by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va .
Written in English
|Statement||Peter L. Meitner, Arthur J. Glassman.|
|Series||NASA technical paper -- 1708., AVRADCOM technical report -- 80-C-13.|
|Contributions||Glassman, Arthur J., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., Lewis Research Center., Propulsion Laboratory (U.S.)|
|The Physical Object|
|Pagination||12 p. :|
|Number of Pages||12|
The influence of variable geometry stators on the stage behavior is analyzed from both theoretical and experimental points of view. A theoretical analysis of the trajectory of some pressure-ratio lines in a loading-to-flow-coefficient diagram leads to the definition of a specific dimensionless parameter: the reduced by: 6. An off-design performance loss model was developed for variable-stator (pivoted vane), radial turbines through analytical modeling and experimental data analysis. Off-design performance loss model for radial turbines with pivoting, variable-area stators / by: Meitner, Peter L.,, et al. Published: () Final report IEA Wind Annex XX: HAWT aerodynamics and models from wind tunnel measurements. Off-design performance of radial turbine wa s first developed in FORTRAN by Glassman as part of NASA gas turbine progra m since (Wasserbauer & Glassman.
Off-design performance loss model for radial turbines with pivoting, variable-area stators / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; . The area of the nozzle throat is a limiting factor in the performance of a turbocharger; many variable geometry turbocharger concepts allows for the alteration of this area. The effective area depends on the height of the passage (which can be altered in a sliding vane system) and the angle of the vanes (which can be altered in a pivoting vane Cited by: Full text of "NASA Technical Reports Server (NTRS) Bibliography of Lewis Research Center technical publications announced in " See other formats. Principles of Operation Cycle (or Thermodynamic) Point of View Turbine Aero Point of View Radial Equilibrium Performance Considerations Basic Performance Parameters Stage Flow Coefficient Reaction The Turbine Map Turbine Loss Sources Design considerations Cooling Considerations 5/5(10).
Full text of "Monthly catalog of United States government publications" See other formats. ADA | Jet Engine | Aerodynamics ADA 11th International Conference on Turbochargers and Turbocharging Home; 11th International Conference on Turbochargers and Turbocharging 13 14 May OFF-DESIGN PERFORMANCE OF RADIAL INFLOW TURBINES. NASA Technical Reports Server (NTRS) Wasserbauer, C. A. This program calculates off design performance of radial inflow turbines. The program uses a one dimensional solution of flow conditions through the turbine along the main streamline. The loss model accounts for stator, rotor.