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US 9,168,716 B2Granted
Metallic sandwich structure having small bend radius
AssigneeThe Boeing Company
InventorsBrenda Benedetti, Robert S. Farrell, Luis R. Leon, Justin H. Lan, Garry A. Booker
Life of this patent
Estimating the term…
Abstract
An acoustic-attenuating wall panel for a nacelle of a turbine engine may include a radiused portion. The radiused portion may include an airflow surface having a concave configuration and which may be exposed to an airflow passing through the nacelle. The radiused portion may include an acoustic attenuating section.
Claims20
An acoustic-attenuating wall panel, comprising:
- a radiused portion of an inner wall panel of a nacelle;
- the radiused portion including an airflow surface having a concave configuration being exposed to an airflow;
- and
- the radiused portion comprising an acoustic attenuating section and formed as a honeycomb sandwich structure having a honeycomb core sandwiched between a pair of face sheets;
- the honeycomb core in the radiused portion has a cell width that is the same as the cell width of the honeycomb core in at least one of the following portions of the inner wall panel:
- a barrel portion, an upper bifurcation, a lower bifurcation.
3 more elements
An inner wall panel, comprising:
- a semi-circular barrel portion having circumferentially opposite ends;
- an upper bifurcation wall portion and a lower bifurcation wall portion extending radially outwardly from the circumferentially opposite ends of the barrel portion;
- an upper radiused portion and a lower radiused portion joining the respective upper and lower bifurcation wall portion to the circumferentially opposite ends of the barrel portion;
- and
- at least one of the upper and lower radiused portions being formed as a honeycomb sandwich structure having a honeycomb core sandwiched between a pair of face sheets, the honeycomb core in the radiused portion has a cell width that is the same as the cell width of the honeycomb core in at least one of the following portions of the inner wall panel:
- a barrel portion, an upper bifurcation, a lower bifurcation;
- and
- the inner wall panel comprising a metallic, one-piece, unitary structure.
5 more elements
An aircraft, comprising:
- a nacelle connected to a turbine engine, the nacelle having an inner wall panel positioned along a duct airflow path of an airflow;
- the inner wall panel having a radiused portion including an airflow surface having a concave configuration being exposed to an airflow;
- the radiused portion comprising an acoustic attenuating section and formed as a honeycomb sandwich structure having a core sandwiched between a pair of face sheets;
- and
- the honeycomb core in the radiused portion has a cell width that is the same as the cell width of the honeycomb core in at least one of the following portions of the inner wall panel:
- a barrel portion, an upper bifurcation, a lower bifurcation.
3 more elements
A method of attenuating noise of a turbine engine, comprising the steps of:
- passing an airflow along a concave airflow surface of a radiused portion of an inner wall panel within a nacelle, the radiused portion comprising a honeycomb sandwich structure including a honeycomb core sandwiched between a pair of face sheets and having a plurality of cells, the honeycomb core in the radiused portion has a cell width that is the same as the cell width of the honeycomb core in at least one of the following portions of the inner wall panel:
- a barrel portion, an upper bifurcation, a lower bifurcation;
- fluidly coupling the cells to the airflow through a plurality of holes formed in an airflow face sheet of the honeycomb sandwich structure;
- and
- absorbing acoustic energy in the airflow fluidly coupled to the cells.
2 more elements
Dependencies are inferred from the claim text.