CN218937775U

CN218937775U - Light aeroengine ignition timing angle detection table

Info

Publication number: CN218937775U
Application number: CN202223550681.8U
Authority: CN
Inventors: 姚尔强; 朱轩; 褚鹏飞; 谢春良; 唐建
Original assignee: Anhui Fiate Aviation Co ltd
Current assignee: Anhui Fiate Aviation Co ltd
Priority date: 2022-12-27
Filing date: 2022-12-27
Publication date: 2023-04-28
Anticipated expiration: 2032-12-27

Abstract

The utility model discloses a light aeroengine ignition timing angle detection table, which relates to the technical field of engine ignition detection and comprises a mounting box body, wherein a detection cavity is arranged in the mounting box body, a telescopic cylinder is vertically arranged in the detection cavity, the telescopic end of the telescopic cylinder is provided with a mounting shaft, and two sides of the mounting shaft are relatively and rotatably connected with two arc-shaped jackets; according to the utility model, the aero-engine is arranged between the two arc-shaped jackets, the mounting shaft and the telescopic cylinder are contracted downwards under pressure, so that the two driving springs are compressed, the two sliding blocks and the lifting blocks are driven to slide along the sliding grooves, the two arc-shaped jackets are mutually close under the action of the two lifting blocks, the two arc-shaped jackets tightly fix the aero-engine, and meanwhile, the two sides of the two arc-shaped jackets can clamp and fix the aero-engines with different radiuses, so that the clamping requirements of the aero-engines with different models can be met, and the applicability of engine fixation is improved.

Description

Light aeroengine ignition timing angle detection table

Technical Field

The utility model relates to the technical field of engine ignition detection, in particular to a light aeroengine ignition timing angle detection table.

Background

Ignition timing: at the end of the compression stroke of the engine, when the piston reaches the top of the stroke, the ignition system provides a high-pressure spark to the spark plug to ignite the compressed mixture in the cylinder to produce work, which is the ignition timing. To maximize the ignition energy, the ignition timing is typically advanced by an amount called the ignition advance angle, so that the piston ignites just before reaching top dead center, rather than just after reaching top dead center;

an existing engine advance angle detection device is disclosed as a first sensor of an engine advance angle detection device in patent grant number CN211825028U, and the first sensor is placed on an engine cylinder body through a first bracket; the second sensor is detachably arranged on the engine cylinder body through a second bracket; a detection pin is movably arranged on the second bracket; the third sensor is arranged on the engine cylinder body at a position close to the crankshaft; namely, the corresponding engine can be fixed and detected only;

when the aero-engine performs ignition intersection detection, the existing angle detection table can only fix aero-engines with corresponding sizes and can not fix aero-engines with different sizes, so that angle detection on the aero-engines with different sizes is inconvenient; meanwhile, the piston positions and the detection positions of the engines of different models are different. To this end, we provide a light aircraft engine ignition timing angle detection station.

Disclosure of Invention

The utility model aims to provide a light aircraft engine ignition timing angle detection table.

The technical problems solved by the utility model are as follows: the existing angle detection table can only fix aeroengines with corresponding sizes and cannot fix aeroengines with different sizes, so that angle detection on aeroengines with different sizes is inconvenient; meanwhile, the piston positions and the detection positions of the engines of different models are different.

The utility model can be realized by the following technical scheme: the utility model provides a light-duty aeroengine ignition timing angle detects platform, includes the installation box, is equipped with the detection chamber in the installation box, and the vertical telescopic cylinder that is provided with in the detection chamber, telescopic cylinder's flexible end is equipped with the installation axle, and the both sides relative rotation of installation axle is connected with two arc jackets, is equipped with the driving piece that drives two arc jackets and is close to each other on the installation box, all is equipped with the detector mounting on each arc jacket.

The utility model further technically improves that: the driving piece includes driving spring, and the both sides of installation box are all vertical to be equipped with the sliding tray, and equal vertical slidable mounting has the slider in the sliding tray, is equipped with the lifter on the slider to two lifter are located the bottom that two arcs pressed from both sides the cover respectively, and two driving spring are vertical setting respectively in two sliding tray, and driving spring's both ends are connected with slider and installation box respectively.

The utility model further technically improves that: one end of the lifting block, which is close to the arc-shaped jacket, is provided with a fixed soft cushion.

The utility model further technically improves that: the two lifting blocks are connected through a connecting rod.

The utility model further technically improves that: each detector mounting piece comprises a mounting plate, the mounting plate is rotationally connected to the arc-shaped jacket, and a plurality of detector mounting holes are formed in the mounting plate.

The utility model further technically improves that: one of the mounting plates is provided with a moving groove, the length direction of the moving groove is parallel to the axial direction of the mounting shaft, a clamping block is slidably mounted in the moving groove, and a penetrating piston detector fixing hole is formed in the clamping block.

Compared with the prior art, the utility model has the following beneficial effects:

(1) According to the detection platform, the aero-engine is arranged between the two arc-shaped jackets, the mounting shaft and the telescopic cylinder are contracted downwards under pressure, so that the two driving springs are compressed, the two sliding blocks and the lifting blocks are driven to slide along the sliding grooves, the two arc-shaped jackets are mutually close under the action of the two lifting blocks, and the two arc-shaped jackets are used for tightly fixing the aero-engine; the two lifting blocks are kept consistent when moving upwards through the connecting rod, so that the two arc-shaped jackets uniformly bear force on two sides of the aero-engine, stability of fixing the aero-engine is improved, and meanwhile, the two sides of the two arc-shaped jackets can clamp and fix the aero-engines with different radiuses, so that the clamping requirements of the aero-engines with different models can be met, and the applicability of fixing the engines is improved;

(2) Make its laminating aeroengine through rotating the mounting panel, install the detector again in corresponding detector mounting hole for the detector in the detector mounting hole detects aeroengine's ignition data, and the joint piece can remove corresponding aeroengine's piston department along the removal groove, passes piston detector fixed orifices with the piston detector again and installs on the piston, makes piston detector detect the piston, thereby can be applicable to the aeroengine detection demand of equidimension not, has improved the suitability that the engine detected.

Drawings

The present utility model is further described below with reference to the accompanying drawings for the convenience of understanding by those skilled in the art.

FIG. 1 is a schematic elevational view of the present utility model;

FIG. 2 is a schematic side view of the present utility model;

fig. 3 is an enlarged view of a portion of the present utility model at a.

In the figure: 1. installing a box body; 2. a telescopic cylinder; 3. a mounting shaft; 4. an arc-shaped jacket; 5. a drive spring; 6. a sliding groove; 7. a slide block; 8. a lifting block; 9. fixing the soft cushion; 10. a mounting plate; 11. a detector mounting hole; 12. a moving groove; 13. a clamping block; 14. a piston detector fixing hole; 15. and (5) connecting a rod.

Detailed Description

In order to further describe the technical means and effects adopted by the utility model for achieving the preset aim, the following detailed description is given below of the specific implementation, structure, characteristics and effects according to the utility model with reference to the attached drawings and the preferred embodiment.

Referring to fig. 1-3, the utility model provides a light aeroengine ignition timing angle detection table, which comprises a mounting box body 1, wherein a detection cavity is arranged in the mounting box body 1, a telescopic cylinder 2 is vertically arranged in the detection cavity, a mounting shaft 3 is arranged at the telescopic end of the telescopic cylinder 2, two arc-shaped jackets 4 are connected with two sides of the mounting shaft 3 in a relative rotation manner, a driving piece for driving the two arc-shaped jackets 4 to mutually approach is arranged on the mounting box body 1, and a detector mounting piece is arranged on each arc-shaped jacket 4; when the aero-engine is arranged between the two arc-shaped jackets 4, the two arc-shaped jackets 4 are driven to be close to each other by the driving piece, so that the two arc-shaped jackets 4 are driven to clamp the two sides of the aero-engine, and clamping and fixing of the aero-engine are completed; meanwhile, the two sides of the two arc-shaped jackets 4 can clamp and fix the aero-engines with different radiuses, so that the clamping requirements of the aero-engines with different models can be met, and the applicability of the device is improved; and then the detector mounting piece is mounted on the aeroengine, so that the detector mounting piece detects the aeroengine, and the ignition timing angle detection process of the aeroengine is completed.

Specifically, in order to drive two arc jackets 4 to carry out the centre gripping to aeroengine, the driving piece includes driving spring 5, the both sides of installation box 1 are all vertical to be equipped with sliding tray 6, all vertical slidable mounting has slider 7 in the sliding tray 6, be equipped with lifter 8 on the slider 7 to two lifter 8 are located the bottom that two arc jackets 4 respectively, and two driving springs 5 are vertical setting respectively in two sliding tray 6, and driving spring 5's both ends are connected with slider 7 and installation box 1 respectively. When the aeroengine is placed between the two arc-shaped jackets 4, the aeroengine drives the two arc-shaped jackets 4 and the mounting shaft 3 to move downwards, so that the telescopic cylinder 2 is contracted, meanwhile, the two driving springs 5 are compressed, and the two sliding blocks 7 and the lifting blocks 8 are driven to slide along the sliding grooves 6, so that the two arc-shaped jackets 4 are mutually close under the action of the two lifting blocks 8, and the two arc-shaped jackets 4 are tightly fixed to the aeroengine, so that the aeroengine is prevented from moving during detection.

The lifting block 8 is provided with a fixed cushion 9 at one end close to the arc jacket 4. The degree of fit between the lifting block 8 and the arc jacket 4 is improved through the fixed cushion 9, so that the degree of fixation of the arc jacket 4 to the aeroengine is improved.

The two lifting blocks 8 are connected through a connecting rod 15. The two lifting blocks 8 are kept consistent when moving upwards through the connecting rod 15, so that the two arc-shaped jackets 4 are guaranteed to uniformly bear the force on two sides of the aero-engine, and the stability of the aero-engine during fixing is improved.

Each detector mounting member includes a mounting plate 10, the mounting plate 10 being rotatably coupled to the arcuate collet 4, the mounting plate 10 being provided with a plurality of detector mounting holes 11. The mounting plate 10 is attached to the aircraft engine by rotating the mounting plate 10, and then the detector is mounted in the detector mounting hole 11, so that the detector in the detector mounting hole 11 detects ignition data of the aircraft engine.

One of the mounting plates 10 is provided with a movable groove 12, the length direction of the movable groove 12 is parallel to the axial direction of the mounting shaft 3, a clamping block 13 is slidably arranged in the movable groove 12, and a through piston detector fixing hole 14 is formed in the clamping block 13. The clamping block 13 is moved to the corresponding piston of the aeroengine, and then the piston detector is installed on the piston through the piston detector fixing hole 14, so that the piston detector detects the piston; and meanwhile, the piston detector fixing holes 14 limit the position of the piston detector, so that the piston detector is prevented from moving during detection.

When the aeroengine is used, the aeroengine is arranged between the two arc-shaped jackets 4, the mounting shaft 3 and the telescopic cylinder 4 are contracted downwards under pressure, so that the two driving springs 5 are compressed, the two sliding blocks 7 and the lifting blocks 8 are driven to slide along the sliding grooves 6, the two arc-shaped jackets 4 are mutually close under the action of the two lifting blocks 8, and the two arc-shaped jackets 4 tightly fix the aeroengine; the two lifting blocks 8 are kept consistent when moving upwards through the connecting rod 15, so that the two arc-shaped jackets 4 are guaranteed to uniformly bear force on two sides of the aero-engine, stability of the aero-engine during fixing is improved, and meanwhile, the two arc-shaped jackets 4 can clamp and fix the aero-engines with different radiuses, so that the clamping requirements of the aero-engines with different models can be met, and the applicability of the device is improved;

make mounting panel 10 laminating aeroengine through rotating mounting panel 10, install the detector again in corresponding detector mounting hole 11 for the detector in the detector mounting hole 11 detects aeroengine's ignition data, and joint piece 13 can remove corresponding aeroengine's piston department along removal groove 12, passes piston detector fixed orifices 14 with the piston detector again and installs on the piston, makes the piston detector detect the piston, thereby can be applicable to the aeroengine detection demand of equidimension not.

The present utility model is not limited to the above embodiments, but is capable of modification and variation in all aspects, including those of ordinary skill in the art, without departing from the spirit and scope of the present utility model.

Claims

1. The utility model provides a light-duty aeroengine ignition timing angle detects platform, includes mounting box (1), be equipped with in mounting box (1) and detect the chamber, its characterized in that, it is vertical to be provided with flexible section of thick bamboo (2) to detect the intracavity, the flexible end of flexible section of thick bamboo (2) is equipped with installation axle (3), the both sides relative rotation of installation axle (3) is connected with two arc jackets (4), be equipped with the driving piece that drives two arc jackets (4) and be close to each other on mounting box (1), all be equipped with the detector mounting on each arc jacket (4).

2. The light aircraft engine ignition timing angle detection table according to claim 1, wherein the driving piece comprises driving springs (5), sliding grooves (6) are vertically formed in two sides of the installation box body (1), sliding blocks (7) are vertically arranged in the sliding grooves (6) in a sliding mode, lifting blocks (8) are arranged on the sliding blocks (7), the two lifting blocks (8) are respectively located at the bottoms of the two arc-shaped clamping sleeves (4), the two driving springs (5) are respectively vertically arranged in the two sliding grooves (6), and two ends of the driving springs (5) are respectively connected with the sliding blocks (7) and the installation box body (1).

3. The light aircraft engine ignition timing angle detection table according to claim 2, wherein a fixed cushion (9) is arranged at one end of the lifting block (8) close to the arc-shaped jacket (4).

4. A light aircraft engine ignition timing angle detection station according to claim 2, characterized in that the two lifting blocks (8) are connected by a connecting rod (15).

5. A light aircraft engine ignition timing angle detection station according to claim 1, characterized in that each detector mount comprises a mounting plate (10), said mounting plates (10) being rotatably connected to the arc-shaped jacket (4), said mounting plates (10) being provided with a plurality of detector mounting holes (11).

6. The light aeroengine ignition timing angle detection table according to claim 5, wherein a moving groove (12) is formed in one mounting plate (10), the length direction of the moving groove (12) is parallel to the axial direction of the mounting shaft (3), a clamping block (13) is slidably mounted in the moving groove (12), and a through piston detector fixing hole (14) is formed in the clamping block (13).