Parametric study of aerodynamic performance of equivalent ducted/un-ducted rotors

2021 ◽  
pp. 106984
Author(s):  
T. Zhang ◽  
G. Qiao ◽  
D.A. Smith ◽  
G.N. Barakos ◽  
A. Kusyumov
Keyword(s):  
Parametric Study ◽  
Aerodynamic Performance ◽  
Ducted Rotors

Parametric study on the aerodynamic performance of a ducted-fan rotor using free-form method

2020 ◽  
Vol 101 ◽  
pp. 105842
Author(s):  
Chengwei Fan ◽  
Richard Amankwa Adjei ◽  
Yadong Wu ◽  
Anjenq Wang
Keyword(s):  
Parametric Study ◽  
Aerodynamic Performance ◽  
Free Form ◽  
Ducted Fan

AERODYNAMIC PERFORMANCE OF AN AXIAL COMPRESSOR WITH A CASING GROOVE COMBINED WITH INJECTION

2013 ◽  
Vol 37 (3) ◽  
pp. 283-292 ◽  
Author(s):  
Dae-Woong Kim ◽  
Jin-Hyuk Kim ◽  
Kwang-Yong Kim
Keyword(s):  
Turbulence Model ◽  
Parametric Study ◽  
Stokes Equations ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Stall Margin ◽  
Transonic Axial Compressor

Aerodynamic performance of a transonic axial compressor with a casing groove combined with injection has been investigated in this work. Three-dimensional Reynolds-averaged Navier–Stokes equations with k-ε turbulence model are discretized by finite volume approximations and solved on hexahedral grids for the flow analyses. For parametric study, the front and rear lengths and height of the casing groove are selected as the geometric parameters and are changed with constant injection to investigate their effects on the stall margin and peak adiabatic efficiency. As a result of the parametric study, the maximum stall margin and peak adiabatic efficiency are found to be obtained in the axial compressor having 70% height of the reference groove. The results show that the application of the casing groove combined with injection to an axial compressor is effective for the simultaneous improvement of both the stall margin and peak adiabatic efficiency of the compressor.

Parametric Study on Aerodynamic Performance of a Transonic Axial Compressor with a Casing Groove and Tip Injection

2013 ◽  
Vol 284-287 ◽  
pp. 872-877 ◽  
Author(s):  
Dae Woong Kim ◽  
Jin Hyuk Kim ◽  
Kwang Yong Kim
Keyword(s):  
Parametric Study ◽  
Stokes Equations ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Navier Stokes ◽  
Stall Margin ◽  
Transonic Axial Compressor ◽  
Tip Injection

This paper presents a parametric study on aerodynamic performance of a transonic axial compressor combined with a casing groove and tip injection using three-dimensional Reynolds-average Navier-Stokes equations. The front and rear lengths and height of the groove are selected as the geometric parameters to investigate their effects on the stall margin and peak adiabatic efficiency. These parameters are changed with constant injection. The validation of the numerical results is performed in comparison with experimental data for the total pressure ratio and adiabatic efficiency. As the results of the parametric study, the maximum stall margin and peak adiabatic efficiency are obtained in the axial compressor having 70% groove height of the reference groove. The stall margin and peak adiabatic efficiency in other cases are also improved in comparison with the axial compressors with the smooth casing and reference groove. The results show that both the stall margin and the peak adiabatic efficiency are considerably improved by the application of the casing groove combined with tip injection in an axial compressor.

Parametric Study of Axial Flow Turbine for Mean-Line Design and Blade Elements

2012 ◽  
Author(s):  
S. V. Ramana Murthy ◽  
S. Kishore Kumar
Keyword(s):  
Parametric Study ◽  
Axial Flow ◽  
Aerodynamic Performance ◽  
Main Step ◽  
Preliminary Design ◽  
Product Cycle ◽  
Thermal Requirements ◽  
Element Profile ◽  
Final Design ◽  
Line Design

A parametric study is carried out for aerodynamic performance of turbines including geometrical requirements, thermal requirements, mechanical integrity and manufacturing requirements. Life cycle costs, product cycle time and weight are additional, possible criteria during the parametric study. Preliminary design plays an important role in reaching the final design of the turbine. Preliminary design steps calculate the mean dimensions of the machine. The main step in the aerodynamic design which is instrumental in providing desired performance is blade element profile generation. During the profile generation, in addition to aerodynamic performance, additional constraints for castability, structural requirements and thermal requirements need to be considered. Thus profile generation is a trade-off between contradicting requirements of aerodynamic performance, structural and thermal performance.

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