Accession Number : ADP006201
Title : Design and Test of a High Blade Speed, High Work Capacity Transonic Turbine,
Corporate Author : ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)
Personal Author(s) : Kingcombe, R. C. ; Bryce, J. D. ; Leversuch, N. P.
Report Date : SEP 1987
Pagination or Media Count : 17
Abstract : A high rim speed turbine has been designed and tested at RAE Pyestock. A major objective in the design was to achieve high aerodynamic efficiency at high work capacity by way of reduced stage loading - facilitated by high blade speed. The design includes three dimensional features such as a parabolic distribution of exit angle and compound trailing edge lean on the nozzle guide vane and a thick root, highly tapered rotor blade - necessary in an engine turbine to moderate blade stress. The paper describes the design approach and presents and discusses the results of cold flow rig tests undertaken at RAE Pyestock. Measurements included NGV and rotor blade surface static pressures as well as detailed traverses.
Descriptors : *GAS TURBINES, *TURBINE COMPONENTS, AERODYNAMICS, ROTOR BLADES, AERODYNAMICS, TRAILING EDGES, COLD FLOW, RIGGING, STATIC PRESSURE, AERODYNAMICS, ANGLES, BLADES, CAPACITY(QUANTITY), COLD FLOW, DISTRIBUTION, EFFICIENCY, ENGINES, EXITS, GUIDE VANES, HIGH RATE, NOZZLES, PARABOLAS, REDUCTION, ROTOR BLADES, STRESSES, TAPER, TEST METHODS, THICKNESS, THREE DIMENSIONAL, TRAILING EDGES, TURBINES, VELOCITY.
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE