Application of Vorticity Method in Auxiliary Impeller Optimization of HTR-PM Main Helium Fan

2018 ◽  
Author(s):  
Mo Fei ◽  
Zhang Youjie
Keyword(s):  
High Pressure ◽  
Flow Field ◽  
Cooling System ◽  
Design Method ◽  
Axial Flow ◽  
Optimized Design ◽  
Small Power ◽  
Small Flow ◽  
Overall Efficiency ◽  
Flow Compressor

The helium circulator is an important part of HTR-PM. In order to avoid the heat which produced by the helium calculator of HTR-PM cumulating in the motor cavity, the heat should be taked out by the way of forced convection. According to the the spatial structure of channel, we need to design a single stage axial flow compressor here which has the technical characteristics with small power, small flow and high pressure. Let it meet the cooling demand of the specific heat of the motor, and also reduce the power consumption of cooling system itself, so as to improve the overall efficiency of the system. To sum up, in the present study, through the design path of the positive problem, the conventional variable method is used to solve the flow field, that is, the flow field is solved by the velocity and pressure terms, and then the vortex in the flow field is deduced according to the velocity distribution According to the distribution of vorticity in the flow field, it provides the direction for the optimal design of the impeller. In the end, we hope to use this optimized design method to further optimize the blades and runner of the auxiliary impeller of helium circulator for HTR-PM.

Inverse Design of Axial-Flow Compressor Blades Using Elastic Surface Algorithm in Subsonic and Transonic Flow Regimes With Separation

2016 ◽  
Author(s):  
M. H. Noorsalehi ◽  
M. Nili-Ahamadabadi ◽  
E. Shirani ◽  
M. Safari
Keyword(s):  
Pressure Distribution ◽  
Transonic Flow ◽  
Design Method ◽  
Axial Flow ◽  
Flow Regimes ◽  
Inverse Design ◽  
Elastic Surface ◽  
Axial Flow Compressor ◽  
Inverse Design Method ◽  
Flow Compressor

In this study, a new inverse design method called Elastic Surface Algorithm (ESA) is developed and enhanced for axial-flow compressor blade design in subsonic and transonic flow regimes with separation. ESA is a physically based iterative inverse design method that uses a 2D flow analysis code to estimate the pressure distribution on the solid structure, i.e. airfoil, and a 2D solid beam finite element code to calculate the deflections due to the difference between the calculated and target pressure distributions. In order to enhance the ESA, the wall shear stress distribution, besides pressure distribution, is applied to deflect the shape of the airfoil. The enhanced method is validated through the inverse design of the rotor blade of the first stage of an axial-flow compressor in transonic viscous flow regime. In addition, some design examples are presented to prove the effectiveness and robustness of the method. The results of this study show that the enhanced Elastic Surface Algorithm is an effective inverse design method in flow regimes with separation and normal shock.

Development of a New Front Stage for an Industrial Axial Flow Compressor

1994 ◽  
Vol 116 (4) ◽  
pp. 597-604 ◽  
Author(s):  
B. Eisenberg
Keyword(s):  
Design Method ◽  
Guide Vane ◽  
Theoretical Calculations ◽  
Axial Flow ◽  
Operating Range ◽  
Performance Curves ◽  
Front Stage ◽  
Inverse Design Method ◽  
Flow Compressor ◽  
High Degree

Industrial axial flow compressors are specially designed to achieve a wide operating range. The analysis of an existing six-stage axial flow research compressor indicated that the front stage could be improved significantly using modern design technique. To demonstrate the advantages of such a technique a redesign of the current front stage was conducted. By controlling the diffusion inside the blade sections with an inverse design method, loading was enlarged. Higher loading normally results in a reduction of profile incidence range. For compensation a wide chord application was chosen. Compared to the original compressor version, experiments resulted in steeper characteristic curves together with larger usable operating range. Keeping the same outer and inner diameter, mass flow was increased by 6 percent. Measurements of performance curves with variable speed and for guide vane control are presented. Theoretical calculations achieve a high degree of agreement with measured performance.

Progress of the 40 MW-Class Advanced Humid Air Turbine Tests

2013 ◽  
Vol 135 (11) ◽  
Author(s):  
Manabu Yagi ◽  
Hidefumi Araki ◽  
Hisato Tagawa ◽  
Tomomi Koganezawa ◽  
Chihiro Myoren ◽  
...  
Keyword(s):  
Metal Surface ◽  
Control Method ◽  
Cooling System ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Test Facility ◽  
Humid Air ◽  
Air Turbine ◽  
Calculation Results ◽  
Flow Compressor

A 40 MW-class test facility has been constructed to verify practicability of applying the advanced humid air turbine (AHAT) system to a heavy-duty gas turbine. Verification tests have been carried out from January 2012, and interaction effects between the key components were established. First, water atomization cooling (WAC) was confirmed to contribute to both increased mass flow rate and pressure ratio for the axial-flow compressor. The good agreement between measured and calculated temperatures at the compressor discharge was also confirmed. These results demonstrated the accuracy of the developed prediction model for the WAC. Second, a control method that realized both flame stability and low nitrogen oxides (NOx) emissions was verified. Although the power output and air humidity were lower than the rated values, NOx concentration was about 10 ppm. Finally, a hybrid nozzle cooling system, which utilized both compressor discharged air and humid air, was developed and tested. The metal surface temperatures of the first stage nozzles were measured, and they were kept under the permissible metal temperature. The measured temperatures on the metal surface reasonably corresponded with calculation results.

scholarly journals 3D Flow Field Measurement Around a Rotating Stall Cell

1998 ◽  
Author(s):  
C. Palomba ◽  
P. Puddu ◽  
F. Nurzia
Keyword(s):  
Flow Field ◽  
Axial Flow ◽  
Rotating Stall ◽  
Operating Conditions ◽  
Field Pattern ◽  
Mean Flow ◽  
Axial Section ◽  
Average Technique ◽  
Compressor Rotor ◽  
Flow Compressor

Rotating stall is an unsteady phenomenon that arises in axial and radial flow compressors. Under certain operating conditions a more or less regular cell of turbulent flow develops and propagates around the annulus at a speed lower than rotor speed. Recently little work has been devoted to the understanding of the flow field pattern inside a rotating cell. However, this knowledge could be of help in the understanding of the interaction between the cell and the surrounding flow. Such information could be extremely important during the modelling process when some hypothesis have to be made about the cell behaviour. A detailed experimental investigation has been conducted during one cell operation of an isolated low-speed axial flow compressor rotor using a slanted hot wire and an ensemble average technique based on the cell revolution time. The three flow field components have been measured on 9 axial section for 800 circumferential points and on 21 radial stations to give a complete description of the flow field upstream and downstream of the rotor. Interpretation of data can give a description of the mean flow field patterns inside and around the rotating cell.

Effects of Endwall Profiling on Axial Flow Compressor Stage

2009 ◽  
Author(s):  
Jialing Lu ◽  
Wuli Chu ◽  
Yanhui Wu
Keyword(s):  
Flow Field ◽  
Engineering Design ◽  
Axial Flow ◽  
Design Tool ◽  
Operating Conditions ◽  
Compressor Stage ◽  
Corner Separation ◽  
Axial Flow Compressor ◽  
Flow Compressor ◽  
Stage Efficiency

In recent years endwall profiling has been well validated as a major new engineering design tool for the reduction of secondary loss in turbines. However, its application on compressors have been rarely performed and reported. This paper documents the findings of the analysis for diminishing compressor stator corner separation using endwall profiling; In the study, novel profiled endwalls were designed and numerically studied on a subsonic axial-flow compressor stage. The compressor stator endwalls were profiled on both axial and azimuthal directions. The results showed, the stator corner separation was significantly suppressed under all the operating conditions by implementing this profiled endwall. Significant improvements on stage pressure ratios and stage efficiency were observed. Detailed flow field changes, as well as endwall profiling methods are provided in the paper, so that the results of this research can be referenced to other compressor designs.

A New Approach to the Experimental Study of Turbomachinery Flow Phenomena

1977 ◽  
Vol 99 (1) ◽  
pp. 97-105 ◽  
Author(s):  
J. P. Gostelow
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Axial Flow ◽  
Centrifugal Pumps ◽  
New Approach ◽  
Static Pressure Distribution ◽  
Compressor Rotor ◽  
Flow Phenomena ◽  
On Line ◽  
Flow Compressor

Measurements of the unsteady flow field over a rotor and within its wake are needed in the development of most turbomachines. The technique advocated is that of data acquisition by on-line computer, using the periodic passing of a blade as a phase reference. The phase-lock averaging process is described as is its use in reducing the noise of raw data traces. Measurements of the unsteady flow over a cascade and of the resulting boundary layer behavior are presented. The approach was used in interpreting the unsteady flow field of an axial-flow compressor rotor and the static pressure distribution over the rotor tip. Finally the application to centrifugal pumps is discussed, enabling the designer to obtain information on the suction pressures and the extent of any separated region.

Oil Source Valve Optimized Design and its Application in Mechanical Loader

2014 ◽  
Vol 1044-1045 ◽  
pp. 930-932
Author(s):  
Yu Ping Wei
Keyword(s):  
Operating System ◽  
High Pressure ◽  
Hydraulic System ◽  
Optimized Design ◽  
Variable Speed ◽  
Small Flow ◽  
Oil Source ◽  
Working Device ◽  
Large Flow

The operating system of loader working device is composed of the boom and bucket. It is operated mainly through multi-way valve axis manipulation, this kind of way is force-large, labor-intensive, but is low efficient. So it is necessary to optimize the oil source valve. Using the hydraulic pilot to control loader multi-way valve to optimize in the loader is safe, comfortable, furnished spirit and can achieve variable speed. Working hydraulic system uses a small flow pilot circuit control. The main oil is controlled by high pressure and large flow, and then the operating force of the working device is reduced greatly.

Development of a New Front Stage for an Industrial Axial Flow Compressor

1993 ◽  
Author(s):  
B. Eisenberg
Keyword(s):  
Design Method ◽  
Guide Vane ◽  
Theoretical Calculations ◽  
Axial Flow ◽  
Operating Range ◽  
Performance Curves ◽  
Front Stage ◽  
Inverse Design Method ◽  
Flow Compressor ◽  
High Degree

Industrial axial flow compressors are specially designed to achieve a wide operating range. The analysis of an existing 6 stage axial flow research compressor indicated that the front stage could be improved significantly using modern design technique. To demonstrate the advantages of such a technique a redesign of the current front stage was conducted. By controlling the diffusion inside the blade sections with an inverse design method, loading was enlarged. Higher loading normally results in a reduction of profile incidence range. For compensation a wide chord application was chosen. Compared to the original compressor version, experiments resulted in steeper characteristic curves together with larger usable operating range. Keeping the same outer and inner diameter, mass flow was increased by 6%. Measurements of performance curves with variable speed and for guide vane control are presented. Theoretical calculations achieve a high degree of agreement with measured performance.

Unsteady flow field under surge and rotating stall in a three-stage axial flow compressor

2011 ◽  
Vol 20 (1) ◽  
pp. 6-12 ◽  
Author(s):  
Takayuki Hara ◽  
Daisuke Morita ◽  
Yutaka Ohta ◽  
Eisuke Outa
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Axial Flow ◽  
Rotating Stall ◽  
Axial Flow Compressor ◽  
Flow Compressor

Numerical Investigation of Non-Axisymmetric Endwalls in a High Pressure Axial Flow Turbine

2015 ◽  
Author(s):  
Zhenzhe Na ◽  
Bo Liu
Keyword(s):  
High Pressure ◽  
Flow Field ◽  
Incidence Angle ◽  
Axial Flow ◽  
Field Calculation ◽  
Complex Flow ◽  
Flow Angle ◽  
Optimization System ◽  
Flow Loss ◽  
Stage Performance

In this paper, an optimization system was applied to design the non-axisymmetric endwalls for the stator of a high pressure axial flow turbine. This optimization system combines the endwall parameterization, 3D Navier-Stokes flow field calculation and genetic algorithm based on artificial neural network, which has the advantages of flexible geometry representation and automatic design of the optimal non-axisymmetric endwalls. And, the 3D steady flow field calculation was carried out to analyze the detailed behavior of complex flow structures pre and post optimization and to examine the influences of the optimized endwalls on the stage performance as well. The results of investigation show that the optimized non-axisymmetric endwalls can significantly decrease the flow loss in the stator, but also affect other aerodynamic parameters at the stator exit, especially the flow angle, and then the flow loss at the rotor exit caused by both the passage vortex in the rotor passage and the tip leakage vortex were increased by changing the incidence angle of the rotor due to the non-axisymmetric endwalls. Finally, the stage performance of the HP turbine is not improved as expected.

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