轴向超音来流新概念风扇级气动热力布局与设计方法研究

As the development of science and technology are always in a spiral upwards pattern, a fan with axial supersonic inflow is the opportunity and direction for developing fan in frame of gas turbine. This project puts forward a new concept aero-thermo configuration of fan, which has an axial supersonic inflow and supersonic through-flow rotor and a stator with strong shock waves in its passage. The new fan hereafter named SSSF, it is the abbreviation of Axial Supersonic Inflow Shock-in-Stator Fan. The fan, with a supersonic through-flow intake before it, decelerates the supersonic flow in the stator with a strong shock wave, and is different from the traditional ones, in which one shock wave exists in the inlet and the other exists in the first traditional transonic fan rotor. The flow field in such a fan stage becomes more complex and more challenging. Focusing on the aero-thermo configuration of SSSF, this application is going to carry out following several research works. This include aero-thermo configuration layout of SSSF, the three-dimensional design methods and flow mechanism of shock free high turning angle supersonic through-flow rotor, the design, flow mechanism and flow control method of shock-in stator, performance characteristics of SSSF, the methodology for stable operation of SSSF, and prediction and evaluation of SSSF propulsion system performance. Theoretical analysis as well as numerical simulation and experiment of typical supersonic through-flow rotor cascade are going to be conducted to solve three fundamental problems, which include the detail schemes of the aero-thermo configuration of SSSF, the three-dimensional design methods of axial supersonic rotor and stator with strong shock waves, control methods of the flow separation and strong shock waves. The researches will provide theoretical basis, design method and tools, knowledge on flow mechanism of SSSF for SSSF going into reality, and make a great contribution for the development of turbomachinery and Aero engine.

轴向超音来流气动热力布局依然是燃气轮机架构下风扇技术发展的机遇和方向。本项目提出新概念风扇气动热力布局——轴向超音来流超音通流转叶+激波静叶新概念风扇级，简称为SSSF，实际将传统压缩系统中分别存在于传统超音进气道和传统跨音风扇中的两道激波合并置于激波静叶中，使其流动更趋复杂、设计也面临更大挑战。围绕SSSF新概念气动热力布局，本申请将主要开展SSSF气动热力布局方案、无激波大折转超音通流转叶三维设计方法及流动机理、激波静叶设计/流动机理及其流动控制方法、SSSF气动热力布局特性及稳定工作调控措施、SSSF推进系统性能预测与评估研究，采用理论分析、数值模拟结合典型叶栅试验方法，解决SSSF所面临的详细气动热力布局方案、大折转无激波超音通流转叶与激波静叶三维设计方法、激波强度/流动分离控制与运行特性调节等三大关键问题。为SSSF步入应用奠定设计理论、经验、方法与工具基础，研究意义重大。

轴向超音来流气动热力布局是燃气轮机架构下风扇技术发展的机遇和重要方向。本项目开展了轴向超音来流激波静叶（SSSF）的方案设计与分析，论证了SSSF的潜在气动性能优势。同时，尽管美国在上世纪以开展过轴向超音通流风扇级（STFF）气动设计方面系统研究，掌握了相关流动机理、设计方法等。但公布的少量NASA报告和论文中并未给出具体叶片设计方法和准则，对于STFF叶片流动机理和设计方法等方面的研究基本空白，由此，针对STFF，项目开展了从叶片基元（叶型）到三维叶片（掠弯积叠），到转静叶子午流路以及整级几何参数对流动结构和气动性能影响的研究。采用理论分析、数值模拟方法，对典型STFF叶型深入开展了流动机理分析，剖析了其损失源分布特点，给出了稠度等关键叶型参数与攻角的耦合作用规律，初步建立了STFF叶型激波结构模型、损失特性与几何的经验关系。针对复合掠弯积叠，重点开展了STFF转子的优化设计研究，初步建立了基于支持向量机的构建代理模型耦合遗传算法的先进优化方法，明确了掠弯积叠对激波结构的作用机制，可为未来STFF的掠弯积叠设计提供借鉴。另外，我们完成了轴向超音来流下STFF叶栅激波结构和损失特性的试验验证，开展了整级定常、非定常流动机理以及优化设计方法研究。对于轴向来流风扇的系列研究来说，本项目的完成仅处于初步阶段，但这一新概念气动热力布局的未来前景巨大，相关技术一旦突破，可实现涡轮发动机工作上限的不断拓展、推力提高以及发动机重量的大幅降低。.项目主要取得的成果已发表SCI/EI共计15篇，其中11篇SCI检索论文，4篇EI检索论文，国际会议8篇，国内会议14篇，申请发明专利4项。值得说明的是，实际科研成果远超过预期，国际会议为预期计划的数倍，SCI发表数量更为预期研究成果的3倍。. 本项目圆满实现了预期目标，利用开发的针对于轴向超音通流风扇叶片的设计工具设计出高性能叶栅，已与相关工程单位开展了相关试验合作。