dc.contributor.author |
D. H. Mallinson |
en_US |
dc.contributor.author |
W. G. E. Lewis |
en_US |
dc.date.accessioned |
2014-10-21T15:52:08Z |
|
dc.date.available |
2014-10-21T15:52:08Z |
|
dc.date.issued |
1947 |
en_US |
dc.identifier.other |
ARC/R&M-2645 |
en_US |
dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/3185 |
|
dc.description.abstract |
This report describes.a theoretical investigation using conventional component-characteristics to discover that division of work between the low and high-pressure compressors of a double-compound simple-jet gas turbine of 12 : 1 design pressure ratio which is likely to result in the most desirable equilibrium operation over the normal engine speed range. Having decided in favour of a pressure ratio of 3 : 1 in the low-pressure compressor and 4 : 1 in the other, a study is then made using more realistic compressor characteristics to determine the probable performance of such an engine under all flight conditions when the design maximum temperature is 900 deg C (1173 deg K). The equilibrium running conditions of the engine are investigated with special reference to the problems introduced by the double-compound type of design. |
en_US |
dc.relation.ispartofseries |
Aeronautical Research Council Reports & Memoranda |
en_US |
dc.title |
Performance calculations for a double-compound turbo-jet engine of 12:1 design compressor pressure ratio |
en_US |