Abstract: A gas turbine engine for an aircraft includes: a flow path boundary, which delimits the flow path through the engine radially on the outside, and a lining, which lines the flow path boundary on the inside, at least along an axial section. Here, the lining includes a plurality of panels, which, in the circumferential direction of the flow path boundary, adjoin each other and which together line a circumferential area of 360°, wherein each panel has two end faces, which each adjoin an end face of an adjacent panel. The panels are of beveled design at their end faces, such that two mutually adjoining panels form a V-shaped gap between them, the minimum clearance of which is realized at the inside of the panels. The panels can be sound-absorbing panels. Also disclosed is a panel for a gas turbine engine.

Abstract: A gas turbine engine for an aircraft includes: a flow path boundary, which delimits the flow path through the engine radially on the outside, and a lining, which lines the flow path boundary on the inside, at least along an axial section. Here, the lining includes a plurality of panels, which, in the circumferential direction of the flow path boundary, adjoin each other and which together line a circumferential area of 360°, wherein each panel has two end faces, which each adjoin an end face of an adjacent panel. The panels are of beveled design at their end faces, such that two mutually adjoining panels form a V-shaped gap between them, the minimum clearance of which is realized at the inside of the panels. The panels can be sound-absorbing panels. Also disclosed is a panel for a gas turbine engine.