US 12,486,804 B2
Joints between acoustic panels
Jackson David Johnson, Mishawaka, IN (US); Benjamin G. Gardell, Bristol, CT (US); and Keith B. Allyn, Rutland, MA (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on May 31, 2023, as Appl. No. 18/326,205.
Prior Publication US 2024/0401533 A1, Dec. 5, 2024
Int. Cl. F02C 7/24 (2006.01); G10K 11/16 (2006.01)
CPC F02C 7/24 (2013.01) [G10K 11/16 (2013.01); F05D 2250/121 (2013.01); F05D 2250/283 (2013.01); F05D 2260/96 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a core engine including a compressor and a turbine;
acoustic structure positioned on a surface of the gas turbine engine, and the acoustic structure including at least a pair of adjacent panels, said panels having edges, and said panels each defining a plurality of cells, a first of said at least a pair of acoustic panels connected to a second of said pair of acoustic panels at adjacent ones of said edges;
there being a pair of spaced faces in each acoustic panel between which the plurality of cells extend, and there being openings in each of said edges of each of said adjacent acoustic panels, and between a first of said faces and a second of said faces, with the openings being spaced from both said first of said faces and said second of said faces with a securing member extending through said openings in each of said first and said second of said adjacent acoustic panels; and
wherein the acoustic structure and the at least a pair of adjacent panels form a full-hoop structure centered on a rotational axis of the core engine.