactions of CSICE, 2001(5):454-458. (in Chinese)
[11] LOU F Y, KEY N L. Design considerations for the final-stage centrifugal compressor in aeroengines[J]. Journal of Propulsion and Power, 2020(2):1-5.
[12] CHUNG J, KIM N, LEE S, et al. Performance improvement of the pressure ratio and rotational speed calculation of a centrifugal compressor model[J]. International Journal of Automotive Technology, 2020, 21(3):703-711.
[13] 王琦, 单鹏. 径流及斜流压气机任意曲面叶型长短叶片的造型设计方法[J]. 航空动力学报, 2006(4):747-753.WANG Q, SHAN P. Design of radial flow and mixed flow compressor rotor splitter blades[J]. Journal of Aerospace Power, 2006(4):747-753. (in Chinese)
