Numerical simulation research of the stall flow field of the transonic compressor blade tip

2010 ◽  
Author(s):  
Yanglin Li ◽  
Qiaojuan Gao ◽  
Bo Zhang
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Compressor Blade ◽  
Simulation Research ◽  
Transonic Compressor ◽  
Blade Tip

Flow Field Analysis of Conducting Trunk of Comb-Type Cotton Picker

2012 ◽  
Vol 468-471 ◽  
pp. 1749-1752
Author(s):  
Chun Yao Wang ◽  
Xue Nong Wang ◽  
Fa Chen ◽  
Yue Liu ◽  
Jiu Peng Chi ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Velocity Field ◽  
Flow Field ◽  
Field Analysis ◽  
Distribution Characteristics ◽  
Pneumatic Conveying ◽  
Simulation Research ◽  
Cotton Picker ◽  
Different Types ◽  
Flow Field Analysis

This article uses the flow field numerical simulation technology, it does simulation research for the flow field of the whole pneumatic conveying cotton trunk, through studying different types of jet orifice of the conveying trunk of comb—type cotton picker, finding out the influence of jet orifice width on pressure and velocity field, further understanding flow field distribution characteristics of the internal pneumatic cotton conveyance system, and providing necessary basis for the machine.

Tip Flow Fields in a Low Aspect Ratio Transonic Compressor

1995 ◽  
Author(s):  
P. Russler ◽  
D. Rabe ◽  
B. Cybyk ◽  
C. Hah
Keyword(s):  
Shock Wave ◽  
Aspect Ratio ◽  
Flow Field ◽  
High Frequency ◽  
High Performance ◽  
Flow Structures ◽  
Transonic Compressor ◽  
Low Aspect Ratio ◽  
Laser Data ◽  
Blade Tip

Experimental data and computational predictions are used to characterize the tip flow field of a high performance, low aspect ratio, transonic compressor. Flow structures near the first stage blade tip are monitored experimentally using two different data acquisition schemes. High frequency pressure and laser fringe anemometry data are used to experimentally define the tip flow structure. The high frequency pressure data were acquired with an array of pressure transducers mounted in the rotor casing. Laser data were acquired through a window in the same position. The transducer and laser data adequately define the shock structure at the tip. Both the movement of the shock wave in the blade passage during changes in compressor loading and the interaction between the shock wave and the tip leakage vortex are detected. Similar flow structures and compressor loading effects are numerically predicted using a three-dimensional Navier-Stokes algorithm. A fundamental understanding of the flow field at the blade tip is obtained using these three complementary methods.

Numerical simulation research of flow field in ammonia-based wet flue gas desulfurization tower

2015 ◽  
Vol 88 (3) ◽  
pp. 284-291 ◽  
Author(s):  
S.J. Wang ◽  
P. Zhu ◽  
G. Zhang ◽  
Q. Zhang ◽  
Z.Y. Wang ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Flue Gas ◽  
Flue Gas Desulfurization ◽  
Simulation Research

Computational Analysis of Effect of Circumferential Groove Casing Treatment With Different Axial Coverage Over Rotor Blade Tip Chord on the Performance of a Transonic Axial Compressor Stage

2015 ◽  
Author(s):  
Nishit J. Mehta ◽  
Dilipkumar Bhanudasji Alone ◽  
Harish S. Choksi
Keyword(s):  
Flow Field ◽  
Rotor Blade ◽  
Stokes Equations ◽  
Flow Behavior ◽  
Base Line ◽  
Compressor Stage ◽  
Casing Treatment ◽  
Transonic Compressor ◽  
Circumferential Groove ◽  
Blade Tip

Previous studies on circumferential groove casing treatments have shown that the effectiveness of casing Grooves highly depends on their axial location over blade tip. The present work aims to study the flow behavior and its impact on the performance of the compressor stage when the casing treatment grooves are placed to provide different axial coverage over rotor chord in each case. Geometry of a transonic compressor stage was modeled for this study. Flow field solutions for this model with smooth casing wall were obtained by solving steady state 3-D Reynolds-Averaged Navier-Stokes equations for three different grids to prove the grid independence of the solutions. Results obtained with the intermediate grid density were used as the baseline results to compare with results of casing treatment geometries. The basic casing treatment geometry has 10 circumferential groves of width 4mm, depth 16mm and axial spacing of 2mm between each groove. This casing treatment geometry was superimposed over the rotor domain with the grooves extending axially over the entire axial chord (58mm) of rotor blade tip and flow field solutions were again obtained. After that, for each case the grooves are removed from the rear side and axial coverage is shortened. Flow solutions for various axial coverage and hence for various number of grooves are thus obtained and compared. These results depict improvement in the operating range when compared to the Base-line results. Results also exhibit that as the grooves from the rear end are removed gradually, recovery in the overall efficiency is seen in compressor performance. Post processing of the flow solutions confirms the trend and shows that the grooves in the rear of the chord are almost idle not providing sufficient flow to pass over from pressure surface to suction surface of the blade and hence contributing very less towards performance enhancement.

Numerical Simulation Research of Air-Assisted Atomizer Internal Gas Flow Field Based on Fluent

2014 ◽  
Vol 599-601 ◽  
pp. 377-380
Author(s):  
Qiao Li ◽  
Ya Yu Huang
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Total Pressure ◽  
High Speed ◽  
Gas Flow ◽  
Static Pressure ◽  
Mutual Influence ◽  
Simulation Research ◽  
Simulation Calculation ◽  
Gas Flow Field

The numerical simulation calculation of air-assisted atomizer internal gas flow field is done, the distribution and changes of the nozzle inside flow field total pressure, velocity, and dynamic and static pressure are analyzed. The analysis shows that the total pressure loss is less; due to the effect of gas viscous, the high-speed air flow is formed vortex flow near the outlet nozzle and the mutual influence between the dynamic and static pressure. A new way is supported for optimizing the nozzle structure according to these studies.

Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors

1999 ◽  
Vol 122 (4) ◽  
pp. 733-742 ◽  
Author(s):  
Dale E. Van Zante ◽  
Anthony J. Strazisar ◽  
Jerry R. Wood ◽  
Michael D. Hathaway ◽  
Theodore H. Okiishi
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Shear Layer ◽  
Tip Clearance ◽  
Numerical Code ◽  
Laser Doppler Velocimeter ◽  
Simple Method ◽  
Tip Clearance Flow ◽  
Transonic Compressor ◽  
Clearance Flow

The tip clearance flows of transonic compressor rotors are important because they have a significant impact on rotor and stage performance. A wall-bounded shear layer formed by the relative motion between the overtip leakage flow and the shroud wall is found to have a major influence on the development of the tip clearance flow field. This shear layer, which has not been recognized by earlier investigators, impacts the stable operating range of the rotor. Simulation accuracy is dependent on the ability of the numerical code to resolve this layer. While numerical simulations of these flows are quite sophisticated, they are seldom verified through rigorous comparisons of numerical and measured data because these kinds of measurements are rare in the detail necessary to be useful in high-speed machines. In this paper we compare measured tip-clearance flow details (e.g., trajectory and radial extent) with corresponding data obtained from a numerical simulation. Laser-Doppler Velocimeter (LDV) measurements acquired in a transonic compressor rotor, NASA Rotor 35, are used. The tip clearance flow field of this transonic rotor is simulated using a Navier–Stokes turbomachinery solver that incorporates an advanced k–ε turbulence model derived for flows that are not in local equilibrium. A simple method is presented for determining when the wall-bounded shear layer is an important component of the tip clearance flow field. [S0889-504X(00)02504-6]

Numerical Simulation of Interior Flow Field of a Variable Thrust Rocket Engine

2011 ◽  
Vol 186 ◽  
pp. 215-219 ◽  
Author(s):  
Chun Guo Yue ◽  
Xin Long Chang ◽  
Shu Jun Yang ◽  
You Hong Zhang
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Rocket Engine ◽  
Molar Fraction ◽  
Simulation Research ◽  
Design And Optimization ◽  
Calculation Results ◽  
Liquid Propellant Rocket Engine ◽  
Interior Flow ◽  
Calculation Ability

With the support of powerful calculation ability of computer and Fluent of CFD software, integrative simulation research of the variable thrust liquid propellant rocket engine was developed. Numerical simulation of interior flow field of a variable thrust rocket engine with flux-oriented injector was done. The distributions of pressure, temperature, molar fraction of product and flow mach numbers were attained. By the contrast of the calculation results, the effects of structure parameters and working condition etc. on total whole performance of variable thrust rocket engine were analyzed. The results also provided theoretic references for design and optimization of variable thrust rocket engine.

The Numerical Simulation Research on Garbage Particles in Airflow Field of Horizontal Air-Separator under Different Conditions

2012 ◽  
Vol 518-523 ◽  
pp. 2263-2266
Author(s):  
Xin Le Yang ◽  
Shuo Yang
Keyword(s):  
Numerical Simulation ◽  
Velocity Field ◽  
Flow Field ◽  
Pressure Field ◽  
Internal Flow ◽  
Simulation Method ◽  
Separation Principle ◽  
Simulation Research ◽  
Airflow Field ◽  
Back Mixing

In air-separator’s operating condition, separation trajectory of air-separator’s internal garbage particles was obtained through comparison of ordinary and improved air-separator’s internal flow field in the numerical was simulated by FLUENT soft software and garbage particles’ flow rules and separation principle was revealed. The results show that velocity field and pressure field of improved horizontal air-separator’s changes smoothly and phenomenon of chaos and back-mixing can be avoided, furthermore, it realizes effective sorting for three different quality garbage particles. The numerical simulation method in this paper provides theoretical and technical way for optimizing the air-separator’s internal structure and improving air-separator’s performance.

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