Author: Mulugeta K. BerhePublisher:
ISBN:
Category :
Languages : en
Pages : 314
Book Description
A Numerical Study of Discrete-hole Film Cooling
Simulation of Discrete Hole Film Cooling Using a Two-dimensional Low Reynolds Number [kappa-epsilon] Model
![Simulation of Discrete Hole Film Cooling Using a Two-dimensional Low Reynolds Number [kappa-epsilon] Model PDF](https://books.google.com/books/content/images/frontcover/pPonOAAACAAJ?fife=w80-h100)
Author: Kevin J. MracekPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 298
Book Description
An Experimental and Numerical Study of Heat Transfer Augmentation Near the Entrance to a Film Cooling Hole
Author: Gerard ScheepersPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Developments regarding internal cooling techniques have allowed the operation of modern gas turbine engines at turbine inlet temperatures which exceed the metallurgical capability of the turbine blade. This has allowed the operation of engines at a higher thermal efficiency and lower specific fuel consumption. Modern turbine blade-cooling techniques rely on external film cooling to protect the outer surface of the blade from the hot gas path and internal cooling to remove thermal energy from the blade. Optimization of coolant performance and blade-life estimation require knowledge regarding the influence of cooling application on the blade inner and outer surface heat transfer. The following study describes a combined experimental and computational study of heat transfer augmentation near the entrance to a film-cooling hole. Steady-state heat transfer results were acquired by using a transient measurement technique in an 80 x actual rectangular channel, representing an internal cooling channel of a turbine blade. Platinum thin-film gauges were used to measure the inner surface heat transfer augmentation as a result of thermal boundary layer renewal and impingement near the entrance of a film-cooling hole. Measurements were taken at various suction ratios, extraction angles and wall temperature ratios with a main duct Reynolds number of 25? 103. A numerical technique, based on the resolution of the unsteady conduction equation, using a Crank-Nicholson scheme, was used to obtain the surface heat flux from the measured surface temperature history. Computational data was generated with the use of a commercial CFD solver.
An Experimental and Numerical Study of the Effect of the Film to Mainstream Temperature Ratio on Film Cooling Heat Transfer
Author: John Russell BiddlePublisher:
ISBN:
Category : Cooling
Languages : en
Pages : 584
Book Description
Experimental and Numerical Study of Supersonic Film Cooling
Author: B. AupoixInvestigation of Film Cooling Effectiveness from Cylindrical Cooling Hole with Anti Vortex Generation by Numerical Simulation
Author: Abdallah Ali Abu.ZaridaPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 65
Book Description
Numerical Heat Transfer and Fluid Flow
Author: D. SrinivasacharyaPublisher: Springer
ISBN: 9811319030
Category : Technology & Engineering
Languages : en
Pages : 657
Book Description
This book comprises selected papers from the International Conference on Numerical Heat Transfer and Fluid Flow (NHTFF 2018), and presents the latest developments in computational methods in heat and mass transfer. It also discusses numerical methods such as finite element, finite difference, and finite volume applied to fluid flow problems. Providing a good balance between computational methods and analytical results applied to a wide variety of problems in heat transfer, transport and fluid mechanics, the book is a valuable resource for students and researchers working in the field of heat transfer and fluid dynamics.
Flow Visualization of Discrete-hole Film Cooling with Spanwise Injection Over a Cylinder
Author: Louis M. RussellNumerical Analysis of Film Cooling at High Blowing Ratio
Author: Lamyaa El-GabryPublisher: BiblioGov
ISBN: 9781289236779
Category :
Languages : en
Pages : 40
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.
Numerical Analysis of Film Cooling Effectiveness Using Compound Cooling Holes at the End of Gas Turbine Engine Combustor
Author: Shahin SalimiPublisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 140
Book Description