Computational investigations were carried out on an advanced serpentine jet
engine inlet duct to understand the development and propagation of secondary flow
structures. Computational analysis which went in tandem with experimental
investigation was required to aid secondary flow control required for enhanced pressure
recovery and decreased distortion at the engine face. In the wake of earlier attempts with
modular fluidic actuators used for this study, efforts were directed towards optimizing
the actuator configurations. Backed by both computational and experimental resources,
many variations in the interaction of fluidic actuators with the mainstream flow were
attempted in the hope of best controlling secondary flow formation. Over the length of
the studies, better understanding of the flow physics governing flow control for 3D
curved ducts was developed.
Blowing tangentially, to the wall at the bends of the S-duct, proved extremely
effective in enforcing active flow control. At practical jet momentum coefficients,
significant improvements characterized by an improved pressure recove ry of 37% and a
decrease in distortion close to 90% were seen.
| Identifer | oai:union.ndltd.org:tamu.edu/oai:repository.tamu.edu:1969.1/ETD-TAMU-1399 |
| Date | 15 May 2009 |
| Creators | Kumar, Abhinav |
| Contributors | Rediniotis, Othon |
| Source Sets | Texas A and M University |
| Language | en_US |
| Detected Language | English |
| Type | Book, Thesis, Electronic Thesis, text |
| Format | electronic, application/pdf, born digital |
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