Stagnation Region Gas Film Cooling for Turbine Blade Leading-Edge Applications

Autor:	D. W. Luckey, D. K. Winstanley, G. J. Hanus, M. R. L'ecuyer
Rok vydání:	1977
Předmět:	Leading edge Materials science Turbine blade Astrophysics::High Energy Astrophysical Phenomena Flow (psychology) Aerospace Engineering Reynolds number Mechanics Heat transfer coefficient law.invention Coolant Physics::Fluid Dynamics symbols.namesake Heat flux law symbols Cylinder
Zdroj:	Journal of Aircraft. 14:494-501
ISSN:	1533-3868 0021-8669
DOI:	10.2514/3.58806
Popis:	An experimental investigation was conducted to model the film-cooling performance for a turbine-vane leading edge using the stagnation region of a cylinder in cross flow. Experiments were conducted with a single row of spanwise-angled coolant holes for a range of the coolant blowing ratio with a freestream-to-wall temperature ratio of about 2.1 and a Reynolds number of 170,000, characteristic of the gas-turbine environment. Data from local heat-flux measurements are presented for coolant-hole injection angles of 25, 35, and 45 deg with the row of holes located at three positions relative to the stagnation line on the cylinder. Results show the spanwise (hole-to-hole) variation of heat-flux reduction due to film cooling and indicate conditions for the optimum film-cooling performance.
Databáze:	OpenAIRE
Externí odkaz:	https://explore.openaire.eu/search/publication?articleId=doi_________::4c2c13198525a75a36c300aa79395beb https://doi.org/10.2514/3.58806 Zobrazit plný text záznamu