Design of Turbine Rotor

Ramamurthy, S and Murugesan, K (1986) Design of Turbine Rotor. Project Report. National Aerospace Laboratories, Bangalore.

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    Abstract

    The initial turbine stage design by . GTRE for their GTX engine had some scope for improvement ,in performance with regard to surface loading distribution . This aspect was required to be looked into through this sponsored project by GTRE . The cooled rotor blade profiles designated as P-27/GTX-35 (Scheme 8) were redesigned to relieve the excessive forward loading of the existing design and to achieve moderate diffusion . .! along the suction surface . The redesign and modification of these blade profiles were carried out through an iterative procedure using both design and analysis solutions based on singularity method . The redesign of turbine blade was carried out at tip, mean and hub sections . Blade, parameters like pitch, chord, throat, inlet and outlet flow angles were maintained more or less same as that of the given blade profile . Blade camber, stagger and thickness were allowed to vary to get the required velocity distribution . The redesigned tip and mean profiles showed an improvement in velocity distribution . The hub profile was not modified_ but only reoriented at reduced stagger and analysed theoretically . This work was sponsored and funded by GTRE, Bangalore for the development, of their turbine stages

    Item Type: Proj.Doc/Technical Report (Project Report)
    Uncontrolled Keywords: Singularity, Turbine Rotor, Loading distribution
    Subjects: AERONAUTICS > Aircraft Propulsion and Power
    Division/Department: Propulsion Division, Propulsion Division
    Depositing User: Ms Indrani V
    Date Deposited: 22 Aug 2012 09:52
    Last Modified: 22 Aug 2012 09:52
    URI: http://nal-ir.nal.res.in/id/eprint/10828

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