Experimental investigation of the flow field downstream of a plane turbine cascade in transonic flow PDF Download
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Author: R. Kiock
Publisher:
ISBN:
Category :
Languages : de
Pages : 38
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Author: R. Kiock
Publisher:
ISBN:
Category :
Languages : de
Pages : 38
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Author: M. Šťastný
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ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 0
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Book Description
The paper presents results from aerodynamic tests on a transonic rotor turbine profile cascade, including interferograms of the flow field and aerodynamic data measured downstream from the cascade. The dimensions and aerodynamic data on the cascade are given in detail. Analysis following the experimental data collection was aimed at investigating the sensitivity of transonic flow in the vicinity of the throat and related conditions leading to the compression effect. Further, the development of the flow structure and the cascade parameters over a wide range of exit Mach numbers, as well as incidence angles are shown. The experimental data are compared with results of calculations based on mathematical models.
Author:
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Category : Aeronautics
Languages : en
Pages : 704
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Author: P. W. Geil
Publisher:
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Category :
Languages : en
Pages : 20
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Presented at the International Gas Turbine and Aeroengine Congress & Exhibition Birmingham, UK - June 10-13, 1996.
Author: J. B. Meyer
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 12
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Author:
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ISBN:
Category : Turbomachines
Languages : en
Pages : 758
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Author:
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ISBN:
Category : Mechanical engineering
Languages : en
Pages : 488
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Extensive experimental and theoretical investigations of different turbine cascades have been performed within the transonic Mach number range. Some problems related to measurements in rectilinear cascades are discussed. From the done flow field calculations using a 2-d time-marching Euler code limitations can be determined when applying the computer code itself as well as when comparing the calculated data with experimental ones. Experimental and theoretical results within the subsonic Mach number range are used to check the accuracy of simplified methods for calculating the downstream flow angle.
Author: Tibor Kiss
Publisher:
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Category : Aerodynamics, Transonic
Languages : en
Pages : 582
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Author: Wolfgang Sanz
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Stockholm, Sweden, June 2 - June 5, 1998.
