旋转爆轰燃烧室与涡轮导向器集成特性数值研究  

Numerical study on characterization of integrated rotating detonation combustor and turbine guide vane

作　　者：孟博威 马虎[1] 夏镇娟 周长省[1] MENG Bowei;MA Hu;XIA Zhenjuan;ZHOU Changsheng(Key Laboratory of Special Engine Technology,Ministry of Education,School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学机械工程学院特种动力技术教育部重点实验室,南京210094

出　　处：《航空学报》2024年第10期124-144,共21页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(12072163,52106161);先进航空动力创新工作站项目(HKCX2020-02-007-002);国防科技重点实验室基金(2023LB013003)。

摘　　要：为了研究叶栅稠度对旋转爆轰燃烧室-涡轮导向器流场分布和工作特性的影响,以便进一步优化旋转爆轰燃烧室与涡轮导向器的相关设计,基于SST k-ω黏性湍流模型求解二维非定常雷诺平均Navier-Stokes控制方程,并结合间歇因子转捩模型,爆轰燃烧机理采用正癸烷-空气单步反应,通过在初始流场施加高温高压区诱发爆轰波,分别对具有6种不同叶栅稠度导向器和不具备导向器的旋转爆轰燃烧室开展数值计算,对瞬态流场演变和波系结构进行了讨论分析,评估了不同叶栅稠度下导向器的工作特性。研究结果表明:导向器上下游均形成了动态的耙式激波包络面,其结构和强度受叶栅稠度影响,爆轰流场特性保证了叶栅通道自起动能力。导向器抑制了上游压力峰值,峰值衰减率最高可达60.87%。爆轰燃烧的总压增益得到提高,导向器出口增压比最高为1.24,出口增压比频率与叶栅稠度大小呈正相关,最高可达143.33 kHz。叶栅通道对爆轰产物具有一定流动调节能力,时均落后角最小为1.84°,出口时均马赫数最高为1.38,此外出口气流角均匀性显著提高。研究结果揭示了导向器对提高连续旋转爆轰涡轮发动机性能的潜在价值,对该种发动机的设计优化以及工程化应用提供了一定指导。This study investigates the influence of cascade solidity on the flow field distribution and working characteristics of the rotating detonation combustor-turbine guide vane to further optimize the design of the rotating detonation combustor and turbine guide vane.Based on the SST k-ωviscous turbulence model,the two-dimensional unsteady Reynolds-averaged Navier-Stokes control equation is solved.Combined with the intermittent factor transition model,the detonation combustion mechanism adopts the n-decane-air single-step reaction.By applying the high temperature and high pressure zone to the initial flow field to induce the detonation wave,we conduct numerical calculation for the rotating detonation combustor with six different cascade solidity turbine guide vanes and without the turbine guide vane,respectively.The instantaneous flow field evolution and wave structure are discussed and analyzed,and the working characteristics of the turbine guide vane under different cascade solidity are evaluated.The results show that the dynamic rake-type shock envelope is formed in both upstream and downstream of the turbine guide vane,with its structure and strength affected by the cascade solidity.The detonation flow field characteristics ensure the self start ability of the cascade channel.The turbine guide vane suppresses the upstream pressure peak,and the peak attenuation rate is up to 60.87%.The total pressure gain of detonation combustion is improved;the maximum total pressure ratio at the outlet of the guide vane is 1.24,and the frequency of the outlet total pressure ratio is positively correlated with the cascade solidity,up to 143.33 kHz.The cascade passage has a certain ability to adjust the flow of detonation products.The minimum time-average deviation angle is 1.84°,the maximum time-average Mach number at the outlet is 1.38,and the uniformity of the outlet flow angle is significantly improved.The research results reveal the potential value of the turbine guide vane to the performance improvement of the continuous r

关 键 词：旋转爆轰燃烧室 涡轮导向器 叶栅稠度 流场结构 工作特性 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]