Sound-absorbing exhaust nozzle center plug
AssigneeRohr, Inc.
InventorsJia Yu, Eugene W. Chien
Life of this patent
Estimating the term…
Abstract
A sound-absorbing exhaust nozzle center plug for an aircraft gas turbine engine can include an outer skin and at least one forward cavity within the outer skin. At least one aft cavity can be located within the outer skin and substantially aft of the forward cavity. A perforated wall including a plurality of first openings can be disposed between the forward and aft cavities. The outer skin can include a second plurality of openings providing an acoustic pathway through the outer skin and into the forward cavity. The forward and aft cavities can be configured to absorb and dissipate relatively low-frequency sound energy emitted from an aircraft gas turbine engine's combustor.
Claims25
A sound-absorbing exhaust center plug for an aircraft gas turbine engine comprising:
- a center plug body adapted for attachment within an exhaust nozzle of the engine and comprising:
- (a) an outer skin;
- (b) at least one forward cavity within the plug body;
- (c) at least one aft cavity within the plug body and substantially aft of the forward cavity;
- and
- (d) a wall separating the forward cavity from the aft cavity, the wall including a plurality of first openings therethrough;
- wherein the outer skin includes a second plurality of openings providing an acoustic pathway through the outer skin and into the forward cavity.
A noise-absorbing center plug for a jet engine exhaust nozzle
- comprising:
- (a) a plug body adapted for assembly within the exhaust nozzle;
- (b) a plurality of walls defining a plurality of circumferentially spaced resonator cavities within the plug body;
- and (c) at least one wall separating at least one of the resonator cavities into a forward sub-cavity and an aft sub-cavity, the wall including a plurality of first openings therethrough.
A noise-absorbing exhaust nozzle center plug for an aircraft gas turbine engine comprising:
- a plug body having a first longitudinal axis and comprising:
- (a) an outer skin surrounding the plug body;
- (b) an inner skin, the outer skin and inner skin forming a substantially annular space therebetween;
- (c) a plurality of walls separating the annular space into a plurality of substantially longitudinally-extending cavities;
- and
- (d) at least one wall dividing the longitudinally extending cavities into forward and aft sub-cavities, the wall including a first plurality of openings therethrough;
- wherein the plug body is configured for assembly within an exhaust nozzle of the aircraft gas turbine engine.
A center plug for an aircraft gas turbine engine exhaust nozzle comprising:
- a plug body comprising:
- (a) a plurality of walls dividing an interior portion of the plug into a plurality of forward cavities and a plurality of aft cavities;
- and
- (b) means for permitting passage of sound energy between the forward and aft cavities;
- and
- (c) means for restricting the sound energy passing between the forward and aft cavities to a substantially plane mode of oscillation;
- wherein the plug body is configured for assembly within the gas turbine engine exhaust nozzle.
An acoustically treated center plug for an aircraft gas turbine engine exhaust nozzle comprising:
- a plug body configured for assembly within the engine exhaust nozzle and comprising:
- (a) an outer skin having a first perforated portion including a first plurality of openings therethrough, and having a second perforated portion including a second plurality of openings therethrough;
- (b) at least one folding resonator cavity within the plug body that is configured to receive sound waves that propagate through the first perforated portion;
- (c) a plurality of non-folding resonator cavities within the body that are configured to receive sound waves that propagate through the second perforated portion;
- and
- (d) an inner skin forming a substantially hollow conduit through the center plug;
- wherein the folding resonator cavity is configured to resonate in response to sound waves in a first range of frequencies, and wherein the non-folding resonator cavities are configured to resonate in response to sound waves in a second range of frequencies different from the first range of frequencies.
A jet engine comprising:
- (a) an exhaust nozzle;
- (b) a center plug at least partially disposed in the exhaust nozzle, the center plug comprising:
- (i) a plurality of walls defining a plurality of circumferentially spaced resonator cavities;
- (ii) at least one wall separating at least one of the resonator cavities into a forward sub-cavity and an aft sub-cavity, the wall including a plurality of openings therethrough.
Dependencies are inferred from the claim text.