Analysis on Flutter Characteristics of Transonic Compressor Blade Row by a Fluid-Structure Coupled Method

Zhang, Mingming; Hou, Anping; Zhou, Sheng; Yang, Xiaodong

doi:10.1115/gt2012-69439

Cited by 9 publications

(9 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…As the non-synchronous blade vibration phenomenon involves the coupling of unsteady flows and blade structures, the time-domain fluid structure coupling simulations [ 31 ] are solved in this paper. The full annulus configuration model is adopted to capture the detailed NSV with flow excitation.…”

Section: Descriptions Of Numerical Methodologymentioning

confidence: 99%

Investigation on the Mechanism and Parametric Description of Non-Synchronous Blade Vibration

Zhang

Hou

Han

2021

Entropy

Self Cite

View full text Add to dashboard Cite

In order to explore the mechanism during the process of the non-synchronous vibration (NSV), the flow field formation development is investigated in this paper. Based on the fluid–structure interaction method, the vibration of rotor blades is found to be in the first bending mode with a non-integral order (4.6) of the rotation speed. Referring to the constant inter blade phase angle (IBPA), the appearances of frequency-locking and phase-locking can be identified for the NSV. A periodical instability flow emerges in the tip region with the mixture of separation vortex and tip leakage flow. Due to the nonlinearities of fluid and structure, the blade vibration exhibits a limit cycle oscillation (LCO) response. The separation vortex presenting a spiral structure propagates in the annulus, indicating a pattern as modal oscillation. A flow induced vibration is initiated by the spiral vortex in the tip. The large pressure oscillation caused by the movement of the spiral vortex is regarded as a main factor for the presented NSV. As the oscillation of blade loading occurs with blade rotating pass the disturbances, the intensity of the reverse leakage flow in adjacent channels also plays a crucial role in the blade vibration.

show abstract

Section: Descriptions Of Numerical Methodologymentioning

confidence: 99%

Investigation on the Mechanism and Parametric Description of Non-Synchronous Blade Vibration

Zhang

Hou

Han

2021

Entropy

Self Cite

View full text Add to dashboard Cite

show abstract

“…The unsteady flow field in the compressor was solved by using the numerical solution of 3-D Navier-Stokes equations adopted in software ANSYS Package. The spatial discretization of the flow governing equations was employed on an upwind scheme, and a second-order backward differencing was integrated for the time-accurate solution [35]. Boundary conditions imposed on the inlet consist of total pressure and total temperature.…”

Section: Data Collection For Machine Learningmentioning

confidence: 99%

Study on the Intelligent Modeling of the Blade Aerodynamic Force in Compressors Based on Machine Learning

2021

Self Cite

View full text Add to dashboard Cite

In order to obtain the aerodynamic loads of the vibrating blades efficiently, the eXterme Gradient Boosting (XGBoost) algorithm in machine learning was adopted to establish a three-dimensional unsteady aerodynamic force reduction model. First, the database for the unsteady aerodynamic response during the blade vibration was acquired through the numerical simulation of flow field. Then the obtained data set was trained by the XGBoost algorithm to set up the intelligent model of unsteady aerodynamic force for the three-dimensional blade. Afterwards, the aerodynamic load could be gained at any spatial location during blade vibration. To evaluate and verify the reliability of the intelligent model for the blade aerodynamic load, the prediction results of the machine learning model were compared with the results of Computation Fluid Dynamics (CFD). The determination coefficient R2 and the Root Mean Square Error (RMSE) were introduced as the model evaluation indicators. The results show that the prediction results based on the machine learning model are in good agreement with the CFD results, and the calculation efficiency is significantly improved. The results also indicate that the aerodynamic intelligent model based on the machine learning method is worthy of further study in evaluating the blade vibration stability.

show abstract

“…According to the number of blades in each row and the mistuning distribution of the guide vanes in the 1.5 stage high speed turbocompressor, the research object is simplified to a half annulus configuration model. As the non-synchronous vibration phenomenon of the turbocompressor involves the coupling of unsteady vortex flow and blade vibration, this paper adopts the time-domain fluid structure coupling iterative numerical simulation method [ 29 , 30 ] to reveal the detailed mechanism of NSV. The commercial CFD software ANSYS Package is used for the current calculation.…”

Section: Descriptions Of Numerical Approachmentioning

confidence: 99%

Investigation on the Flow Field Entropy Structure of Non-Synchronous Blade Vibration in an Axial Turbocompressor

Zhang

Hou

2020

Entropy

Self Cite

View full text Add to dashboard Cite

In order to explore the inducing factors and mechanism of the non-synchronous vibration, the flow field structure and its formation mechanism in the non-synchronous vibration state of a high speed turbocompressor are discussed in this paper, based on the fluid–structure interaction method. The predicted frequencies fBV (4.4EO), fAR (9.6EO) in the field have a good correspondence with the experimental data, which verify the reliability and accuracy of the numerical method. The results indicate that, under a deviation in the adjustment of inlet guide vane (IGV), the disturbances of pressure in the tip diffuse upstream and downstream, and maintain the corresponding relationship with the non-synchronous vibration frequency of the blade. An instability flow that developed at the tip region of 90% span emerged due to interactions among the incoming main flow, the axial separation backflow, and the tip leakage vortices. The separation vortices in the blade passage mixed up with the tip leakage flow reverse at the trailing edge of blade tip, presenting a spiral vortex structure which flows upstream to the leading edge of the adjacent blade. The disturbances of the spiral vortexes emerge to rotate at 54.5% of the rotor speed in the same rotating direction as a modal oscillation. The blade vibration in the turbocompressor is found to be related to the unsteadiness of the tip flow. The large pressure oscillation caused by the movement of the spiral vortex is regarded as the one of the main drivers for the non-synchronous vibration for the present turbocompressor, besides the deviation in the adjustment of IGV.

show abstract

Analysis on Flutter Characteristics of Transonic Compressor Blade Row by a Fluid-Structure Coupled Method

Cited by 9 publications

References 0 publications

Investigation on the Mechanism and Parametric Description of Non-Synchronous Blade Vibration

Investigation on the Mechanism and Parametric Description of Non-Synchronous Blade Vibration

Study on the Intelligent Modeling of the Blade Aerodynamic Force in Compressors Based on Machine Learning

Investigation on the Flow Field Entropy Structure of Non-Synchronous Blade Vibration in an Axial Turbocompressor

Contact Info

Product

Resources

About