Aerodynamic and Heat Transfer Studies on HUB sections of a high pressure turbine blade: summary report

Chandrappa, BK and Krishnamurthy, SJ and Krishnamoorthy, V and Murthy, MVA and Murugesan, K and Pai, BR and Ramachandra, MS and Ramamurthy, S and Swamy, KMM and Shambarkar, TR and Soundranayagam, S (1991) Aerodynamic and Heat Transfer Studies on HUB sections of a high pressure turbine blade: summary report. Project Report. National Aerospace Laboratories, Bangalore.

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Abstract

The stator and rotor blade hub sections designed for a high pressure turbine stage were studied in detail for their aerodynamic and heat transfer characteristics . The profile sections were tested in the National Aeronautical Laboratory Cascade Tunnels over a range of exit flow Mach numbers . The flow field and heat transfer characteristics of the cascades were also code based on Denton's method and the boundary layer code incorporating K- E turbulence model. The results indicated that there was a scope for improving the blade profile sections for high Mach number applications.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Mach Number, Cascade, Transonic flow, Heat Transfer, co-efficient, subsonic Flow, Boundary, Layer, Velocity, Distribution, Pressure distribution, energy loss.
Subjects: AERONAUTICS > Aircraft Propulsion and Power
Depositing User: Ms Indrani V
Date Deposited: 04 Jan 2013 08:45
Last Modified: 04 Jan 2013 08:45
URI: http://nal-ir.nal.res.in/id/eprint/11419

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