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Axial Turbine Loss Analysis and Efficiency Prediction Method.

AD479973

Publication Date	1966
Personal Author	Hong, Y. S.; Groh, F. G.
Page Count	121
Abstract	A method is presented to predict axial stage turbine efficiency using detailed aerodynamic component losses. Suitable computer programs were set up for the more time consuming portions of the calculations. Boundary layer theory plus empirical test data was used to obtain numerical values for the flow losses. The method was applied to typical Boeing turbine tests and stage efficiencies were compared with the measured values. Calculated and measured stage efficiencies agreed within plus or minus one percent in all cases. This achievement proved to be far superior to existing prediction methods which yielded efficiency accuracies ranging from 2 to 7 percent. Using the developed method, the performance of a given turbine stage can be optimized without spending an excessive amount of time for numerical calculations by evaluating various combination of aspect ratio, solidity, number of blades, trailing edge thickness, and rotor tip clearance. All the investigated cases were checked for only single stage axial turbines. The accuracy of the method for multi-stage application has yet to be verified by experiment. (Author)
Keywords	Axial flow turbines Effectiveness Computer programming Mathematical prediction Turbine stators Gas turbines Design Optimization Experimental data Boundary layer Flow separation Rotor blades(Turbomachinery) Trailing edge Aspect ratio Walls Shear stresses Reynolds number Two dimensional flow Subsonic flow Velocity
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	94I - Hydraulic & Pneumatic Equipment
Corporate Authors	Boeing CO Seattle Wash Turbine Div
Document Type	Technical Report
NTIS Issue Number	198104

Axial Turbine Loss Analysis and Efficiency Prediction Method.

Axial Turbine Loss Analysis and Efficiency Prediction Method.
AD479973

Publication Date	1966
Personal Author	Hong, Y. S.; Groh, F. G.
Page Count	121
Abstract	A method is presented to predict axial stage turbine efficiency using detailed aerodynamic component losses. Suitable computer programs were set up for the more time consuming portions of the calculations. Boundary layer theory plus empirical test data was used to obtain numerical values for the flow losses. The method was applied to typical Boeing turbine tests and stage efficiencies were compared with the measured values. Calculated and measured stage efficiencies agreed within plus or minus one percent in all cases. This achievement proved to be far superior to existing prediction methods which yielded efficiency accuracies ranging from 2 to 7 percent. Using the developed method, the performance of a given turbine stage can be optimized without spending an excessive amount of time for numerical calculations by evaluating various combination of aspect ratio, solidity, number of blades, trailing edge thickness, and rotor tip clearance. All the investigated cases were checked for only single stage axial turbines. The accuracy of the method for multi-stage application has yet to be verified by experiment. (Author)
Keywords	Axial flow turbines Effectiveness Computer programming Mathematical prediction Turbine stators Gas turbines Design Optimization Experimental data Boundary layer Flow separation Rotor blades(Turbomachinery) Trailing edge Aspect ratio Walls Shear stresses Reynolds number Two dimensional flow Subsonic flow Velocity
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	94I - Hydraulic & Pneumatic Equipment
Corporate Authors	Boeing CO Seattle Wash Turbine Div
Document Type	Technical Report
NTIS Issue Number	198104