Investigation of Various Parametric Influences on Leading Edge Film Cooling PDF Download

Author: Michael W. Cruse
Publisher:
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Category :
Languages : en
Pages : 0

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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Orlando, FL, Jun 2 - Jun 5, 1997.

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Category : Mechanical engineering
Languages : en
Pages : 574

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Author: Je-Chin Han
Publisher: CRC Press
ISBN: 1439855684
Category : Science
Languages : en
Pages : 892

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Book Description
A comprehensive reference for engineers and researchers, Gas Turbine Heat Transfer and Cooling Technology, Second Edition has been completely revised and updated to reflect advances in the field made during the past ten years. The second edition retains the format that made the first edition so popular and adds new information mainly based on selected published papers in the open literature. See What’s New in the Second Edition: State-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling Modern experimental methods for gas turbine heat transfer and cooling research Advanced computational models for gas turbine heat transfer and cooling performance predictions Suggestions for future research in this critical technology The book discusses the need for turbine cooling, gas turbine heat-transfer problems, and cooling methodology and covers turbine rotor and stator heat-transfer issues, including endwall and blade tip regions under engine conditions, as well as under simulated engine conditions. It then examines turbine rotor and stator blade film cooling and discusses the unsteady high free-stream turbulence effect on simulated cascade airfoils. From here, the book explores impingement cooling, rib-turbulent cooling, pin-fin cooling, and compound and new cooling techniques. It also highlights the effect of rotation on rotor coolant passage heat transfer. Coverage of experimental methods includes heat-transfer and mass-transfer techniques, liquid crystal thermography, optical techniques, as well as flow and thermal measurement techniques. The book concludes with discussions of governing equations and turbulence models and their applications for predicting turbine blade heat transfer and film cooling, and turbine blade internal cooling.

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Category : Mechanical engineering
Languages : en
Pages : 576

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Category :
Languages : en
Pages : 14

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Category : Computer-aided design
Languages : en
Pages : 894

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Author:
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Category :
Languages : en
Pages : 18

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Author: Mulugeta K. Berhe
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Category :
Languages : en
Pages : 314

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Author: Justin Kwok
Publisher: World Scientific
ISBN: 1783261064
Category : Computers
Languages : en
Pages : 952

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Book Description
IC-SEC 2002 serves as a forum for engineers and scientists who are involved in the use of high performance computers, advanced numerical strategies, computational methods and simulation in various scientific and engineering disciplines. The conference creates a platform for presenting and discussing the latest trends and findings about the state of the art in their particular field(s) of interest. IC-SEC also provides a forum for the interdisciplinary blending of computational efforts in various diversified areas of science, such as biology, chemistry, physics and materials science, as well as all branches of engineering. The proceedings cover a broad range of topics and an application area which involves modelling and simulation work using high performance computers.

Author: Jacob Damian Moore
Publisher:
ISBN:
Category :
Languages : en
Pages : 484

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The leading-edge regions of turbine vanes and blades require careful attention to their cooling designs because of the high heat loads. External cooling is typically accomplished with dense "showerhead" arrangements of film cooling holes surrounding the stagnation point at the airfoil leading edge. In modern film cooling studies, shaped holes are prevalent in downstream areas of turbine airfoils; however, the literature contains few studies of shaped holes in the showerhead. This leads to a lack of physics-based insight that would lead to the design of high-performing showerhead arrays. This study examined the performance and physical behavior of several showerhead arrangements at the leading edge of a scaled-up turbine blade. A low-speed linear cascade test section was used to simulate the blade environment, and experiments were conducted at scaled engine-realistic conditions. First, the cooling performances of baseline cylindrical and shaped hole designs were compared. The shaped hole design mimicked a standard design in the literature for flat plate studies but with some modifications expected to improve performance specifically at the leading edge. The result was a novel off-center, elliptically-expanding hole. Adiabatic effectiveness and thermal field measurements revealed that the baseline shaped hole had 20-100% performance due to better jet attachment, stemming from its diffuser, which effectively decreased the exit momenta of the coolant jets. The expansion area ratio was increased by 40% for a subsequent design to gauge sensitivity to this parameter; but, surprisingly, the performances of the new design and of the baseline one were nearly identical. A third shaped hole design with a 45% larger breakout area but an identical expansion area resulted in slightly worse performance than either, highlighting the detrimental effect of increasing breakout area and expansion angle. These experiments informed a new proposed scaling parameter incorporating both of these areas and their counteracting effects to predict shaped hole performance in the showerhead. The highest performing design of the group was then tested with an engine-realistic impingement coolant feed, for which performance was overall similar. Supplemental thermal fields using this configuration were performed to construct a 3D representation of the flow field in the showerhead region