Adjustable bracket for tail nozzle of turbojet engine

Abstract

The present invention provides an adjustable bracket for the tail nozzle of a turbojet engine, comprising a lead screw and an adjustable bracket installed at the end of the lead screw, characterized in that the adjustable bracket comprises a mounting seat and a countersunk head; a driving device is installed on the side wall of the countersunk head, a driven part corresponding to the driving device is provided on the lead screw, the end of the lead screw is installed in the countersunk head, the lead screw is driven by the driving device to rotate the angle so that the lead screw changes its length; the countersunk head is installed in the mounting seat through a shock-absorbing block, and the shock-absorbing block plays a shock-absorbing role when the lead screw swings. In the adjustable bracket for the tail nozzle of a turbojet engine described in the present invention, the lower end of the lead screw is connected to the spherical groove through a spherical bottom, and the side of the countersunk head is supported by the shock-absorbing block. When the lead screw swings, the spherical bottom rotates in the spherical groove, the countersunk head squeezes the shock-absorbing block, and the shock-absorbing block undergoes elastic deformation to play a shock-absorbing role.

Description

Technical Field

[0001] The invention belongs to the technical field of turbine engines, and in particular relates to an adjustable bracket for a tail nozzle of a turbojet engine. Background Art

[0002] During the test and research of turbine engines, it is necessary to adjust the tail nozzle of the turbine engine at a small angle. At the same time, during the test, the overall vibration amplitude of the engine is required to be as small as possible to improve the test accuracy of various performance parameters of the engine.

[0003] The brackets of existing test benches are generally fixed and have poor vibration reduction effects. At the same time, the tail nozzle cannot be adjusted, which is not convenient for studying the changes in engine performance parameters when the tail nozzle direction changes. To this end, we propose an adjustable bracket for the tail nozzle of a turbojet engine to solve the above problems. Summary of the invention

[0004] In view of this, the present invention aims to propose an adjustable bracket for the tail nozzle of a turbojet engine, so as to realize the adjustment of the tail nozzle and facilitate the study of the change of the performance parameters of the engine when the direction of the tail nozzle changes.

[0005] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0006] An adjustable bracket for a tail nozzle of a turbojet engine, comprising a lead screw, the lead screw being used to adjust the angle of the tail nozzle, and the adjustable bracket being mounted on the end of the lead screw, characterized in that the adjustable bracket comprises a mounting seat and a countersunk head;

[0007] A driving device is installed on the side wall of the countersunk head, a driven part corresponding to the driving device is provided on the lead screw, and the end of the lead screw is installed in the countersunk head. The lead screw is driven by the driving device to rotate at an angle. When the lead screw rotates, its length can be extended or shortened;

[0008] The top of the lead screw is connected to a sleeve, one end of the sleeve is rotatably mounted with a lead screw nut that matches the lead screw, and the other end of the sleeve is hinged to the tail nozzle, which is mounted on the engine body.

[0009] The length between the lead screw and the sleeve can be adjusted, thereby achieving adjustment of the tail nozzle angle.

[0010] The countersunk head is installed in the mounting seat through a shock-absorbing block, and the shock-absorbing block plays a shock-absorbing role when the lead screw swings.

[0011] Furthermore, a spherical groove is provided on the mounting seat, and a spherical bottom is integrally formed at the lower end of the countersunk head, and the spherical bottom is arranged in the spherical groove.

[0012] Furthermore, the inner wall of the spherical groove extends toward the top of the mounting seat with multiple slide grooves, and the shock-absorbing block is provided with a number corresponding to the multiple slide grooves. Each shock-absorbing block is installed in the corresponding slide groove, and each slide groove extends outward from the mounting seat with a bolt hole. A locking bolt is installed in each bolt hole, and the locking bolt is tightened against the side wall of the shock-absorbing block.

[0013] It can be seen that each slide groove is larger than the length of the shock absorbing block, so the extrusion force between the shock absorbing block and the countersunk head can be controlled by tightening the shock absorbing block with the locking bolt.

[0014] The number of the shock absorbing blocks is 4, and the 4 shock absorbing blocks are evenly arranged around the side surface of the mounting seat.

[0015] Furthermore, a connecting groove is provided on the side of the shock absorbing block, and a connecting clamp ring is provided on the side wall of the countersunk head, and the connecting clamp ring is clamped in the connecting groove.

[0016] Furthermore, a rotating block is provided at the bottom of the lead screw, a rotating groove corresponding to the rotating block is provided at the top of the countersunk head, and the rotating block is located in the rotating groove.

[0017] Furthermore, the driving device is a motor, a first gear is installed on the rotating shaft end of the motor, the driven part on the lead screw (6) is a second gear, and the first gear is meshed with the second gear.

[0018] Compared with the prior art, the adjustable bracket for the tail nozzle of a turbojet engine described in the present invention has the following advantages:

[0019] (1) In the adjustable bracket of the tail nozzle of a turbojet engine described in the present invention, the lower end of the lead screw is connected to the spherical groove through the spherical bottom, and the side of the countersunk head is supported by the shock-absorbing block. When the lead screw swings, the spherical bottom rotates in the spherical groove, the countersunk head squeezes the shock-absorbing block, and the shock-absorbing block undergoes elastic deformation to play a shock-absorbing role;

[0020] (2) When the angle of the tail nozzle of a turbojet engine described in the present invention needs to be adjusted, the external power supply of the motor is turned on, the output shaft of the motor drives the first gear to rotate, the first gear drives the second gear to rotate, the second gear drives the lead screw to rotate, and the lead screw is driven by the driving device to rotate the angle. When the lead screw rotates, its length can be extended or shortened, so as to facilitate the adjustment of the direction of the tail nozzle;

[0021] (3) When installing the adjustable bracket for the tail nozzle of a turbojet engine described in the present invention, the countersunk head is placed in the spherical groove, and the locking bolt is rotated to drive the shock-absorbing block to slide in the direction of the countersunk head, so that the connecting clamping ring is clamped in the connecting clamping groove. By rotating the locking bolt, the pre-tightening force of the shock-absorbing block on the countersunk head can be easily adjusted. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0023] Figure 1 This is a schematic diagram of a connection structure between an adjustable bracket and a tail nozzle of a turbojet engine according to an embodiment of the present invention;

[0024] Figure 2 A cross-sectional structural diagram of the connection between an adjustable bracket and a lead screw of a turbojet engine tail nozzle according to an embodiment of the present invention;

[0025] Figure 3 This is a schematic diagram of the adjustable bracket structure according to an embodiment of the present invention;

[0026] Figure 4 This is a schematic diagram of the lead screw structure described in an embodiment of the present invention.

[0027] Description of reference numerals:

[0028] 1. Mounting seat; 2. Shock absorber block; 3. Rotating block; 4. Rotating groove; 5. Second gear; 6. Screw; 7. First gear; 8. Motor; 9. Countersunk head; 10. Locking bolt; 11. Spherical bottom; 12. Spherical groove; 13. Slide groove; 14. Connecting snap ring; 15. Engine body; 16. Tail nozzle; 61. Screw nut; 62. Sleeve. DETAILED DESCRIPTION

[0029] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0030] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0031] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0032] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0033] like Figures 1 to 4 As shown, the present invention provides a technical solution: an adjustable bracket for a tail nozzle of a turbojet engine, comprising a lead screw 6, a sleeve 62 is connected to the top of the lead screw 6, a lead screw nut 61 cooperating with the lead screw 6 is rotatably mounted on one end of the sleeve 62, the other end of the sleeve 62 is hinged to the tail nozzle 16, the tail nozzle 16 is mounted on the engine body 15, a mounting seat 1 is mounted on the lower end of the lead screw 6, a spherical groove 12 is arranged in the mounting seat 1, the lower end of the lead screw 6 is rotatably connected to a countersunk head 9, the lower end of the countersunk head 9 is integrally formed with a spherical bottom 11, and the spherical bottom 11 is arranged in the spherical groove 12;

[0034] The inner wall of the spherical groove 12 is slidably provided with a damping block 2, and the side of the countersunk head 9 is integrally formed with a connecting snap ring 14. The side of the damping block 2 is provided with a connecting snap groove, and the connecting snap ring 14 is clamped in the connecting snap groove;

[0035] like Figure 2 As shown, the lower end of the lead screw 6 of the present invention is connected to the spherical groove 12 through the spherical bottom 11, and the side of the countersunk head 9 is supported by the shock-absorbing block 2. When the lead screw 6 swings, the spherical bottom 11 rotates in the spherical groove 12, the countersunk head 9 squeezes the shock-absorbing block 2, and the shock-absorbing block 2 undergoes elastic deformation to achieve a shock-absorbing effect.

[0036] The turbojet engine is connected to the tail nozzle.

[0037] like Figure 1 and Figure 4 As shown, one end of the screw 6 is hingedly connected to the tail nozzle 16, wherein when the screw 6 is driven by the driving device, the length of the screw 6 and the sleeve 62 is adjusted, so that the angle rotation of the tail nozzle 16 can be realized. When the tail nozzle 16 rotates, the relative angle between the tail nozzle 16 and the axis of the turbojet engine body 15 can be changed according to the actual adjustment situation. Its specific structure is set according to the actual situation and will not be described in detail here. In addition, the present application is used in turbojet engine experiments, so the tail nozzle structure can be improved for the experiment.

[0038] like Figure 4As shown, when the lead screw 6 is driven by the motor 8, the lead screw 6 rotates and the lead screw nut 61 rotates, and the lead screw 6 extends into the sleeve, so that the length of the lead screw 6 and the sleeve 6 can be adjusted.

[0039] like Figure 3 As shown, the countersunk head 9 is fixed with a motor 8, the output shaft of the motor 8 is connected with the first gear 7, the screw 6 is fixed with the second gear 5, the second gear 5 and the first gear 7 are meshingly connected, when the tail nozzle angle needs to be adjusted, the external power supply of the motor 8 is turned on, the output shaft of the motor 8 drives the first gear 7 to rotate, the first gear 7 drives the second gear 5 to rotate, the second gear 5 drives the screw 6 to rotate, and the screw is driven by the driving device to rotate the angle. When the screw rotates, its length can be extended or shortened, so as to adjust the direction of the tail nozzle.

[0040] like Figure 2 As shown, as a technical optimization solution of the present invention, the mounting seat 1 is provided with a slide groove 13, the shock absorbing block 2 and the slide groove 13 are slidably connected, the mounting seat 1 is threadedly connected with a locking bolt 10, the head of the locking bolt 10 is in close contact with the rear end of the shock absorbing block 2, and when installing, the countersunk head 9 is placed in the spherical groove 12, and the locking bolt 10 is rotated to drive the shock absorbing block 2 to slide in the direction of the countersunk head 9, so that the connecting clamping ring 14 is inserted into the connecting clamping groove, and by rotating the locking bolt 10, it is convenient to adjust the tightening force of the shock absorbing block 2 on the countersunk head 9.

[0041] like Figure 1 As shown, as a technical optimization solution of the present invention, a rotating block 3 is provided at the lower end of the screw 6, and a rotating groove 4 is provided at the countersunk head 9, and the rotating block 3 and the rotating groove 4 are rotatably connected.

[0042] like Figure 2 As shown, as a technical optimization solution of the present invention, the number of the shock absorbing blocks 2 is 4, and the 4 shock absorbing blocks 2 are evenly arranged around the side of the mounting seat 1.

[0043] Working principle: the lower end of the screw 6 is connected to the spherical groove 12 through the spherical bottom 11, and the side of the countersunk head 9 is supported by the shock-absorbing block 2. When the screw 6 swings, the spherical bottom 11 rotates in the spherical groove 12, the countersunk head 9 squeezes the shock-absorbing block 2, and the shock-absorbing block 2 undergoes elastic deformation to play a shock-absorbing role. When the tail nozzle angle needs to be adjusted, the external power supply of the motor 8 is turned on, and the output shaft of the motor 8 drives the first gear 7 to rotate, the first gear 7 drives the second gear 5 to rotate, and the second gear 5 drives the screw 6 to rotate. The screw 6 is driven by the driving device to rotate the angle. When the screw 6 rotates, its length can be extended or shortened, which is convenient for adjusting the direction of the tail nozzle. During installation, the countersunk head 9 is placed in the spherical groove 12, and the locking bolt 10 is rotated to drive the shock-absorbing block 2 to slide in the direction of the countersunk head 9, so that the connecting clamping ring 14 is snapped into the connecting clamping groove. By rotating the locking bolt 10, the pre-tightening force of the shock-absorbing block 2 on the countersunk head 9 can be adjusted.

[0044] Preferably, the present invention can use one set of adjustable brackets, but is not limited to more than one set of devices, to accurately position the tail nozzle, and use a coordinated control method to accurately adjust the angle of the tail nozzle of the turbojet engine.

[0045] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An adjustable bracket for a turbojet engine tail nozzle, characterized in that: It comprises a lead screw (6) used for adjusting the angle of the tail nozzle (16), an adjustable bracket mounted on the end of the lead screw (6), and the adjustable bracket comprises a mounting seat (1) and a countersunk head (9); A driving device is installed on the side wall of the countersunk head (9), a driven portion corresponding to the driving device is provided on the lead screw (6), an end of the lead screw (6) is installed in the countersunk head (9), and the lead screw (6) is driven by the driving device to rotate at an angle; The countersunk head (9) is installed in the mounting seat (1) through a shock absorbing block (2), and the shock absorbing block (2) plays a shock absorbing role when the lead screw (6) swings; A spherical groove (12) is provided on the mounting seat (1), a spherical bottom (11) is integrally formed at the lower end of the countersunk head (9), and the spherical bottom (11) is arranged in the spherical groove (12); The inner wall of the spherical groove (12) is provided with a plurality of slide grooves (13) extending toward the top of the mounting seat (1); the damping block (2) is provided with a number corresponding to the plurality of slide grooves (13); each damping block (2) is installed in a corresponding slide groove (13); each slide groove (13) is provided with a bolt hole extending outward from the mounting seat (1); a locking bolt (10) is installed in each bolt hole; the locking bolt (10) is pressed against the side wall of the damping block (2).

2. The adjustable bracket for the tail nozzle of a turbojet engine according to claim 1, characterized in that: A connecting slot is provided on the side of the damping block (2), and a connecting snap ring (14) is provided on the side wall of the countersunk head (9), and the connecting snap ring (14) is clamped in the connecting slot.

3. The adjustable bracket for the tail nozzle of a turbojet engine according to claim 1, characterized in that: A rotating block (3) is provided at the bottom of the lead screw (6), a rotating groove (4) corresponding to the rotating block (3) is provided at the top of the countersunk head (9), and the rotating block (3) is located in the rotating groove (4).

4. The adjustable bracket for the tail nozzle of a turbojet engine according to claim 1, characterized in that: The driving device is a motor (8), a first gear (7) is installed on the rotating shaft end of the motor (8), the driven part on the lead screw (6) is a second gear (5), and the first gear (7) is meshed with the second gear (5).

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