Apparatus and method for reducing noise emissions from a gas turbine engine inlet
AssigneeThe Boeing Company
InventorRobert P. Dougherty
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Abstract
Noise attenuating linings for a turbofan engine inlet are installed around the upper crown area and/or around the lower lip. The acoustical lining at the upper crown area attenuates those fan noise emissions which are normally reflected from the crown area downward toward the ground. The acoustical lining at the lower inlet lip attenuates those fan noise emissions which travel along the inner surface of the lip and are diffracted around the lower lip downward toward the ground.
Claims7
An inlet for a turbofan engine comprising:
- a. an upper inlet portion having a leading edge;
- b. a lower inlet portion having a leading edge wherein the leading edge of the lower inlet portion extends forward of the leading edge of the upper inlet portion;
- c. a throat portion;
- and
- d. noise attenuating material located at the leading edge of the lower inlet portion in a manner that the noise attenuating material extends rearward from the leading edge of the lower inlet portion along an inner surface of the lower inlet portion to the throat portion, and in a manner that the noise attenuating, material extends rearward from the leading edge of the lower inlet portion along an outer surface of the lower inlet portion to a location which is below the throat portion of the inlet.
A method for reducing noise emissions from an inlet of a turbofan engine, the method comprising the steps of:
- a. installing noise attenuating material at a lower portion of the inlet having a lower leading edge;
- b. installing the noise attenuating material in a manner that it extends from the lower leading edge in a direction rearward along an inner surface of the lower inlet portion to a throat portion of the inlet;
- and
- c. installing the noise attentuating material in a manner that it extends from the lower leading edge in a direction rearward along an outer surface of the lower inlet portion to a location which is below the throat portion of the inlet.
Dependencies are inferred from the claim text.