Detailed film cooling effectiveness and three component velocity field measurements on a first stage turbine vane subject to high freestream turbulence PDF Download
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Author: Marcus Damian Polanka
Publisher:
ISBN:
Category : Gas-turbanes
Languages : en
Pages : 718
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Author: Marcus Damian Polanka
Publisher:
ISBN:
Category : Gas-turbanes
Languages : en
Pages : 718
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Book Description
Author:
Publisher:
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 726
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Book Description
Annotation This is Volume 1 of five volumes that comprise the proceedings of the June 2002 conference, sponsored by the International Gas Turbine Institute (IGTI), a technical institute of the American Society of Mechanical Engineers. The purpose of the conference was to facilitate international exchange and development of educational and technical information related to the design, application, manufacture, operation, maintenance, and environmental impact of all types of gas engines. With an emphasis upon the need for more efficient, cleaner, and more reliable gas turbines, the approximately 130 articles cover various technical aspects of aircraft engines; coal, biomass, and alternative fuels; combustion and fuels; education; electric power; and vehicular and small turbomachines. There is no subject index. Annotation c. Book News, Inc., Portland, OR (booknews.com).
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 412
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Author: Roger W. Radomsky
Publisher:
ISBN:
Category :
Languages : en
Pages : 368
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Author:
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 732
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Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 414
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Author: D. Granser
Publisher:
ISBN:
Category : Cooling
Languages : en
Pages : 0
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Book Description
After compressor discharge air has initially been used to cool the heat shields of the hot gas inlet casing, it can subsequently be employed for film cooling of the first-stage vane shrouds. Since the flow field near these shrouds is three-dimensional, the film cooling effectiveness cannot be predicted correctly by common two-dimensional codes. The secondary flow transports the film from the pressure side to the suction side where it can even climb up the airfoil to cool its trailing section. Such film cooling effectiveness was first investigated experimentally in a linear vane cascade at atmospheric pressure. The temperatures and static pressure levels at the adiabatic shrouds, as well as the temperature measurements within the vane cascade, are reported for different cooling film blowing rates. In addition, the secondary flow was analysed numerically using a partially-parabolic computer code for 3D viscous flows. It involves mutual interaction of the boundary layer with the mainstream. The secondary flow can also be modelled with this algorithm, which requires less numerical effort than solving the fully 3D elliptic flow equations. The numerical results of the experiment and numerical predictions are compared. In addition, the application of these results to a high-temperature gas turbine is presented.
Author:
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 590
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Annotation Volumes 3A and 3B are part of a five-volume set comprising the proceedings of the June 2002 conference held in the Netherlands. Approximately 125 articles address heat transfer, and manufacturing materials and metallurgy. A sampling of topics: the effect of freestream turbulence on film cooling adiabatic effectiveness; the influence of periodic unsteady inflow conditions on leading edge film cooling; and fluid dynamcis of a pre-swirl rotor-stator system. No subject index. Annotation c. Book News, Inc., Portland, OR (booknews.com).
Author: S. Yavuzkurt
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 238
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Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 956
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