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航空动力学报 2017年第5期32卷 1183-1194页

作者： Yang Ling ZHONG jing-jun han ji-ang Marine Engineering College Dalian Maritime University

The design methods of typical supersonic aircraft intakes and shock wave compression technology have been applied to ram-rotor,an attractive compression system.A ram-rotor is of a typical structure including the compression ramp,the throat and the subsonic diffuser;a scrampressor is similar to ram-rotor,the only difference is that scrampressor has no subsonic *** work was the continuation of the preparatory *** order to further study the effect of throat contraction ratio and strake stagger angle on the flow field and performance of a scrampressor,the flow field of a scrampressor with a three-dimensional flow path was numerically simulated with different throat contraction ratios and strake stagger *** results indicated that the optional aerodynamic performance of a scrampressor could be achieved with an adiabatic efficiency of 0.8413atotal pressure recovery coefficient of 0.8446,a total pressure ratio of 7.14 and a static pressure ratio of 5.17for a throat contraction ratio of 0.6 and a strake stagger angle of 12°.It was therefore concluded that an appropriate decrease in throat contraction ratio and an increase in strake stagger angle could help the comprehensive improvement of a scrampressor in performance.

关键词： scrampressor flow field aerodynamic performance throat contraction ratio strake stagger angle

Effect of Meridional Characteristic angle on Aerodynamic Performance of Ram-Rotor

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Journal of Thermal Science 2020年第3期29卷 753-762页

作者： han ji'ang GUAN jian ZHONG jingjun CHEN Luting Naval Architecture and Ocean Engineering College Dalian Maritime UniversityDalian 116026China Merchant Marine College Shanghai Maritime UniversityShanghai 201306China

A kind of meridional concept which has a shape of contraction-expansion(Con-Exp)was applied to the ram-rotor in the paper,and detailed numerical simulation to understand the impact of meridional shape and geometric characteristic angle on the aerodynamic behavior of ram-rotors has been *** to baseline,there was a positive effect in intensifying shock train and suppressing low momentum fluid in Con-Exp scheme,and the pressure ratio and efficiency of Con-Exp scheme increased by 2.075%and 3.160%,*** the contracting angle was increasing,supersonic flow at and after throat region accelerated remarkably,and the static pressure rise was decreased *** terminating shock train was transformed to terminating shock,and the efficiency of ram-rotor was unfavorable to improve due to low throttle *** expanding angle rose,the terminating shock moved forward and turned to shock train *** pressure rise capacity and throttling ability of ram-rotor were *** low momentum fluid was accumulated near the middle and upper flow-path,yielding greater flow loss at large expanding angle.

关键词： ram-rotor meridional shape contracting angle expanding angle numerical simulation

Numerical simulation of the three-dimensional flow-path in a ram-rotor

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航空动力学报 2010年第6期25卷 1358-1365页

作者： han ji-ang ZHONG jing-jun YAN Hong-ming Marine Engineering College Dalian Maritime UniversityDalian 116026China School of Energy Science and Engineering Harbin institute of TechnologyHarbin 150001China

A kind of three-dimensional flow-path of the ram-rotor was designed in this paper according to the design method of the typical supersonic intake of aircraft and missiles,especially the design method of the compression ramp,the throat and the subsonic *** design Mach number of the flow-path was based on the averaged relative Mach number,regardless of the change of incoming Mach number along radial direction of the ***,the flowfield of the designed flow-path was simulated numerically with computational fluid dynamics software at design *** purpose of simulation was to obtain the details of the flowfield,including the structure of the shock wave system,position of flow separation zone,and so *** performance of the ram-rotor was also *** numerical results show the structure of the shock wave system in the flow-path is similar to that in the supersonic *** improve the overall performance of the ram-rotor,the reasonable compromise between the total pressure ratio and the isentropic adiabatic efficiency should be *** structure optimization of the flow-path and the configuration of the shock wave system have great influence on the performance of the ram-rotor.

关键词： ram-rotor flow-path supersonic intake numerical simulation design point

Effect of Vane Opening on Aerodynamic Performance of the Ram-rotor Test System

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Journal of Thermal Science 2016年第3期25卷 207-215页

作者： han ji-ang GUAN jian ZHONG jingjun YUAN Chenguang Marine Engineering College Dalian Maritime University

In order to research the influence of adjustable vane on the aerodynamic performance of the ram-rotor test system, FLUENT soft-ware has been adopted to simulate the flow passage of the ram-rotor test system numerically. The vane opening is controlled by changing the stagger angle of the vane blades. Results show that flow uniformity of vane outlet is influenced by the vane openings, which has an impact on the aerodynamic loss to some extent. Total pressure ratio, adiabatic efficiency and mass flow rate can be regulated by different openings of the vane. Compared with -8° vane opening, top efficiency of the ram-rotor increases by about 13.8% at ＋6° opening. And total pressure ratio drops by 5.87%. The rising opening increases the relative Mach number at inlet of the ram-rotor and weakens the intensity of the tip clearance leakage, which comes to a decreasing aerodynamic loss.

关键词： adjustable vane ram-rotor test system aerodynamic performance numerical simulation

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隔板型式对旋转冲压压缩转子性能的影响

推进技术 2017年第3期38卷 710-720页

作者：韩吉昂孙云钟兢军管健大连海事大学轮机工程学院辽宁大连116026

为了改善旋转冲压压缩转子的总体性能,通过改变隔板前、后段的型式获得不同的隔板改型方案,并利用FLUENT流体计算软件对采用不同隔板改型方案的旋转冲压压缩转子进行了数值研究。结果表明,改变隔板前段型式可以改变隔板前缘激波和进气流... 详细信息

为了改善旋转冲压压缩转子的总体性能,通过改变隔板前、后段的型式获得不同的隔板改型方案,并利用FLUENT流体计算软件对采用不同隔板改型方案的旋转冲压压缩转子进行了数值研究。结果表明,改变隔板前段型式可以改变隔板前缘激波和进气流量,进而影响旋转冲压压缩转子的总体性能;改变隔板后段型式,可以改变旋转冲压压缩转子的流场结构,并影响其增压能力;融合隔板前、后段最佳型式的隔板组合改型方案对旋转冲压压缩转子性能的提升最大,其总压比和效率相较于原型分别提升了12.0%和7.1%。

关键词：隔板型式旋转冲压压缩转子性能流场结构数值研究

高负荷局部进气涡轮内部流场不均匀性数值研究

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工程热物理学报 2016年第12期37卷 2549-2556页

作者：陈帝云钟兢军韩吉昂大连海事大学轮机工程学院大连116026

以高负荷局部进气涡轮为研究对象,对其进行了数值研究,并着重对该局部进气涡轮内部流场不均匀性进行了分析。结果表明:局部进气涡轮内部流场的流动情况十分复杂,局部进气堵塞段的存在,使其后面对应的动叶栅进出口速度矢量偏向周向,导致... 详细信息

以高负荷局部进气涡轮为研究对象,对其进行了数值研究,并着重对该局部进气涡轮内部流场不均匀性进行了分析。结果表明:局部进气涡轮内部流场的流动情况十分复杂,局部进气堵塞段的存在,使其后面对应的动叶栅进出口速度矢量偏向周向,导致该区域叶片流道内形成了大尺度的旋涡结构,降低了流道的通流能力,增大了该区域的损失水平;各级动叶进出口静压沿周向分布极不均匀,从第一级动叶入口至第二级动叶出口,静压周向不均匀性参数分别为:1.5593、1.0179、0.9163和0.1551,不均匀性沿轴向逐渐衰减;处于不同周向位置的叶片表面压力分布差异明显,直接影响了动叶的做功能力。

关键词：高负荷局部进气涡轮流场不均匀性数值研究

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单/双向进气再入式涡轮内部流动特性研究

工程热物理学报 2018年第8期39卷 1697-1705页

作者：钟兢军陈帝云韩吉昂大连海事大学轮机工程学院大连116026

利用三维数值计算方法,得到了单/双向进气再入式涡轮总体性能参数,并对其内部流动进行了详细研究。通过对数值模拟结果的分析表明:单向进气再入式涡轮尺寸较大、结构复杂的再入管道,使得流经其中的燃气总压损失大于双向进气结构型式,且... 详细信息

利用三维数值计算方法,得到了单/双向进气再入式涡轮总体性能参数,并对其内部流动进行了详细研究。通过对数值模拟结果的分析表明:单向进气再入式涡轮尺寸较大、结构复杂的再入管道,使得流经其中的燃气总压损失大于双向进气结构型式,且单向进气再入涡轮第二级动叶进口负冲角更大,造成更高的进气损失,因而其总静效率较双向进气结构型式低2.37%。单向进气再入涡轮动叶排两侧压力沿周向分布不均匀性参数分别为1.0472和1.6530,双向进气结构型式为1.8497和1.1233,双向进气结构型式压力沿周向不均匀性更大,导致轴向间隙内的燃气沿周向窜流的程度更大,且双向进气结构型式的第一级进气扇区与出口段布置在同侧,使得沿周向窜动的燃气更易直接流出涡轮,降低了再入管道对前面级燃气的收集能力。

关键词：单/双向进气再入式涡轮性能参数不均匀性参数数值模拟

环形中心钝体驻涡燃烧室驻涡腔有无喷射的对比

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航空动力学报 2015年第2期30卷 331-340页

作者：韩吉昂李晓东钟兢军大连海事大学轮机工程学院辽宁大连116026

采用三维雷诺平均Navier-Stokes(N-S)方程、renormalization group(RNG)k-ε湍流模型和标准壁面函数对驻涡腔有无喷射的环形中心钝体驻涡燃烧室的冷态流场进行了数值仿真,分析了驻涡腔有无喷射对环形中心钝体驻涡燃烧室涡系结构、驻涡... 详细信息

采用三维雷诺平均Navier-Stokes(N-S)方程、renormalization group(RNG)k-ε湍流模型和标准壁面函数对驻涡腔有无喷射的环形中心钝体驻涡燃烧室的冷态流场进行了数值仿真,分析了驻涡腔有无喷射对环形中心钝体驻涡燃烧室涡系结构、驻涡腔流动参数和燃烧室总体性能的影响.结果表明:相比于无喷射时,驻涡腔添加喷射可以使驻涡腔内形成相对稳定的双驻涡结构;驻涡腔喷射的存在使得环形中心钝体驻涡燃烧室出口截面总压损失系数降低约9.2%,并能提高驻涡腔内的平均气流参数;驻涡腔喷射对环形中心钝体驻涡燃烧室出口截面流动参数沿流道高度方向的变化趋势影响不大.

关键词：环形中心钝体驻涡燃烧室驻涡腔喷射冷态流场涡系结构

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局部进气涡轮优化设计研究

工程热物理学报 2020年第4期41卷 829-839页

作者：陈帝云韩吉昂钟兢军大连海事大学轮机工程学院大连116026 上海海事大学商船学院上海201306

为了能够有效优化局部进气涡轮性能,通过对现有软件模块进行二次开发,并利用人工神经网络结合粒子群-遗传混合算法,建立了局部进气涡轮气动优化设计平台,分别在全周进气单流道和局部进气环境下对涡轮进行了分步优化。结果表明:在全周进... 详细信息

为了能够有效优化局部进气涡轮性能,通过对现有软件模块进行二次开发,并利用人工神经网络结合粒子群-遗传混合算法,建立了局部进气涡轮气动优化设计平台,分别在全周进气单流道和局部进气环境下对涡轮进行了分步优化。结果表明:在全周进气单流道条件下,通过对各排动静叶进出口几何角、安装角和第一级动叶积叠规律的优化,改善了涡轮内部流动状态,使涡轮总静效率在全周进气单流道条件下累计提升了3.24%;通过对全周进气单流道优化结果进行局部进气构型,并进一步在局部进气环境下对第一级动叶叶型进行优化,消除了第一级动叶排根部因局部进气气动参数周向分布不均匀而导致的流动分离,使优化后的局部进气涡轮总静效率较原型累计提升了3.72%。

关键词：局部进气涡轮优化设计平台智能优化算法性能优化

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喷水推进轴流泵的水力设计及性能分析

工程热物理学报 2014年第12期35卷 2412-2416页

作者：韩吉昂李臣钟兢军杨凌大连海事大学轮机工程学院辽宁大连116026

借鉴陆用轴流泵设计经验,利用Concepts NREC软件设计了三种不同安装角的喷水推进轴流泵,并采用三维雷诺平均N-S方程和S-A湍流模型对其流场和性能进行数值仿真。计算结果表明:叶片安装角对喷水推进轴流泵的性能和流场影响较大,动叶进口... 详细信息

借鉴陆用轴流泵设计经验,利用Concepts NREC软件设计了三种不同安装角的喷水推进轴流泵,并采用三维雷诺平均N-S方程和S-A湍流模型对其流场和性能进行数值仿真。计算结果表明:叶片安装角对喷水推进轴流泵的性能和流场影响较大,动叶进口安装角减小6°后效率可提高3%~5%,叶片进口的狭窄高压区明显改善,动叶吸力面分离区和分离流动损失明显减小,叶片载荷分布更加均匀;静叶进口安装角减小后扬程和效率都有所提高,静叶出口的流场形态得到改善,角区分离得到控制、回流损失减小。

关键词：喷水推进轴流泵几何安装角水力性能数值仿真