The Effect of Boundary Layer Changes Due to Transient Heat Transfer on the Performance of an Axial-Flow Air Compressor

Format:

Conference/Event

Author/Creator:

Maccallum, N. R. L., author.

Conference Name:

1977 International Automotive Engineering Congress and Exposition (1977-02-28 : Detroit, Michigan, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1977

Summary:

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

Notes:

Vendor supplied data

Publisher Number:

770284

Access Restriction:

Restricted for use by site license