Acoustically treated exhaust centerbody for jet engines and associated methods
AssigneeThe Boeing Company
InventorsMark D. Gilcreest, Trevor G. Sleath, Daniel F. Gelzer, Merlin C. Windels
Life of this patent
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Abstract
An acoustically treated exhaust centerbody comprising a body including a body fore portion and a body aft portion. An internal passageway extends through the body in the axial direction. A resonator in the body fore portion includes a plurality of acoustic chambers. A plurality of ribs in the resonator form fore/aft walls of the acoustic chambers. Each rib is shaped substantially as a section of an annulus. A plurality of radial fins extend between adjacent ribs. The fins form sidewalls of the acoustic chambers. A skin overlies the acoustic chambers and forms an outer surface of the resonator.
Claims24
An exhaust centerbody, comprising:
- a body including a body fore portion and a body aft portion;
- an internal passageway extending through the body in an axial direction;
- a resonator in the body fore portion, the resonator including a plurality of acoustic chambers;
- a plurality of ribs in the resonator with each rib extending along an interior circumference of the resonator, each rib forming a wall of one of the acoustic chambers with two walls between adjacent acoustic chambers;
- a plurality of radial fins extending between adjacent ribs, the fins forming sidewalls of the acoustic chambers;
- and
- a skin overlying the acoustic chambers and forming an outer surface of the resonator.
A method of attenuating sound energy generated by a jet engine, the method comprising:
- installing an exhaust centerbody within an exhaust system of the jet engine;
- passing exhaust gases from the jet engine over the exhaust centerbody;
- venting air from the jet engine through an internal passageway of the exhaust centerbody;
- trapping the sound energy generated by the jet engine in a resonator within the exhaust centerbody;
- configuring the resonator with at least one acoustic chamber, at least one rib and at least one radial fin;
- configuring the resonator with a plurality of acoustic chambers;
- and
- configuring the resonator with a plurality of ribs with each rib extending along an interior circumference of the resonator, each rib forming a wall of one of the acoustic chambers with two walls between adjacent acoustic chambers.
An exhaust centerbody configured to be disposed within an exhaust nozzle of a jet engine so that exhaust gases from the jet engine travel over an outside surface of the exhaust centerbody, while vented air from the jet engine travels through an internal passageway of the exhaust centerbody, the exhaust centerbody being further configured to attenuate sound energy generated by the jet engine, the exhaust centerbody comprising:
- a body including a body fore portion and a body aft portion, with the internal passageway extending through the body in an axial direction and being configured to receive the vented air from the jet engine;
- a resonator in the body fore portion, the resonator including a plurality of acoustic chambers configured to trap the sound energy;
- a plurality of ribs in the resonator with each rib extending along an interior circumference of the resonator, each rib forming a wall of one of the acoustic chambers and being shaped substantially as a third of an annulus with two walls between adjacent acoustic chambers;
- a plurality of radial fins extending between adjacent ribs, the fins forming sidewalls of the acoustic chambers;
- three cavities extending in radial and axial directions through the resonator and subdividing the acoustic chambers into three circumferentially spaced groups, the radial fins defining sidewalls of the cavities;
- and
- a skin overlying the acoustic chambers and forming an outer surface of the resonator, the skin including perforations that enhance the ability of the acoustic chambers to trap the sound energy.
A method of attenuating sound energy generated by a jet engine using an exhaust centerbody disposed within an exhaust nozzle of the jet engine, the method comprising:
- installing the exhaust centerbody within the exhaust nozzle of the jet engine;
- passing exhaust gases from the jet engine over the exhaust centerbody;
- passing vented air from the jet engine through an internal passageway of the exhaust centerbody;
- and
- trapping the sound energy generated by the jet engine in a resonator within the exhaust centerbody;
- wherein the resonator includes
- a body including a body fore portion and a body aft portion, with the internal passageway extending through the body in an axial direction and being configured to receive the vented air from the jet engine;
- a resonator in the body fore portion, the resonator including a plurality of acoustic chambers configured to trap the sound energy;
- a plurality of ribs in the resonator with each rib extending along an interior circumference of the resonator, each rib forming a wall of one of the acoustic chambers and being shaped substantially as a third of an annulus with two walls between adjacent acoustic chambers;
- a plurality of radial fins extending between adjacent ribs, the fins forming sidewalls of the acoustic chambers;
- three cavities extending in radial and axial directions through the resonator and subdividing the acoustic chambers into three circumferentially spaced groups, the radial fins defining sidewalls of the cavities;
- and
- a skin overlying the acoustic chambers and forming an outer surface of the resonator, the skin including perforations that enhance the ability of the acoustic chambers to trap the sound energy.
Dependencies are inferred from the claim text.