Zobrazeno 1 - 8
of 8
pro vyhledávání: '"G. J. Van Fossen"'
Publikováno v:
Journal of Turbomachinery. 120:305-313
Turbine blade endwall heat transfer measurements are given for a range of Reynolds and Mach numbers. Data were obtained for Reynolds numbers based on inlet conditions of 0.5 and 1.0 x 106, for isentropic exit Mach numbers of 1.0 and 1.3, and for free
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::07bf1dd3fba6bf15361a2adff69aa983
https://doi.org/10.1115/1.2841407
https://doi.org/10.1115/1.2841407
Publikováno v:
Journal of Heat Transfer. 117:597-603
The purpose of the present work was threefold: (1) to determine if a free-stream turbulence length scale existed that would cause the greatest augmentation in stagnation-region heat transfer over laminar levels; (2) to investigate the effect of veloc
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::3a5d4749b9b21916da1990cf78f6a9b3
https://doi.org/10.1115/1.2822619
https://doi.org/10.1115/1.2822619
Publikováno v:
Journal of Aircraft. 28:908-911
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0e815cd96bd6f61676c7389ac292b1a7
https://doi.org/10.2514/3.46116
https://doi.org/10.2514/3.46116
Publikováno v:
Journal of Aircraft. 28:892-898
Local convective heat transfer coefficients were measured from a smooth NACA 0012 airfoil having a chord length of 0.533 m. Flight data were taken for the smooth airfoil at Reynolds numbers based on chord in the range 1.24 to 2.50 million and at vari
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::820a61c8da6719836042f717012d722c
https://doi.org/10.2514/3.46114
https://doi.org/10.2514/3.46114
Publikováno v:
Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration.
Detailed heat transfer measurementa and predictions are given for a turbine rotor with 136° of turning and an axial chord of 12.7 cm. Data were obtained for inlet Reynolds numbers of 0.5 and 1.0 × 106, for isentropic exit Mach numbers of 1.0 and 1.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::30681a7625d3fdb2fe566d0ece31bdb1
https://doi.org/10.1115/99-gt-125
https://doi.org/10.1115/99-gt-125
Autor:
I. Lopez, W. P. Camperchioli, P. W. Giel, T. A. Jett, G. J. Van Fossen, R. J. Boyle, D. R. Thurman, H. La
Publikováno v:
Volume 1: Turbomachinery.
Three-dimensional flow field measurements are presented for a large scale transonic turbine blade cascade. Flow field total pressures and pitch and yaw flow angles were measured at an inlet Reynolds number of 1.0 × 106 and at an isentropic exit Mach
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::68a76c7ed35c4b4dd3f254cbd20d9292
https://doi.org/10.1115/96-gt-113
https://doi.org/10.1115/96-gt-113
Autor:
D. L. Rigby, G. J. Van Fossen
Publikováno v:
22nd Fluid Dynamics, Plasma Dynamics and Lasers Conference.
The present study numerically demonstrates how small spanwise variations in velocity upstream of a body can cause relatively large increases in the spanwise-averaged heat transfer to the leading edge. Vorticity introduced by spanwise variations, firs
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::cdc8f29c4709e63ad43daa29aadf38ca
https://doi.org/10.2514/6.1991-1739
https://doi.org/10.2514/6.1991-1739
Publikováno v:
22nd Aerospace Sciences Meeting.
Local heat transfer coefficients were obtained on irregular cylindrical shapes which typify the accretion of ice on circular cylinders in cross flow. The ice shapes were grown on a 5.1 cm (2.0 in.) diameter cylinder in the NASA Lewis Icing Research T
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d8134d6b2f15f808336c58a82a76e8d3
https://doi.org/10.2514/6.1984-17
https://doi.org/10.2514/6.1984-17