Flutter Analysis of a Rotating Blade Row Under Aerodynamic Interaction with a Neighboring Blade Row

2005 ◽  
Author(s):  
Masanobu Namba ◽  
R. Nishino
Keyword(s):  
Rotating Blade ◽  
Aerodynamic Interaction ◽  
Blade Row ◽  
Flutter Analysis

Analysis of the Effect of Multirow and Multipassage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration—Part I: Aerodynamic Excitation

2018 ◽  
Vol 140 (5) ◽  
Author(s):  
Harald Schoenenborn
Keyword(s):  
Three Dimensional ◽  
Forced Response ◽  
Frame Of Reference ◽  
Aerodynamic Damping ◽  
Aerodynamic Interaction ◽  
Blade Row ◽  
Random Mistuning ◽  
Compressor Map ◽  
Response Variation ◽  
Turbomachinery Design

The aeroelastic prediction of blade forcing is still a very important topic in turbomachinery design. Usually, the wake from an upstream airfoil and the potential field from a downstream airfoil are considered as the main disturbances. In recent years, it became evident that in addition to those two mechanisms, Tyler–Sofrin modes, also called scattered or spinning modes, may have a significant impact on blade forcing. It was recently shown in literature that in multirow configurations, not only the next but also the next but one blade row is very important as it may create a large circumferential forcing variation, which is fixed in the rotating frame of reference. In the present paper, a study of these effects is performed on the basis of a quasi three-dimensional (3D) multirow and multipassage compressor configuration. For the analysis, a harmonic balancing code, which was developed by DLR Cologne, is used for various setups and the results are compared to full-annulus unsteady calculations. It is shown that the effect of the circumferentially different blade excitation is mainly contributed by the Tyler–Sofrin modes and not to blade-to-blade variation in the steady flow field. The influence of various clocking positions, coupling schemes and number of harmonics onto the forcing is investigated. It is also shown that along a speed-line in the compressor map, the blade-to-blade forcing variation may change significantly. In addition, multirow flutter calculations are performed, showing the influence of the upstream and downstream blade row onto aerodynamic damping. The effect of these forcing variations onto random mistuning effects is investigated in the second part of the paper.

Flutter Analysis of Contra-Rotating Blade Rows

AIAA Journal ◽  
2006 ◽  
Vol 44 (11) ◽  
pp. 2612-2620 ◽  
Author(s):  
Masanobu Namba ◽  
Ryohei Nishino
Keyword(s):  
Rotating Blade ◽  
Flutter Analysis

Influence of Aerodynamic Loading on Rotor-Stator Aerodynamic Interaction in a Two-Stage Low Pressure Research Turbine

2006 ◽  
Author(s):  
Edward Canepa ◽  
Piergiorgio Formosa ◽  
Davide Lengani ◽  
Daniele Simoni ◽  
Marina Ubaldi ◽  
...  
Keyword(s):  
Turbulence Intensity ◽  
Low Pressure ◽  
Potential Interaction ◽  
Two Stage ◽  
Average Technique ◽  
High Lift ◽  
Second Stage ◽  
Aerodynamic Loading ◽  
Aerodynamic Interaction ◽  
Blade Row

The unsteady flow within a two-stage low-pressure research turbine equipped with high lift profiles has been investigated in detail for three different aerodynamic loading conditions. Experiments have been carried out at low speed. Velocity and turbulence intensity in the blade-to-blade plane at midspan have been measured by means of a crossed hot-wire probe, upstream and downstream of each blade row. The probe has been traversed circumferentially over 1.5 bladings pitch and the phase-locked data acquisition and ensemble average technique have been used to reconstruct the flow in space and time. The effects of multistage configuration have been identified and analyzed by considering the velocity components and turbulence intensity. Potential interaction from the downstream blading in relative motion, periodic wake perturbations from the upstream blading and preceding stage perturbations make the flow in the second stage extremely complex. Overall the flow downstream of rotors is perturbed in space by upstream and downstream stators, while flow downstream of stators is mostly perturbed in time by rotor effects. As expected, high lift profiles are significantly sensitive to incidence variation, with this effect further enhanced by the multistage cumulative interactions.

The interaction between a high-frequency gust and a blade row

1992 ◽  
Vol 241 ◽  
pp. 261-289 ◽  
Author(s):  
N. Peake
Keyword(s):  
Flat Plates ◽  
Rotating Blade ◽  
Reduced Frequency ◽  
Blade Row ◽  
Method Of Solution ◽  
Physical Insight ◽  
Formal Limit ◽  
Underlying Mechanisms ◽  
High Level ◽  
Unsteady Lift

The ingestion of convected vorticity by a high-solidity rotating blade row is a potent noise source in modern aeroengines, due largely to the high level of mutual aerodynamic interactions between adjacent blades. In order to model this process we solve the problem of determining the unsteady lift on an infinite cascade of finite-chord flat plates due to an incident vorticity wave. The method of solution is the Wiener–Hopf technique, and we consider the case of the reduced frequency, Ω, being large, allowing application of asymptotic analysis in the formal limit Ω → ∞. This approach yields considerable simplification, both in allowing the truncation of an infinite reflection series to just two terms, and in allowing algebraic expressions for the Wiener–Hopf split functions to be found. The unsteady lift distribution is derived in closed form, and the accuracy of the asymptotic Wiener–Hopf factorization demonstrated for even modest values of Ω by comparison with exact (but less tractable) methods. Our formulae can easily be incorporated into existing noise prediction codes: the advantage of our scheme is that it handles a regime in which conventional numerical approaches become unwieldy, as well as providing significant physical insight into the underlying mechanisms.

scholarly journals NUMERICAL SIMULATION OF THE ACOUSTIC WAVE REFLECTION FROM A ROTATING BLADE ROW

2018 ◽  
pp. 5-15 ◽  
Author(s):  
Nikolay Shuvaev ◽  
◽  
Aleksandr Siner ◽  
Nikita Bolshagin ◽  
Ruslan Kolegov ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Acoustic Wave ◽  
Wave Reflection ◽  
Rotating Blade ◽  
Blade Row

The Unsteady Response of a Blade Row From Measurements of the Time-Mean Total Pressure

1973 ◽  
Author(s):  
R. E. Henderson
Keyword(s):  
Experimental Data ◽  
Theoretical Analysis ◽  
Total Pressure ◽  
Theoretical Data ◽  
Two Dimensional ◽  
Interference Effects ◽  
Experimental Procedure ◽  
Rotating Blade ◽  
Reduced Frequency ◽  
Blade Row

An experimental procedure is described which permits the unsteady response of a rotating blade row to spatial variations in its inlet flow to be determined from measurements of the time-mean total pressure. This procedure has been employed to determine the unsteady circulation of a non-lifting rotor as a function of reduced frequency for two values of space-chord ratio. Comparisons of these experimental data are made with a recent theoretical analysis of the indirect or design problem of unsteady lift in a moving two-dimensional cascade. Both the experimental and theoretical data are shown to exhibit the same trends with variations in space-chord ratio and reduced frequency. These results demonstrate that the unsteady blade interference effects are significant, and that the representation of the unsteady response of a turbomachine blade row as an isolated airfoil is not valid for reduced frequencies less than 1.2.

Influence of Aerodynamic Loading on Rotor-Stator Aerodynamic Interaction in a Two-Stage Low Pressure Research Turbine

2006 ◽  
Vol 129 (4) ◽  
pp. 765-772 ◽  
Author(s):  
Edward Canepa ◽  
Piergiorgio Formosa ◽  
Davide Lengani ◽  
Daniele Simoni ◽  
Marina Ubaldi ◽  
...  
Keyword(s):  
Turbulence Intensity ◽  
Low Pressure ◽  
Potential Interaction ◽  
Two Stage ◽  
Average Technique ◽  
High Lift ◽  
Second Stage ◽  
Aerodynamic Loading ◽  
Aerodynamic Interaction ◽  
Blade Row

The unsteady flow within a two-stage low-pressure research turbine equipped with high lift profiles has been investigated in detail for three different aerodynamic loading conditions. Experiments have been carried out at low speed. Velocity and turbulence intensity in the blade-to-blade plane at midspan have been measured by means of a crossed hot-wire probe, upstream and downstream of each blade row. The probe has been traversed circumferentially over 1.5 bladings pitch and the phase-locked data acquisition and ensemble average technique have been used to reconstruct the flow in space and time. The effects of multistage configuration have been identified and analyzed by considering the velocity components and turbulence intensity. Potential interaction from the downstream blading in relative motion, periodic wake perturbations from the upstream blading and preceding stage perturbations make the flow in the second stage extremely complex. Overall the flow downstream of rotors is perturbed in space by upstream and downstream stators, while flow downstream of stators is mostly perturbed in time by rotor effects. As expected, high lift profiles are significantly sensitive to incidence variation, with this effect further enhanced by the multistage cumulative interactions.

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