超跨音涡轮复杂激波现象机理与弱化激波方法研究

Shock waves affect aerodynamic loss, structure response and heat transfer of supersonic/transonic turbines, and are becoming a bottleneck factor when try to maximize the power output of turbines. However, in open literature the studies on shock wave structure, its effects, mechanisms and measures to reduce it are insufficient or even blank. This project will focus on turbine cascade shock wave structure and loss, shock wave/blades unsteady interactions, shock wave impacts on blade surface heat transfer and shock strength weakening methods. After calibration of CFD tools using experiment data of supersonic/transonic turbine cascades or turbine stages, theoretical analysis and numerical simulation will be conducted to correlate the design parameters of turbine cascade or blades with shock structures and their characteristics of loss, blade force fluctuation and heat transfer. Then, after modeling the multi-throat turbine flow, its aerodynamic effects and stability will be studied. Based on this, investigations will focus on mechanism of shock wave evolution, losses, force fluctuation and heat transfer characteristics in unsteady flow environment, and the experience rules associated with the key geometric parameters will be refined. Suppression measures to negative effects of shock waves on aerodynamic loss and structure response, i.e. reduced shock wave methods, will be provided. To validate the methods, reduced shock wave cascades will be designed and tested. And a highly loaded supersonic/transonic turbine stage will also be designed and studied numerically. This work will found sound design rules, mechanism understanding and methodology basis for developing high performance turbine component of aero engines (with aims of trust/weight ratio of 12-15 ) and industry gas turbines.

激波问题影响涡轮气动损失、结构响应和传热，是掣肘涡轮负荷最大化的瓶颈因素，现有文献对相关机理和弱化措施研究还不充分甚至空白。项目将针对涡轮叶栅内激波结构与损失、激波/叶排非定常相互作用、激波对换热影响、弱化激波方法等关键方面，在数值工具详细校核基础上，以现存涡轮叶栅、涡轮级试验数据为基础，采用理论分析、数值模拟方法，提炼涡轮几何、气动参数与激波特征、损失特性、脉动力特性、换热特性的经验关系，研究多喉道流动气动稳定性，非定常环境下激波结构形态演化、损失、激振、流热耦合的机理，并提炼与关键几何参数相关的经验规律，提出激波导致气动、结构响应负面效应的抑制措施，系统开发弱化激波方法，完成验证叶栅设计与试验验证，开展弱化激波涡轮级方案设计，最终为推比12-15航空发动机高负荷涡轮研制提供激波影响规律、机理认识和弱化激波设计方法与工具基础，推动我国航空发动机和地面燃气轮机技术发展。

随着航空燃气轮机技术水平的发展和性能需求的提高，其涡轮部件已从早期转静叶全亚音变为现今存在一排超/跨音叶排，甚至出现了单级涡轮转静叶全超跨音的情况，其中激波影响已经愈来愈难以忽略，是掣肘涡轮负荷最大化的瓶颈因素，现有文献对相关机理和弱化措施研究还不充分甚至空白。项目针对涡轮叶栅内激波结构与损失、激波/叶排非定常相互作用、弱化激波方法等关键方面，在数值工具详细校核基础上，以现存涡轮叶栅、涡轮级试验数据为基础，采用理论分析、数值模拟方法，建立了涡轮叶栅内激波结构模型，提炼涡轮几何、气动参数与激波特征、损失特性、脉动力特性经验关系，研究多喉道流动气动稳定性，非定常环境下激波结构形态演化、损失机理，并提炼与关键几何参数相关的经验规律，提出激波导致气动、结构响应负面效应的抑制措施，系统开发弱化激波方法，完成验证叶栅设计与试验验证，开展弱化激波涡轮级方案设计，最终为推比12-15航空发动机高负荷涡轮研制提供激波影响规律、机理认识和弱化激波设计方法与工具基础，推动我国航空发动机和地面燃气轮机技术发展。同时改进实现伴随方法的全局寻优能力，实现了大量应用。. 项目执行期间共发表论文27篇，其中SCI期刊文章2篇(1篇刊登，1篇在审)，EI文章12篇，会议论文14篇。参加国际学术会议2次，国内学术会议3次。申请专利2项。. 本项目圆满实现了预期目标，所开发超跨音涡轮弱化激波方法及程序已获中航集团606、624研究所进一步资助，并已成功用于多种预研、型号设计中