Three-dimensional Inverse Design of Centrifugal Impeller Blade

2015 ◽  
Author(s):  
Li Sun ◽  
Jie Chen ◽  
Guoping Huang
Keyword(s):  
Three Dimensional ◽  
Inverse Design ◽  
Centrifugal Impeller ◽  
Impeller Blade

An Approximate Three-Dimensional Aerodynamic Design Method for Centrifugal Impeller Blades

1990 ◽  
Vol 112 (1) ◽  
pp. 44-49 ◽  
Author(s):  
Zhao Xiaolu ◽  
Qin Lisen
Keyword(s):  
Centrifugal Compressor ◽  
Design Method ◽  
Fluid Dynamic ◽  
Three Dimensional ◽  
Design Procedure ◽  
Taylor Series Expansion ◽  
Centrifugal Impeller ◽  
Aerodynamic Design ◽  
Impeller Blade ◽  
Blade Geometry

An aerodynamic design method, which is based on the Mean Stream Surface Method (MSSM), has been developed for designing centrifugal compressor impeller blades. As a component of a CAD system for centrifugal compressor, it is convenient to use the presented method for generating impeller blade geometry, taking care of manufacturing as well as aerodynamic aspects. The design procedure starts with an S2m indirect solution. Afterward from the specified S2m surface, by the use of Taylor series expansion, the blade geometry is generated by straight-line elements to meet the manufacturing requirements. Simultaneously, the fluid dynamic quantities across the blade passage can be determined directly. In terms of these results, the designer can revise the distribution of angular momentum along the shroud and hub, which are associated with blade loading, to get satisfactory velocities along the blade surfaces in order to avoid or delay flow separation.

Non-Periodic 3D Diffusers for Mitigating Aerodynamic Exciters

2014 ◽  
Author(s):  
Mikhail Grigoriev ◽  
James Hitt
Keyword(s):  
Energy Distribution ◽  
Three Dimensional ◽  
Leading Edge ◽  
Great Majority ◽  
Temporal Variations ◽  
Centrifugal Impeller ◽  
Pressure Waves ◽  
Impeller Blade ◽  
Wide Range ◽  
Leading Edges

The great majority of the modern centrifugal stages utilize periodic stationary structures such as inlet guide vanes and/or diffuser vanes. To maximize the aerodynamic performance of the centrifugal stage, these vanes must be positioned at a close proximity of the centrifugal impeller. This arrangement results in a dramatic interaction between rotating impeller and stationary vanes due to reflection of the pressure waves from the periodic vanes back onto the impeller blades. The periodic nature of the reflected pressure waves may lead to an excitation of the impeller blade eigenmodes if the fundamental frequency (or, its multiple) of the external force matches with the natural frequency of the subject impeller. As the impeller blades provide very little to no damping, there is a strong possibility of the high cycle fatigue resonance failure of the impeller blades if the impeller design does not provide with a sufficient separation from the resonance modes. We should note that ensuring such a separation is not straightforward task for many stages with periodic exciters, and may not be even feasible for some practical design cases. This presentation focuses on a novel way to mitigate possible resonance issues for centrifugal impellers due to pressure reflection waves emanating from the diffuser blades. We propose to utilize non-periodic centrifugal diffuser together with the sculpting leading edges for the three-dimensional diffuser vanes. In order to demonstrate the attractiveness and feasibility of this approach, we have utilized Computational Fluid Dynamics (CFD) tools to perform time-accurate unsteady turbulent flow analyses in centrifugal stages and capture cyclic pressure waves acting on the impeller blades. The present work considers a regular periodic low-solidity diffuser with two-dimensional vanes, a three-dimensional periodic diffuser with a sculpted leading edge, and, finally, a non-periodic three-dimensional diffuser with an unequal, non-repeating stagger. We have utilized eighteen CFD pressure probes located on the impeller blade pressure and suction sides to monitor temporal variations of the static pressure that capture the pressure reflection waves from the diffuser vanes. The Fourier series decomposition facilitates detailed analyses of the pressure energy distribution over a wide range of frequencies. The results of the numerical studies demonstrate that even the use of the periodic diffuser with 3D sculpted leading edges help reduce the magnitude of the pressure oscillations at the dominant frequency and its integer multiples. However, the pressure energy distribution changes dramatically when using the non-periodic diffuser arrangement together with the sculpted leading edge vanes. The strength of the pressure waves associated with the dominant harmonics and its integer multiples are reduced about 30% to 85% and spread over the frequencies that constitute integer multiples of the fundamental impeller frequency. This pressure energy redistribution of the 3D non-periodic diffuser is a significant aid to the aerodynamicist. By significantly reducing the mechanical constraint compromises, the designer is allowed to focus more on aerodynamic component efficiency.

A Study on the Effects of Blade Thickness on the Performance of Low Specific Speed Centrifugal Pump

2014 ◽  
Vol 1070-1072 ◽  
pp. 1957-1962 ◽  
Author(s):  
Yong Xin Jin ◽  
Wen Wu Song ◽  
Fu Jie
Keyword(s):  
Centrifugal Pump ◽  
Three Dimensional ◽  
Leaf Thickness ◽  
Centrifugal Impeller ◽  
Flow Area ◽  
Impeller Blade ◽  
Performance Effect ◽  
Blade Thickness ◽  
Low Specific Speed ◽  
Specific Speed

The effects of blade thickness on impeller performance is seldom considered when design the low specific speed centrifugal pump and only considered crowding coefficient when use the speed coefficient method calculate the head of the impeller was designed. It was didn't consider the fundamental relationship how leaf thickness and low specific speed centrifugal impeller performance effect each other. The three-dimensional of flow area would have large influence if the leaf thickness changes . Here the best true thickness of the low specific speed centrifugal impeller blade was obtained though study how the thickness of blade influence on the performance of low specific speed centrifugal pump.

Inverse Design of Radial Compressor Components by Modern CFD

2000 ◽  
Author(s):  
R. A. Van den Braembussche ◽  
J. Antolin ◽  
R. Thygesen
Keyword(s):  
Velocity Distribution ◽  
Inverse Method ◽  
Three Dimensional ◽  
Inverse Methods ◽  
Inverse Design ◽  
Centrifugal Impeller ◽  
Design Criteria ◽  
Radial Compressor ◽  
Inlet Guide Vanes ◽  
Return Channel

Abstract The use of a three-dimensional inverse method for the design of inlet guide vanes, a centrifugal impeller and return channel is demonstrated. The geometry of the different components are iteratively defined until a prescribed velocity distribution is obtained. The procedure and design criteria for each component are described and the final result is presented. The advantages, disadvantages and problems related to the use of inverse methods are discussed.

The influence of the trailing edge angle of the micro centrifugal impeller on the performance of the centrifugal compressor

2021 ◽  
pp. 1-15
Author(s):  
Xu Yu-dong ◽  
Li Cong ◽  
Lv Qiong-ying ◽  
Zhang Xin-ming ◽  
Mu Guo-zhen
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Centrifugal Impeller ◽  
Centrifugal Compressors ◽  
Trailing Edge ◽  
Sweep Angle ◽  
Impeller Blade ◽  
Bending Angle ◽  
Edge Angle ◽  
Isentropic Efficiency

In order to study the effect of the trailing edge sweep angle of the centrifugal impeller on the aerodynamic performance of the centrifugal compressor, 6 groups of centrifugal impellers with different bending angles and 5 groups of different inclination angles were designed to achieve different impeller blade trailing edge angle. The computational fluid dynamics (CFD) method was used to simulate and analyze the flow field of centrifugal compressors with different blade shapes under design conditions. The research results show that for transonic micro centrifugal compressors, changing the blade trailing edge sweep angle can improve the compressor’s isentropic efficiency and pressure ratio. The pressure ratio of the compressor shows a trend of increasing first and then decreasing with the increase of the blade bending angle. When the blade bending angle is 45°, the pressure ratio of the centrifugal compressor reaches a maximum of 1.69, and the isentropic efficiency is 67.3%. But changing the inclination angle of the blade trailing edge has little effect on the isentropic efficiency and pressure ratio. The sweep angle of blade trailing edge is an effective method to improve its isentropic efficiency and pressure ratio. This analysis method provides a reference for the rational selection of the blade trailing edge angle, and provides a reference for the design of micro centrifugal compressors under high Reynolds numbers.

The Extension of a Solution-Adaptive Three-Dimensional Navier–Stokes Solver Toward Geometries of Arbitrary Complexity

1993 ◽  
Vol 115 (2) ◽  
pp. 283-295 ◽  
Author(s):  
W. N. Dawes
Keyword(s):  
Guide Vane ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Centrifugal Impeller ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
Wide Range ◽  
Nozzle Guide Vane ◽  
Recent Developments ◽  
Nozzle Guide

This paper describes recent developments to a three-dimensional, unstructured mesh, solution-adaptive Navier–Stokes solver. By adopting a simple, pragmatic but systematic approach to mesh generation, the range of simulations that can be attempted is extended toward arbitrary geometries. The combined benefits of the approach result in a powerful analytical ability. Solutions for a wide range of flows are presented, including a transonic compressor rotor, a centrifugal impeller, a steam turbine nozzle guide vane with casing extraction belt, the internal coolant passage of a radial inflow turbine, and a turbine disk cavity flow.

Optimization and Investigation on the Impact of Centrifugal Impeller Blade Thickness Distribution on Hydro-Induced Vibration

2018 ◽  
Author(s):  
B. Qian ◽  
D. Z. Wu
Keyword(s):  
Secondary Flow ◽  
Thickness Distribution ◽  
Suction Side ◽  
Centrifugal Impeller ◽  
Impeller Blade ◽  
Streamwise Location ◽  
Unbalanced Rotor ◽  
Blade Thickness ◽  
Vibration Performance ◽  
The Impact

The vibration performance of centrifugal impellers is of great importance for pumps in some application areas such as automobiles and ships. Apart from mechanical excitations for instance, unbalanced rotor and misalignment, attentions should be concentrated on the hydraulic excitations. The complex internal secondary flow in the centrifugal impeller brings degradation on both hydraulic and vibration performances. On the purpose of repressing the internal secondary flow and alleviating vibration, an attempt of optimization by controlling the thickness distribution of centrifugal impeller blade is given. The vibration performances of the impellers are investigated numerically and experimentally. Meanwhile, further study on the mechanism of the influence of the thickness distribution optimization on vibration is conducted. There is a relative velocity gradient from suction side (SS) to pressure side (PS) due to the Coriolis force, which causes non-uniformity of energy distribution. By means of thickness distribution optimization, the impeller blade angle on the PS and SS along the blade-aligned (BA) streamwise location is respectively modified and therefore the flow field can be improved.

Inverse Design of 3D Multi-Stage Transonic Fans at Dual Operating Points

2013 ◽  
Author(s):  
James H. Page ◽  
Paul Hield ◽  
Paul G. Tucker
Keyword(s):  
Design Method ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Inverse Design ◽  
Flow Angle ◽  
Trade Offs ◽  
Multi Stage ◽  
Full Speed ◽  
Computational Fluid Dynamics Cfd ◽  
Operating Points

Semi-inverse design is the automatic re-cambering of an aerofoil, during a computational fluid dynamics (CFD) calculation, in order to achieve a target lift distribution while maintaining thickness, hence “semi-inverse”. In this design method, the streamwise distribution of curvature is replaced by a stream-wise distribution of lift. The authors have developed an inverse design code based on the method of Hield (2008) which can rapidly design three-dimensional fan blades in a multi-stage environment. The algorithm uses an inner loop to design to radially varying target lift distributions, an outer loop to achieve radial distributions of stage pressure ratio and exit flow angle, and a choked nozzle to set design mass flow. The code is easily wrapped around any CFD solver. In this paper, we describe a novel algorithm for designing simultaneously for specified performance at full speed and peak efficiency at part speed, without trade-offs between the targets at each of the two operating points. We also introduce a novel adaptive target lift distribution which automatically develops discontinuous changes of calculated magnitude, based on the passage shock, eliminating erroneous lift demands in the shock vicinity and maintaining a smooth aerofoil.

Hydrodynamic Design System for Pumps Based on 3-D CAD, CFD, and Inverse Design Method

2002 ◽  
Vol 124 (2) ◽  
pp. 329-335 ◽  
Author(s):  
Akira Goto ◽  
Motohiko Nohmi ◽  
Takaki Sakurai ◽  
Yoshiyasu Sogawa
Keyword(s):  
Computer Aided Design ◽  
High Performance ◽  
Design Method ◽  
High Reliability ◽  
Secondary Flows ◽  
System Structure ◽  
Inverse Design ◽  
Design System ◽  
Centrifugal Impeller ◽  
Inverse Design Method

A computer-aided design system has been developed for hydraulic parts of pumps including impellers, bowl diffusers, volutes, and vaned return channels. The key technologies include three-dimensional (3-D) CAD modeling, automatic grid generation, CFD analysis, and a 3-D inverse design method. The design system is directly connected to a rapid prototyping production system and a flexible manufacturing system composed of a group of DNC machines. The use of this novel design system leads to a drastic reduction of the development time of pumps having high performance, high reliability, and innovative design concepts. The system structure and the design process of “Blade Design System” and “Channel Design System” are presented. Then the design examples are presented briefly based on the previous publications, which included a centrifugal impeller with suppressed secondary flows, a bowl diffuser with suppressed corner separation, a vaned return channel of a multistage pump, and a volute casing. The results of experimental validation, including flow fields measurements, were also presented and discussed briefly.

scholarly journals Three-Dimensional Inverse Design Method for Hydraulic Machinery

Energies ◽  
2019 ◽  
Vol 12 (17) ◽  
pp. 3210
Author(s):  
Wei Yang ◽  
Benqing Liu ◽  
Ruofu Xiao
Keyword(s):  
High Performance ◽  
Design Method ◽  
Three Dimensional ◽  
Inverse Design ◽  
Blade Loading ◽  
Hydraulic Machinery ◽  
Main Challenge ◽  
Blade Shape ◽  
Stacking Condition ◽  
Inverse Design Method

Hydraulic machinery with high performance is of great significance for energy saving. Its design is a very challenging job for designers, and the inverse design method is a competitive way to do the job. The three-dimensional inverse design method and its applications to hydraulic machinery are herein reviewed. The flow is calculated based on potential flow theory, and the blade shape is calculated based on flow-tangency condition according to the calculated flow velocity. We also explain flow control theory by suppression of secondary flow and cavitation based on careful tailoring of the blade loading distribution and stacking condition in the inverse design of hydraulic machinery. Suggestions about the main challenge and future prospective of the inverse design method are given.

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