Kishor Kumar, and Senthil Kumaran, R and Swamy, KMM and Jagannatha Rao, B and Krishnoji Rao, NS and Poornima, N and Loganathan, KS (2010) Aerodynamic Investigations on a Single Stage Turbine to Benchmark LSRR. Project Report. CSIR-NAL, Bangalore, Bangalore, INDIA.Full text available as:
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The Large Scale Rotating Rig (LSRR) was transferred from Pratt and Whitney, USA to National Aerospace Laboratories (NAL), Bangalore, India on a collaborative project. The rig is now successfully installed and commissioned at NAL. The rig currently incorporates a single stage axial flow reaction turbine (a row of stator vanes and a row of rotor blades) which was earlier tested by Pratt & Whitney, USA at UTRC. A sophisticated indigenous data acquisition system was designed and developed to cater to the various experimental requirements of the rig such as vane, blade, casing, hub surface pressure measurement, vane / blade exit wake flow measurement, temperature measurements and online calibration of pressure transducers. In order to benchmark the rig, few experiments were carried out and the aerodynamic parameters of the vane and rotor were evaluated. The aerodynamic parameters such as total pressure coefficient and flow angles (past the vane and rotor) were evaluated. These parameters were determined by traversing five / three hole pressure probes in the wake flows. The measurements were made at three different radial locations past the vane and the rotor. The probe data were reduced using a multiple regression model that was earlier used by Pratt & Whitney, USA. The details of the rig, experimental methodology and a brief discussion of the results are provided in this report. The aerodynamic data from the benchmark experiments are also compared with that supplied by Pratt and Whitney, USA. As expected, the flow near the hub and tip region was highly complex due to the secondary flows.
|Item Type:||Proj.Doc/Technical Report (Project Report)|
|Subjects:||AERONAUTICS > Aerodynamics|
|Division/Department:||Propulsion Division, Propulsion Division, Propulsion Division, Propulsion Division, Propulsion Division, Propulsion Division, Propulsion Division|
|Depositing User:||Mr. Kishor Kumar|
|Date Deposited:||01 Jul 2011 11:16|
|Last Modified:||01 Jul 2011 11:16|
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