Effect of boundary-layer removal on high velocity flame stabilization

AIAA Journal ◽  
1964 ◽  
Vol 2 (11) ◽  
pp. 2030-2031
Author(s):  
JAMES R. MAUS ◽  
WILLIAM T. SNYDER
Keyword(s):  
Boundary Layer ◽  
High Velocity ◽  
Flame Stabilization ◽  
Layer Removal

Flame stabilization by baffles in a high velocity gas stream

1948 ◽  
Vol 3 (1) ◽  
pp. 40-44 ◽  
Author(s):  
J.P. Longwell ◽  
J.E. Chenevey ◽  
W.W. Clark ◽  
E.E. Frost
Keyword(s):  
High Velocity ◽  
Flame Stabilization

A New Method to Measure Prandtl Number and Thermal Conductivity of Fluids

1957 ◽  
Vol 24 (1) ◽  
pp. 25-28
Author(s):  
E. R. G. Eckert ◽  
T. F. Irvine
Keyword(s):  
Thermal Conductivity ◽  
Boundary Layer ◽  
Prandtl Number ◽  
High Velocity ◽  
Atmospheric Pressure ◽  
New Method ◽  
Test Results ◽  
Test Setup ◽  
Velocity Boundary Layer ◽  
Layer Flow

Abstract A new method is described by which the Prandtl number and indirectly the thermal conductivity of fluids can be measured. The method is based on the fact that a well-established, unique relation exists between the Prandtl number and the recovery factor for laminar high-velocity boundary-layer flow. The test setup is described which has been devised for such measurements, and test results are presented for air at atmospheric pressure and temperatures between 60 and 350 F.

Flame Stabilization in a Boundary Layer

1957 ◽  
Vol 27 (1) ◽  
pp. 28-30 ◽  
Author(s):  
HOYT C. HOTTEL ◽  
TAU-YI TOONG ◽  
JOHN J. MARTIN
Keyword(s):  
Boundary Layer ◽  
Flame Stabilization

Flame stabilization in high-velocity heterogeneous fuel-air mixtures

1992 ◽  
Vol 8 (6) ◽  
pp. 1138-1143 ◽  
Author(s):  
M. R. Baxter ◽  
A. H. Lefebvre
Keyword(s):  
High Velocity ◽  
Flame Stabilization

Flame Stabilization in the Boundary Layer of Heated Plates

1958 ◽  
Vol 28 (9) ◽  
pp. 592-599 ◽  
Author(s):  
RICHARD W. ZIEMER ◽  
ALI BULENT CAMBEL
Keyword(s):  
Boundary Layer ◽  
Flame Stabilization ◽  
Heated Plates

Step-induced turbulence in a high-velocity boundary layer

1989 ◽  
Vol 24 (1) ◽  
pp. 150-153
Author(s):  
V. Ya. Kiselev ◽  
V. I. Lysenko
Keyword(s):  
Boundary Layer ◽  
High Velocity ◽  
Velocity Boundary Layer

Numerical Investigation of Endwall Boundary Layer Removal on Highly-Loaded Axial Compressor Blade Rows

2005 ◽  
Author(s):  
V. Gu¨mmer ◽  
M. Goller ◽  
M. Swoboda
Keyword(s):  
Boundary Layer ◽  
Flow Field ◽  
Reverse Flow ◽  
Axial Compressor ◽  
Flow Path ◽  
Compressor Blade ◽  
Main Flow ◽  
Local Flow ◽  
Layer Removal ◽  
Highly Loaded

This paper presents results of numerical investigations carried out to explore the benefit of endwall boundary layer removal from critical regions of highly-loaded axial compressor blade rows. At the loading level of modern aero-engine compressors the performance is primarily determined by three-dimensional flow phenomena occuring in the endwall regions. 3DNS simulations were conducted on both a rotor and a stator test case in order to evaluate basic effects and the practical value of bleeding air from specific locations at the casing endwall. The results of the numerical survey demonstrated substantial benefits of relatively small bleed rates to the local flow field and to the performance of the two blade rows. On the rotor, boundary layer fluid was removed from the main flow path through an axisymmetric slot in the casing over the rotor tip. This proved to give some control over the tip leakage vortex flow and the associated loss generation. On the stator, boundary layer fluid was taken from the flow path through a single bleed hole within the passage. Two alternative off-take configurations were evaluated, revealing a large impact of the bleed hole shape and location on the cross-passage flow and the suction side corner separation. On both blade rows investigated, rotor and stator, boundary layer removal resulted in a reduction of local reverse flow, blockage and losses in the respective near-casing region. This paper gives insight into changes occuring in the 3D passage flow field near the casing and summarises the effects on the radial matching and pitchwise-averaged performance parameters, namely loss and deviation of the rotor and stator when suction is active. Primary focus is put on the aerodynamics in the blade rows in the main flow path; details of the internal flow structure within the bleed off-take cavities/ports are not discussed here.

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