Aerodynamical Investigations on Reaction Turbine Blades

Youssef, M. R (1941) Aerodynamical Investigations on Reaction Turbine Blades. PhD thesis, University of Glasgow.

Abstract

So far no theory of the Reaction Turbine has as yet been investigated which is capable of clarifying fully the effect of such factors as the number of blades, the blade angle, the blade pitch and the breadth of the blade upon the action of these machines. It Is known that the "lift" of biplanes and triplanes per unit of wing surface is Inferior to that of a monoplane, and that the degree of departure depends upon the gap-chord ratio. Published data indicate that the lift increases with increasing gap, apparently towards some limiting value. Regarding steam turbine wheels as rings of multiplanes, it may be asked "Is there any direct evidence that the torque on each blade Is influenced by the presence of the other blades?" Many experiments have been made to determine the optimum circumferential pitch for a given blade shape, but most of these have aimed simply at arriving empirically at the best efficiency, without inquiry into the factors involved. The present investigations were carried out on Model Reaction Blades reproduced several times the actual full size so that the Reynold's number is maintained at a value of interest in turbine design, but with comparatively low air speeds usual in WIND TUNNEL work, to examine the effects of the number of blades, the blade pitch and the blade angle.

• Item Type: Thesis (PhD)
• Qualification Level: Doctoral
• Keywords: Mechanical engineering, Aerospace engineering
• Date of Award: 1941
• Depositing User: Enlighten Team
• Unique ID: glathesis:1941-79520
• Copyright: Copyright of this thesis is held by the author.
• Date Deposited: 05 Mar 2020 08:55
• Last Modified: 05 Mar 2020 08:55
• URI: https://theses.gla.ac.uk/id/eprint/79520