Airplane tail fairing assembly

Abstract

The invention belongs to the technical field of aero-engine design, and relates to an airplane tail fairing assembly comprising fairings (1) and a limiting ring (3). The front ends of the fairings areconnected to the inner surface of an airplane tail cover (2) through springs (5). The rear ends of the fairings are fixed to a force bearing ring (13) of an engine jet pipe through bolt assemblies and are connected with outer regulation pieces in a lap joint manner. The outer ring of the limiting ring (3) is fixed to the tail portion of the airplane tail cover (2), and the inner ring of the limiting ring (3) is elastically connected to the fairings (1) in a lap joint manner. When the end portion of the limiting ring (3) is connected to the fairings (1) in a lap joint manner, the springs are in the stretched manner, and a gap is formed between the front end of each fairing and a force exertion barrel body. By means of the airplane tail fairing assembly, the fairings can be prevented from making direct contact with the force exertion barrel body and the airplane tail cover, it is ensured that the force exertion barrel body and the fairings themselves are not scratched or abraded, and meanwhile existing functions of the fairings are not influenced. The provided airplane tail fairing assembly can be automatically regulated and is simple in structure, low in fault rate and wide in application range.

Description

technical field [0001] The present application belongs to the technical field of aero-engine design, and in particular relates to an aircraft tail fairing assembly. Background technique [0002] The fairing is an elastic part that overlaps the engine and the rear fuselage of the aircraft, and is fixed on the outermost side of the nozzle. Its main functions are: connecting the engine and the aircraft to make a smooth transition, eliminating the installation difficulties caused by the machining error of the engine or the aircraft; enabling the airflow between the aircraft and the engine to be continuous, so that the cooling airflow flowing through the engine compartment flows out from the back, so as to facilitate the cooling effect. The moving cylinder, the adjusting sheet (sealing sheet) and the nozzle force transmission mechanism; keep the outer wall of the nozzle intact and reduce the rear body resistance in flight. [0003] figure 2 The part in the middle shows the exis...

AI Technical Summary

Problems solved by technology

[0003]Figure The part in 2 shows the existing rectifier installation method: the rear end of the rectifier 1 is fixed on the bearing ring (13) of the engine nozzle through a bolt assembly, and overlaps with the outer regulator (12), The middle part is installed on the supporting ring by one or two rows of screws in the circumferential direction. The free state of the front end is a cantilever structure, located between the afterburner cylinder 9 and the tail cover 2, and the installation state is to push against the inner wall of the tail cover in the circumferential direction. It is covered by the tail cover of the aircraft. During the flight, due to the strong pressure difference between the inner and outer flows, the front end of the rectifier is directly compressed to the outer surface of the afterburner cylinder. Due to the instability of the air flow, the The place is in stress contact for a long time, resulting in deep cut marks in the circumferential direction of the afterburner cylinder, which has a great impact on the structural strength of the rear end of the afterburner cylinder. , the outer surface of the elastic sheet and the tail end of the tail cover are often in a state of fretting friction, and deep cut marks will appear on the outer surface of the rectifier after use, which poses a threat to the safety of the engine

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