Turbomachinery Blade Profile Design

Ramamurthy, S and Murugesan, K (1987) Turbomachinery Blade Profile Design. In: 3rd National Conference on Aerodynamics, 1987, IIT,Bombay. (Submitted)

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Turbomachinery blade profiles in use today were all derived out of conventional methods. For example an impulse blading of a turbine is derived out of multi circular arcs of different radii for, suction surface and pressure surface with a suitable leading and trailing edge radii. The reaction bladings were designed purely out of empirism based on the amount of acceleration or Gulf factor i.e., the ratio of throat opening to pitch (Ref-l),where as compressor blade profiles were derived by imposing a suitable c r on a known base profile with a chosen thickness distribution.The performance of these profiles were assessed by conducting series of experiments which involves the measurement of surface velocity distribution and profile loss. From the experimental results each profile can be given a tag of operating range. Selection of blade profile for a given velocity distribution involves the complete scanning of experimental results, which becomes tedious and time consuming. Now a days many theoretical methods are available to evaluate the performance of the blade profile. These methods were extensively used to update the blade profiles originated during the early decades.

Item Type: Conference or Workshop Item (Lecture)
Uncontrolled Keywords: Turbomachinery, velocity distribution, profile loss,
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aircraft Propulsion and Power
Depositing User: Dr S Ramamurthy
Date Deposited: 10 Aug 2010 08:21
Last Modified: 10 Aug 2010 08:21
URI: http://nal-ir.nal.res.in/id/eprint/8912

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