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Titolo:
Numerical investigation into the effects of a radial gap on hydraulic turbine performance
Autore:
Sato, K; He, L;
Indirizzi:
Univ Durham, Sch Engn, Durham DH1 3LE, England Univ Durham Durham England DH1 3LE am, Sch Engn, Durham DH1 3LE, England
Titolo Testata:
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART A-JOURNAL OF POWER AND ENERGY
fascicolo: A1, volume: 215, anno: 2001,
pagine: 99 - 107
SICI:
0957-6509(2001)215:A1<99:NIITEO>2.0.ZU;2-M
Fonte:
ISI
Lingua:
ENG
Soggetto:
FLOW TURBINES;
Keywords:
radial turbomachinery; unsteady flows; rotor/stator blade row interaction;
Tipo documento:
Article
Natura:
Periodico
Settore Disciplinare:
Engineering, Computing & Technology
Citazioni:
14
Recensione:
Indirizzi per estratti:
Indirizzo: He, L Univ Durham, Sch Engn, South Rd, Durham DH1 3LE, England Univ DurhamSouth Rd Durham England DH1 3LE Durham DH1 3LE, England
Citazione:
K. Sato e L. He, "Numerical investigation into the effects of a radial gap on hydraulic turbine performance", P I MEC E A, 215(A1), 2001, pp. 99-107

Abstract

The effects of the rotor/stator blade row interaction on the performance of radial turbine stages are investigated numerically. A three-dimensional unsteady incompressible Navier-Stokes method based on the dual-time steppingand the pseudocompressibility method is developed for the performance prediction A centrifugal pump with a vaned diffuser is calculated for validation purposes, and the predicted unsteady flow results show reasonable agreement with the experimental data. The method is applied to analysis of hydraulic turbine stages. A generic turbine rotor is combined with a row of nozzleguide vanes with three settings of radial gap and numerical now simulations are conducted for the performance evaluations. The predicted efficiency of the hydraulic turbine stages deteriorates if the radial gap between bladerows is reduced although the difference is very small. The entropy rises along the streamlines suggest that the differences in the stage efficiency level can be largely attributed to the loss generated in the nozzle vane passages.

ASDD Area Sistemi Dipartimentali e Documentali, Università di Bologna, Catalogo delle riviste ed altri periodici
Documento generato il 09/04/20 alle ore 13:29:18