Three-dimensional flow measurements down-stream of an axial compressor rotor using a four-hole pressure probe

1998 ◽  
Author(s):  
W. Vikatos ◽  
O. Jadayel ◽  
H. Ekerol
Keyword(s):  
Three Dimensional ◽  
Axial Compressor ◽  
Pressure Probe ◽  
Three Dimensional Flow ◽  
Flow Measurements ◽  
Hole Pressure ◽  
Dimensional Flow ◽  
Compressor Rotor

The Three-Dimensional Flow and Blade Wake in an Axial Plane Downstream of an Axial Compressor Rotor

1978 ◽  
Author(s):  
P. Kool ◽  
J. DeRuyck ◽  
Ch. Hirsch
Keyword(s):  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Plane ◽  
Hot Wire ◽  
Three Dimensional Flow ◽  
Dimensional Flow ◽  
Wall Boundary Layer ◽  
Compressor Rotor ◽  
Three Dimensional Finite Element ◽  
Flow Variables

The three-dimensional flow field has been measured in an axial plane downstream of a low speed axial compressor rotor with a rotated single slanted hot wire. A method is described which allows one to calculate three mutually perpendicular velocity components from hot-wire data, and use is made of the technique of periodic sampling and averaging to extract the pitchwise fluctuating flow from the stationary hot-wire signals. These data contain useful information. The radial distribution of the pitchwise averaged flow variables is compared with classical pneumatic measurements and with the results of a quasi three-dimensional finite-element calculation and a three-dimensional end-wall boundary layer calculation. Finally, the wake characteristics are given and a simple correlation is presented which allows one to determine the wake velocity defect from a single wake shape factor.

Three-dimensional flow measurements in a static mixer

AIChE Journal ◽  
2012 ◽  
Vol 59 (5) ◽  
pp. 1746-1761 ◽  
Author(s):  
R. T. M. Jilisen ◽  
P. R. Bloemen ◽  
M. F. M. Speetjens
Keyword(s):  
Three Dimensional ◽  
Static Mixer ◽  
Three Dimensional Flow ◽  
Flow Measurements ◽  
Dimensional Flow

Effects of Reynolds Number and Freestream Turbulence on Turbine Tip Clearance Flow

2005 ◽  
Vol 128 (1) ◽  
pp. 166-177 ◽  
Author(s):  
Takayuki Matsunuma
Keyword(s):  
Reynolds Number ◽  
Turbulence Intensity ◽  
Three Dimensional ◽  
Tip Clearance ◽  
Pressure Probe ◽  
Turbine Cascade ◽  
Freestream Turbulence ◽  
Tip Leakage Flow ◽  
Three Dimensional Flow ◽  
Dimensional Flow

Tip clearance losses represent a major efficiency penalty of turbine blades. This paper describes the effect of tip clearance on the aerodynamic characteristics of an unshrouded axial-flow turbine cascade under very low Reynolds number conditions. The Reynolds number based on the true chord length and exit velocity of the turbine cascade was varied from 4.4×104 to 26.6×104 by changing the velocity of fluid flow. The freestream turbulence intensity was varied between 0.5% and 4.1% by modifying turbulence generation sheet settings. Three-dimensional flow fields at the exit of the turbine cascade were measured both with and without tip clearance using a five-hole pressure probe. Tip leakage flow generated a large high total pressure loss region. Variations in the Reynolds number and freestream turbulence intensity changed the distributions of three-dimensional flow, but had no effect on the mass-averaged tip clearance loss of the turbine cascade.

Three-Dimensional-Flow Theories for Axial Compressors and Turbines

1948 ◽  
Vol 159 (1) ◽  
pp. 255-268 ◽  
Author(s):  
A. D. S. Carter
Keyword(s):  
Three Dimensional ◽  
Axial Compressor ◽  
Physical Nature ◽  
Secondary Flows ◽  
Operating Conditions ◽  
Tip Clearance ◽  
Three Dimensional Flow ◽  
Axial Compressors ◽  
Dimensional Flow ◽  
Blade Row

It has long been known that the energy losses occurring in an axial compressor or turbine cannot be fully accounted for by the skin-friction losses on the blades and annulus walls. The difference, usually termed secondary loss, is attributed to miscellaneous secondary flows which take place in the blade row. These flows both cause losses in themselves and modify the operating conditions of the individual blade sections, to the detriment of the overall performance. This lecture analyses the three-dimensional flow in axial compressors and turbines, so that, by appreciation of the factors involved, possible methods of improving the performance can readily be investigated. The origin of secondary flow is first examined for the simple case of a straight cascade. The physical nature of the flow, and theories which enable quantitative estimates to be made, are discussed at some length. Following this, the three-dimensional flow in an annulus with a stationary blade row is examined, and, among other things, the influence of radial equilibrium on the flow pattern is noted. All physical restrictions are then removed, and the major factors governing the three-dimensional flow in an actual machine are investigated as far as is possible with existing information, particular attention being paid to the influence of a non-uniform velocity profile, tip clearance, shrouding, and boundary layer displacement. Finally the various empirical factors used in design are discussed, and the relationships between them established.

Quantitative Density Visualization in a Transonic Compressor Rotor

1977 ◽  
Vol 99 (3) ◽  
pp. 460-475 ◽  
Author(s):  
A. H. Epstein
Keyword(s):  
Boundary Layer ◽  
Three Dimensional ◽  
Imaging Systems ◽  
Three Dimensional Flow ◽  
Transonic Compressor ◽  
Dimensional Flow ◽  
Compressor Rotor ◽  
Density Maps ◽  
Shock System ◽  
High Work

The flow in a 59-cm dia high work, transonic compressor rotor has been visualized using a fluorescent gas, 2,3, butanedione, as a tracer. The technique allows the three-dimensional flow to be imaged as a set of distinct planes. Quantitative static density maps were obtained by correcting the images for distortion and nonlinearities introduced by the illumination and imaging systems. These images and maps were used to analyze the three-dimensional nature of the blade’s boundary layer and shock system.

A Horseshoe Vortex in a Duct

1984 ◽  
Vol 106 (3) ◽  
pp. 668-676 ◽  
Author(s):  
J. Moore ◽  
T. J. Forlini
Keyword(s):  
Vortex Flow ◽  
Three Dimensional ◽  
Leading Edge ◽  
Horseshoe Vortex ◽  
The Body ◽  
Test Case ◽  
Three Dimensional Flow ◽  
Flow Measurements ◽  
Dimensional Flow ◽  
Side Walls

A Rankine half-body is used to model the three-dimensional flow caused by a blunt obstruction in a flow passage. The body is located in a duct bounded by two plane endwalls and two side walls shaped like potential-flow streamlines. A thick turbulent boundary layer on the endwall forms a horseshoe vortex flow as it encounters the leading edge of the body. Flow measurements are presented showing the inlet flow and the three-dimensional flow downstream of the leading edge. Sufficient data are presented for this to be a test case for the development of three-dimensional viscous flow codes.

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