An Experimental Investigation of the Effects of Induced High Turbulence in Film Cooling Flows PDF Download
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Author: Jason I. Shapiro
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 186
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Book Description
A survey into the effects of turbulence intensity induced in film cooling flows was performed using thermal anemometry and thermocouple temperature measurements.
Author: Jason I. Shapiro
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 186
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Book Description
A survey into the effects of turbulence intensity induced in film cooling flows was performed using thermal anemometry and thermocouple temperature measurements.
Author: James Edward Mayhew
Publisher:
ISBN:
Category :
Languages : en
Pages : 482
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Author: S. Stephen Papell
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 68
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Author: David Seager
Publisher:
ISBN:
Category :
Languages : en
Pages : 228
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Author: Justin Hodges
Publisher:
ISBN:
Category :
Languages : en
Pages : 217
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Book Description
Film cooling is a technology used in the field of turbomachinery, such as in landbased power generation and in aircraft engines, which serves to help provide a safe thermal condition in key hot hardware components. With a significant presence of turbulence present in the flow-field, these film cooling jets emanate into a crossflow environment in such a way that is very challenging for computational fluid dynamics to accurately predict. One impact of such is significant uncertainty for those in industry when conducting both aerodynamic and thermal designs.
Author: Cecil J. Marek
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 36
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Author: Stefan Bernsdorf
Publisher:
ISBN: 9783183476077
Category :
Languages : en
Pages : 175
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Author: T. Hansmann
Publisher:
ISBN:
Category : Aerothermodynamics
Languages : en
Pages : 18
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Author: Robert Schroeder
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Gas turbines are heavily used for electricity generation and aircraft propulsion with a strong desire in both uses to maximize thermal efficiency while maintaining reasonable power output. As a consequence, gas turbines run at high turbine inlet temperatures that require sophisticated cooling technologies to ensure survival of turbine components. One such technology is film cooling with shaped holes, where air is withdrawn from latter stages of the compressor, is bypassed around the combustor, and is eventually ejected out holes in turbine component surfaces. Air ejected from these shaped holes helps maintain components at temperatures lower than flow from the combustor. Many studies have investigated different factors that influence shaped hole performance. However, no studies in open literature have investigated how cooling performance is affected by roughness along interior walls of the shaped hole. The effect of in-hole roughness on shaped hole film cooling was the focus of this research. Investigation of in-hole roughness effects first required the determination of behavior for a shaped hole with smooth walls. A public shaped hole, now used by other investigators as well, was designed with a diffused outlet having 7 degree expansion angles and an area ratio of 2.5. At low freestream turbulence intensity of 0.5%, film cooling adiabatic effectiveness for this smooth hole was found to peak at a blowing ratio of 1.5. Measurements of flowfields and thermal fields revealed causes of this behavior. Blowing ratio increases above 1.5 caused the jet from the smooth hole to penetrate higher into the surrounding mainstream, exhibit a stronger counter-rotating vortex pair, and have narrower contact with the wall than at lower blowing ratios. Experiments performed at high freestream turbulence intensity of 13% revealed dynamics of how freestream turbulence both diluted and laterally spread coolant. At the high blowing ratio of 3 the dilution and spreading were competing effects, such that elevated freestream turbulence did not cause a decrease in area-averaged effectiveness. At the blowing ratio of 1.5, high freestream turbulence caused area-averaged effectiveness to decrease 17% relative to the low freestream turbulence case. Film cooling performance was measured for the shaped hole geometry with several different configurations of in-hole roughness. At low freestream turbulence intensity, in-hole roughness caused decreases in area-averaged adiabatic effectiveness up to 61% relative to the smooth hole performance. These percent decreases in adiabatic effectiveness were more severe with increasing roughness levels and with increasing blowing ratios. Flowfield and thermal field measurements for the configuration with largest roughness size showed that the decrease in adiabatic effectiveness for rough holes as compared to smooth holes was due to thicker boundary layers along the interior walls of the cooling holes. The thicker boundary layers resulted in faster jet core flow, which in turn caused increased penetration of coolant into the mainstream and increased turbulence intensity inside the jet, with both leading to reduced adiabatic effectiveness. Detrimental effects of in-hole roughness persisted at the high freestream turbulence conditions as well.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 324
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Book Description
