|
|
|
|
|
Peng Zhang, Rixin Cheng and Yonghong Li
Bionic herringbone riblets are applied to relieve the flow near the blade endwall in a linear compressor cascade under the incidence angle of -4° to 6° at a Reynolds number of 382,000. The herringbone riblets are placed at the endwall upstream of the bla...
ver más
|
|
|
|
|
|
|
|
|
|
|
Jingbo Tan, Chun Zhang, Huiling Zhu, Ling Zhou and Lucheng Ji
To explore the influence of circumferential grooved casing treatment on subsonic cascade performance, a numerical simulation of subsonic cascade was conducted. In contrast to traditional research on variable single parameters for casing treatment, this p...
ver más
|
|
|
|
|
|
|
|
|
|
|
Xiaobin Xu, Baojie Liu, Xianjun Yu and Guangfeng An
The geometry of a compressor leading edge has an important effect on the aerodynamic performance at an off-designed incidence angle. The current geometric design methods of the leading edge are usually developed based on the flow characteristics at the d...
ver más
|
|
|
|
|
|
|
|
|
|
|
Hefang Deng, Kailong Xia, Jinfang Teng, Xiaoqing Qiang, Mingmin Zhu and Shaopeng Lu
The moving endwall has a great influence on the development and stability of axial compressor leakage flow. This paper presents a novel experimental facility with a high-speed moving endwall for studying axial compressor leakage flow. The uniqueness of t...
ver más
|
|
|
|
|
|
|
|
|
|
|
Edwin Joseph Munoz Lopez, Alexander Hergt, Till Ockenfels, Sebastian Grund and Volker Gümmer
The successful design of compressor blades through numerical optimization relies on accurate CFD-RANS solvers that are able to capture the general performance of a given design candidate. However, this is a difficult task to achieve in transonic flow con...
ver más
|
|
|
|
|
|
|
|
|
|
|
Long Wang, Huawei Lu, Zhitao Tian, Yi Yang, Shuang Guo, Hong Wang and Xiaozhi Kong
The influence of the ratio of dimple depth-to-print diameter (λ" role="presentation">???
?
) on the highly loaded compressor cascade NACA0065-K48 is investigated based on the Reynolds-averaged Navier?Stokes (RANS) method. Simulations are conduc...
ver más
|
|
|
|
|
|
|
|
|
|
|
Yinxin Zhu, Zhenbing Luo, Wenqiang Peng, Qiang Liu, Yan Zhou, Wei Xie, Pan Cheng, Zhengxue Ma and Xuzhen Xie
To effectively reduce shock wave loss at the trailing edge of a supersonic cascade under high back-pressure, a shock wave control method based on air jets is proposed. The air jet was arranged on the pressure side of the blade in the upstream of the trai...
ver más
|
|
|
|
|
|
|
|
|
|
|
George Hill, Julian Gambel, Sabine Schneider, Dieter Peitsch and Sina Stapelfeldt
Modern aeroengine designs strive for peak specific fuel and thermal efficiency. To achieve these goals, engines have more highly loaded compressor stages, thinner aerofoils, and blended titanium integrated disks (blisks) to reduce weight. These configura...
ver más
|
|
|
|
|
|
|
|
|
|
|
Xiangjun Li, Jiezhong Dong, Hua Chen and Huawei Lu
Nowadays, with the increase of the thrust-to-weight ratio of the aero engines, the high aerodynamic load has made corner separation an issue for axial compressors. The complex three-dimensional flow field makes it challenging to suppress the corner separ...
ver más
|
|
|
|
|
|
|
|
|
|
|
Marco Rauseo, Mehdi Vahdati and Fanzhou Zhao
Aeroelastic instabilities such as flutter have a crucial role in limiting the operating range and reliability of turbomachinery. This paper offers an alternative approach to aeroelastic analysis, where the sensitivity of aerodynamic damping with respect ...
ver más
|
|
|
|
|
|