Nalazite se na CroRIS probnoj okolini. Ovdje evidentirani podaci neće biti pohranjeni u Informacijskom sustavu znanosti RH. Ako je ovo greška, CroRIS produkcijskoj okolini moguće je pristupi putem poveznice www.croris.hr
izvor podataka: crosbi !

Improved Cooling fo Gas Turbine Blades (CROSBI ID 477354)

Prilog sa skupa u zborniku | izvorni znanstveni rad | međunarodna recenzija

Ruševljan, Miroslav ; Guzović, Zvonimir ; Josipović, Jasenko Improved Cooling fo Gas Turbine Blades // Thermal Sciences 2000 / Bergles, Arthur E. ; Golobič, Iztok (ur.). Ljubljana: ASME Inetnational - ZSITS, 2000. str. 459-466-x

Podaci o odgovornosti

Ruševljan, Miroslav ; Guzović, Zvonimir ; Josipović, Jasenko

engleski

Improved Cooling fo Gas Turbine Blades

Improved cooling of typical internally air-cooled gas turbine vanes and blades is proposed, with the intention of reducing temperature gradients within the blade material. Inside and/or outside blade surfaces are covered with the graphite foil, which has an anisotropic heat conductivity, as well as with the protective metal foil. It is supposed that the good contact heat transfer between the blade material and the graphite foil can be assured by vacuum. On the rotor blades, artificial roughening of internal surfaces can compensate the low strength of the graphite foil, but with external surfaces the problem is more complex. Numerical calculations of temperature distribution, performed for typical heat transfer conditions, show advantages of applying the graphite foil with anisotropic heat conductivity. Temperature gradients are substantially reduced by applying the graphite foil on the inside and/or outside surfaces of the turbine blade, compared to the turbine blade of the same geometry but without the graphite foil. When applied to cooling passages, the graphite foil can reduce local concentrations of the heat flux, and thus the cooling-air consumption can also be reduced. Although there are technological problems that have to be solved to enable a successful application of this new approach to the cooling of vanes and blades, its potential in reducing temperature gradients within the turbine blade material, simplifying the cooling channels geometry, and thus the reduction of the cooling air flow rate and the pressure drop, seems to be worth of investigation.

gas turbine blades; improved cooling

nije evidentirano

nije evidentirano

nije evidentirano

nije evidentirano

nije evidentirano

nije evidentirano

Podaci o prilogu

459-466-x.

2000.

objavljeno

Podaci o matičnoj publikaciji

Thermal Sciences 2000

Bergles, Arthur E. ; Golobič, Iztok

Ljubljana: ASME Inetnational - ZSITS

Podaci o skupu

The ASME-ZSITS International Thermal Science Seminar 2000

predavanje

11.06.2000-14.06.2000

Bled, Slovenija

Povezanost rada

Strojarstvo