Turbojet engine nozzle for attenuating core and turbine noise

Details Turbojet engine nozzle for attenuating core and turbine noise Turbojet engine nozzle for attenuating core and turbine noise

1976-12-30

1979-02-06

Hix, L. T.

Acoustics

Sound-modifying means

Muffler, fluid conducting type

181269, 181286, 181292, 181293, F01N 100

Patent

active

041379926

ABSTRACT:
Core noise, a low frequency noise component believed to be partly caused by the combustion processes within the engine, and turbine noise, a higher frequency noise component caused by the interaction of high velocity gases with the engine's turbine, are attenuated by noise absorbing structures that are disposed within the engine's nozzle and that in part define the physical geometry of the nozzle duct. The nozzle is formed of an outer sleeve and an inner generally bulb-shaped plug which are coaxially arranged to define an annular nozzle duct that channels the flow of gases rearwardly from the outlet of the engine's turbine. The plug has a hollow interior that is partitioned into a plurality of cavities that communicate with the nozzle duct via perforations provided in an outer wall of the plug. The size, shape and positioning of the interior cavities and outer plug wall perforations are selected so as to absorb noise energy existing in the exhaust gases, both at the relatively low frequencies characteristic of core noise and at the relatively higher frequencies characteristic of turbine noise.

REFERENCES:
patent: 1820972 (1931-09-01), Haas
patent: 2916101 (1959-12-01), Naman
patent: 2988302 (1961-06-01), Smith
patent: 3542152 (1970-11-01), Adamson et al.
patent: 3655009 (1972-04-01), Hilbig
patent: 3819009 (1974-06-01), Motsinger

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