During transient operation of a gas turbine there are significant heat transfers between the fluid stream and the blades of the compressor and turbine. At the end of a rapid deceleration from maximum speed to idling speed, heat transfer to the compressor blade boundary layers may cause sufficient disturbance to delay any immediate re-acceleration. As a first estimate in one severe case - at altitude in an aircraft engine of compression ratio 20 - the surge margin prior to the re-acceleration is reduced by about 40% due to boundary layer effects, and by a further 25% due to “bulk” heat transfer.
The Effect of Boundary Layer Changes Due to Transient Heat Transfer on the Performance of an Axial-Flow Air Compressor
Sae Technical Papers
1977 International Automotive Engineering Congress and Exposition ; 1977
01.02.1977
Aufsatz (Konferenz)
Englisch
Discussion of boundary-layer characteristics near wall of axial-flow compressor
Engineering Index Backfile | 1952
|Axial flow compressor performance deterioration
AIAA | 1984
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