Experimental Investigation of Compressor Rotor Wakes.

1980 ◽  
Author(s):  
Robert P. Dring ◽  
H. D. Joslyn ◽  
L. W. Hardin
Keyword(s):  
Experimental Investigation ◽  
Compressor Rotor

Compressor/Diffuser/Combustor Aerodynamic Interactions in Lean Module Combustors

2008 ◽  
Vol 130 (1) ◽  
Author(s):  
A. Duncan Walker ◽  
Jon F. Carrotte ◽  
James J. McGuirk
Keyword(s):  
Experimental Investigation ◽  
Guide Vane ◽  
Interaction Effects ◽  
Single Stage ◽  
Flow Rates ◽  
Fuel Injectors ◽  
Compressor Rotor ◽  
Outer Annulus ◽  
Mass Flows ◽  
External Aerodynamics

The paper reports an experimental investigation into the possibility of increased interactions between combustor external aerodynamics and upstream components, e.g., prediffuser, compressor outlet guide vane (OGV), and even the compressor rotor, caused by the trend in lean module fuel injectors to larger mass flows entering the combustor cowl. To explore these component interaction effects, measurements were made on a fully annular rig comprising a single stage compressor, an advanced integrated OGV/prediffuser, followed by a dump diffuser and a generic combustor flametube with metered cowl and inner/outer annulus flows. The flow split entering the cowl was increased from 30% to 70%. The results demonstrate that, with fixed geometry, as the injector flow increases, the performance of the prediffuser and feed annuli suffer. Prediffuser losses increase and at high injector flow rates, the diffuser moves close to separation. The substantial circumferential variation in cowl flow can feed upstream and cause rotor forcing. Notable differences in performance were observed inline and between injectors at the OGV exit, suggesting that geometry changes such as an increased dump gap or nonaxisymmetric prediffuser designs may be beneficial.

A Fundamental Criterion for the Application of Rotor Casing Treatment

1979 ◽  
Vol 101 (2) ◽  
pp. 237-243 ◽  
Author(s):  
E. M. Greitzer ◽  
J. P. Nikkanen ◽  
D. E. Haddad ◽  
R. S. Mazzawy ◽  
H. D. Joslyn
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Total Pressure ◽  
The Other ◽  
Substantial Decrease ◽  
Stall Margin ◽  
Casing Treatment ◽  
Compressor Rotor

An experimental investigation has been carried out on the influence of grooved casing treatment on the stall margin of a compressor rotor. Tests were conducted with two rotor builds having different solidities (but all other parameters identical) so that one of the rotors exhibited a wall, or casing, type of stall, while the other showed a blade stall. It was found that the casing treatment, when compared to the solid casing, was very effective in increasing the stall margin of the wall stall configuration, whereas there was little or no change in the stall point of the blade stall configuration. Detailed relative frame measurements of the rotor exit flow field were also taken as part of the program. These showed that in a wall stall situation, the use of casing treatment produced a substantial decrease in the relative total pressure defect, compared with the solid casing, while this was not true for the blade stall type of blading. The results of the experiments, both in overall measurements and in the detailed relative frame traverses, support the hypothesis that casing treatment is effective only in a situation in which a wall stall exists.

Compressor/Diffuser/Combustor Aerodynamic Interactions in Lean Module Combustors

2007 ◽  
Author(s):  
A. Duncan Walker ◽  
Jon F. Carrotte ◽  
James J. McGuirk
Keyword(s):  
Experimental Investigation ◽  
Interaction Effects ◽  
Single Stage ◽  
Flow Rates ◽  
Fuel Injectors ◽  
Component Interaction ◽  
Compressor Rotor ◽  
Outer Annulus ◽  
Mass Flows ◽  
External Aerodynamics

The paper reports an experimental investigation into the possibility of increased interactions between combustor external aerodynamics and upstream components e.g. pre-diffuser, compressor OGV and even the compressor rotor, caused by the trend in lean module fuel injectors to larger mass flows entering the combustor cowl. To explore these component interaction effects, measurements were made on a fully annular rig comprising a single stage compressor, an advanced integrated OGV/pre-diffuser, followed by a dump diffuser and a generic combustor flametube with metered cowl and inner/outer annulus flows. The flow split entering the cowl was increased from 30% to 70%. The results demonstrate that, with fixed geometry, as the injector flow increases, the performance of the pre-diffuser and feed annuli suffer. Pre-diffuser losses increase and at high injector flow rates the diffuser moves close to separation. The substantial circumferential variation in cowl flow can feed upstream and cause rotor forcing. Notable differences in performance were observed inline and between injectors at OGV exit, suggesting that geometry changes such as an increased dump gap or non axisymmetric pre-diffuser designs may be beneficial.

scholarly journals Experimental Investigation of Unsteady Pressure on an Axial Compressor Rotor Blade Surface

2010 ◽  
Vol 02 (02) ◽  
pp. 131-136 ◽  
Author(s):  
Qingwei Wang ◽  
Bo Liu ◽  
Xiaorong Xiang ◽  
Xiangfeng Bo ◽  
Weimin Hou
Keyword(s):  
Experimental Investigation ◽  
Rotor Blade ◽  
Axial Compressor ◽  
Blade Surface ◽  
Unsteady Pressure ◽  
Compressor Rotor

Do moods and expectancies have unique or interactive effects?: An experimental investigation

2014 ◽  
Author(s):  
Shane Close ◽  
Victoria Adkins ◽  
Kandice Perry ◽  
Katheryn Eckles ◽  
Jill Brown ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Interactive Effects

Visually-induced motion sickness: An experimental investigation

2004 ◽  
Author(s):  
Mustapha Mouloua ◽  
Janan Smither ◽  
Robert C. Kennedy ◽  
Robert S. Kenned ◽  
Dan Compton ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Motion Sickness ◽  
Visually Induced Motion Sickness ◽  
Induced Motion
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