EXPERIMENTAL INVESTIGATIONS ON SEMI-CRYO ROCKET ENGINE TURBO PUMP TURBINE PROFILES PART II - ROTOR PROFILE

Senthil Kumaran, R and Swamy, KMM (2009) EXPERIMENTAL INVESTIGATIONS ON SEMI-CRYO ROCKET ENGINE TURBO PUMP TURBINE PROFILES PART II - ROTOR PROFILE. Technical Report. National Aerospace Laboratories, Bangalore.

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    Abstract

    LPSC, ISRO, as part of their semi-cryogenic rocket engine development program for the reusable launch vehicle, desired to get its turbo pump turbine profiles tested in the NAL Transonic Cascade Tunnel (TCT), to obtain basic aerodynamic performance data. The mean section profiles of the nozzle vane and rotor blade of this turbo pump turbine were tested in TCT. The test details and results of the rotor blade profile are discussed in this report viz a viz Part II and the details pertaining to the nozzle vane profile are furnished in Part I. The aerodynamic performance parameters such as profile loss, flow deflection, flow velocities and surface Mach number distribution were evaluated during the cascade tests. Both the profiles were tested over a range of inlet flow angles and outlet Mach numbers covering their respective design and off-design conditions. Detailed post processing of the test results were carried out and key aspects such as the effect of incidence and effect of Mach number on the performance were studied. An oil flow visualization study was also conducted on these profiles at their respective design condition, to ascertain the flow pattern over the blade surfaces.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Subjects: PHYSICS
    Division/Department: Propulsion Division, Propulsion Division
    Depositing User: Mr R Senthil Kumaran
    Date Deposited: 05 Aug 2010 11:55
    Last Modified: 05 Aug 2010 11:55
    URI: http://nal-ir.nal.res.in/id/eprint/8893

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