Horizontal thrust testing device for small aero-engine

Abstract

The utility model discloses a small aero-engine horizontal thrust testing device, which belongs to the technical field of aero-engine testing, and comprises a workbench, the top surface of the workbench is fixedly connected with two supporting seats, the side surfaces of the two supporting seats are provided with sliding chutes, and a plurality of sliding columns are connected between the two sliding chutes in a sliding manner. According to the utility model, the small-sized engine is installed and supported through cooperation of the supporting seat, the sliding groove, the sliding column, the movable bottom plate and the installation mechanism, and the small-sized engine drives the movable bottom plate and the sliding column to slide forwards during detection, so that the thrust of the small-sized engine can be tested by using the thrust sensor in front of the movable bottom plate; and lubricating oil is injected into the inner cavity of the sliding groove through the oil injection mechanism, and the friction force between the sliding groove and the sliding column is reduced, so that the accuracy of testing the thrust of the small-sized aero-engine by the thrust sensor is ensured, and the practicability of the horizontal thrust testing device for the small-sized aero-engine is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aero-engine test technology more particularly, relate to a small aero-engine horizontal thrust testing device. BACKGROUND

[0002] The aero-engine is a kind of highly complex and precision thermodynamic machinery, as the heart of aircraft, not only the power of aircraft flight, also is the important driving force for promoting the development of aviation industry.Small aero-engine production and research and development in the process, the thrust provided by the engine needs to be tested.

[0003] Through the retrieval, the utility model discloses a small aero-engine horizontal thrust testing device, the device is by bottom plate, support seat, movable frame bottom plate, engine frame, sensor mounting bracket, sensor fixed base, ball head is formed, support seat bottom is fixed on bottom plate by screw, top has the through-hole, steel cable passes through ball head and support seat top through-hole respectively with support seat and movable frame ground plate fixed suspension;Ball head top has the through-hole, one end side face bore, and there is thread on side hole wall, steel cable passes through top through-hole, and internal hexagonal stud is fixed by the thread extrusion steel cable of side face hole;Sensor mounting bracket bottom is fixed in movable frame bottom plate two sides by nut, hexagonal head bolt respectively passes through sensor mounting bracket front end and knuckle bolt with nut fixed, and sensor one end is connected with knuckle bolt thread;Sensor fixed base bottom is fixed on bottom plate, hexagonal head bolt respectively passes through sensor fixed base front end and knuckle bolt with nut fixed, and sensor other end is connected with knuckle bolt thread;The patent structure principle is simple, and installation is convenient, can adapt to the installation fixed and thrust measurement of different size small aero-engine.But the above-mentioned patent still has the following insufficient: although through steel cable can be suspended installation to movable frame bottom plate, in the process that engine drives movable frame bottom plate to move forward, the existence of steel cable can pull movable frame bottom plate, influence the accuracy of sensor detection;In addition, when the thrust of engine is too large, sensor and steel cable etc. Structure can not prevent movable plate base to move forward, engine together with movable plate base is easy to damage sensor and steel cable out of control and move forward, there is certain dangerous nature, for this, we propose a small aero-engine horizontal thrust testing device. UTILITY MODEL CONTENTS

[0004] In view of the problems in the prior art, the utility model aims at providing a small aero-engine horizontal thrust testing device.

[0005] To solve the above problems, the utility model adopts the following technical scheme:

[0006] The utility model provides a small -size aeroengine horizontal thrust test device, including the workbench, the top surface of workbench is fixedly connected with two support seat, the side surface of two support seat is all set up with the sliding slot, a plurality of slide columns are connected between two sliding slots, the middle part of a plurality of slide columns is fixedly sleeved with movable bottom plate, the top surface of movable bottom plate is provided with two mounting mechanism, the top surface of workbench is fixedly connected with front resistance seat, the front resistance seat and movable bottom plate are fixedly installed with the thrust sensor between, the top surface of workbench is fixedly connected with rear pull seat, the side surface of rear pull seat is fixedly connected with a plurality of steel wire ropes, and the other end of steel wire rope is connected with movable bottom plate, and the workbench is provided with oil injection mechanism.

[0007] As a preferred scheme of the utility model, the oil injection mechanism comprises an oil tank fixedly connected to the bottom surface of the workbench, two oil extraction pumps fixedly installed on the two sides of the oil tank, two oil guide steel pipes fixedly connected to the two ends of the two oil extraction pumps, the ends of the two oil guide steel pipes extending into the inner cavity of the oil tank, and two other oil guide steel pipes fixedly sleeved to the top of the workbench and fixedly connected with oil injection steel pipes, a plurality of oil injection holes provided on the side surfaces of the two oil injection steel pipes and located on the side portions of the sliding slots.

[0008] As a preferred scheme of the utility model, the mounting mechanism comprises a lower arc-shaped support provided on the top of the movable bottom plate and a plurality of screw holes provided on the top surface of the movable bottom plate, an upper arc-shaped support installed on the top of the lower arc-shaped support, and a plurality of bolts sleeved to the lower arc-shaped support and screwed into the inner cavities of the screw holes.

[0009] As a preferred scheme of the utility model, the bottom surface of the workbench is fixedly connected with a plurality of support legs, the bottom ends of the plurality of support legs are fixedly connected with a mounting seat, and a plurality of mounting holes are provided on the mounting seat.

[0010] As a preferred scheme of the utility model, the end of the oil tank is screwed with a threaded plug, and the end of the threaded plug extends into the inner cavity of the oil tank.

[0011] As a preferred scheme of the utility model, the front surface of the workbench is fixedly installed with a control panel, and the control panel is electrically connected with the thrust sensor and the oil extraction pump.

[0012] Compared with the prior art, the utility model has the advantages that:

[0013] (1) The utility model discloses a support seat, sliding slot, slide column, movable bottom plate and the cooperation of installation mechanism are used to the installation support of small engine, and when detecting, the movable bottom plate and slide column are driven by small engine and slide forward, so that the thrust of small engine is tested by the thrust sensor of movable bottom plate front, and the inner chamber of sliding slot is sprayed into lubricating oil through the oil injection mechanism, the friction between sliding slot and slide column is reduced, thereby guaranteeing the accuracy of the thrust sensor to the small aeroengine thrust test, and the practicability is good.

[0014] (2) The utility model discloses a rear pull seat and the cooperation of steel wire rope are used, when movable bottom plate is driven by small engine and moves forward, steel wire rope is gradually straightened, when the thrust of small engine is too big and leads to the damage of thrust sensor and front resistance seat, movable bottom plate is stopped by rear pull seat and steel wire rope and moves, prevents small engine and moves forward, and the safety of the small aeroengine horizontal thrust test device is improved. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is whole structure schematic diagram of the utility model;

[0016] Figure 2 It is whole structure explosion drawing of the utility model;

[0017] Figure 3 It is structure schematic diagram of support seat of the utility model;

[0018] Figure 4 It is structure schematic diagram of oil injection mechanism of the utility model.

[0019] Mark explanation in drawing:

[0020] 1, workbench;2, support seat;3, sliding slot;4, slide column;5, movable bottom plate;6, installation mechanism;7, front resistance seat;8, thrust sensor;9, rear pull seat;10, steel wire rope;11, oil injection mechanism;12, control panel;13, oil tank;14, oil pump;15, oil guide steel pipe;16, oil injection steel pipe;17, oil injection hole;18, threaded plug;19, lower arc support;20, upper arc support;21, screw hole;22, bolt;23, support leg;24, mounting seat;25, mounting hole. DETAILED DESCRIPTION

[0021] The technical schemes in the embodiments of the utility model will be described clearly and completely in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments, and all other embodiments obtained by the ordinary skilled in the art without creative labor based on the embodiments in the utility model belong to the protection scope of the utility model.

[0022] In the description of the utility model, it needs to explain, the term "upper", "lower", "internal", "external", "top / bottom end" and so on indicate the orientation or position relation is based on the orientation or position relation shown in the drawing, only for the convenience of describing the utility model and simplifying the description, and not indicate or imply that the device or element must have a particular orientation, construct and operate with a particular orientation, therefore cannot be understood as the limitation of the utility model. In addition, the term "first", "second" is only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0023] In the description of the utility model, it needs to explain, unless otherwise explicitly provided and limited, the term "installation", "set with", "sleeve set / interface", "connection" and so on, should be understood broadly, for example, "connection", can be fixed connection, can be detachable connection, or integrally connected, can be mechanical connection, can be electrical connection, can be directly connected, can be indirectly connected through intermediate medium, can be the communication inside two elements. For ordinary skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0024] Embodiment:

[0025] Please refer to Figures 1-4 A small aero-engine horizontal thrust testing device, including workbench 1, the top surface of workbench 1 is fixedly connected with two support seats 2, the side surface of two support seats 2 is all set with sliding slot 3, a plurality of slide columns 4 are slidably connected between two sliding slots 3, the middle part of a plurality of slide columns 4 is fixedly sleeved with movable bottom plate 5, the top surface of movable bottom plate 5 is provided with two mounting mechanisms 6, the top surface of workbench 1 is fixedly connected with front abutment 7, front abutment 7 and movable bottom plate 5 are fixedly installed with thrust sensor 8, the top surface of workbench 1 is fixedly connected with rear pull seat 9, rear pull seat 9 is fixedly connected with a plurality of steel wires 10 on the side surface, the end of steel wire 10 is connected with the other end of movable bottom plate 5, and oil injection mechanism 11 is arranged on workbench 1.

[0026] In the embodiment, steel wire 10 is in a relaxed state under normal circumstances.

[0027] Specifically, please refer to Figures 1 to 4 Oil injection mechanism 11 includes oil tank 13 fixedly connected to the bottom surface of workbench 1, oil tank 13 is fixedly installed with oil pump 14 on both sides, two ends of two oil pumps 14 are fixedly connected with oil guide steel pipes 15, ends of two oil guide steel pipes 15 extend to the inner cavity of oil tank 13, ends of other two oil guide steel pipes 15 are fixedly sleeved to the top of workbench 1 and fixedly connected with oil injection steel pipes 16, a plurality of oil injection holes 17 are formed in the side surface of two oil injection steel pipes 16 and located at the side of sliding slot 3.

[0028] In this embodiment, the oil sprayed from the oil injection hole 17 just sprays into the sliding groove 3, so as to lubricate the sliding groove 3 and the sliding column 4, and to reduce the friction between the sliding groove 3 and the sliding column 4 as much as possible.

[0029] Specifically, please refer to Figure 1 and Figure 2 The mounting mechanism 6 comprises a lower arc-shaped support 19 arranged on the top of the movable bottom plate 5 and a plurality of threaded holes 21 arranged on the top surface of the movable bottom plate 5, the top of the lower arc-shaped support 19 is provided with an upper arc-shaped support 20, a plurality of bolts 22 are sleeved on the lower arc-shaped support 19, and the bottom ends of the plurality of bolts 22 are respectively screwed into the inner cavities of the threaded holes 21.

[0030] In this embodiment, the mounting mechanism 6 is mounted on the movable bottom plate 5 through the cooperation of the threaded holes 21 and the bolts 22, and the movable bottom plate 5 can be replaced to mount the aero-engine with different outer diameters, and the upper arc-shaped support 20 and the lower arc-shaped support 19 are mounted through screws, so as to mount the aero-engine on the mounting mechanism 6.

[0031] Specifically, please refer to Figure 1 The bottom surface of the workbench 1 is fixedly connected with a plurality of supporting legs 23, the bottom ends of the plurality of supporting legs 23 are fixedly connected with mounting seats 24, and a plurality of mounting holes 25 are arranged on the mounting seats 24.

[0032] In this embodiment, the workbench 1 is supported by the supporting legs 23 and the mounting seats 24, and the mounting seats 24, the supporting legs 23 and the workbench 1 are fixed on the ground through the cooperation of the screws and the mounting holes 25, so as to ensure the stability of the device.

[0033] Specifically, please refer to Figure 4 The end of the oil tank 13 is screwed with a threaded plug 18, and the end of the threaded plug 18 extends into the inner cavity of the oil tank 13.

[0034] In this embodiment, the threaded plug 18 is removed to fill the lubricating oil into the inner cavity of the oil tank 13.

[0035] Specifically, please refer to Figure 1 and Figure 4 The front surface of the workbench 1 is fixedly provided with a control panel 12, and the control panel 12 is electrically connected with the thrust sensor 8 and the oil pump 14.

[0036] In this embodiment, the control panel 12 is used to control the oil pump 14, and the data detected by the thrust sensor 8 is displayed.

[0037] Working principle: when using, first, the lower arc-shaped support 19 matched with the small engine to be detected is installed on the movable bottom plate 5 through the cooperation of the bolt 22 and the screw hole 21, and the small engine is placed on the lower arc-shaped support 19, and the upper arc-shaped support 20 is threadedly installed on the lower arc-shaped support 19 to fix the small engine, then the two oil pumps 14 are started to pump the lubricating oil in the inner cavity of the oil tank 13 into the oil injection steel pipe 16, and the lubricating oil in the oil injection steel pipe 16 is sprayed from the oil injection hole 17 to the chute 3, so as to lubricate the space between the slide column 4 and the inner wall of the chute 3, and reduce the friction therebetween, then the small engine is started, the thrust of the small engine drives the installation mechanism 6 and the movable bottom plate 5 to move towards the front abutting seat 7, and the thrust of the movable bottom plate 5 is detected by the thrust sensor 8, so as to test the thrust of the small engine, finally, in the process that the movable bottom plate 5 moves together with the slide column 4, the steel wire rope 10 is gradually straightened, when the thrust of the small engine is too large to damage the thrust sensor 8 and the front abutting seat 7, the movable bottom plate 5 is stopped by the rear pulling seat 9 and the steel wire rope 10, and the small engine is prevented from moving forward.

[0038] The above is only the preferred specific implementation mode of the present application, but the protection scope of the present application is not limited to this, any skilled person in the art can make equivalent replacement or change according to the technical scheme and the improvement concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A small aeroengine horizontal thrust test device comprising a workbench (1), characterized in that: The top surface of the workbench (1) is fixedly connected with two support seats (2), the side surfaces of the two support seats (2) are each provided with a sliding groove (3), a plurality of slide columns (4) are slidably connected between the two sliding grooves (3), the middle portions of the plurality of slide columns (4) are fixedly sleeved with movable bottom plates (5), the top surfaces of the movable bottom plates (5) are provided with two mounting mechanisms (6), the top surface of the workbench (1) is fixedly connected with a front abutting seat (7), a thrust sensor (8) is fixedly installed between the front abutting seat (7) and the movable bottom plate (5), the top surface of the workbench (1) is fixedly connected with a rear pulling seat (9), a plurality of steel wires (10) are fixedly connected to the side surface of the rear pulling seat (9), the other end of the steel wire (10) is connected with the end of the movable bottom plate (5), and the workbench (1) is provided with an oil injection mechanism (11).

2. A small aeroengine horizontal thrust test device according to claim 1, characterized in that: The oil injection mechanism (11) comprises an oil tank (13) fixedly connected to the bottom surface of the workbench (1), two oil extraction pumps (14) are fixedly installed on the two sides of the oil tank (13), two oil guide steel pipes (15) are fixedly connected to the two ends of the two oil extraction pumps (14), the ends of the two oil guide steel pipes (15) extend into the inner cavities of the oil tank (13), the ends of the other two oil guide steel pipes (15) are fixedly sleeved to the top of the workbench (1) and are fixedly connected with oil injection steel pipes (16), and a plurality of oil injection holes (17) are formed in the side surfaces of the two oil injection steel pipes (16) and located at the side portions of the sliding grooves (3).

3. A small aeroengine horizontal thrust test device according to claim 1, characterized in that: The mounting mechanism (6) comprises a lower arc-shaped support (19) arranged on the top of the movable bottom plate (5) and a plurality of screw holes (21) formed in the top surface of the movable bottom plate (5), an upper arc-shaped support (20) is installed on the top of the lower arc-shaped support (19), a plurality of bolts (22) are sleeved on the lower arc-shaped support (19), and the bottom ends of the plurality of bolts (22) are respectively threadedly installed into the inner cavities of the screw holes (21).

4. The small aeroengine horizontal thrust test device of claim 1, wherein: The bottom surface of the workbench (1) is fixedly connected with a plurality of support legs (23), the bottom ends of the plurality of support legs (23) are fixedly connected with mounting seats (24), and a plurality of mounting holes (25) are formed in the mounting seats (24).

5. A small aeroengine horizontal thrust test device according to claim 2, characterized in that: The end of the oil tank (13) is threadedly installed with a threaded plug (18), and the end of the threaded plug (18) extends into the inner cavity of the oil tank (13).

6. A small aeroengine horizontal thrust test device according to claim 2, characterized in that: The front surface of the workbench (1) is fixedly installed with a control panel (12), and the control panel (12) is electrically connected with the thrust sensor (8) and the oil extraction pump (14).

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