scholarly journals Form-finding as a modelling tool for shaping mechanical components: A feasibility case study of an axial-flow compressor blade

2011 ◽  
Vol 33 (9) ◽  
pp. 2612-2620
Author(s):  
W.J. Lewis ◽  
J.S. Brew ◽  
P. Bryanston-Cross ◽  
J. Nawasra
Keyword(s):  
Axial Flow ◽  
Compressor Blade ◽  
Form Finding ◽  
Axial Flow Compressor ◽  
Mechanical Components ◽  
Flow Compressor

An Implicit Off-Design Deviation Angle Correlation of Axial Flow Compressor Blade Elements

2017 ◽  
Author(s):  
Wu Dong-run ◽  
Teng Jin-fang ◽  
Qiang Xiao-qing ◽  
Feng Jin-zhang
Keyword(s):  
Experimental Data ◽  
Incidence Angle ◽  
High Reliability ◽  
Axial Flow ◽  
Compressor Blade ◽  
Deviation Angle ◽  
Axial Flow Compressor ◽  
New Correlation ◽  
Classical Correlations ◽  
Flow Compressor

This paper applies a new analytical/empirical method to formulate the off-design deviation angle correlation of axial flow compressor blade elements. An implicit function of deviation angle is used to map off-design deviation curves into linear correlations (minimum linear correlation coefficient R = 0.959 in this paper). Solution of the coefficients in the correlation is given through the study of classical theories and statistical analysis of the experimental data. The off-design deviation angle can be calculated numerically. The approach requires only knowledge of the blade element geometry. The comparison among 2 classical correlations and the new correlation proposed in this paper shows the new correlation has minimum error over the entire range of incidence angle while classical correlations show high reliability only in a limited range. Experimental data in this paper is collected from NASA’s open technical reports. Rotors and stators are studied together. Considering there is significant deviation angle variation along spanwise direction, only data at 50% span is studied, if possible. The error among experimental data, statistical regressions of the experimental data, and numerical results based on the new correlation is discussed. It has to be noted that the influence of the flow condition other than incidence angle is only being discussed but with less break through.

Material Optimizations on UAV’s axial flow compressor blade by using FSI Approach

2022 ◽  
Author(s):  
Vijayanandh Raja ◽  
Meenakshi Samy ◽  
Keerthana Nachimuthu ◽  
Samrithi Sathyamoorthy ◽  
Deviparameswari Krishnasamy ◽  
...  
Keyword(s):  
Axial Flow ◽  
Compressor Blade ◽  
Axial Flow Compressor ◽  
Flow Compressor

scholarly journals Numerical simulation of dynamic stall phenomena in axial flow compressor blade rows

1997 ◽  
Author(s):  
C. Rivera ◽  
L. Sankar ◽  
J. Prasad ◽  
C. Rivera ◽  
L. Sankar ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Axial Flow ◽  
Compressor Blade ◽  
Dynamic Stall ◽  
Axial Flow Compressor ◽  
Flow Compressor

Some Practical Aspects of Compressor Blade Vibration

1960 ◽  
Vol 64 (591) ◽  
pp. 117-130 ◽  
Author(s):  
E. K. Armstrong ◽  
R. E. Stevenson
Keyword(s):  
Axial Flow ◽  
Practical Aspect ◽  
Compressor Blade ◽  
Blade Vibration ◽  
Axial Flow Compressor ◽  
Multi Stage ◽  
Complete Failure ◽  
Blade Failure ◽  
Flow Compressor ◽  
The Many

The object of this paper is to set down an overall picture of the practical aspects of compressor blade vibration. In doing so it is inevitable that a certain content is effectively a repeat of other people's contributions to the subject. The authors make no apology for this and offer the paper as a "state of the art" as practised at Bristol Siddeley Engines Ltd. In bringing together the many relevant issues of this problem, it is hoped that a useful presentation is obtained.There is little hesitation in indicating the most obvious and important practical aspect of blade vibration as that of the inherent danger of blade failure and it is known that the axial flow compressor is susceptible to complete failure caused by the fatigue of one blade.The multi-stage axial flow compressor is a highly complex aerodynamic machine with, its early and late stages required to operate over wide ranges of incidence and Mach number conditions. To some extent, of course, use of variable geometry can reduce this to less taxing proportions. The aerodynamic environment of front stages has broad boundaries somewhat wider than those relating to rear stages, while middle blade rows generally operate under sensibly constant conditions. This diminishing “severity” of operation, front, rear to middle stage blading is not unrelated to the incidence of blade vibration problems which shows a similar pattern.

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