Swan neck duct

From Wikipedia, the free encyclopedia
Jump to navigation Jump to search

A swan neck duct is a jet engine component, usually situated within the compression or turbine expansion system.[1]

Many jet engines have a short annular passageway, linking two components, where there is a large change in mean radius, from front to rear; the shape of the resulting passageway is often similar to that of a swan or goose neck. Consequently, such a passageway is called a swan (or goose) neck duct; the duct provides a continuous matching of the flows between the high pressure and low pressure turbines and a diffusion of the flow upstream of the low pressure turbine. For the latter purpose a swan neck duct is an example of an inter-turbine diffuser.[2]

See also[edit]


  1. ^ Soares, Claire. Gas Turbines: A Handbook of Air, Land and Sea Applications. Elsevier. p. 179. ISBN 9780124104853. Retrieved 27 August 2016.
  2. ^ Dominy, Robert G.; Kirkham, David A. (13 June 1994). "The Influence of Blade Wakes on the Performance of Inter-Turbine Diffusers". ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. 1: V001T01A072. doi:10.1115/94-GT-207. Retrieved 28 August 2016.