Aerodynamic Optimization Design of a Turbocharger Compressor Impeller

2012 ◽  
Vol 455-456 ◽  
pp. 389-394
Author(s):  
Chun Jun Ji ◽  
Xiao Qing Li
Keyword(s):  
Optimization Design ◽  
Flow Analysis ◽  
Internal Flow ◽  
Design Parameters ◽  
Trial And Error ◽  
Aerodynamic Optimization ◽  
Compressor Impeller ◽  
Final Design ◽  
Compressor Performance ◽  
Design Software

The flow inside the impeller and diffuser of a turbocharger compressor was analyzed numerically in this paper. The results indicate that the internal flow is disturbed and efficiency is low. There exists a big vortex in the diffuser which dissipates a large amount of energy. Based on the commercial design software, different design parameters were optimized by trial-and-error. Numerical flow analysis results of the final design show that the efficiency is increased by 6.26% and internal flow is improved greatly. It can be concluded that the meridian radius of the impeller flow path has great effect on the compressor performance.

Multiobjective Optimization Design of a Pump–Turbine Impeller Based on an Inverse Design Using a Combination Optimization Strategy

2013 ◽  
Vol 136 (1) ◽  
Author(s):  
Wei Yang ◽  
Ruofu Xiao
Keyword(s):  
Response Surface ◽  
Optimization Design ◽  
Design Method ◽  
Inverse Design ◽  
Design Parameters ◽  
Surface Model ◽  
Optimization Strategy ◽  
Pump Turbine ◽  
Combination Optimization ◽  
Final Design

This paper presents an automatic multiobjective hydrodynamic optimization strategy for pump–turbine impellers. In the strategy, the blade shape is parameterized based on the blade loading distribution using an inverse design method. An efficient response surface model relating the design parameters and the objective functions is obtained. Then, a multiobjective evolutionary algorithm is applied to the response surface functions to find a Pareto front for the final trade-off selection. The optimization strategy was used to redesign a scaled pump–turbine. Model tests were conducted to validate the final design and confirm the validity of the design strategy.

scholarly journals THRUST FORCE ANALYSIS OF SPIKE BELL NOZZLE

2013 ◽  
pp. 274-279
Author(s):  
V.GOPALA DEVA KOWSIK ◽  
CHRIS JOSEPH ◽  
M.P.ARUN JUSTIN ◽  
R. SAINATH ◽  
D.THANIKAIVEL MURUGAN ◽  
...  
Keyword(s):  
Mach Number ◽  
Theoretical Approach ◽  
Flow Analysis ◽  
Internal Flow ◽  
Chamber Pressure ◽  
Design Parameters ◽  
Ansys Cfx ◽  
Shaped Nozzle ◽  
Exit Mach Number ◽  
Aerospike Nozzle

Aerospike nozzle is often described as an inside-out bell shaped nozzle and named for its prominent spike located at centre. This project mainly focuses on design of various types of nozzles such as aerospike, truncated aerospike and spike bell nozzles. In theoretical approach, the efficiency of rocket nozzles is calculated with design parameters such as throat area, exit area, chamber pressure and so on. From theoretical approach it is inferred that the spike bell nozzle has an increased value of thrust when compared to other nozzle types. So meshing and internal flow analysis is carried out for spike bell nozzle alone by using ANSYS CFX 13.0 software. From this flow analysis it can be inferred that the exit Mach number of spike bell nozzle comes close to the theoretical design exit Mach number .Also the flow simulations for the spike bell nozzle is carried out for various parameters such as pressure, temperature and velocity.

The CFD Analysis of Internal Flow Field in Turbocharger Compressor

2014 ◽  
Vol 628 ◽  
pp. 279-282 ◽  
Author(s):  
Xiang Ling Liu ◽  
Liao Ping Hu ◽  
Jin Ke Gong ◽  
Jia Qiang E
Keyword(s):  
Flow Field ◽  
Optimization Design ◽  
Gasoline Engine ◽  
Flow Analysis ◽  
Internal Flow ◽  
Field Analysis ◽  
Analysis Model ◽  
Vaneless Diffuser ◽  
Flow Field Analysis ◽  
Cfd Method

In this paper, the 3D flow analysis model of gasoline engine turbocharger compressor was built by using the software NUMECA. The flow fields of the vaneless diffuser and volute, such as airflow velocity field, temperature field, pressure field and the entropy field were simulated. The internal flow performance of the vaneless diffuser and volute were analyzed. The simulation results show that the field changes accord with the compressor characteristics, thus the vaneless diffuser and volute of the compressor design is reasonable. The approach of numerical simulation and flow field analysis by using CFD method can accurately predict the compressor performance. The research methods and conclusions provide theoretical and practical reference for the optimization design of the compressor.

Unsteady flow characteristics and cavitation prediction in the double-suction centrifugal pump using a novel approach

2019 ◽  
Vol 234 (3) ◽  
pp. 283-299 ◽  
Author(s):  
Ji Pei ◽  
Majeed Koranteng Osman ◽  
Wenjie Wang ◽  
Jianping Yuan ◽  
Tingyun Yin ◽  
...  
Keyword(s):  
Centrifugal Pump ◽  
Optimization Design ◽  
Flow Analysis ◽  
Prediction Method ◽  
Internal Flow ◽  
Computational Time ◽  
The Novel ◽  
Centrifugal Pumps ◽  
Pump Design ◽  
Novel Approach

The recent advances in centrifugal pump design do not only require a better suction performance but also there have been attempts to reduce design time at a lower cost. The traditional trial-and-error optimization design method, however, depends on the designer's experience, which requires longer cycles. This is because the computational process of calculating the net positive suction head required (NPSHr) involves several calculation steps and this consumes a lot of computational time. An investigation was therefore carried out to test a novel NPSHr prediction method in a double-suction centrifugal pump using unsteady numerical simulations. In the new approach, a new boundary pair was introduced and an algorithm was used to estimate a good value for a static pressure value that correlates to a 3% drop in pump head to determine the critical cavitation point. Experiments were conducted to validate the hydraulic performance and the cavitation model. The NPSHr and the characteristic “sudden” head-drop were very well predicted by the novel approach in only three simulation steps. The internal flow analysis showed that for 0.6 Q d, the flow around the volute tongue was uneven at NPSH = 10.06 m, inducing flow separation and recirculation at the tongue region. Attached cavities were also observed around the suction ring in the spiral suction domain. The pressure fluctuations were analyzed also and the dominant frequency at the pump outlet and tongue region was the blade passing frequency. Consequently, the novel approach proved very robust and efficient in NPSHr prediction and would be a good alternative to shorten simulation time during cavitation optimization design process in centrifugal pumps.

Low Aspect Ratio Transonic Rotors: Part 1 — Baseline Design and Performance

1992 ◽  
Author(s):  
C. H. Law ◽  
A. R. Wadia
Keyword(s):  
Flow Analysis ◽  
Axial Flow ◽  
Test Point ◽  
Design Parameters ◽  
Design Study ◽  
Baseline Design ◽  
Design Variables ◽  
Compressor Design ◽  
Compressor Performance ◽  
And Performance

The analytical design and experimental test of a single-stage transonic axial-flow compressor are described. This design is the baseline of a compressor design study in which several blade design parameters have been systematically varied to determine their independent effects on compressor performance. The baseline design consisted of ruggedizing an existing compressor design, that demonstrated outstanding aerodynamic performance, to correct some undesirable aeromechanical characteristics. The design study was performed by varying only one design parameter at a time, keeping other design variables as close as possible to the baseline design. Specific design parameters of interest were those for which very little data was available to determine their sensitivity on compressor performance. This paper describes the baseline compressor design and its experimental performance. A detailed definition and flow analysis of the baseline design test point (used as the basis for all subsequent design variations) are provided.

scholarly journals Multipoint and Multiobjective Optimization of a Centrifugal Compressor Impeller Based on Genetic Algorithm

2017 ◽  
Vol 2017 ◽  
pp. 1-18 ◽  
Author(s):  
Xiaojian Li ◽  
Zhengxian Liu ◽  
Yujing Lin
Keyword(s):  
Genetic Algorithm ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Flow Analysis ◽  
Optimization Method ◽  
Aerodynamic Optimization ◽  
Data Mining Technique ◽  
Nsga Ii ◽  
Transonic Compressor ◽  
Compressor Impeller

The design of high efficiency, high pressure ratio, and wide flow range centrifugal impellers is a challenging task. The paper describes the application of a multiobjective, multipoint optimization methodology to the redesign of a transonic compressor impeller for this purpose. The aerodynamic optimization method integrates an improved nondominated sorting genetic algorithm II (NSGA-II), blade geometry parameterization based on NURBS, a 3D RANS solver, a self-organization map (SOM) based data mining technique, and a time series based surge detection method. The optimization results indicate a considerable improvement to the total pressure ratio and isentropic efficiency of the compressor over the whole design speed line and by 5.3% and 1.9% at design point, respectively. Meanwhile, surge margin and choke mass flow increase by 6.8% and 1.4%, respectively. The mechanism behind the performance improvement is further extracted by combining the geometry changes with detailed flow analysis.

Low Aspect Ratio Transonic Rotors: Part 1—Baseline Design and Performance

1993 ◽  
Vol 115 (2) ◽  
pp. 218-225 ◽  
Author(s):  
C. H. Law ◽  
A. R. Wadia
Keyword(s):  
Flow Analysis ◽  
Axial Flow ◽  
Test Point ◽  
Design Parameters ◽  
Design Study ◽  
Baseline Design ◽  
Design Variables ◽  
Compressor Design ◽  
Compressor Performance ◽  
Few Data

The analytical design and experimental test of a single-stage transonic axial-flow compressor are described. This design is the baseline of a compressor design study in which several blade design parameters have been systematically varied to determine their independent effects on compressor performance. The baseline design consisted of ruggedizing an existing compressor design that demonstrated outstanding aerodynamic performance, to correct some undesirable aeromechanical characteristics. The design study was performed by varying only one design parameter at a time, keeping the other design variables as close as possible to the baseline design. Specific design parameters of interest were those for which very few data were available to determine their sensitivity on compressor performance. This paper describes the baseline compressor design and its experimental performance. A detailed definition and flow analysis of the baseline design test point (used as the basis for all subsequent design variations) are provided.

Internal Flow Analysis on Sweeping Jet Actuator

2019 ◽  
Author(s):  
Sushanth Gowda B C ◽  
Vinuth N ◽  
Poornananda T ◽  
Dhanush G J, ◽  
T Paramesh
Keyword(s):  
Flow Analysis ◽  
Internal Flow

scholarly journals Prediction and Evaluation of Waterjet Pump Performance under Nonuniform Inflow Using Parallel Compressor Theory

Water ◽  
2021 ◽  
Vol 13 (1) ◽  
pp. 99
Author(s):  
Puyu Cao ◽  
Rui Zhu
Keyword(s):  
Flow Instability ◽  
Internal Flow ◽  
Weighted Sum ◽  
Pump Performance ◽  
Inlet Velocity ◽  
Inlet Distortion ◽  
Pump Head ◽  
Compressor Performance ◽  
Waterjet Pump ◽  
External Characteristics

Parallel compressor theory (PCT) is commonly used to estimate effects of inlet distortion on compressor performance. As well as compressor, the actual inflow to pump is also nonuniform and unfavorable for performances. Nowadays, insufficient understanding of nonuniform inflow effects on pump performance restricts its development. Therefore, this paper applies PCT to predict external characteristics and evaluate internal flow instability of waterjet pump under nonuniform inflow. According to features of nonuniform inflow, the traditional PCT is modified and makes waterjet pump sub-divided into two circumferential tubes owning same performances but with different inlet velocity (representing nonuniform inflow). Above all, numerical simulation has been conducted to validated the applicability and accuracy of PCT in head prediction of waterjet pump under nonuniform inflow, since area-weighted sum of each tube head (i.e., theoretical pump head) is highly consistent with simulated result. Moreover, based on identifications of when and which tube occurs stall, PCT evaluates four stall behaviors of waterjet pump: partial deep stall, partial stall, pre-stall and full stall. Furthermore, different stall behavior generates different interactions between head variation of each tube, resulting in a multi-segment head curve under nonuniform inflow. The modified PCT with associated physical interpretations are expected to provide a sufficient understanding of nonuniform inflow effects on pump performances.

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