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Xiaohan Xu, Xudong Huang, Dianfang Bi and Ming Zhou
Aerodynamic compressor designs require considerable prior knowledge and a deep understanding of complex flow fields. With the development of computer science, artificial intelligence (AI) has been widely applied to compressors design. Among the various A...
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Daniel Franke, Daniel Möller, Maximilian Jüngst, Heinz-Peter Schiffer, Thomas Giersch and Bernd Becker
This study investigates the aerodynamic and aeroelastic characteristics of a transonic axial compressor, focusing on blade count reduced rotor behavior. The analysis is based on experiments, conducted at the Transonic Compressor Darmstadt test rig at Tec...
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Julien Marty and Cédric Uribe
The present study focuses on the impact of the underlying RANS turbulence model in the Zonal Detached Eddy Simulation (ZDES) method when used for secondary flow prediction. This is carried out in light of three issues commonly investigated for hybrid RAN...
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Motoyuki Kawase and Aldo Rona
The tip leakage flow over the blades of an axial compressor rotor adversely affects the axial rotor efficiency and can determine the onset of tip leakage stall. The performance of a new casing treatment concept in the shape of an axisymmetric recirculati...
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J. Michael Owen, Hui Tang and Gary D. Lock
Increasing pressures in gas-turbine compressors, particularly in aeroengines where the pressure ratios can be above 50:1, require smaller compressor blades and an increasing focus on blade-clearance control. The blade clearance depends on the radial grow...
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J. Michael Owen, Hui Tang and Gary D. Lock
Increasing pressures in gas-turbine compressors, particularly in aeroengines where the pressure ratios can be above 50:1, require smaller compressor blades and an increasing focus on blade-clearance control. The blade clearance depends on the radial grow...
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Shiji Zhou, Shengfeng Zhao, Chuangxin Zhou, Yunfeng Wu, Hang Yuan and Xingen Lu
To explore the internal flow mechanism and improve the performance of a supersonic compressor, an efficient global optimization design method was developed for an axial flow compressor and applied in the optimization design of a prototype supersonic comp...
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Yan Chen, Chunxiang Gao and Wuli Chu
In order to prolong the service life of multistage axial compressors, it is increasingly important to study the influence of blade surface roughness on the compressor performance. In this paper, a five-stage axial compressor of a real aero-engine was sel...
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Jerzy A. Owczarek
This Technical Note calls attention to the fact that observed initiation of stall in an axial flow compressor can be explained by the pressure pulses reflecting between the stator and rotor blades. The phenomenon of reflection of pressure pulses between ...
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Tilman Raphael Schröder, Sebastian Schuster and Dieter Brillert
The designers of radial turbomachinery need detailed information on the impact of the side chamber flow on axial thrust and torque. A previous paper investigated centripetal flow through narrow rotor?stator cavities and compared axial thrust, rotor torqu...
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Marhamat Zeinali, Sarallah Abbasi, Abolfazl Hajizadeh Aghdam
Pág. 288 - 295
Commencement and development processes of unsteadiness, caused by blade row tip leakage flow in a low speed axial compressor, are investigated and results are presented in this paper. Analyses are based on results obtained through numerical simulation of...
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Clémence Rannou, Julien Marty, Geoffrey Tanguy and Antoine Dazin
The tip gap region of an axial compressor rotor is a source of complex flows, inducing losses and stability issues. Recent works have proven the ability of blowing high-speed jets in the tip region to improve the surge margin of an axial compressor stage...
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Jonas Foret, Daniel Franke, Fabian Klausmann, Alexandra Schneider, Heinz-Peter Schiffer, Bernd Becker and Hauke Müller
This paper experimentally investigates a highly-loaded 1.5-stage transonic axial compressor, which comprises a variable inlet guide vane, a BLISK rotor, and a variable stator in tandem arrangement. A detailed comparison between the newly designed compres...
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Baojie Liu, Du Fu and Xianjun Yu
This paper presents a model for predicting the reference minimum-loss incidence and deviation angles of a blade arrangement with splitter vanes, which is probably a solution for future ultra-highly loaded axial compressor designs. The motivation of the m...
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Wenhui Yan, Zhaozheng Sun, Junwei Zhou, Kun Zhang, Jiahui Wang, Xiao Tian and Junqian Tian
One of the most commonly used techniques in aerospace engineering is the RANS (Reynolds average Navier?Stokes) approach for calculating the transonic compressor flow field, where the accuracy of the computation is significantly affected by the turbulence...
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Lucilene Silva, Tomas Grönstedt, Carlos Xisto, Luiz Whitacker, Cleverson Bringhenti and Marcus Lejon
The ratio between blade height and chord, named the aspect ratio (AR), plays an important role in compressor aerodynamic design. Once selected, it influences stage performance, blade losses and the stage stability margin. The choice of the design AR invo...
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Hengtao Shi
This paper researches the parametric optimization of a two-stage transonic compressor having a large air bypass at partial rotating speed according to flow analysis for a turbine-based combined cycle engine (TBCC). To obtain adequate thrust, the inlet tr...
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Roman Varbanets, Oleksij Fomin, Václav Pí?tek, Valentyn Klymenko, Dmytro Minchev, Alexander Khrulev, Vitalii Zalozh and Pavel Kucera
The article presents the acoustic method of marine low-speed engine turbocharger parameter estimation under operating conditions when a prompt assessment of instantaneous turbocharger speed and rotor vibration level is required. The method lies in the an...
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Alessandro Vulpio, Alessio Suman, Nicola Casari and Michele Pinelli
Helicopters often operate in dusty sites, ingesting huge amounts of contaminants during landing, take-off, hover-taxi, and ground operations. In specific locations, the downwash of the rotor may spread soil particles from the ground into the environment ...
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Alberto Baretter, Benjamin Godard, Pierric Joseph, Olivier Roussette, Francesco Romanò, Raphael Barrier and Antoine Dazin
On many occasions, fan or compressor stages have to face azimuthal flow distortion at inlet, which affects their performance and stability. These flow distortions can be caused by external events or by some particular geometrical features. The aim of thi...
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