Qingjun Zhao

Chinese Academy of Sciences

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Jianzhong Xu

Chinese Academy of Sciences

Huishe Wang

Chinese Academy of Sciences

Wei Zhao

Institute of Engineering Thermophysics

Xiaorong Xiang

Chinese Academy of Sciences

Xiuming Sui

Chinese Academy of Sciences

Wei Zhao

Institute of Engineering Thermophysics

Xiaolu Zhao

Chinese Academy of Sciences

Sanqun Ren

Institute of Engineering Thermophysics

Weiwei Luo

Institute of Engineering Thermophysics

Fei Tang

Tsinghua University

Cooperative Institutions

Chinese Academy of Sciences

Institute of Engineering Thermophysics

University of Chinese Academy of Sciences

Shanghai Jiao Tong University

National University of Defense Technology

Peking University

Tsinghua University

Harbin Institute of Technology

University of Science and Technology of China

Central South University

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Investigation of Hot Streak-to-Airfoil Count Ratio Effects in High Pressure Stage of Vaneless Counter-Rotating Turbine

Huishe Wang Jianzhong Xu Xiaolu Zhao Qingjun Zhao

Streak

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A tip-leakage loss reduction method using a front-loaded blade profile for the high-pressure rotor of a vaneless counter-rotating turbine

Proceedings of the Institution of Mechanical Engineers Part A Journal of Power and Energy (2022)

Tiantian Dong Qingjun Zhao Xiuming Sui Wei‐Wei Luo Wei Zhao

To reduce tip-leakage losses, this paper presents a front-loaded blade profile design method for the high-pressure (HP) rotor of a highly loaded vaneless counter-rotating turbine (VCRT). The method is to decrease the blade exit angle and increase the stagger angle with unchanged throat area to obtain front-loaded blade profiles at both the tip-leakage vortex upper and lower boundaries. As the relative exit Mach numbers in the tip region of the VCRT’s HP rotor are all over 1.5, the shearing of the high-speed leakage jet and passage flow near the trailing edge is very strong. To reduce the shearing losses, decreasing the blade exit angle of the HP rotor is adopted to reduce the tip loading near the trailing edge. This means the leakage jet mass-flow rate and speed near the trailing edge are reduced. Hence, the shearing strength and losses of the leakage jet and passage flow near the trailing edge are lower. Since decreasing the blade exit angle of the HP rotor results in increased throat area, increasing the stagger angle is employed to maintain unchanged throat area. Increasing the stagger angle also reduces the tip loading near the trailing edge, leading to reduced high-speed leakage jet mass-flow rate. Thus, the shearing strength and losses of the high-speed leakage jet and passage flow near the trailing edge are further reduced. The efficiency of the HP rotor and VCRT are raised by 0.45% and 0.53% respectively.

Trailing edge

Leakage (economics)

Shearing (physics)

Leading edge

Tip clearance

10.1177/09576509221111074

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Optimizing of the Structural Parameters of an Asymmetric Ramp Micro-Vortex Generator in Supersonic Flow

Gongcheng Rewuli Xuebao (2016)

Kai Wang Zhang Binbin Jing Li Qingjun Zhao

Vortex generator

Choked flow

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Analysis of Flow Field and Hub Suction in Ramrotor

Gongcheng Rewuli Xuebao (2011)

Yanlin Hu Sun Xiaolei Fei Tang Qingjun Zhao Xu Jianzhong

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膨張空気タービンの最大状態調整法則と性能解析【JST・京大機械翻訳】

Gongcheng Rewuli Xuebao (2016)

Huang Chen Xiaorong Xiang Zhang Binbin Zhao Wei Qingjun Zhao

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遷音速ロータ翼の流れ特性に及ぼす端部吸引の影響を研究した。【JST・京大機械翻訳】

Tuijin Jishu (2016)

Xin An Sun Xiaolei Cui Weiwei Qingjun Zhao

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Optimization of Nonlinear Energy Sinks in Low-Order Thin-Shell Models and Analysis of Broadband Vibration Suppression

Shen Liu Yingqun Ma Wei Zhao Qingjun Zhao Xuesen Yang

10.2139/ssrn.5037991

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Film Cooling Performance of Converging-Slot Holes on a Gas Turbine Blade Tip

Qingjun Zhao Wensan Wang Zhao Xiaolu

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Three-dimensional numerical investigation of vaneless counter-rotating turbine

Journal of Propulsion Technology (2006)

Qingjun Zhao Huishe Wang

In order to reveal the flow characteristics in a VCRT,a three-dimentional,viscous,steady CFD analysis was performed for investigating the turbine performance.Results show that the performance of this VCRT basically reaches the original objective,which indicates that a convergent-divergent blade passage in the high pressure rotor and a convergent-divergent meridian plane of the VCRT are suitable for the VCRT.All of these blade rows of the VCRT,especially high pressure rotor,need much more optimization.The efficiency of the VCRT can be improved through some optimized methods,such as blade curving,throat location adjusting,and so on.The results of the numerical simulations also show that the pitch-averaged Mach number of the outflow of the high pressure rotor is about from 1.4 at the hub to 1.6 at the shroud.The strength of oblique shock waves is strongest on the midspan in the trailing edge of the high pressure rotor.However,it is weaker on the hub and the shroud.Meantime,the results also indicate that the performance of the VCRT will decrease with the increase of the outlet pressure.The performance of the high pressure rotor is retained with the change of outlet pressure.However,performance of the low pressure rotor is greatly influenced with the change of outlet pressure.

Shroud

Overall pressure ratio

Trailing edge

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Citations (6)

A study on 4,4 '-diaminobenzene sulfonanilide (DABSA) and the properties of dyes derived from DABSA

高等学校化学研究(英文版) (2001)

ZW Wu LM Wang Jy Dai Wang JQ Xiao

a single crystal of 4,4 ' -diaminobenzene sulfonanilide (dabsa) was determined by x-ray diffraction method. it is shown that the two benzene rings are non-planar with an angle of 55.1 degrees. owing to the non-planar configuration, the dyes derived from dabsa possess a lower substantivity on fiber but better permeability in substrate, the color of these azo dyes could be matched by two individual azo dyes locating on both sides of the dabsa molecule.

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