The influence of micro vortex generator on inception cavitation

2021 ◽  
Vol 33 (10) ◽  
pp. 103312
Author(s):  
Jie Chen ◽  
Changli Hu ◽  
Mengjie Zhang ◽  
Biao Huang ◽  
Hanzhe Zhang
Keyword(s):  
Vortex Generator ◽  
Micro Vortex Generator

Micro vortex generator control of axisymmetric high-speed laminar boundary layer separation

Shock Waves ◽  
2014 ◽  
Vol 25 (5) ◽  
pp. 521-533 ◽  
Author(s):  
D. Estruch-Samper ◽  
L. Vanstone ◽  
R. Hillier ◽  
B. Ganapathisubramani
Keyword(s):  
Boundary Layer ◽  
Laminar Boundary Layer ◽  
High Speed ◽  
Vortex Generator ◽  
Boundary Layer Separation ◽  
Layer Separation ◽  
Micro Vortex Generator

Impact of a Combination of Micro-Vortex Generator and Boundary Layer Suction on Performance in a High-Load Compressor Cascade

2018 ◽  
Author(s):  
Shan Ma ◽  
Wuli Chu ◽  
Haoguang Zhang ◽  
Chuanle Liu
Keyword(s):  
Boundary Layer ◽  
Pressure Loss ◽  
Total Pressure ◽  
Vortex Generator ◽  
Aerodynamic Performance ◽  
Total Pressure Loss ◽  
Control Methods ◽  
Compressor Cascade ◽  
Boundary Layer Suction ◽  
Micro Vortex Generator

The performance of a compressor cascade is considerably influenced by flow control methods. In this paper, the synergistic effects of combination between micro-vortex generators (MVG) and boundary layer suction (BLS) are discussed in a high-load compressor cascade. Seven cases, which are grouped by a kind of micro-vortex generator and boundary layer suction with three locations, are investigated to control secondary flow effects and enhance the aerodynamic performance of the compressor cascade. The MVG is mounted on the end-wall in front of the passage. The rectangle suction slot with three radial positions is installed on the blade suction surface near the trailing edge. The numerical results show that: at the design condition, the total pressure loss is effectively decreased as well as the static pressure coefficient increase when the combined MVG and SBL method (COM) is used, which is superior to MVG in an aerodynamic performance. At the stall condition, the induced vortex coming from MVG could mix the low-energy fluid and mainstream, which result in the reduced separation, and the total pressure loss decreased by 11.54% when the suction flow ratio is 1.5%. The total pressure loss decreases by 14.59% when the COM control methods are applied.

scholarly journals Effect of Micro-Vortex Generator in Hypersonic Inlet

2011 ◽  
pp. 10-13
Author(s):  
Vivek V. Kumar ◽  
Surendra Bogadi
Keyword(s):  
Boundary Layer ◽  
Flow Field ◽  
Vortex Generator ◽  
Adverse Pressure Gradient ◽  
Actual Case ◽  
Hypersonic Inlet ◽  
Hypersonic Speeds ◽  
Structured Meshes ◽  
Free Stream Mach Number ◽  
Micro Vortex Generator

In the present study computational tests were carried out to get an understanding of the flow field in a pure mixedcompression hypersonic inlet at a free stream Mach number of 7 and an altitude of 35km. Structured meshes have been used for depicting the motion of fluid inside the inlet. First, a grid has been selected after conducting a grid study. Two dimensional simulations were carried out with standard sst k-ω model using FLUENT. Computational results are compared with the available data. The results obtained from the computational tests revealed several important flow field details at hypersonic speeds. The basic shock structure inside the inlet was obtained. The boundary layer formed inner side of the engine had an adverse pressure gradient on the top ramp. Due to this the boundary layer thickens and the static pressure starts to decrease whose effect leads till the trailing edge of inlet. By providing small wedge shaped Micro-Vortex Generator (MVG) where the shockboundary layer occurs we can smooth the boundary layer formed inside the inlet. Thus there will be more efficient compression than the actual case. The results obtained in the present series of tests, could help the hypersonic inlet design optimization at offdesign condition

Effect of the Micro Vortex Generator for Control of Separation around an Airfoil

2004 ◽  
Vol 2004.2 (0) ◽  
pp. 307-308
Author(s):  
Hiroyuki ABE ◽  
Takehiko SEGAWA ◽  
Yoshihiro KIKUSHIMA ◽  
Hiro YOSHIDA
Keyword(s):  
Vortex Generator ◽  
Micro Vortex Generator
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