초록 ▼

An exhaust silencer assembly comprising a casing having an exhaust gas entrance opening, an exhaust gas exit opening, and a cooling air inlet opening, and an acoustic-attenuating porous liner disposed within an interior chamber of the casing, thereby dividing the interior chamber into an inner regio

An exhaust silencer assembly comprising a casing having an exhaust gas entrance opening, an exhaust gas exit opening, and a cooling air inlet opening, and an acoustic-attenuating porous liner disposed within an interior chamber of the casing, thereby dividing the interior chamber into an inner region located between the exhaust gas entrance opening and the exhaust gas exit opening, and an outer region located between the acoustic-attenuating porous liner and the casing, where the cooling air inlet opening is located at the outer region.

대표청구항 ▼

The invention claimed is: 1. An exhaust silencer assembly for use with a turbine engine, the exhaust silencer assembly comprising: a casing defining an interior chamber, and having an exhaust gas entrance opening, an exhaust gas exit opening, and a cooling air inlet opening; and an acoustic-attenua

The invention claimed is: 1. An exhaust silencer assembly for use with a turbine engine, the exhaust silencer assembly comprising: a casing defining an interior chamber, and having an exhaust gas entrance opening, an exhaust gas exit opening, and a cooling air inlet opening; and an acoustic-attenuating porous liner disposed within the interior chamber of the casing, thereby dividing the interior chamber into an inner region located between the exhaust gas entrance opening and the exhaust gas exit opening, and an outer region located between the acoustic-attenuating porous liner and the casing, wherein the cooling air inlet opening is located at the outer region, so as to create a flow path from the cooling air inlet opening, through the acoustic-attenuating porous liner, to the exhaust gas exit opening. 2. The exhaust silencer assembly of claim 1, further comprising an air inlet duct secured to the casing at the cooling air inlet opening and forming part of the flow path with the cooling air inlet opening, through the acoustic-attenuating porous liner, to the exhaust gas exit opening. 3. The exhaust silencer assembly of claim 1, wherein the casing is integrated with an exterior structure of an aircraft. 4. The exhaust silencer assembly of claim 1, wherein the acoustic-attenuating porous liner comprises a plurality of passage holes that have a combined surface area ranging from about 5% to about 40% of a total surface area of the acoustic-attenuating porous liner. 5. The exhaust silencer assembly of claim 4, wherein the combined surface area of the plurality of passage holes ranges from about 10% to about 30% of the total surface area of the acoustic-attenuating porous liner. 6. The exhaust silencer assembly of claim 1, wherein the acoustic-attenuating porous liner has a diameter that increases from the exhaust gas entrance opening to the exhaust gas exit opening. 7. The exhaust silencer assembly of claim 1, further comprising an outboard outlet duct secured to the casing at the outer region, wherein the outboard outlet duct and the exhaust gas exit opening are positioned on opposite sides of the acoustic-attenuating porous liner. 8. The exhaust silencer assembly of claim 1, wherein the cooling air inlet opening comprises an eductor entrance for receiving cooling air from an interior compartment of an aircraft. 9. The exhaust silencer assembly of claim 1, in combination with a gas turbine engine. 10. An exhaust silencer assembly for use with a turbine engine, the exhaust silencer assembly comprising: at least one attenuation stage comprising: a casing having an entrance opening configured to be positioned downstream from the turbine engine, an exit opening disposed downstream from the entrance opening; and a cooling air inlet opening; and an acoustic-attenuating porous liner disposed within the casing, thereby providing an inner region located between the entrance opening and the exit opening, and an outer region located between the acoustic-attenuating porous liner and the casing, wherein the cooling air inlet opening is located at the outer region, so as to create a flow path from the cooling air inlet opening, through the acoustic-attenuating porous liner, to the exit opening; and an air inlet duct secured to the casing of the at least one attenuation stage at the cooling air inlet opening and forming part of the flow path with the cooling air inlet opening, through the acoustic-attenuating porous liner, to the exit opening. 11. The exhaust silencer assembly of claim 10, further comprising a heat exchanger disposed along the air inlet duct. 12. The exhaust silencer assembly of claim 10, wherein the casing is integrated with an exterior structure of an aircraft. 13. The exhaust silencer assembly of claim 10, wherein the casing also has an outlet opening located at the outer region, wherein the exhaust silencer assembly further comprises an outlet duct secured to the casing at the outlet opening, and wherein the outlet opening and the exit opening are positioned on opposite sides of the acoustic-attenuating porous liner. 14. The exhaust silencer assembly of claim 10, wherein the cooling air inlet opening is disposed at an axially offset location along the casing from the entrance opening. 15. The exhaust silencer assembly of claim 10, in combination with a gas turbine engine. 16. An exhaust silencer assembly for use with a turbine engine, the exhaust silencer assembly comprising: a casing having an exhaust gas passageway; a liner disposed within the casing and axially around the exhaust gas passageway, the liner comprising a plurality of passage holes configured to dissipate acoustic energy; an annular hollow region disposed between the casing and the liner; and at least one cooling air inlet opening extending through the casing into the annular hollow region. 17. The exhaust silencer assembly of claim 16, wherein the exhaust gas passageway comprises an entrance opening in the casing that is configured to be positioned downstream from the turbine engine, and an exit opening in the casing that is configured to be positioned upstream from an exhaust pipe. 18. The exhaust silencer assembly of claim 16, further comprising an air inlet duct secured to the casing at the at least one cooling air inlet opening and sharing a flow path with the at least one cooling air inlet opening. 19. The exhaust silencer assembly of claim 16, wherein the casing further includes an outlet opening located at the annular hollow region, wherein the exhaust silencer assembly further comprises an outlet duct secured to the casing at the outlet opening, and wherein the outlet duct and the exhaust gas passageway are positioned on opposite sides of the liner. 20. The exhaust silencer assembly of claim 16, wherein the at least one cooling air inlet opening comprises an eductor entrance for receiving cooling air from an interior compartment of an aircraft. 21. The exhaust silencer assembly of claim 16, wherein the plurality of passage holes have a combined surface area ranging from about 5% to about 40% of a total surface area of the liner. 22. The exhaust silencer assembly of claim 16, wherein the plurality of passage holes have an average holes size ranging from about 1 millimeter to about 10 millimeters. 23. The exhaust silencer assembly of claim 16, in combination with a gas turbine engine.