Author : Jeffrey E. Haas
Publisher :
Page : 28 pages
File Size : 14,45 MB
Release : 1975
Category : Axial flow
ISBN :
A solid blade version of a single-stage, axial-flow turbine was investigated to determine its performance over a range of speeds from 0 to 105 percent of equivalent design speed and over a range of total to static pressure ratios from 1.62 to 5.07.
Author : Jeffrey E. Haas
Publisher :
Page : 32 pages
File Size : 33,54 MB
Release : 1977
Category : Gas-turbines
ISBN :
Author :
Publisher :
Page : 46 pages
File Size : 10,6 MB
Release : 1977
Category :
ISBN :
Author :
Publisher :
Page : 540 pages
File Size : 32,88 MB
Release : 1977
Category : Astronautics
ISBN :
Author :
Publisher :
Page : 326 pages
File Size : 11,23 MB
Release : 1975
Category :
ISBN :
Author : United States. National Aeronautics and Space Administration
Publisher :
Page : 964 pages
File Size : 47,37 MB
Release : 1977
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 52 pages
File Size : 34,80 MB
Release : 1978
Category :
ISBN :
Author :
Publisher :
Page : 56 pages
File Size : 18,64 MB
Release : 1978
Category : Aeronautics
ISBN :
Author : Technology Reports Centre (Great Britain)
Publisher :
Page : 460 pages
File Size : 29,99 MB
Release : 1978
Category :
ISBN :
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 38 pages
File Size : 16,95 MB
Release : 2018-08-22
Category :
ISBN : 9781726001458
An air cooled version of a single-stage, axial-flow turbine was investigated to determine aerodynamic performance with and without air ejection from the stator and rotor blades surfaces to simulate the effect of cooling air discharge. Air ejection rate was varied from 0 to 10 percent of turbine mass flow for both the stator and the rotor. A primary-to-air ejection temperature ratio of about 1 was maintained. Haas, J. E. and Kofskey, M. G. Glenn Research Center NASA-TP-1018 RTOP 505-04...
