But the aerodynamic optimization of the turbomachinery blade, especially the transonic compressor blade, is still a challenge area.
但是叶轮机械，尤其是跨音速轴流压气机叶片的气动优化设计仍然是一个具有挑战性的研究领域。
This paper describes the initial experimental results of aeroelastic instability of BF-1 rotors on a transonic axial compressor facility at BIAA.
本文介绍了在跨音压气机试验台上对BF - 1系列转子开展气动弹性失稳的实验研究工作。
Numerical calculations were performed on a two-stage transonic fan and a five-stage compressor. The two-stage fan flow predictions show a good agreement with experimental data.
对某双级跨音速风扇及五级压气机流场进行了计算，双级风扇各状态的计算结果与实验数据吻合较好。
The paper presents some research works on the internal flow shock wave measurement of transonic compressor by PIV technique.
在跨音压气机试验台上进行了用PIV技术测量内流激波结构的试验研究。
According to the "General Theory of Three-Dimensional flow in Turbomachines", the quasi-three dimensional calculation of the transonic flow field has been achieved for a compressor rotor.
本文依据三元流动的通用理论，完成了一个跨声速压气机转子流场的准三元迭代计算。
The experimental investigation on aeroelastic instability and dynamic response of the BF-1 rotors by a transonic axial-flow compressor test rig are presented in this paper.
本文介绍了在跨音压气机试验台上对BF - 1系列转子开展气动弹性失稳和动态响应的实验研究工作。
This thesis investigated transonic cascade of a certain compressor in order to increase the static pressure ratio of the cascade and reduce the coefficient of the cascade losses.
本课题以某型压气机的跨音速叶栅为研究平台，以提高叶栅静压增压比，减少叶栅流动损失为目标。
The optimum design of Controlled Diffusion Airfoils (CDA) is one of the main research fields in subsonic and transonic profile design for multistage compressor.
可控扩散叶型（CDA）的优化设计是目前国外对亚音、跨音速压气机叶型研究的主要内容之一。
A 3d numerical simulation software was developed to calculate the tip-clearance flow of ATS-2, a high-loading transonic compressor, and the results were compared with the experiments.
利用自行开发的叶轮机三维数值模拟软件对高负荷跨音压气机ats - 2转子进行了带叶尖间隙的三维流动数值模拟，并与实验的结果进行了比较。
The probe has been successfully used for measuring rotating stall signals of a single stage transonic compressor.
用该探针成功地测出了一台跨音速单级轴流压气机的旋转失速信号。
NF-6 wind tunnel is the first pressurized continuous transonic cryogenic two dimensional wind tunnel in China. The performance of the NF-6 wind tunnel depend up on axial compressor to large extent.
针对正在建设中的我国第一座增压连续式跨音速翼型风洞（NF-6风洞），提出用虚拟仪器观念和技术来开发风洞智能测控系统的构思和设想，概述了风洞压缩机状态监测与管理系统的软硬件构成。
NF-6 wind tunnel is the first pressurized continuous transonic cryogenic two dimensional wind tunnel in China. The performance of the NF-6 wind tunnel depend up on axial compressor to large extent.
针对正在建设中的我国第一座增压连续式跨音速翼型风洞（NF-6风洞），提出用虚拟仪器观念和技术来开发风洞智能测控系统的构思和设想，概述了风洞压缩机状态监测与管理系统的软硬件构成。
应用推荐