Mounting structure of low-thrust turbojet engine

Abstract

The invention relates to the technical field of turbojet engine stator casing installation auxiliary tools, and discloses a low-thrust turbojet engine installation structure. The low-thrust turbojet engine mounting structure comprises a mounting frame, the mounting frame is of a semi-surrounding structure, one end of the mounting frame is fixedly connected with a main mounting section and at least one auxiliary mounting section, and inserting rods are inserted into the main mounting section and the auxiliary mounting sections; one end of the inserting rod is shrunk into a circular truncated cone-shaped structure, the other end of the inserting rod is fixedly connected with a hanging rod, a clamping plate is clamped on the hanging rod, and a first fixing bolt is arranged on the clamping plate in a penetrating manner; a bolt penetrating hole is formed in the mounting frame, and a second fixing bolt is mounted through the bolt penetrating hole; a pin penetrating hole is formed in the mounting frame, and a positioning pin is mounted through the pin penetrating hole; the fixing device has the advantages that the fixing device is convenient to install and fix on the stator casing, the stator casing can be conveniently installed in a narrow space, and threats to the safety performance of an engine can be effectively avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of installation auxiliary tools for the stator casing of a turbojet engine, and specifically to an installation structure for a small-thrust turbojet engine. Background Technique

[0002] The engine mounting lug, as a fixed component of the engine on the aircraft, generally includes a main mounting structure and an auxiliary mounting structure. The main mounting structure bears the thrust of the engine and is an important assembly that transmits the engine thrust to the aircraft, and is the axial positioning point of the engine on the aircraft. The main function of the auxiliary mounting structure is to provide auxiliary connection between the engine and the aircraft, and together with the main mounting structure of the engine, bear the loads generated by the engine and transmit the thrust generated by the engine to the aircraft, so as to enable the engine to drive the aircraft to work. Its connection method needs to meet multiple requirements such as high strength, high reliability, and high durability.

[0003] In the existing design of the engine mounting lug, in this narrow space, a ring-shaped mounting lug structure is mostly used to provide a mounting lug with full-degree-of-freedom constraint. Specifically, as Figure 5 shown: The main mounting lug 1002 is a split structure (such as a hoop), and the split main mounting lug 1002 is fixed to the stator casing 1001 of the engine through multiple groups of fastening bolts 10033. An auxiliary mounting lug 1004 is designed at another position of the engine. The auxiliary mounting lug 1004 can be selected as a lug, and the engine is connected to the aircraft through the main mounting lug 1002 and the auxiliary mounting lug 1004.

[0004] During the high-speed and high-pressure operation of the engine, the engine casing will generate a certain amount of radial thermal expansion. If the mounting lug is a rigid structure with full-degree-of-freedom constraint by bolts at this time, the radial thermal expansion will generate greater stress on the engine body or the aircraft, which will pose a great threat to the safety performance of the engine. Therefore, the requirements for the structural strength of the engine and the aircraft are more stringent. Summary of the Invention

[0005] (I) Technical Problems to be Solved

[0006] Aiming at the deficiencies of the prior art, the present invention provides an installation structure for a small-thrust turbojet engine, which can effectively solve the problems proposed in the background technique.

[0007] (II) Technical Solutions

[0008] To achieve the above object, the present invention provides the following technical solution: An installation structure for a small-thrust turbojet engine, which is used to assist in the installation and fixation of the stator casing 1001 of a small-thrust turbojet engine in a narrow space. The stator casing 1001 has threaded holes for connection and fixation and pin holes for positioning. It includes:

[0009] The mounting bracket is of a semi - enclosed structure. At one end of the mounting bracket, a main mounting section and at least one auxiliary mounting section are fixedly connected. Plug rods are inserted into both the main mounting section and the auxiliary mounting section. One end of the plug rod is shrunk into a frustum - shaped structure, and the other end of the plug rod is fixedly connected with a hanging rod. A clamping plate is clamped on the hanging rod, and a first fixing bolt is inserted through the clamping plate. Bolt through - holes are formed on the mounting bracket, and a second fixing bolt is installed through the bolt through - holes. A lock washer is sleeved on the second fixing bolt. Pin through - holes are formed on the mounting bracket, and a positioning pin is installed through the pin through - holes.

[0010] Preferably, both the main mounting section and the auxiliary mounting section are in interference fit with the plug rods, and the main mounting section, the auxiliary mounting section and the mounting bracket are integrally formed.

[0011] Preferably, a plurality of card slots are arranged at intervals along the axial direction of the hanging rod on the outer peripheral side surface of the hanging rod and are arranged around the axis of the hanging rod.

[0012] Preferably, threaded connection holes for the first fixing bolt to pass through the clamping plate and engaging grooves for cooperating with the card slots are formed on the clamping plate. Auxiliary grooves are formed on the wall surface of the engaging grooves and penetrate through the clamping plate.

[0013] Preferably, the threaded part of the second fixing bolt cooperates with the threaded hole on the stator casing.

[0014] Preferably, the positioning pin is inserted into the pin hole on the stator casing.

[0015] Compared with the prior art, the present invention provides a mounting structure for a small - thrust turbojet engine, having the following beneficial effects:

[0016] 1. The main mounting section, the auxiliary mounting section and the mounting bracket are integrally formed, and the geometric tolerances during processing are easy to control, avoiding the concentricity problem of the connection between the main and auxiliary mounting sections caused by machining errors and assembly errors of components, which affects the aerodynamic performance of the engine and thus the overall performance. The mounting ring is of a semi - enclosed structure, which can effectively avoid the influence of the radial thermal expansion of the engine casing on the engine body and the aircraft.

[0017] 2. By making the main mounting section, the auxiliary mounting section and the mounting bracket an integral structure, the installation method of the main mounting section, the auxiliary mounting section and the mounting bracket on the stator casing is very simple. It only needs to align the pin through - hole on the mounting bracket with the pin hole on the stator casing and then insert the positioning pin into the pin through - hole and the pin hole, and align the bolt through - hole with the threaded hole on the stator casing and then pass the second fixing bolt through the bolt through - hole and screw it into the threaded hole. The installation and fixing operation on the stator casing is convenient, facilitating the installation of the stator casing in a narrow space.

[0018] 3. The threaded holes mating with the second fixing bolts and the pin holes mating with the positioning pins are both provided on the end face of the stator casing. The mounting ring is connected to the casing end face, which can effectively avoid setting connection ports on the outer surface of the casing, is more beneficial to the overall strength and stiffness margin design of the engine, and can effectively avoid threatening the safety performance of the engine. Brief Description of the Drawings

[0019] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0020] Figure 2 It is an exploded view of the structure of the present invention;

[0021] Figure 3 It is a schematic diagram of the structure of the hanging rod of the present invention;

[0022] Figure 4 It is a schematic diagram of the structure of the clamping plate of the present invention;

[0023] Figure 5 It is a schematic diagram of the use of the installation structure of a small-thrust turbojet engine in the prior art.

[0024] Wherein: 1001, casing; 1002, main installation structure; 1003, fastening bolt; 1004, auxiliary installation joint structure; 1, mounting bracket; 2, main installation joint; 3, auxiliary installation joint; 4, insertion rod; 5, hanging rod; 51, card slot; 6, clamping plate; 61, threaded connection hole; 62, engaging groove; 63, auxiliary groove; 7, first fixing bolt; 8, second fixing bolt; 9, lock washer; 10, positioning pin; 101, bolt perforation; 102, pin perforation. Detailed Description of the Invention

[0025] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0026] Please refer to Figures 1-4 , a small-thrust turbojet engine installation structure for assisting in the installation and fixation of the stator casing 1001 of a small-thrust turbojet engine in a narrow space. The stator casing 1001 has threaded holes for connection and fixation and pin holes for positioning, and both the threaded holes and the pin holes are provided on the end face of the stator casing 1001; the small-thrust turbojet engine installation structure includes:

[0027] The mounting frame 1 is a semi-enclosed structure. A bolt through hole 101 is provided on the mounting frame 1, and a second fixing bolt 8 is installed through the bolt through hole 101. A locking washer 9 is sleeved on the second fixing bolt 8. A pin through hole 102 is provided on the mounting frame 1, and a positioning pin 10 is installed through the pin through hole 102;

[0028] A main mounting section 2 and at least one auxiliary mounting section 3, the main mounting section 2 and the auxiliary mounting section 3 are both fixed to one end of the mounting frame 1 and are integrally formed with the mounting frame 1;

[0029] At least two insertion rods 4 are respectively inserted into the main installation section 2 and the auxiliary installation section 3, one end of the insertion rod 4 is contracted into a truncated cone structure, and the other end of the insertion rod 4 is fixedly connected to a hanging rod 5, and a plurality of card slots 51 arranged around the axis of the hanging rod 5 are arranged on the outer peripheral side surface of the hanging rod 5 at intervals along the axial direction of the hanging rod 5;

[0030] There are at least two clamping plates 6 and at least two No. 1 fixing bolts 7. Each clamping plate 6 is provided with a threaded connection hole 61 for the No. 1 fixing bolt 7 to pass through the clamping plate 6 and a bite groove 62 that cooperates with the clamping groove 51. The clamping plate 6 is clamped on the hanging rod 5 through the cooperation of the bite groove 62 and the clamping groove 51.

[0031] As a further explanation of the above technical solution, an auxiliary groove 63 is opened on the groove wall surface of the bite groove 62, and the auxiliary groove 63 passes through the card plate 6. Specifically, the auxiliary groove 63 passes through two end faces on the card plate 6 located in the axial direction of the bite groove 62 and an end face parallel to the axial direction of the bite groove 62. With the assistance of the auxiliary groove 63, the bite groove 62 can be more conveniently inserted into the card slot 51, and the bite groove 62 can also be conveniently detached from the card slot 51, so that the bite groove 62 can be switched from one card slot 51 to another card slot 51 as needed, which is convenient for the installation and use of the card plate 6 on the hanging rod 5.

[0032] The main installation section 2 and the auxiliary installation section 3 are both interference fit with the plug rod 4, and the connection between the plug rod 4 and the main installation section 2 and the connection between the plug rod 4 and the auxiliary installation section 3 are both detachable connections; when the plug rod 4 is not installed, the main installation section 2 and the auxiliary installation section 3 can be used as lifting ears, and the mounting frame 1 can be lifted to the stator casing 1001 through the cooperation of the main installation section 2, the auxiliary installation section 3 and the lifting equipment, so as to facilitate the installation of the mounting frame 1 on the stator casing 1001. The main installation section 2 limits the displacement of the engine on the vertical plane with the rotating shaft, but allows the axial displacement of the engine; the auxiliary installation section 3 limits the axial displacement of the engine, but allows the displacement of the engine on the vertical plane with the rotating shaft.

[0033] The threaded portion of the No. 2 fixing bolt 8 matches with the threaded hole on the stator casing 1001 .

[0034] The positioning pin 10 is inserted into the pin hole on the stator casing 1001 .

[0035] It should be noted that during use, the specific geometric shape of the mounting bracket 1 is determined according to the specific usage scenarios and conditions, and it can be C-shaped, X-shaped or other shapes.

[0036] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A mounting structure for a small-thrust turbojet engine, which is used to assist in the installation and fixation of the stator casing (1001) of the small-thrust turbojet engine in a narrow space. The stator casing (1001) has threaded holes for connection and fixation and pin holes for positioning. It is characterized in that: It includes a mounting frame (1). The mounting frame (1) is a semi-enclosed structure. At one end of the mounting frame (1), a main mounting section (2) and at least one auxiliary mounting section (3) are fixedly connected. Plug rods (4) are inserted into both the main mounting section (2) and the auxiliary mounting section (3); one end of the plug rod (4) is shrunk into a frustum-shaped structure, and the other end of the plug rod (4) is fixedly connected with a hanging rod (5). A clamping plate (6) is clamped on the hanging rod (5), and a first fixing bolt (7) is passed through the clamping plate (6); bolt through holes (101) are opened on the mounting frame (1), and a second fixing bolt (8) is installed through the bolt through holes (101). A lock washer (9) is sleeved on the second fixing bolt (8); pin through holes (102) are opened on the mounting frame (1), and a positioning pin (10) is installed through the pin through holes (102).

2. A mounting structure for a small-thrust turbojet engine according to claim 1, It is characterized in that: Both the main mounting section (2) and the auxiliary mounting section (3) are in interference fit with the plug rod (4), and the main mounting section (2), the auxiliary mounting section (3) and the mounting frame (1) are integrally formed.

3. A mounting structure for a small-thrust turbojet engine according to claim 1, It is characterized in that: A plurality of card slots (51) arranged around the axis of the hanging rod (5) are spaced along the axial direction of the hanging rod (5) on the outer peripheral side surface of the hanging rod (5).

4. A mounting structure for a small-thrust turbojet engine according to claim 3, It is characterized in that: Threaded connection holes (61) for the first fixing bolt (7) to pass through the clamping plate (6) and engaging grooves (62) for cooperating with the card slots (51) are opened on the clamping plate (6). Auxiliary grooves (63) are opened on the groove wall surface of the engaging grooves (62), and the auxiliary grooves (63) penetrate through the clamping plate (6).

5. A mounting structure for a small-thrust turbojet engine according to claim 1, It is characterized in that: The threaded part of the second fixing bolt (8) cooperates with the threaded holes on the stator casing (1001).

6. A mounting structure for a small-thrust turbojet engine according to claim 1, It is characterized in that: The positioning pin (10) is inserted into the pin holes on the stator casing (1001).

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