- About
-
The Global ETD Search service is a free service for researchers
to find electronic theses and dissertations. This service is
provided by the
Networked Digital Library of Theses and Dissertations.
Our metadata is collected from universities around the world. If you manage a university/consortium/country archive and want to be added, details can be found on the NDLTD website.
Search results
Showing 71 to 80 of 498 (0.024 seconds)| 71 |
The influence of blade stacking on turbine lossesHarrison, Stephen January 1989 (has links)
No description available.
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| 72 |
An investigation into the absolute life of an internal combustion engineHassaan, H. A. January 1983 (has links)
No description available.
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| 73 |
The effects of reaction on axial compressor performanceFarmakalides, C. D. January 1992 (has links)
No description available.
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| 74 |
Flowfield prediction of NOx and smoke production in aircraft enginesAlizadeh, Sohail January 1993 (has links)
No description available.
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| 75 |
The application of aero gas turbine engine monitoring systems to military aircraftBurgess, C. A. R. January 1990 (has links)
No description available.
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| 76 |
Study of the flowfield in the tip clearance region of compressor bladingsDoukelis, Angelos F. January 1998 (has links)
No description available.
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| 77 |
Smoke production in turbulent kerosene spray flames burning at elevated temperature and pressureFisher, B. A. January 1996 (has links)
No description available.
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| 78 |
A fast time-marching method for non-equilibrium wet steam flows in turbines ?Moheban, M. January 1983 (has links)
No description available.
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| 79 |
Condensation in steam turbine cascadesWhite, Alexander John January 1992 (has links)
No description available.
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| 80 |
Development of a modular-type computer program for the calculation of gas turbine off-design performanceMacMillan, W. L. January 1974 (has links)
This thesis presents a computer program written (in Fortran IV) to simulate the steady state off design point performance of virtually any gas turbine configuration (dealing primarily with aerospace applications). The performance is calculated using component characteristic maps for compressors, combustion chambers, turbines (both compressor turbines and free turbines) and a map giving the velocity coefficient for exhaust nozzles. The off design point performance is determined by using a modified Newton-Raphson method. Cont/d.
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