Serrated nozzle trailing edge for exhaust noise suppression

Details Serrated nozzle trailing edge for exhaust noise suppression Serrated nozzle trailing edge for exhaust noise suppression

2005-08-10

2009-06-09

Rodríguez, William H (Department: 3741)

Power plants

Reaction motor

Particular exhaust nozzle feature

C060S039500, C060S226100

Reexamination Certificate

active

07543452

ABSTRACT:
A nozzle for a gas turbine engine is provided with undulations on a core and/or fan exhaust flow nozzle. An annular wall defines a fluid flow passage and includes a base portion and an adjoining exit portion. The base portion is typically generally frustoconical in shape and includes an arcuate contour in an axial direction. The exit portion includes undulations in a generally radial direction that provide lobes and troughs each respectively including trailing edges. One of the lobe and trough trailing edges are recessed from the other of the lobe and trough trailing edges in a generally axial direction. The other of the lobe and trough trailing edges form apexes with the apexes provided on tabs. The troughs extend radially inward in the axial direction towards the trough trailing edges.

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Samimy, Zaman and Reeder, “Effect of Tabs on the Flow and Noise Field of an Axisymmetric Jet”, AIAA Journal vol. 31, No. 4, Apr. 1993, p. 609-619, American Institute of Aeronautics and Astronaustics, Inc.

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