Author: Kenneth Delos HallPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 148
Book Description
The Effect of Radius of Curvature on Film Cooling Effectiveness
Author: Kenneth Delos HallPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 148
Book Description
Curvature Effects on Film Cooling With Injection Through Two Rows of Holes
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
The adiabatic film cooling effectiveness on convex and concave curved surfaces (as a model for suction and pressure side film cooling of gas turbine blades) with two staggered rows of injection holes are investigated by using a mass transfer technique. Additionally measurements on a flat plate are made for comparison. Two different radii of curvature (R/D = plus or minus 60, plus or minus 120) and two streamwise distances of the rows (12D and 24D) with film cooling holes inclined at 40 degrees are considered. The blowing rates are varied in a wide range from 0.25 to 2.0 and the main stream Reynolds numbers (Re(sub D)) between 10000 and 50000. At low and moderate blowing rates the effectiveness is enhanced on convex and reduced on concave curved surfaces compared to results obtained on the flat surface. At high blowing rates the effectiveness is not greatly influenced by surface curvature. The effect of curvature was found to be negligible between the two rows and reduced downstream of the second row compared to results described in the literature for single row injection.
Effects of Convex Curvature on Adiabatic Effectiveness for a Film Cooled Turbine Vane
Author: James R. WinkaPublisher:
ISBN:
Category :
Languages : en
Pages : 246
Book Description
A series of experiments were carried out to measure the effects of convex surface curvature on film cooling. In the first series of experiments cooling holes were positioned along the vane such that their non-dimensional curvature parameter, 2r/d, was matched. Single row of holes with the same diameter were placed at high and moderate curvature position along a turbine vane resulting in 2r/d = 28 and 40, accordingly. A third row of holes was installed on the vane at the same location as the moderate curvature row with a larger hole diameter, resulting in 2r/d = 28, matching the high curvature row. Adiabatic temperature measurements were then carried out for blowing ratios of M = 0.30 to 1.60 tested at a density ratio of DR = 1.20. The results indicated that there was some scaling of performance present with matching 2r/d, but there was not an exact matching of performance. The second series of experiments focused on the effects of a changing surface curvature downstream of injection. Two row of holes were positioned along the vane surface such that the local radius of curvature and hole diameters were equivalent, with one row positioned upstream of the maximum curvature point and the other downstream of the maximum curvature point. Adiabatic temperature measurements were carried out for blowing ratios of M = 0.30 to 1.60 and tested at a density ratio of DR = 1.20. The results show that the change in curvature downstream plays a significant role in the performance of film cooling and that the local surface curvature is insufficient in capturing its effects. Additional experiments were carried out to measure the effects of the approaching boundary layer influence on film cooling as well as the effect of injection angle at a weakly convex surface.
Influence of Coolant Tube Curvature on Film Cooling Effectiveness as Detected by Infrared Imagery
Author: S. Stephen PapellThe Influence of Curvature on Film Cooling Performance
Author: Publisher:
ISBN:
Category : Convex surfaces
Languages : en
Pages : 0
Book Description
The effects of injection rate and strength of curvature on film cooling performance of gas injected through a row of holes on a convex surface are studied. Comparisons are made to film cooling of concave and flat surfaces. Three different relative strengths of curvature (ratio of radius of curvature to radius of injection hole), two density ratios (0.95 and 2.0), and a wide range of blowing rates (0.3 to 2.7) are considered. A foreign gas injection technique (mass transfer analogy) is used. The strength of curvature was controlled by varying the injection hole diameter. At low blowing rates, film cooling is more effective on the convex surface than on a flat or a concave surface. The cross-stream pressure gradient present in curved flows tends to push the jet into the convex wall. As the injection rate is increased, normal and tangential jet momentum promote liftoff from the convex surface, thereby lowering performance. In contrast, previous studies show that on a concave surface, tangential jet momentum, flow instabilities, and blockage improve performance on a concave surface as blowing rate is increased.
Influence of Coolant Tube Curvature on Film Cooling Effectiveness as Detected by Infrared Imagery
Author: S. Stephen PapellPublisher:
ISBN:
Category : Cooling curves
Languages : en
Pages : 24
Book Description
Dossier Ushio Amagatsu
Author: Discrete Film Cooling in a Rocket with Curved Walls
Author: Jonathan Floyd McCallPublisher:
ISBN:
Category : Cooling
Languages : en
Pages : 318
Book Description
A Numerical Study of Discrete-hole Film Cooling
Author: Mulugeta K. BerheInfluence of Coolant Tube Curvature on Film Cooling Effectiveness as Detected by Infrared Imagery
Author: S. Stephen PapellPublisher:
ISBN:
Category : Cooling curves
Languages : en
Pages : 14
Book Description