CN217496562U

CN217496562U - Be applicable to aeroengine torsion detection frock

Info

Publication number: CN217496562U
Application number: CN202220911889.9U
Authority: CN
Inventors: 梁振华; 汤佳; 赖智勇; 方程; 陈开朋; 闫彬彬; 朱时浩
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-04-20
Filing date: 2022-04-20
Publication date: 2022-09-27
Anticipated expiration: 2032-04-20

Abstract

The utility model discloses a be applicable to aeroengine torsion detection frock relates to and detects frock technical field, should detect the frock and include: the torsion plate is at least provided with 3 connecting holes in the circumferential direction, and the connecting holes are used for being connected with a flange plate of an output shaft of a propeller of an engine speed reducer; the middle part of the torsion plate is provided with a driving hole; the ratchet head of the fixed-force wrench is matched with the driving hole. The utility model provides a pair of be applicable to aeroengine torsion and detect frock has avoided having the potential safety hazard of unhook in the use, detects more accurately.

Description

Be applicable to aeroengine torsion detection frock

Technical Field

The utility model relates to a detect frock technical field, more specifically the say so and relate to a be applicable to aeroengine torsion and detect frock.

Background

At present, a transmission shaft of an unmanned aerial vehicle engine reduction gearbox mounting propeller (hereinafter referred to as an engine reducer propeller output shaft) needs to test rotating torque to judge whether the engine reduction gearbox meets requirements.

In the prior art, a flange plate on a propeller transmission shaft of a reduction gearbox of an engine is linked through a lever, and a tension scale is used for manually downwards pulling a measured torsion, so that the method has the defects of uneven tension and inaccurate scale of visual observation, and the measurement error is overlarge; meanwhile, in the manual pulling-down process, the hook point of the tension scale and the lever fall off frequently to cause sprain and fall injury of personnel, and potential safety hazards exist.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the utility model discloses a following technical scheme:

the utility model provides a be applicable to aeroengine torsion and detect frock, includes:

the torsion plate is at least provided with 3 connecting holes in the circumferential direction and is used for being connected with a flange plate of an output shaft of a propeller of an engine speed reducer; a driving hole is formed in the middle of the torsion plate;

the ratchet head of the fixed-force wrench is matched with the driving hole.

Furthermore, the connecting holes are arranged corresponding to the fixing holes of the flange plate.

Furthermore, the centers of at least 3 connecting holes form the center of a reference circle which is concentric with the center of the torsion plate.

Further, at least 3 connecting holes are uniformly arranged along the circumferential direction of the torsion plate.

Furthermore, the centers of at least 3 connecting holes form the center of a reference circle which is concentric with the center of the driving disk.

Further, the number of the connecting holes is 3 or 6.

Furthermore, the connecting hole is a counter bore, and the large-diameter hole end of the counter bore is located on one side of the flange plate far away from the output shaft of the propeller of the engine speed reducer.

Further, the counter bore is a cylindrical counter bore.

According to the technical scheme, compare with prior art, the utility model discloses a be applicable to aeroengine torsion and detect frock uses the pulling force balance to replace with torsion disc complex mode deciding power spanner, has avoided the pulling force balance to have the potential safety hazard of unhook in the use, detects more accurately.

And simultaneously, the utility model provides a be applicable to aeroengine torsion detection frock, the operation is simpler, just can accomplish alone, does not need the pull-down tension balance another individual observation reading alone of traditional approach.

Furthermore, the utility model provides a be applicable to aeroengine torsion detection frock judges qualifiedly through the principle of deciding power spanner limited torque, has changed that traditional approach needs to judge qualifiedly through manual calculation after the measured data.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.

Fig. 1 is a schematic view of the overall structure of the detection tool provided by the present invention;

fig. 2 is another view of the detection tool provided by the present invention;

FIG. 3 is a schematic structural view of the torsion plate;

FIG. 4 is another perspective of the torsion plate;

FIG. 5 is a front view of the torsion plate;

FIG. 6 is a sectional view taken along line A-A of FIG. 5;

fig. 7 is a schematic structural view of the constant force wrench.

Wherein: 1 is a torsion plate; 2 is a constant force wrench; 3 is a connecting hole; 4 is a driving hole; and 5, a ratchet head.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-7, the embodiment of the utility model discloses be applicable to aeroengine torsion detection frock, include: a torque plate 1 and a fixed-force wrench 2.

The torsion plate 1 is at least provided with 3 connecting holes 3 in the circumferential direction, and the connecting holes 3 are used for being connected with a flange plate of an output shaft of a propeller of an engine speed reducer; the middle part of the torsion plate 1 is provided with a driving hole 4.

In the present embodiment, the circumferential direction of the torsion plate 1 refers to the direction around the axis of the torsion plate 1, which is perpendicular to the axis and also perpendicular to the cross-sectional radius.

In this embodiment, the flange of the output shaft of the propeller of the engine reducer refers to a flange which is installed on the output shaft of the engine reducer of the unmanned aerial vehicle and used for connection.

Wherein, 1 circumference of torsion dish is provided with 3 connecting holes 3 at least, can avoid torsion dish 1 and the ring flange of engine reduction gear screw output shaft to produce the rotation trend after passing through the screw connection.

In the present embodiment, at least 3 connection holes 3 are uniformly arranged along the circumferential direction of the torsion plate 1.

The ratchet head 5 of the fixed force wrench 2 is engaged with the drive hole 4. Wherein the shape of the driving hole 4 is adapted to the ratchet head 5 of the fixed force wrench 2.

In this embodiment, the ratchet head 5 of the fixed force wrench 2 has a square shape, and the ratchet head 5 is provided with a ball catch that fits into the drive hole 4.

In this embodiment, the driving hole 4 is square and is adapted to the ratchet head 5, wherein a protrusion is provided at the center of the torsion plate 1, the protrusion has an inner cavity forming the driving hole 4, and a mounting hole adapted to the collision ball of the ratchet head 5 is provided on the cavity wall of the protrusion.

In this embodiment, a groove is disposed between the protruding portion and the end surface of the torsion plate 1, wherein the height of the protruding portion should be smaller than the thickness of the torsion plate 1, so as to ensure that the protruding end surface of the protruding portion does not interfere with the flange.

A button for controlling the separation of the collision ball and the mounting hole on the lug boss is arranged on one side of the ratchet head 5 far away from the driving hole 4.

In this embodiment, the connection hole 3 corresponds to a fixing hole of the flange, wherein the torsion plate 1 is fixedly connected to the flange by a screw and a nut passing through the connection hole 3 and the fixing hole of the flange.

In this embodiment, in order to ensure the stability of the fixed connection between the torsion plate 1 and the flange, the number of the connection holes 3 is preferably 6, and the positions of the 6 connection holes 3 should be arranged in 2 equilateral triangles, so as to realize the stability of the connection between the torsion plate 1 and the flange.

In another embodiment, the number of the connection holes 3 is 3, wherein the positions of the 3 connection holes 3 are arranged in an equilateral triangle.

In the present embodiment, since the flange plate of the output shaft of the engine retarder propeller is circular in shape, the torsion plate 1 is preferably circular.

In other embodiments, the shape of the torsion disc 1 may vary depending on the shape of the flange of the output shaft of the engine retarder propeller.

In this embodiment, the 6 connecting holes 3 are uniformly arranged along the circumferential direction of the torsion plate 1, and the centers of the 6 connecting holes 3 form the center of the reference circle, the center of the driving hole 4, the center of the torsion plate 1, and the center of the flange plate.

In other embodiments, the centers of the 6 connecting holes 3 may form the center of the reference circle, the center of the driving hole 4, and the center of the flange plate.

In this embodiment, the connecting hole 3 is a counter bore, and the large-diameter hole end of the counter bore is located on one side of the flange plate far away from the output shaft of the propeller of the engine speed reducer.

Wherein, the counter bore is toper counter bore or cylindricality counter bore, preferably cylindricality counter bore, and the screw is under torsion dish 1 and flange fixed connection's state, and the screwhead is located the cylindricality counter bore to guarantee the terminal surface planarization of torsion dish 1.

The utility model provides an application method suitable for aeroengine torsion detects frock does:

1. the torsion plate of the tool is fixed on a flange plate of an output shaft of a propeller of an engine speed reducer through screws and nuts.

2. And adjusting the torque value of the fixed-force wrench to a preset value, wherein the preset value is required to meet the technical file requirement of the engine speed reducer.

3. And the ratchet head of the fixed-force wrench is arranged on the driving hole so as to realize the link between the fixed-force wrench and the torque plate.

4. Rotating the torque wrench to drive the output shaft of the propeller to rotate, and if the torque is larger than the range specified by the technical requirements, slipping the constant force wrench to judge that the torque is out of tolerance; otherwise, the product is qualified.

The embodiments of the present invention are described in a progressive manner, each embodiment is mainly described as different from the other embodiments, and the same similar parts between the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. The utility model provides a be applicable to aeroengine torsion and detect frock which characterized in that includes:

the ratchet head of the fixed-force wrench is matched with the driving hole.

2. The tool for detecting the torsion of the aero-engine according to claim 1, wherein the connecting holes are arranged corresponding to the fixing holes of the flange plate.

3. The tool for detecting the torsion of the aero engine according to claim 1, wherein the centers of at least 3 connecting holes form a reference circle, and the center of the reference circle is concentric with the center of the torsion disc.

4. The torsion detection tool suitable for the aero-engine according to claim 3, wherein at least 3 connecting holes are uniformly arranged in the circumferential direction of the torsion disc.

5. The tool for detecting the torsion of the aero engine according to claim 4, wherein the centers of at least 3 connecting holes form a reference circle, and the center of the reference circle is concentric with the center of the driving hole.

6. The torsion detection tool suitable for the aero-engine according to claim 1, wherein the number of the connecting holes is 3 or 6.

7. The tool suitable for detecting the torsion of the aero-engine according to claim 1, wherein the connecting hole is a counterbore, and a large-diameter hole end of the counterbore is located on one side of a flange plate far away from an output shaft of a propeller of the engine speed reducer.

8. The tool suitable for detecting the torsion of the aero-engine according to claim 7, wherein the counter bore is a cylindrical counter bore.