A multi-point approach for aerodynamic modeling in complex flow-fields

1994 ◽  
Author(s):  
Paul Jaramillo ◽  
Yongseung Cho ◽  
M. Nagati
Keyword(s):  
Flow Fields ◽  
Complex Flow ◽  
Aerodynamic Modeling

scholarly journals Flow Visualization in a Simulated Brush Seal

1990 ◽  
Author(s):  
M. J. Braun ◽  
R. C. Hendricks ◽  
V. Canacci
Keyword(s):  
Flow Visualization ◽  
Flow Fields ◽  
Inlet Pressure ◽  
Complex Flow ◽  
Axial Pressure ◽  
Interface Motion ◽  
Pressure Profiles ◽  
Brush Seal ◽  
Brush Seals

A method to visualize and characterize the complex flow fields in simulated brush seals is presented. The brush seal configuration was tested in a water and then in an oil tunnel. The visualization procedure revealed typical regions that are rivering, jetting, vortical or lateral flows and exist upstream, downstream or within the seal. Such flows are engendered by variations in fiber void that are spatial and temporal and affect changes in seal leakage and stability. While the effects of interface motion for linear or cylindrical configurations have not been considered herein, it is believed that the observed flow fields characterize flow phenomenology in both circular and linear brush seals. The axial pressure profiles upstream, across and downstream of the brush in the oil tunnel have been measured under a variety of inlet pressure conditions and the ensuing pressure maps are presented and discussed.

Flow Field Analysis of Under-Expanded Supersonic Jets Impinging on an Inclined Flat Plate: Analysis With PSP/Schlieren Images and CFD Simulations

2005 ◽  
Author(s):  
Kozo Fujii ◽  
Akira Oyama ◽  
Nobuyuki Tsuboi ◽  
Moto Tsukada ◽  
Hirofumi Ouchi ◽  
...  
Keyword(s):  
Flat Plate ◽  
Flow Structure ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Flow Fields ◽  
Field Analysis ◽  
Geometrical Parameters ◽  
Complex Flow ◽  
Plate Analysis ◽  
Complex Flow Structure

Flow fields of Mach number 2.2 jet impinging on an inclined flat plate are experimentally investigated using the Pressure Sensitive Paints (PSP) and Schlieren flow visualization. The flow filed structure is mainly determined by two geometrical parameters (nozzle-plate distance and plate angle against the jet) and one flow parameter (pressure ratio). The results suggest that all the observed flow fields can actually be classified into three types of flow structure based on the three parameters above. As an extension of the authors’ earlier work, experiments are carried out for higher plate angles. The new results show the effectiveness and limitation of the classification that we proposed. To find out the flow structure, some of the flow fields are computationally simulated. Good agreement of the pressure distributions with the experiment validates the simulation. Although analysis so far is limited, the result reveals three dimensional complex flow structure that created pressure peaks over the plate surface.

Morphology evolution of immiscible polymer blends in complex flow fields

Polymer ◽  
2001 ◽  
Vol 42 (13) ◽  
pp. 5651-5659 ◽  
Author(s):  
Concetta Testa ◽  
Immacolata Sigillo ◽  
Nino Grizzuti
Keyword(s):  
Polymer Blends ◽  
Flow Fields ◽  
Morphology Evolution ◽  
Complex Flow ◽  
Immiscible Polymer Blends ◽  
Immiscible Polymer

scholarly journals CFD Technique for Estimating Flow Distortion Effects on Lidar Measurements When Made in Complex Flow Fields

2013 ◽  
Vol 7 (3) ◽  
pp. 324-333 ◽  
Author(s):  
M. Stickland ◽  
S. Fabre ◽  
T. Scanlon ◽  
A. Oldroyd ◽  
T. Mickelson ◽  
...  
Keyword(s):  
Flow Fields ◽  
Complex Flow ◽  
Flow Distortion ◽  
Lidar Measurements ◽  
Made In

Comparing different methods of bed shear stress estimates in simple and complex flow fields

2004 ◽  
Vol 29 (11) ◽  
pp. 1403-1415 ◽  
Author(s):  
Pascale M. Biron ◽  
Colleen Robson ◽  
Michel F. Lapointe ◽  
Susan J. Gaskin
Keyword(s):  
Shear Stress ◽  
Flow Fields ◽  
Bed Shear Stress ◽  
Complex Flow

Uncertainty Propagation Analyses of Lean Burn Combustor Exit Conditions for a Robust Nozzle Cooling Design

2020 ◽  
Vol 142 (5) ◽  
Author(s):  
Marius Schneider ◽  
Heinz-Peter Schiffer ◽  
Knut Lehmann
Keyword(s):  
Guide Vane ◽  
Uncertainty Propagation ◽  
Flow Fields ◽  
Secondary Flows ◽  
Complex Flow ◽  
Lean Burn ◽  
Numerical Predictions ◽  
Cooling Design ◽  
Parameterized Model ◽  
Nozzle Guide

Abstract Knowing the flow conditions at the combustor turbine interface is a key asset for an efficient cooling design of high-pressure turbines. However, measurements and numerical predictions of combustor exit conditions are challenging due to the extreme temperatures and complex flow patterns in modern combustors. Even the time-averaged flow fields at the combustor exit which are commonly used as inlet condition for simulations of the turbine are therefore subject to uncertainty. The goal of this paper is to illustrate how aleatory uncertainties in the magnitude and position of residual swirl and hot spots at the combustor exit affect uncertainties in the prediction of cooling and heat load of the first nozzle guide vane. Also, it is identified which of these uncertain parameters have the greatest impact. An iso-thermal test rig and an engine realistic setup with lean burn inflow conditions are investigated. The analysis combines a parameterized model for combustor exit flow fields with uncertainty quantification methods. It is shown that the clocking position of turbine inlet swirl has a large effect on the formation of secondary flows on the vane surface and thus affects the uncertainty of thermal predictions on the hub and vanes.

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