CN110466783B

CN110466783B - Aircraft afterbody fairing subassembly

Info

Publication number: CN110466783B
Application number: CN201910683398.6A
Authority: CN
Inventors: 王殿磊; 郭新贤; 杜桂贤
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2019-07-26
Filing date: 2019-07-26
Publication date: 2023-03-28
Anticipated expiration: 2039-07-26
Also published as: CN110466783A

Abstract

The application belongs to the technical field of aircraft engine design, and relates to an aircraft tail fairing assembly which comprises a fairing (1) and a limiting ring (3), wherein the front end of the fairing is connected to the inner surface of a tail cover (2) through a spring (5), and the rear end of the fairing is fixed on a bearing ring (13) of an engine spray pipe through a bolt assembly and is in lap joint with an outer adjusting piece; the outer ring of the limiting ring (3) is fixed at the tail part of the tail cover (2), and the inner ring is elastically lapped on the fairing (1); when the tip overlap-joint of spacing ring (3) was gone up to commutator segment (1), the spring was in tensile state, just have the clearance between commutator segment front end and the afterburning barrel. The application can prevent the commutator segment from directly contacting with the boosting cylinder and the tail cover, ensure that the boosting cylinder and the commutator segment are not rubbed or abraded, and simultaneously do not influence the original function of the commutator segment. The aircraft tail rectifier assembly can realize automatic adjustment, and has the advantages of simple structure, low failure rate and wide application range.

Description

Aircraft afterbody fairing subassembly

Technical Field

The application belongs to the technical field of aero-engine design, and particularly relates to an aircraft tail fairing assembly.

Background

The fairing is used as an elastic part for lapping the engine and the rear fuselage of the airplane, is fixed on the outermost side of the spray pipe, and is an elastic piece with a fairing function, which is formed by switching an outer adjusting piece of the engine spray pipe and a tail cover of the airplane. The main functions are as follows: connecting the engine and the airplane to enable the engine and the airplane to be in smooth transition, and eliminating installation difficulty caused by machining errors of the engine or the airplane; the airflow between the airplane and the engine can be continuous, and the cooling airflow flowing through the engine compartment flows out from the rear side so as to cool the actuating cylinder, the adjusting sheet (sealing sheet) and the nozzle force transmission mechanism; the outer wall surface of the spray pipe is kept complete, and the resistance of the rear body in flight is reduced.

The part in fig. 2 illustrates a conventional fillet installation method: the rear end of the fairing 1 is fixed on a bearing ring (13) of an engine spray pipe through a bolt assembly and is lapped with an outer adjusting piece (12), the middle part of the fairing is arranged on a support ring through one or two rows of screws in the circumferential direction, the front end of the fairing is in a cantilever structure and is positioned between a stress application cylinder 9 and a tail cover 2, and the installation state is that the fairing circumferentially abuts against the inner wall surface of the tail cover, namely the fairing is hooped and covered in the support ring by the tail cover of an airplane.

Disclosure of Invention

To solve one of the above problems, the present application provides an aircraft tail fairing assembly including:

the front end of the rectifier plate is connected to the inner surface of the tail cover through a spring, and the rear end of the rectifier plate is fixed on a bearing ring of the engine spray pipe through a bolt assembly and is in lap joint with the outer adjusting plate;

the outer ring of the limiting ring is fixed at the tail part of the tail cover, and the inner ring of the limiting ring is elastically lapped on the rectifier plate;

when the tip overlap joint of spacing ring is to the fairing, the spring is in tensile state, just have the clearance between fairing front end and the afterburning barrel.

Preferably, the fairing includes a plurality of fairings arranged circumferentially along the aft cowl, each fairing being connected to the aft cowl by a respective corresponding spring.

Preferably, the number of the segments is any one of 15, 16 or 18.

Preferably, the two ends of the spring are respectively provided with an upper supporting block and a lower supporting block, the lower supporting block is fixedly connected to the front end of the commutator segment, and the upper supporting block is fixedly connected to the inner wall of the tail cover.

Preferably, the lower support block is welded with the front end of the fairing, and the upper support block is welded with the inner wall of the tail cover.

Preferably, the lower support block is connected with the front end of the fairing through a bolt, and the upper support block is connected with the inner wall of the tail cover through a bolt.

Preferably, the limiting ring is fixed at the end part of the tail cover through a bolt and a nut.

Preferably, the inner ring of the limit ring is elastically overlapped on the rectifying sheet through an arc-shaped surface.

The thrust augmentation cylinder can be prevented from being in direct contact with the thrust augmentation cylinder and the tail cover, the thrust augmentation cylinder and the commutator are prevented from being scratched and abraded, and the original functions of the commutator are not affected. The aircraft tail rectifier assembly provided by the application can realize automatic adjustment, and is simple in structure, low in failure rate and wide in application range.

Drawings

Fig. 1 is a schematic cross-sectional view of an aircraft tail fairing assembly according to the present application.

Fig. 2 is a schematic view of an application of an aircraft tail fairing assembly according to the application.

Fig. 3 is a side view of the aircraft tail fairing assembly of the present application, fig. 1.

The thrust jet engine comprises 1-a fairing, 2-a tail cover, 3-a limiting ring, 4-an upper supporting block, 5-a spring, 6-a lower supporting block, 7-a bolt, 8-a nut, 9-a stress application cylinder, 10-a jet pipe convergence section, 11-a jet pipe expansion section, 12-an outer adjusting piece and 13-a bearing ring.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are implementations that are part of this application and not all implementations. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.

The utility model aims at providing an aircraft afterbody fairing subassembly prevents fairing and afterbody barrel, tail cover direct contact, guarantees that afterbody barrel and fairing itself do not receive to cut to pieces to rub, wearing and tearing, guarantees the original function of fairing simultaneously.

The application provides an aircraft afterbody fairing subassembly, as shown in fig. 1, mainly include fairing 1, tail cover 2, spacing ring 3, go up supporting block 4, spring 5, bottom suspension bracer 6, bolt 7, nut 8 and afterburning barrel 9, specifically do:

the front end of the fairing 1 is connected to the inner surface of the tail cover 2 through a spring 5, and the rear end of the fairing is fixed on a bearing ring 13 of an engine spray pipe through a bolt assembly and is lapped with an outer adjusting piece 12;

the outer ring of the limiting ring 3 is fixed at the tail part of the tail cover 2, and the inner ring is elastically lapped on the fairing 1;

when the end part of the limiting ring 3 is lapped on the commutator segment 1, the spring 5 is in a stretching state, and a gap is arranged between the front end of the commutator segment and the stressing cylinder 9.

In some optional embodiments, the fairing 1 comprises a plurality of fairings 1 arranged circumferentially along the nacelle 2, each fairing 1 being connected to the nacelle 2 by a respective spring 5.

In some optional embodiments, spring 5's both ends are provided with supporting block 4 and bottom suspension fagging 6 respectively, and bottom suspension fagging 6 fixed connection is at the front end of cowling piece 1, and last supporting block 4 fixed connection is in the inner wall of tail cover 2, refer to fig. 3, in this application cowling piece 1, last supporting block 4, spring 5, bottom suspension fagging 6 quantity is the same, circumference 15, 16 or 18 equipartitions, goes up supporting block 4, bottom suspension fagging 6 and fixes respectively at tail cover 2 internal surface, cowling piece 1 surface, and spring 5 is fixed respectively at both ends from top to bottom on supporting block 4, bottom suspension fagging 6, is in tensile state after the installation, and spacing ring 3 quantity is 1, and the front end passes through bolt 7, nut 8 fastening at the tail cover rear end, spacing ring 3 rear end and cowling piece 1 circumference elastic contact during non-working state, top on cowling piece 1 surface.

In some alternative embodiments, the lower support block 6 is welded to the front end of the fairing 1, and the upper support block 4 is welded to the inner wall of the tail cover 2. In alternative embodiments, a bolted connection may also be used.

In some alternative embodiments, the inner ring of the limiting ring 3 is elastically overlapped on the fairing 1 through an arc surface.

Referring to fig. 1 and 2, in fig. 2, the rear end of the thrust cylinder 9 is a nozzle, and includes a nozzle convergent section 10 and a nozzle divergent section 11, the nozzle divergent section 11 is connected to an external adjustment piece 12 of the nozzle (not shown), and the operation principle of the fairing assembly is as follows: when the aircraft flies at high altitude, the airflow pressure is unstable, and when the pressure of the outer flow (A) is smaller than the pressure of the inner flow (B), the fairing 1 is propped against the rear end of the limiting ring 3, so that the front end of the fairing is prevented from being cut and rubbed with the rear end of the tail cover 2; when the pressure of the outer flow (A) is greater than the pressure of the inner flow (B), the commutator segment 1 is pressed down and is under the stretching damping action of the spring 5 in the process, so that the front end of the commutator segment is prevented from directly contacting the stressing cylinder 9, and the stressing cylinder 9 is prevented from being scratched.

The application can prevent the commutator segment from directly contacting with the boosting cylinder and the tail cover, ensure that the boosting cylinder and the commutator segment are not rubbed or abraded, and simultaneously do not influence the original function of the commutator segment. The aircraft tail fairing component provided by the application can realize automatic adjustment, and is simple in structure, low in failure rate and wide in application range.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An aircraft tail fairing assembly comprising:

the front end of the fairing (1) is connected to the inner surface of the tail cover (2) through a spring (5), and the rear end of the fairing is fixed on a bearing ring (13) of an engine spray pipe through a bolt assembly and is lapped with an outer adjusting piece (12);

the outer ring of the limiting ring (3) is fixed at the tail part of the tail cover (2), and the inner ring is elastically lapped on the fairing (1);

when the end part of the limiting ring (3) is lapped on the commutator segment (1), the spring (5) is in a stretching state, and a gap is formed between the front end of the commutator segment and the stress application cylinder body (9);

wherein, fairing (1) includes a plurality ofly, follows tail cover (2) circumference arranges, every fairing (1) all connects through respective corresponding spring (5) tail cover (2).

2. The aircraft tail fairing assembly of claim 1, wherein the number of fairings (1) is any of 15, 16 or 18.

3. The aircraft tail fairing assembly as recited in claim 1, characterized in that an upper supporting block (4) and a lower supporting block (6) are respectively arranged at two ends of the spring (5), the lower supporting block (6) is fixedly connected at the front end of the fairing (1), and the upper supporting block (4) is fixedly connected on the inner wall of the tail cover (2).

4. The aircraft tail fairing assembly as claimed in claim 3, characterized in that the lower support block (6) is welded to the front end of the fairing (1) and the upper support block (4) is welded to the inner wall of the tail cover (2).

5. The aircraft tail fairing assembly as claimed in claim 3, characterized in that the lower supporting block (6) is bolted to the front end of the fairing (1) and the upper supporting block (4) is bolted to the inner wall of the tail cover (2).

6. The aircraft tail fairing assembly as claimed in claim 1, characterized in that the stop collar (3) is fastened to the end of the tail cover (2) by means of bolts (7) and nuts (8).

7. The aircraft tail fairing assembly as claimed in claim 1, characterized in that the inner ring of the retaining ring (3) overlaps the fairing (1) elastically by means of an arc.