Turbojet engine exhaust nozzle structure

Abstract

The utility model relates to an exhaust nozzle structure of a turbojet engine, which belongs to the technical field of turbojet engines and comprises an exhaust nozzle, an insertion piece and a fairing connected in the exhaust nozzle through the insertion piece. A connecting ring is arranged at one end of the exhaust nozzle, a tail nozzle is arranged at the other end of the exhaust nozzle, a plurality of first insertion piece grooves are evenly formed in the pipe wall, close to the connecting ring, of the exhaust nozzle at intervals, a plurality of second insertion piece grooves are formed in the cover wall of the fairing, and the first insertion piece grooves and the second insertion piece grooves correspond in position and are equal in number. The inserting piece is inserted into the exhaust nozzle and the fairing through the first inserting piece groove and the second inserting piece groove, one end of the inserting piece is located in the fairing, the other end of the inserting piece is fixedly located outside the pipe wall of the exhaust nozzle, and a sharp edge is arranged on one side edge of the inserting piece and faces one side of the connecting ring. The fairing in the exhaust nozzle is fixed by adopting an insertion piece, so that the exhaust nozzle is more stable; the insertion sheet occupies a small space; airflow from the exhaust nozzle can be easily cut and shunted by the sharp edges of the insertion pieces, so that the stability of the turbojet engine is facilitated; installation is convenient, and internal welding is not needed.

Description

TECHNICAL FIELD

[0001] The utility model relates to turbojet engine technical field, in particular to a turbojet engine tail nozzle structure. BACKGROUND

[0002] The turbojet engine is a kind of highly complex and precision thermodynamic machinery, and provides the engine required for aircraft flight power.The engine is used, and fuel is ejected by tail nozzle after burning in its interior, to provide a propulsive force for the aircraft.Due to the advancement of science and technology and manufacturing industry and so on, aircraft tends to miniaturization more and more.In military and civil, with the wide attention of micro air vehicle, the application of micro turbojet engine is increasingly widespread.Model aircraft is a reduced version of aircraft, and turbojet engine model aircraft is the best choice for aircraft model enthusiasts.

[0003] Some existing turbojet engine tail nozzles adopt screw locking to connect inner and outer rings of tail nozzle, and some adopt sheet metal bending piece welding to support inner and outer rings:

[0004] The screw is cylindrical, which is not conducive to the steady flow and direction of engine jet;

[0005] Sheet metal welding piece has the risk of being blown off by high temperature of engine, and occupies larger space, has no sharp edge, and jet is blocked when jetting out, interferes with airflow, and is not conducive to engine work. INNOVATION CONTENT

[0006] The utility model aims at providing a turbojet engine tail nozzle structure to solve the problems in the above background technology.

[0007] To achieve the above object, the utility model provides the following technical scheme:

[0008] A turbojet engine tail nozzle structure, comprising a tail nozzle, an insert piece, a fairing connected in the tail nozzle through the insert piece;The tail nozzle is provided with a connecting ring at one end and a tail jet opening at the other end, a plurality of insert piece grooves one are evenly and spaced apart on the wall of the tail nozzle close to the connecting ring, a plurality of insert piece grooves two are provided on the cover wall of the fairing, the positions of the insert piece grooves one and the insert piece grooves two correspond and the number is equal, the insert piece is inserted in the tail nozzle and the fairing through the insert piece grooves one and the insert piece grooves two, one end of the insert piece is located in the fairing, and the other end is fixed on the wall outside the tail nozzle, the insert piece is provided with a sharp edge on one side, and the sharp edge is directed to the connecting ring side.

[0009] Preferably, a plurality of screw holes are evenly and spaced apart on the connecting ring, and the connecting ring is installed on the turbojet engine through the screw holes.

[0010] Preferably, the fairing is a smooth cone, and the axis of the fairing is coaxial with the tail nozzle.

[0011] Preferably, the shape and size of the insert slot one and the insert slot two are matched with the insert, and the size of the insert is 10mm in width, 1.0mm in thickness and 18mm in length.

[0012] Preferably, the insert protrudes from the tail nozzle wall by 0.3-0.7mm at one end, and is fixed on the tail nozzle wall by laser melting welding.

[0013] Preferably, the number of the insert, the insert slot one and the insert slot two is 7.

[0014] Preferably, the tail nozzle outlet adopts a convergent cylinder structure.

[0015] Compared with the prior art, the utility model has the beneficial effects that:

[0016] The utility model adopts the insert type fixed fairing in the tail nozzle, makes the tail nozzle structure more stable, reduces the interference to the engine jet airflow, the insert occupies smaller space, the airflow out of the tail nozzle is cut and divided by the sharp edge of the insert easily, is favorable for the stability of the turbojet engine, is convenient to install and does not need internal welding. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is the structure schematic view of the utility model;

[0018] Figure 2 It is the side view of the utility model;

[0019] Figure 3 It is the side sectional view of the utility model;

[0020] Figure 4 It is the exploded view of the utility model;

[0021] Figure 5 It is the insert structure schematic view of the utility model.

[0022] REFERENCE NUMERALS

[0023] 1. tail nozzle, 2. connecting ring, 3. screw hole, 4. tail nozzle outlet, 5. insert slot one, 6. fairing, 7. insert slot two, 8. insert, 9. sharp edge. DETAILED DESCRIPTION

[0024] In order to further explain the technical means and effects taken by the present application to achieve the predetermined invention purposes, the specific embodiments, structures, features and effects according to the present application are described in detail as follows in combination with the drawings and preferred embodiments.

[0025] For example, Figures 1-5As shown, a turbojet engine nozzle structure includes a nozzle 1, a plug 8, a fairing 6 connected in the nozzle 1 through the plug 8, the fairing 6 is a smooth cone, the shape is beneficial to the optimization of the flow field, the axis of the fairing 6 is coaxial with the nozzle 1; the nozzle 1 is provided with a connecting ring 2 at one end and a tail jet 4 at the other end, the tail jet 4 adopts a convergent cylinder structure; a plurality of screw holes 3 are evenly and spacedly arranged on the connecting ring 2, and the connecting ring 2 is installed on the turbojet engine through the screw holes 3.

[0026] A plurality of plug grooves one 5 are evenly and spacedly arranged on the wall of the nozzle 1 close to the connecting ring 2, a plurality of plug grooves two 7 are arranged on the cover wall of the fairing 6, the positions of the plug grooves one 5 and the plug grooves two 7 correspond and the number is equal, the plug 8 is inserted in the nozzle 1 and the fairing 6 through the plug grooves one 5 and the plug grooves two 7, one end of the plug 8 is located in the fairing 6, and the other end is fixed on the wall outside the nozzle 1, one end of the plug 8 protrudes 0.3-0.7mm outside the wall of the nozzle 1, and is fixed on the wall of the nozzle 1 by laser melting welding.

[0027] One side of the plug 8 is provided with a sharp edge 9, and the sharp edge 9 faces one side of the connecting ring 2; the shape and size of the plug grooves one 5 and the plug grooves two 7 match the plug 8, the size of the plug 8 is 10mm wide, 1.0mm thick and 18mm long; the number of the plug 8, the plug grooves one 5 and the plug grooves two 7 is 7.

[0028] The plug 8 is used to fix the fairing 6 in the nozzle 1, so that the structure of the nozzle 1 is more stable, and the interference on the jet flow of the engine is reduced; the plug 8 occupies a small space; the jet flow out of the nozzle 1 is easily cut and divided by the sharp edge 9 of the plug 8, which is beneficial to the stability of the turbojet engine; the installation is more convenient, and internal welding is not required.

[0029] The above is only a preferred embodiment of the present application, and does not limit the present application in any form, although the present application has been disclosed as above, however, it is not intended to limit the present application, any person skilled in the art, without departing from the technical solution of the present application, can make some changes or modifications to the above-mentioned disclosed technical content to make equivalent embodiments with equivalent changes, but as long as it does not deviate from the technical solution of the present application, any modification, equivalent change and modification of the above-mentioned embodiments according to the technical essence of the present application, all still belong to the scope of the technical solution of the present application.

Claims

1. A structure of a turbojet engine nozzle, characterized in that: The tail nozzle, the insert, the fairing connected in the tail nozzle through the insert; the tail nozzle is equipped with the connecting ring in one end and the tail jet in the other end, the pipe wall of the tail nozzle is equipped with several insert slots one in the even interval near the connecting ring, the cover wall of the fairing is equipped with several insert slots two, the position of the insert slots one and the insert slots two corresponds and the quantity is equal, the insert is inserted in the tail nozzle and the fairing through the insert slots one and the insert slots two, one end of the insert is located in the fairing, the other end is fixed in the pipe wall outside of the tail nozzle, the one side of the insert is equipped with the sharp edge, the sharp edge is towards the connecting ring side.

2. A turbojet engine nozzle structure according to claim 1, characterized in that: The connecting ring is equipped with several screw holes in the even interval, the connecting ring is installed on the turbojet engine through the screw hole.

3. The turbojet engine nozzle structure of claim 1, wherein: The fairing is a smooth cone, the axis of the fairing is coaxial with the tail nozzle.

4. The turbojet engine nozzle structure of claim 1, wherein: The shape and size of the insert slots one and the insert slots two match the insert, the size of the insert is 10mm wide, 1.0mm thick and 18mm long.

5. A turbojet engine nozzle structure according to claim 4, characterized in that: One end of the insert is 0.3-0.7mm protruding in the pipe wall outside of the tail nozzle and is fixed on the pipe wall of the tail nozzle by laser melting welding.

6. The turbojet engine nozzle structure of claim 1, wherein: The quantity of the insert, the insert slots one and the insert slots two is 7.

7. The turbojet engine nozzle structure of claim 1, wherein: The tail jet adopts the convergent cylinder structure.

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