Zobrazeno 1 - 8
of 8
pro vyhledávání: '"G. James Van Fossen"'
Autor:
G. James Van Fossen, Chan Y. Ching
Publikováno v:
International Journal of Rotating Machinery, Vol 3, Iss 2, Pp 117-132 (1997)
The purpose of the present work was twofold: first, to determine if a length scale existed that would cause the greatest augmentation in stagnation region heat transfer for a given turbulence intensity and second, to develop a prediction tool for sta
Externí odkaz:
https://doaj.org/article/a2f8bac0bd84423b9b1e1d2877a3b449
Publikováno v:
Journal of Aircraft. 40:1161-1167
Experimental Frossling numbers are presented for two aluminum castings of ice-roughened NACA 0012 airfoil surfaces at 0-deg angle of attack for chord Reynolds number ranging from 4.00 £ £10 5 to 1.54£10 6 . The castings were meticulously obtained
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::78ae9187ff5fa37bcd7d300d3d7e67ef
https://doi.org/10.2514/2.7205
https://doi.org/10.2514/2.7205
Publikováno v:
Journal of Aircraft. 36:948-956
Experimental Stanton numbers are presented for seven aluminum model castings of ice-roughened surfaces in parallel air e ow for Rex ranging from 5 :3 £ 10 4 to 1:3 £ 10 6 . The Stanton numbers were generally higher than those for previous studies w
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0e65bae62ae19f3b0c88422fc7965cfe
https://doi.org/10.2514/2.2556
https://doi.org/10.2514/2.2556
Autor:
Ali Ameri, Steven A. Hippensteele, G. James Van Fossen, Philip E. Poinsatte, Frederick C. Yeh
Publikováno v:
Journal of Propulsion and Power. 10:868-875
Experimental data on pressure distribution and heat transfer on a turbine airfoil were obtained over a range of Reynolds numbers from 0.75 to 7.0 x 10(exp 6) and a range of turbulence intensities from 1.8 to about 15%. The purpose of this study was t
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::41f261b139ba1cb11a3b1aadd539dd1b
https://doi.org/10.2514/3.23825
https://doi.org/10.2514/3.23825
Publikováno v:
Journal of Aircraft. 36:896-898
The equivalentangle®¤ has been plottedvs ® for differentvalues of in Fig. 2. It is obvious that, when D 0, then ® D a¤, whereas when ®D 0, then ®¤D . For small (typically, for < 5 deg), ®1⁄4 ®¤, but, otherwise, there is a signi cant di
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::66ec2e4d74b9c1e8783b8dba892962fa
https://doi.org/10.2514/2.2527
https://doi.org/10.2514/2.2527
Publikováno v:
Volume 3: Turbo Expo 2002, Parts A and B.
Heat transfer measurements have been made in the stagnation region of a flat plate with an elliptical leading edge. The radius of curvature at the stagnation point was similar to that of a first stage turbine vane airfoil used in a large commercial h
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0a6a77193224e51dbad6355ef8cfb194
https://doi.org/10.1115/gt2002-30184
https://doi.org/10.1115/gt2002-30184
Publikováno v:
Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration.
Detailed heat transfer measurements and predictions are given for a power generation turbine rotor with 129 deg of nominal turning and an axial chord of 137 mm. Data were obtained for a set of four exit Reynolds numbers comprised of the design point
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::dee2c54974849c0b29d56b4bd8c43446
https://doi.org/10.1115/2000-gt-0209
https://doi.org/10.1115/2000-gt-0209
Publikováno v:
Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration.
Heat transfer measurements have been made in the stagnation region of a flat plate with a circular leading edge. Electrically heated aluminum strips placed symmetrically about the leading edge stagnation region were used to measure spanwise averaged
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::80fffa11d4427b593c347c194791e34d
https://doi.org/10.1115/2000-gt-0215
https://doi.org/10.1115/2000-gt-0215