scholarly journals Flow structure interaction around an axial-flow hydrokinetic turbine: Experiments and CFD simulations

2014 ◽  
Vol 555 ◽  
pp. 012097
Author(s):  
S Kang ◽  
L Chamorro ◽  
C Hill ◽  
R Arndt ◽  
F Sotiropoulos
Keyword(s):  
Flow Structure ◽  
Axial Flow ◽  
Cfd Simulations ◽  
Structure Interaction ◽  
Hydrokinetic Turbine

Wet Modal Analysis of Wire-Wrapped Fuel Rod With the Axial Flow

2017 ◽  
Author(s):  
Haidong Liu ◽  
Deqi Chen ◽  
Lian Hu
Keyword(s):  
Modal Analysis ◽  
Elastic Strain ◽  
Axial Flow ◽  
Added Mass ◽  
The Finite Element Method ◽  
Cfd Simulations ◽  
Modal Shape ◽  
Inlet Velocity ◽  
Structure Interaction ◽  
Fuel Rod

Dynamic characteristics of wire-wrapped fuel rod was studied when the structure was coupled with fluid. In this paper, the wet modal analysis of wire-wrapped fuel rod in the axial flow was investigated by using the finite element method, which relied on fluid-structure interaction calculation. This numerical simulation is compared to experiments in the literature and the results agree well. The Lead-Bismuth Eutectic (LBE) was used as the working fluids. The CFD Simulations of a wire-wrapped fuel rod were performed with different boundary conditions. By comparing the modal characteristics of the fuel rod in the LBE and in vacuum, the results showed that the added mass of the fluid has important effect on vibration frequency of the wire-wrapped fuel rod. The different three frequencies and modal shape can be obtained under the different inlet velocity. According to the simulation result, it could be found that the maximal equivalent elastic strain occurred in the constrained end.

Influence of Leading Edge Fillet and Nonaxisymmetric Contoured Endwall on Turbine NGV Exit Flow Structure and Interactions With the Rim Seal Flow

2013 ◽  
Author(s):  
Özhan H. Turgut ◽  
Cengiz Camcı
Keyword(s):  
Flow Structure ◽  
Total Pressure ◽  
Guide Vane ◽  
Axial Flow ◽  
Leading Edge ◽  
Turbine Rotor ◽  
Rotor Blades ◽  
Constant Thickness ◽  
Computational Evaluation ◽  
Nozzle Guide

Three different ways are employed in the present paper to reduce the secondary flow related total pressure loss. These are nonaxisymmetric endwall contouring, leading edge (LE) fillet, and the combination of these two approaches. Experimental investigation and computational simulations are applied for the performance assessments. The experiments are carried out in the Axial Flow Turbine Research Facility (AFTRF) having a diameter of 91.66cm. The NGV exit flow structure was examined under the influence of a 29 bladed high pressure turbine rotor assembly operating at 1300 rpm. For the experimental measurement comparison, a reference Flat Insert endwall is installed in the nozzle guide vane (NGV) passage. It has a constant thickness with a cylindrical surface and is manufactured by a stereolithography (SLA) method. Four different LE fillets are designed, and they are attached to both cylindrical Flat Insert and the contoured endwall. Total pressure measurements are taken at rotor inlet plane with Kiel probe. The probe traversing is completed with one vane pitch and from 8% to 38% span. For one of the designs, area averaged loss is reduced by 15.06%. The simulation estimated this reduction as 7.11%. Computational evaluation is performed with the rotating domain and the rim seal flow between the NGV and the rotor blades. The most effective design reduced the mass averaged loss by 1.28% over the whole passage at the NGV exit.

scholarly journals Aerodynamic Analysis of Multistage Turbomachinery Flows in Support of Aerodynamic Design

1999 ◽  
Author(s):  
John J. Adamczyk
Keyword(s):  
Unsteady Flow ◽  
Axial Flow ◽  
Operating Conditions ◽  
Design Environment ◽  
Cfd Simulations ◽  
Average Flow ◽  
Flow Models ◽  
Time Average ◽  
Semi Empirical ◽  
Future Work

This paper summarizes the state of 3D CFD based models of the time average flow field within axial flow multistage turbomachines. Emphasis is placed on models which are compatible with the industrial design environment and those models which offer the potential of providing credible results at both design and off-design operating conditions. The need to develop models which are free of aerodynamic input from semi-empirical design systems is stressed. The accuracy of such models is shown to be dependent upon their ability to account for the unsteady flow environment in multistage turbomachinery. The relevant flow physics associated with some of the unsteady flow processes present in axial flow multistage machinery are presented along with procedures which can be used to account for them in 3D CFD simulations. Sample results are presented for both axial flow compressors and axial flow turbines which help to illustrate the enhanced predictive capabilities afforded by including these procedures in 3D CFD simulations. Finally, suggestions are given for future work on the development of time average flow models.

Experimental Investigation of Flow-Structure Interaction for a Compliant Panel under a Mach 2 Compression-Ramp

2022 ◽  
Author(s):  
Yoo-Jin Ahn ◽  
Mustafa N. Musta ◽  
Marc A. Eitner ◽  
Jayant Sirohi ◽  
Noel T. Clemens
Keyword(s):  
Experimental Investigation ◽  
Flow Structure ◽  
Structure Interaction ◽  
Compression Ramp

Biomechanics of self-excited oscillation induced by flow-structure interaction in airway constriction

2006 ◽  
Vol 39 ◽  
pp. S601 ◽  
Author(s):  
S. Deguchi ◽  
Y. Miyake ◽  
A. Shiota ◽  
Y. Tamura ◽  
S. Washio
Keyword(s):  
Flow Structure ◽  
Structure Interaction ◽  
Airway Constriction ◽  
Excited Oscillation

Analysis of Local Flow Structure and Global Compressor Performance During Rotating Stall

2004 ◽  
Author(s):  
Chiara Palomba
Keyword(s):  
Flow Field ◽  
Flow Structure ◽  
Rotational Speed ◽  
Axial Flow ◽  
Rotating Stall ◽  
Performance Parameters ◽  
Flow Conditions ◽  
Local Flow ◽  
Flow Parameters ◽  
Compressor Performance

Rotating stall is an instability phenomenon that arises in axial flow compressors when the flow is reduced at constant rotational speed. It is characterised by the onset of rotating perturbations in the flow field accompanied by either an abrupt or gradual decrease of performances. Although the flow field is unsteady and non axisymmetric, the global operating point is stable and a stalled branch of performance curve may be experimentally determined. The number, rotational speed, circumferential extension of the rotating perturbed flow regions named rotating cells may vary from one compressor to another and may depend on the throttle position. The present work focuses on the interaction between local flow parameters and global compressor performance parameters with the aim of reaching a better understanding of the phenomenon. Starting from the Day, Greitzer and Cumpsty [1] model the detailed flow conditions during rotating stall are studied and related to the global performance parameters. This is done both to verify if the compressor under examination fits to the model and if the detailed flow structure may highlight the physics that in the simple model may hide behind the correlation’s used.

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