Attenuation of the shock in a shock tube due to the effect of wall boundary layer

1968 ◽  
Author(s):  
G. ANDERSON ◽  
V. MURTHY
Keyword(s):  
Boundary Layer ◽  
Shock Tube ◽  
Wall Boundary Layer ◽  
Wall Boundary

Further Experiments on Shock Tube Wall Boundary-Layer Transition

AIAA Journal ◽  
1983 ◽  
Vol 21 (7) ◽  
pp. 1046-1048 ◽  
Author(s):  
Michael J. Chaney ◽  
William J. Cook
Keyword(s):  
Boundary Layer ◽  
Shock Tube ◽  
Tube Wall ◽  
Boundary Layer Transition ◽  
Layer Transition ◽  
Wall Boundary Layer ◽  
Wall Boundary

Further experiments on shock tube wall boundary-layer transition

AIAA Journal ◽  
1985 ◽  
Vol 23 (8) ◽  
pp. 1298-1299
Author(s):  
William J. Cook ◽  
Michael J. Chancy
Keyword(s):  
Boundary Layer ◽  
Shock Tube ◽  
Tube Wall ◽  
Boundary Layer Transition ◽  
Layer Transition ◽  
Wall Boundary Layer ◽  
Wall Boundary

An accurate experimental investigation of the shock-tube end-wall boundary layer in argon

1980 ◽  
Vol 23 (6) ◽  
pp. 799-803 ◽  
Author(s):  
A. Hirschberg ◽  
W.H.H. van Heugten ◽  
J.F.H. Willems ◽  
M.E.H. van Dongen
Keyword(s):  
Boundary Layer ◽  
Experimental Investigation ◽  
Shock Tube ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
End Wall

Experiments on Flame Flashback in a Quasi-2D Turbulent Wall Boundary Layer for Premixed Methane-Hydrogen-Air Mixtures

2010 ◽  
Author(s):  
Christian Eichler ◽  
Thomas Sattelmayer
Keyword(s):  
Boundary Layer ◽  
Boundary Layers ◽  
Turbulent Flows ◽  
Turbulent Transport ◽  
Wall Friction ◽  
Evaluation Procedure ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Flame Flashback ◽  
Turbulent Wall

Premixed combustion of hydrogen-rich mixtures involves the risk of flame flashback through wall boundary layers. For laminar flow conditions, the flashback mechanism is well understood and is usually correlated by a critical velocity gradient at the wall. Turbulent transport inside the boundary layer considerably increases the flashback propensity. Only tube burner setups have been investigated in the past and thus turbulent flashback limits were only derived for a fully-developed Blasius wall friction profile. For turbulent flows, details of the flame propagation in proximity to the wall remain unclear. This paper presents results from a new experimental combustion rig, apt for detailed optical investigations of flame flashbacks in a turbulent wall boundary layer developing on a flat plate and being subject to an adjustable pressure gradient. Turbulent flashback limits are derived from the observed flame position inside the measurement section. The fuels investigated cover mixtures of methane, hydrogen and air at various mixing ratios. The associated wall friction distributions are determined by RANS computations of the flow inside the measurement section with fully resolved boundary layers. Consequently, the interaction between flame back pressure and incoming flow is not taken into account explicitly, in accordance with the evaluation procedure used for tube burner experiments. The results are compared to literature values and the critical gradient concept is reviewed in light of the new data.

Wall Boundary Layers in Turbomachines

1972 ◽  
Vol 14 (6) ◽  
pp. 411-423 ◽  
Author(s):  
H. Marsh ◽  
J. H. Horlock
Keyword(s):  
Boundary Layer ◽  
Integral Equations ◽  
Cross Flow ◽  
Inlet Guide Vanes ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Alternative Approach ◽  
Flow Through ◽  
The Many ◽  
Momentum Integral

Equations for the passage-averaged flow in a cascade are used to derive the momentum integral equations governing the development of the wall boundary layer in turbomachines. Several existing methods of analysis are discussed and an alternative approach is given which is based on the passage-averaged momentum integral equations. The analysis leads to an anomaly in the prediction of the cross flow and to avoid this it is suggested that for the many-bladed cascade there should be a variation of the blade force through the boundary layer. This variation of the blade force can be included in the analysis as a force deficit integral. The growth of the wall boundary layer has been calculated by four methods and the predictions are compared with two sets of published experimental results for flow through inlet guide vanes.

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