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Yao Y.,Nanjing University of Aeronautics and Astronautics | Zhang J.,Nanjing University of Aeronautics and Astronautics | He F.,Hongdu Aviation Industry Group | Guo W.,China Gas Turbine Establishment
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2010

The three-dimensional turbulent flow in a turbine cascade with blade film cooling is numerically investigated using a RNG turbulence model under different Reynolds numbers ranging from 4×10 5 to 6×10 5 and blowing ratios ranging from 0.5 to 3.0. The influence of the converging slot hole location at the blade suction surface (corresponding to the upstream of the throat, the cascade throat and the downstream of the throat) on the aerodynamic loss of the turbine cascade is investigated. Results show that the injection from the converging slot holes has effect only on the pressure coefficient distribution near the film cooling holes. The kinetic loss and total pressure loss induced by the injection from the film holes located at the upstream of the throat are lower than those induced by the other two locations, while the aerodynamic loss coefficients corresponding to the downstream of the throat location are the largest in most cases. Compared with cylindrical holes, the converging slot holes at the upstream of the throat exhibit both higher cooling effectiveness and lower aerodynamic loss coefficient. Source


Yao Y.,Nanjing University of Aeronautics and Astronautics | Zhang J.,Nanjing University of Aeronautics and Astronautics | He F.,Hongdu Aviation Industry Group | Guo W.,China Gas Turbine Establishment
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2010

The film cooling characteristics of a converging slot hole on the blade suction surface of a turbine are numerically investigated using the RNG turbulence model under different turbine cascade inlet Reynolds numbers (ranging from 4×105 to 6×105 ) and blowing ratios (ranging from 0.5 to 3.0 ). The influence of the location of the converging slot hole at the blade suction surface (corresponding respectively to the upstream of the throat, the cascade throat and the downstream of the throat) on film cooling effectiveness is investigated. The results show that the converging slot hole cooling effectiveness in different locations all increases with the increase of the mainstream Reynolds number and coolant blowing ratio. Compared with the cylindrical hole, the converging slot hole cooling effectiveness is improved obviously and more uniform in lateral variation in all locations. Under the same condition, the cooling effectiveness of the converging slot hole at the upstream of the throat is nearly always higher than that in the other locations. Source


Mo J.,Shanghai Aerospace Space System Engineering Institute | Mo J.,Shanghai University | Shen L.,Hongdu Aviation Industry Group | Wei B.,Xidian University | And 2 more authors.
IET Conference Publications | Year: 2013

In this paper, a Method of Moments with Higher-Order basis functions (HOBMoM), parallel implementation based on Message Passing Interface (MPI) and Out-of-Core technology (OOC) has been proposed to compute the Radar Cross Section (RCS) of an aircraft's engine. The block-partitioned parallel scheme for the large dense MoM matrix is designed to achieve excellent load balancing and high parallel efficiency. Because of the bottleneck of the RAM limitation, the out-of-core technology is employed. Some numerical results demonstrate that the Higher-Order basis used in this paper is superior to the conventional RWG basis and is capable of solving various electrically large problems such as the computation of RCS. Source


Long D.U.,Hongdu Aviation Industry Group
Journal of Thermoplastic Composite Materials | Year: 2011

A novel composite wing with Z-pin reinforced foam core sandwich panels was presented. It has high torsional and bending stiffness as well as improved damage tolerance. The collapse modes of Z-pinned core were summarized and developed, and then the failure envelopes under various stress conditions were given based on the Tsai-Wu failure criterion. An analytical approach was developed to assess the bending-twist properties of wing box, and the change of ply orientation of sandwich panel facesheets on the coupling coefficient was demonstrated. The Z-pinning parameter is determined by the applied bending moment and transverse loads. Numerical examples were presented to show the design parameters of Z-pinning for a given load case. © 2011 The Author(s). Source


Yi L.,Hongdu Aviation Industry Group | Peng Y.,Nanchang Hangkong University
Jixie Qiangdu/Journal of Mechanical Strength | Year: 2013

The linear viscoelastic constitutive model, which in most popular FEM (finite element method) software, is unsuitable for solid propellant with large deformation. Based on the subroutine VUMAT (vectorized user defined material subroutine), a nonlinear viscoelastic constitutive model developed by Swanson was implemented into Abaqus. The constitutive model was coded using Fortran, and can be called as a subroutine. The validify of the subroutine had been proven through the standard uniaxial tensile model. The subroutine can be used for the analysis of large solid rocket motor. The shortage of Abaqus which only has linear viscoelastic constitutive model is remedied. Some useful technology, including the detail process of implementing a material constitutive model, was presented. It can be referred for extending the material constitutive model in Abaqus. Source

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