The wake of an exhaust stack in a crossflow
| dc.contributor.advisor | Bergstrom, Donald J. | en_US |
| dc.contributor.advisor | Sumner, David | en_US |
| dc.contributor.committeeMember | Simonson, Carey J. | en_US |
| dc.contributor.committeeMember | Maule, Charles P. | en_US |
| dc.contributor.committeeMember | Martinuzzi, Robert | en_US |
| dc.contributor.committeeMember | Guo, Huiqing | en_US |
| dc.contributor.committeeMember | Bugg, James D. | en_US |
| dc.creator | Adaramola, Muyiwa S | en_US |
| dc.date.accessioned | 2008-04-21T12:47:17Z | en_US |
| dc.date.accessioned | 2013-01-04T04:29:39Z | |
| dc.date.available | 2009-04-23T08:00:00Z | en_US |
| dc.date.available | 2013-01-04T04:29:39Z | |
| dc.date.created | 2008 | en_US |
| dc.date.issued | 2008 | en_US |
| dc.date.submitted | 2008 | en_US |
| dc.description.abstract | Relatively few studies have been carried out on the turbulent wake structure of a finite circular cylinder and a stack partially immersed in a flat-plate turbulent boundary layer. There is a need to develop a better understanding of the wakes of these structures, since they have many important engineering applications. This thesis investigates the influence of the aspect ratio on the wake of a finite circular cylinder and the effects of the ratio of jet flow velocity to crossflow velocity (velocity ratio, R) on the wake of a stack in a cross-flow. The wake characteristics of flows over a finite circular cylinder at four different aspect ratios (AR = 3, 5, 7 and 9) were investigated experimentally at a Reynolds number of ReD = 6⨯10⁴ using two-component thermal anemometry. Each cylinder was mounted normal to a ground plane and was either completely or partially immersed in a flat-plate turbulent boundary layer. The ratio of boundary layer thickness to the cylinder diameter was 3. A similar turbulent wake structure (time-averaged velocity, turbulence intensity, and Reynolds shear stress distributions) was found for the cylinders with AR = 5, 7, and 9, while a distinctly different turbulent wake structure was found for the cylinder with AR = 3. This was consistent with the results of a previous study that focused on the time-averaged streamwise vortex structures in the wake. In addition, irrespective of the value of AR, high values were observed for the skewness and flatness factors around the free end of the cylinders, which may be attributed to the interaction of the tip vortex structures and downwash flow that dominates this region of the cylinder. The wake characteristics of a stack of aspect ratio AR = 9 were investigated using both the seven-hole pressure probe and thermal anemometry. The seven-hole probe was used to measure the three components of the time-averaged velocity field, while the thermal anemometry was used to measure two components of the turbulent velocity field at various downstream locations from the stack. The stack was mounted normal to the ground plane and was partially immersed in a flat-plate turbulent boundary layer, for which the ratio of boundary layer thickness to the stack diameter was 4.5. In addition, measurements of the vortex shedding frequency were made with a single-component hot-wire probe. The cross-flow Reynolds number was ReD = 2.3 x 10⁴, the jet Reynolds number ranged from Red = 7.6 x 10³ to 4.7 x 10⁴, and R was varied from 0 to 3. In the stack study, three flow regimes were identified depending on the value of R: the downwash (R < 0.7), cross-wind-dominated (0.7 < R < 1.5), and jet-dominated (R ≥ 1.5) flow regimes. Each flow regime had a distinct structure for the time-averaged velocity and streamwise vorticity fields, and turbulence characteristics, as well as the variation of the Strouhal number and the power spectrum of the streamwise velocity fluctuations along the stack height. The turbulence structure is complex and changes in the streamwise and wall-normal directions within the near and intermediate stack and jet wakes. In the downwash and crosswind-dominated flow regimes, two pairs of counter-rotating streamwise vortex structures were identified within the stack wake. The tip-vortex pair and base-vortex pair were similar to those found in the wake of a finite circular cylinder, located close to the free end and the base of the stack (ground plane), respectively. In the jet-dominated flow regime, a third pair of streamwise vortex structures was observed, referred to as the jet-wake vortex pair, which occurred within the jet-wake region above the free end of the stack. The jet-wake vortex pair has the same orientation as the base vortex pair and is associated with the jet rise. | en_US |
| dc.identifier.uri | http://hdl.handle.net/10388/etd-04212008-124717 | en_US |
| dc.language.iso | en_US | en_US |
| dc.subject | Vortex Shedding | en_US |
| dc.subject | Vortex Structures | en_US |
| dc.subject | Stack | en_US |
| dc.subject | Finite Cylinder | en_US |
| dc.subject | Bluff Body Aerodynamics | en_US |
| dc.subject | Turbulent Wake | en_US |
| dc.subject | Turbulent Jet | en_US |
| dc.title | The wake of an exhaust stack in a crossflow | en_US |
| dc.type.genre | Thesis | en_US |
| dc.type.material | text | en_US |
| thesis.degree.department | Environmental Engineering | en_US |
| thesis.degree.discipline | Environmental Engineering | en_US |
| thesis.degree.grantor | University of Saskatchewan | en_US |
| thesis.degree.level | Doctoral | en_US |
| thesis.degree.name | Doctor of Philosophy (Ph.D.) | en_US |