Experimental and numerical conjugate flow and heat transfer investigation of the influence of density ratio and blowing ratio on the film-cooling efficiency of a first stage.., ASME 99-GT-199 PDF Download
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Author: Dieter E. Bohn
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-10, 1999.
Author: Dieter E. Bohn
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-10, 1999.
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 556
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Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 574
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Author: Michael Gritsch
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-10, 1999.
Author: Joshua Brian Anderson
Publisher:
ISBN:
Category :
Languages : en
Pages : 572
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Book Description
Film cooling is widely used in gas turbine engines to manage temperatures within the hot section of the engine. In this work, several investigations are described, all of which studied how fundamental hydrodynamic and thermal parameters influence the performance of film cooling. The first investigation studied the impact of freestream turbulence, boundary layer thickness, Reynolds number, and Mach number on film cooling performance, using axial shaped film cooling holes. The second study considered a similar set of parameters, and investigated their impact on compound-angle oriented film cooling holes. Both of these studies utilized measurements of adiabatic effectiveness and heat transfer coefficient augmentation. In general, the parameters had effects which were dependent on the coolant flow rate and density ratio. The final study considered methods to reduce the experimental uncertainty which arises from conduction and radiation errors in thermal measurements. A careful evaluation of the thermal boundary layer was used to validate these corrections
Author: James Edward Mayhew
Publisher:
ISBN:
Category :
Languages : en
Pages : 482
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Author: Gunter Wilfert
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-June 10, 1999.
Author: Mohammed Aref Al-Hemyari
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 58
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"Cooling gas turbine blades is a crucial technique to allow higher turbine inlet temperatures. A higher turbine inlet temperature allows boosting gas turbine efficiency, which reduces fuel consumption. One of the main cooling techniques of the turbine blades is film cooling where a relatively low air temperature is used to form a blanket of cool air around the blade to shield it from high temperature gases. Many complex interrelated geometry and flow parameters affect the effectiveness of the film cooling. The complex interrelations between these parameters are considered the main challenge in properly understanding the effect of these parameters on film cooling. Testing such cooling techniques under actual engine conditions is even more challenging due to difficulty of installing proper instrumentations. Numerical techniques are viable analysis techniques that are used to better understand film cooling techniques. In this study, a simplified 2D film cooling jet blown from the slot jet is investigated under multiple variable parameters, mainly, the blowing ratio, jet angle, density ratio and centrifugal force. The performance of the film cooling is reported using local and average adiabatic film effectiveness. The main contribution of this study is exploring the effect of the centrifugal force and wall material selection using conjugate heat transfer on film cooling effectiveness. The centrifugal force reduces the overall adiabatic film effectiveness. A correlation between the blowing ratio, density ratio and injection angle is developed in this work. The highest film cooling performance was founded at a blowing ratio of 0.8, an injection angle of 30° and density ratio of 1.2."--Abstract.
Author: Lamyaa El-Gabry
Publisher: BiblioGov
ISBN: 9781289236779
Category :
Languages : en
Pages : 40
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Book Description
Computational Fluid Dynamics is used in the analysis of a film cooling jet in crossflow. Predictions of film effectiveness are compared with experimental results for a circular jet at blowing ratios ranging from 0.5 to 2.0. Film effectiveness is a surface quantity which alone is insufficient in understanding the source and finding a remedy for shortcomings of the numerical model. Therefore, in addition, comparisons are made to flow field measurements of temperature along the jet centerline. These comparisons show that the CFD model is accurately predicting the extent and trajectory of the film cooling jet; however, there is a lack of agreement in the near-wall region downstream of the film hole. The effects of main stream turbulence conditions, boundary layer thickness, turbulence modeling, and numerical artificial dissipation are evaluated and found to have an insufficient impact in the wake region of separated films (i.e. cannot account for the discrepancy between measured and predicted centerline fluid temperatures). Analyses of low and moderate blowing ratio cases are carried out and results are in good agreement with data.
Author: Dean Russell Pedersen
Publisher:
ISBN:
Category : Gas flow
Languages : en
Pages : 744
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Book Description
