CASCADE TESTS ON CE 20 LOX TURBINE SECOND ROTOR BLADE PROFILE

Senthil Kumaran, R and Swamy, KMM (2006) CASCADE TESTS ON CE 20 LOX TURBINE SECOND ROTOR BLADE PROFILE. Technical Report. National Aerospace Laboratories, Bangalore.

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    Abstract

    LPSC, ISRO as part of their CE 20 cryogenic engine development program, desired to get the liquid oxygen [LOX] turbo pump turbine profiles tested in the NAL Transonic Cascade Tunnel to obtain basic aerodynamic performance data. The LOX turbine consists of a nozzle, first rotor, stator and second rotor. Similar profiles have been designed for the first rotor, stator and second rotor with minor changes in stagger angle and pitch. Hence, the same cascade blades were used to test the first rotor, stator and second rotor configurations at respective pitch, stagger and flow conditions. The tests on the first rotor and stator configuration have been completed earlier. The test details and results of the LOX second rotor configuration are presented in this report. The LOX second rotor configuration was tested at three different inlet flow angles and six outlets Mach numbers. Performance parameters such as profile loss, exit flow angle, flow velocities and surface Mach number distribution were evaluated.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Subjects: AERONAUTICS > Aerodynamics
    AERONAUTICS > Research and Support Facilities (Air)
    ASTRONAUTICS > Spacecraft Propulsion & Power
    ENGINEERING > Fluid Mechanics and Thermodynamics
    Division/Department: Propulsion Division, Propulsion Division
    Depositing User: Mr R Senthil Kumaran
    Date Deposited: 05 Aug 2010 11:52
    Last Modified: 05 Aug 2010 11:52
    URI: http://nal-ir.nal.res.in/id/eprint/8890

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