Variation of aerodynamic damping of vibrations of a plane grid of compressor-blade models, with angle of attack

1974 ◽  
Vol 6 (4) ◽  
pp. 464-467
Author(s):  
A. A. Kaminer ◽  
N. Ya. Nastenko
Keyword(s):  
Angle Of Attack ◽  
Compressor Blade ◽  
Aerodynamic Damping ◽  
Plane Grid ◽  
Damping Of Vibrations

Aerodynamic damping of vibrations in rotor blades

1986 ◽  
Vol 80 (3) ◽  
pp. 997-997
Author(s):  
Brian Barry ◽  
Christopher Freeman
Keyword(s):  
Rotor Blades ◽  
Aerodynamic Damping ◽  
Damping Of Vibrations

Influence of the Tip Clearance on a Compressor Blade Aerodynamic Damping

2017 ◽  
Vol 33 (1) ◽  
pp. 227-233 ◽  
Author(s):  
Fanny M. Besem ◽  
Robert E. Kielb
Keyword(s):  
Compressor Blade ◽  
Tip Clearance ◽  
Aerodynamic Damping

Rig Testing of the Operability of a Transonic Compressor Blade of an Industrial Gas Turbine

2019 ◽  
Author(s):  
Hyunsu Kang ◽  
Sungjong Ahn ◽  
Kyusic Hwang ◽  
Justin Bock ◽  
Jeongseek Kang ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Large Scale ◽  
Load Condition ◽  
Compressor Blade ◽  
Guide Vanes ◽  
Aerodynamic Damping ◽  
Transonic Compressor ◽  
Full Speed ◽  
Industrial Gas Turbine

Abstract This paper describes the flow and vibrations measured in a 1.5-stage transonic research compressor tested at the Notre Dame Turbomachinery Laboratory. The compressor is a sub-scale version of a large-scale industrial gas turbine. The experiment measured the compressor performance and investigated the operability issues of stall and flow-induced blade vibrations due to buffet and flutter. The buffet was investigated at full-speed with fully-closed inlet guide vanes; the full-speed, no-load condition of gas turbines used for power generation. The flutter was investigated at part-speed conditions with partially closed guide vanes; the part-power condition where stall flutter typically occurs for aero-engines. At both of these conditions the blades operate with high incidence and moderate velocity, which can result in flow-induced vibrations. Aero-elastic simulations were performed to predict the flutter boundary. The flutter analysis predicted positive aerodynamic damping near the operating line, and a decrease in aerodynamic damping as the stall boundary was approached. No flutter was observed in the stable operating range of the compressor. The experimental campaign used blade tip timing to measure the vibrations and unsteady pressure transducers above the compressor blade. These two types of data were correlated to better understand the drivers of vibration. The paper describes the behavior of the aerodynamic drivers of buffet and flutter and the resulting vibration.

Application of Aeroelastic Methods in Compressor Cascade Configurations Using Commercial Code Coupling

2008 ◽  
Author(s):  
Sven Schrape ◽  
Jens Nipkau ◽  
Arnold Ku¨hhorn ◽  
Bernd Beirow
Keyword(s):  
Compressor Blade ◽  
Two Dimensional ◽  
Compressor Cascade ◽  
Aerodynamic Damping ◽  
High Pressure Compressor ◽  
Commercial Code ◽  
Bending Mode ◽  
Blade Vibrations ◽  
Coupling Approach ◽  
Pressure Compressor

This paper presents the results of fluid structure coupled simulations of compressor blade vibrations of two compressor cascade configurations in order to determine aeroelastic parameters such as aerodynamic damping and the corresponding frequency shift. Therefore a partitioned code coupling approach was employed in order to couple the FE-code ABAQUS with the CFD-code FLUENT via MpCCI (Mesh based Code Coupling Interface) developed by Fraunhofer SCAI. The code coupling is used to compute the unsteady, two-dimensional, inviscid and viscid flow around a NACA 3506 airfoil for blade vibrations in a torsional modeshape. This first example is used to validate the results against results from literature. Further on the unsteady, two-dimensional, viscid flow around a research high-pressure compressor airfoil is computed for a bending mode. The results of those computations are implemented into a simplified, structural blisk model approximating the air flow influence by a mechanical model.

Some Vibration Characteristics of Pin-Fixed Compressor Blades

1967 ◽  
Vol 89 (4) ◽  
pp. 491-501 ◽  
Author(s):  
J. I. Goatham ◽  
G. T. Smailes
Keyword(s):  
Stress Distribution ◽  
Natural Frequencies ◽  
Compressor Blade ◽  
Vibration Characteristics ◽  
Bending Stress ◽  
Compressor Blades ◽  
Blade Vibration ◽  
Aerodynamic Damping ◽  
Modes Of Vibration ◽  
Critical Direction

The nature of some of the modes of vibration of blades having a free-pin attachment is discussed, with particular reference to expected positions of failure, bending-stress distribution, and calculation of natural frequencies. Some aspects of aerodynamic damping and prediction of amplitudes in distorted flow are also treated, and a critical direction of blade vibration is indicated and shown to exist in a particular mode of a compressor blade.

scholarly journals Analytical model for instantaneous lift and shape deformation of an insect-scale flapping wing in hover

2014 ◽  
Vol 11 (101) ◽  
pp. 20140933 ◽  
Author(s):  
Chang-kwon Kang ◽  
Wei Shyy
Keyword(s):  
Structural Dynamics ◽  
A Priori ◽  
Angle Of Attack ◽  
Beam Equation ◽  
High Lift ◽  
Aerodynamic Damping ◽  
Fluid Physics ◽  
Effective Angle ◽  
Unsteady Fluid ◽  
Wing Deformation

In the analysis of flexible flapping wings of insects, the aerodynamic outcome depends on the combined structural dynamics and unsteady fluid physics. Because the wing shape and hence the resulting effective angle of attack are a priori unknown, predicting aerodynamic performance is challenging. Here, we show that a coupled aerodynamics/structural dynamics model can be established for hovering, based on a linear beam equation with the Morison equation to account for both added mass and aerodynamic damping effects. Lift strongly depends on the instantaneous angle of attack, resulting from passive pitch associated with wing deformation. We show that both instantaneous wing deformation and lift can be predicted in a much simplified framework. Moreover, our analysis suggests that resulting wing kinematics can be explained by the interplay between acceleration-related and aerodynamic damping forces. Interestingly, while both forces combine to create a high angle of attack resulting in high lift around the midstroke, they offset each other for phase control at the end of the stroke.

Positioning the Angle of Attack Sensor on an Unmanned Aerial Vehicle Wing

2016 ◽  
Vol 3 (1) ◽  
pp. 25-33
Author(s):  
Amir Birjandi ◽  
◽  
Valentin Guerry ◽  
Eric Bibeau ◽  
Hamidreza Bolandhemmat ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Angle Of Attack ◽  
Aerial Vehicle

AXISYMMETRIC BODY AT AN ANGLE OF ATTACK IN HYPERSONIC FLOW: HEAT PROBLEM

2015 ◽  
Vol 46 (2) ◽  
pp. 107-121
Author(s):  
Vyacheslav Antonovich Bashkin ◽  
Ivan Vladimirovich Egorov ◽  
Ivan Valeryevich Ezhov
Keyword(s):  
Hypersonic Flow ◽  
Angle Of Attack ◽  
Axisymmetric Body ◽  
Heat Problem ◽  
Flow Heat
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