阅读说明：本技术 一种航空涡喷发动机启动自动脱离装置 (Automatic disengaging device for starting aviation turbojet engine ) 是由 韩品连 孔国奇 包天宇 于 2021-10-11 设计创作，主要内容包括：本发明涉及航空涡喷发动机技术领域,具体公开了一种航空涡喷发动机启动自动脱离装置,与涡喷发动机外接轴传动连接；包括电机轴、套装在电机轴外侧且与电机轴同轴连接的空心转轴、安装在空心转轴外侧的脱离装置、以及与套装在电机轴外侧且分别与空心转轴和电机轴连接的弹性组件；所述空心转轴分别与电机轴、涡喷发动机外接轴沿其轴向滑动配合。本发明能够有效的实现带动涡喷发动机正常转动,并在涡喷发动机达到正常工作转速时使得涡喷发动机与本装置相脱离,结构简单、实用性强。(The invention relates to the technical field of aviation turbojet engines, and particularly discloses an automatic starting disengaging device of an aviation turbojet engine, which is in transmission connection with an external shaft of the turbojet engine; the motor comprises a motor shaft, a hollow rotating shaft, a separation device and an elastic assembly, wherein the hollow rotating shaft is sleeved on the outer side of the motor shaft and is coaxially connected with the motor shaft, the separation device is arranged on the outer side of the hollow rotating shaft, and the elastic assembly is sleeved on the outer side of the motor shaft and is respectively connected with the hollow rotating shaft and the motor shaft; the hollow rotating shaft is respectively matched with the motor shaft and the external shaft of the turbojet engine in a sliding mode along the axial direction of the motor shaft and the external shaft of the turbojet engine. The device can effectively drive the turbojet engine to normally rotate, enables the turbojet engine to be separated from the device when the turbojet engine reaches the normal working rotating speed, and is simple in structure and high in practicability.)

1. An automatic disengaging device for starting an aviation turbojet engine is in transmission connection with an external shaft of the turbojet engine; the device is characterized by comprising a motor shaft, a hollow rotating shaft, a separation device and an elastic assembly, wherein the hollow rotating shaft is sleeved on the outer side of the motor shaft and is coaxially connected with the motor shaft, the separation device is arranged on the outer side of the hollow rotating shaft, and the elastic assembly is sleeved on the outer side of the motor shaft and is respectively connected with the hollow rotating shaft and the motor shaft;

the hollow rotating shaft is respectively matched with the motor shaft and the external shaft of the turbojet engine in a sliding mode along the axial direction of the motor shaft and the external shaft of the turbojet engine.

2. The automatic release device for starting of the aviation turbojet engine as claimed in claim 1, wherein the release device comprises a hinge seat mounted on the outer side of the hollow rotating shaft, and a release assembly hinged to the hinge seat and clamped to the hollow rotating shaft;

the disengaging assembly is arranged on one side, away from the motor shaft, of the hinged seat.

3. The automatic release device for starting of the aviation turbojet engine as claimed in claim 2, wherein the release assembly comprises a release rod with one end connected with the hinge base, a clamping rod arranged on one side of the release rod close to the hollow rotating shaft, and a clamping groove matched with the clamping rod and arranged on the hollow rotating shaft;

the clamping groove is communicated with the inside of the hollow rotating shaft; the hinged seat is arranged between the separating rod and the motor shaft.

4. The automatic disengaging device for starting of the aviation turbojet engine as claimed in claim 3, further comprising a magnetic assembly and a first mounting groove which is arranged on the hollow rotating shaft and used for mounting the magnetic assembly; the separation rod is arranged corresponding to the mounting groove.

5. The automatic release device for starting of the aviation turbojet engine as claimed in claim 4, wherein the release rod is provided with a second mounting groove along the length direction of the release rod, and a magnetic assembly is mounted in the second mounting groove; the first mounting groove and the second mounting groove are arranged in a one-to-one correspondence mode.

6. The automatic release device for the start of an aviation turbojet engine as recited in claim 3, wherein the clamping rod is of an arc-shaped configuration, and an opening of the clamping rod is disposed on a side away from the shaft of the motor.

7. The automatic disengaging device for starting of the aviation turbojet engine as claimed in any one of claims 1 to 6, wherein the disengaging devices are in a plurality of groups and are uniformly arranged along the circumferential direction of the hollow rotating shaft.

8. The automatic disengaging device for starting of an aviation turbojet engine as claimed in claim 7, wherein the motor shaft comprises a shaft seat, a connecting shaft rod coaxially connected with the shaft seat and sleeved in the hollow rotating shaft; the connecting shaft lever is connected with the hollow rotating shaft through a spline.

9. The automatic release device for the start of an aviation turbojet engine as claimed in claim 8, wherein the resilient member is a spring, and both ends of the spring are connected to the shaft seat and the hollow rotating shaft respectively.

10. The automatic release device for the start of the aviation turbojet engine as claimed in claim 8, wherein the motor shaft is located at a distance D from the turbojet engine external shaft 4 near the end of the turbojet engine external shaft and at a distance E from the turbojet engine external shaft near the side of the clamping groove near the motor shaft when the elastic assembly is in the free state, wherein E > D.

Technical Field

The invention relates to the technical field of aviation turbojet engines, in particular to an automatic disengaging device for starting an aviation turbojet engine.

Background

The aviation turbojet engine is designed to have a working rotating speed (rotating speed point or rotating speed interval), and before the engine reaches the working rotating speed, the engine needs to be driven to rotate by auxiliary equipment, so that the starting process of the engine is the process of enabling the rotating speed of a rotor of the engine to reach the working rotating speed from zero. The existing starting and disengaging device is too complex, and the adaptation of different aviation turbojet engines is not perfect.

Disclosure of Invention

The technical problem to be solved by the invention is to provide an automatic disengaging device for starting an aviation turbojet engine, which can effectively drive the turbojet engine to normally rotate, enables the turbojet engine to be disengaged from the device when the turbojet engine reaches a normal working rotating speed, and has the advantages of simple structure and strong practicability.

The technical problem to be solved by the invention is as follows:

an automatic disengaging device for starting an aviation turbojet engine is in transmission connection with an external shaft of the turbojet engine; the motor comprises a motor shaft, a hollow rotating shaft, a separation device and an elastic assembly, wherein the hollow rotating shaft is sleeved on the outer side of the motor shaft and is coaxially connected with the motor shaft, the separation device is arranged on the outer side of the hollow rotating shaft, and the elastic assembly is sleeved on the outer side of the motor shaft and is respectively connected with the hollow rotating shaft and the motor shaft;

the hollow rotating shaft is respectively matched with the motor shaft and the external shaft of the turbojet engine in a sliding mode along the axial direction of the motor shaft and the external shaft of the turbojet engine.

When the motor is assembled, the hollow rotating shaft is controlled to move towards one side far away from the motor shaft, so that the elastic assembly is in a stretching state, and at the moment, the relative position of the hollow rotating shaft and the motor shaft is locked through the disengaging device, so that the elasticity is in the stretching state when the motor starts to rotate; when the motor shaft rotates, one end of the motor shaft, which is far away from the hollow rotating shaft, is coaxially connected in a transmission way, the other end of the motor shaft is sleeved in the hollow rotating shaft and is connected in a transmission way, and the hollow rotating shaft is driven to rotate under the condition that the motor shaft rotates; the turbojet engine connecting shaft is connected with the hollow rotating shaft through a spline, and meanwhile, the turbojet engine connecting shaft and the hollow rotating shaft are in sliding fit along the axis of the hollow rotating shaft, and the turbojet engine connecting shaft rotates under the condition that the hollow rotating shaft rotates so as to drive the turbojet engine to rotate; along with the increase of the rotating speed, when the rotating speed reaches the starting rotating speed of the turbojet engine, the separation device is separated from the hollow rotating shaft under the action of centrifugal force, and at the moment, the elastic component restores to the initial state and drives the hollow rotating shaft to slide towards one side close to the motor shaft; so that the connecting shaft of the turbojet engine is separated from the hollow connecting shaft; the turbojet engine is brought to the working rotating speed by the hollow rotating shaft, so that the turbojet engine can work independently.

In some possible embodiments, to effectively achieve that the elastic component is in a stretched state; the separation device comprises a hinge seat arranged on the outer side of the hollow rotating shaft and a separation assembly hinged with the hinge seat and clamped with the hollow rotating shaft;

the disengaging assembly is arranged on one side, away from the motor shaft, of the hinged seat.

In some possible embodiments, in order to effectively realize the connection of the disengaging component and the hollow rotating shaft;

the separation assembly comprises a separation rod with one end connected with the hinge seat, a clamping rod arranged on one side of the separation rod close to the hollow rotating shaft, and a clamping groove matched with the clamping rod and arranged on the hollow rotating shaft;

the clamping groove is communicated with the inside of the hollow rotating shaft; the hinged seat is arranged between the separating rod and the motor shaft.

In some possible embodiments, in order to effectively ensure that the turbojet engine reaches the working rotating speed, the centrifugal force is utilized to overcome the magnetic force, so that the separation component is separated from the hollow rotating shaft;

the separation device also comprises a magnetic component and a first mounting groove which is arranged on the hollow rotating shaft and used for mounting the magnetic component; the separation rod is arranged corresponding to the mounting groove.

In some possible embodiments, the release rod is provided with a second installation groove along the length direction thereof, and the second installation groove is internally provided with the magnetic component; the first mounting groove and the second mounting groove are arranged in a one-to-one correspondence mode.

In some possible embodiments, the clamping rod is in an arc-shaped configuration, the opening of which is arranged on the side remote from the motor shaft.

In some possible embodiments, in order to effectively ensure the connection of the disengaging device and the hollow rotating shaft, the hollow rotating shaft is uniformly stressed;

the separation devices are arranged in a plurality of groups and are uniformly arranged along the circumferential direction of the hollow rotating shaft.

In some possible embodiments, in order to effectively realize the installation of the elastic component and the hollow rotating shaft;

the motor shaft comprises a shaft seat and a connecting shaft rod which is coaxially connected with the shaft seat and sleeved in the hollow rotating shaft; the connecting shaft lever is connected with the hollow rotating shaft through a spline.

In some possible embodiments, the elastic component is a spring, and two ends of the spring are respectively connected with the shaft seat and the hollow rotating shaft.

In some possible embodiments, when the elastic assembly is in the free state, the end of the motor shaft close to the turbojet engine external shaft 4 is at a distance D from the turbojet engine external shaft, and the side of the clamping groove close to the motor shaft is at a distance E from the turbojet engine external shaft, where E > D.

Compared with the prior art, the invention has the beneficial effects that:

the separation of the external shaft of the turbojet engine and the hollow rotating shaft is effectively controlled under the action of the separation device and the elastic assembly;

the invention drives the external shaft of the turbojet engine to rotate through the transmission connection of the motor shaft and the hollow rotating shaft;

by arranging the magnetic assembly, the separation of the separation rod and the hollow rotating shaft is effectively avoided when the turbojet engine does not reach the normal rotating speed, so that the condition that the rotating speed of the turbojet engine does not meet the requirement is caused;

the invention has simple structure and strong practicability.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic cross-sectional view of FIG. 1;

FIG. 3 is a schematic elevational view of FIG. 1;

FIG. 4 is a schematic view showing a state of use in which the detachment assembly is detached from the hollow shaft according to the present invention;

FIG. 5 is a schematic cross-sectional view of FIG. 4;

FIG. 6 is a schematic elevational view of FIG. 4;

wherein: 1. a motor shaft; 2. an elastic component; 3. a hollow rotating shaft; 31. a clamping groove; 32. a first mounting groove; 4. a turbojet engine external shaft; 5. a disengaging means; 51. a hinged seat; 52. a release lever; 53. and clamping the rod.

Detailed Description

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; either directly or indirectly through intervening media, either internally or in any other relationship. Reference herein to "first," "second," and similar words, does not denote any order, quantity, or importance, but rather are used to distinguish one element from another. Also, the use of the terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. In the implementation of the present application, "and/or" describes an association relationship of associated objects, which means that there may be three relationships, for example, a and/or B, which may mean: a exists alone, A and B exist simultaneously, and B exists alone. In the description of the embodiments of the present application, the meaning of "a plurality" means two or more unless otherwise specified. For example, the plurality of positioning posts refers to two or more positioning posts. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

The present invention will be described in detail below.

As shown in fig. 1-6:

an automatic disengaging device 5 for starting an aviation turbojet engine is in transmission connection with an external shaft 4 of the turbojet engine; the device comprises a motor shaft 1, a hollow rotating shaft 3 which is sleeved outside the motor shaft 1 and is coaxially connected with the motor shaft 1, a separation device 5 which is arranged outside the hollow rotating shaft 3, and an elastic component 2 which is sleeved outside the motor shaft 1 and is respectively connected with the hollow rotating shaft 3 and the motor shaft 1;

the hollow rotating shaft 3 is respectively in sliding fit with the motor shaft 1 and the turbojet engine external shaft 4 along the axial direction of the hollow rotating shaft; the motor shaft 1, the hollow rotating shaft 3, the external shaft of the turbojet generator and the elastic component 2 are coaxially arranged.

A through hole is formed in the hollow rotating shaft 3 along the axial direction of the hollow rotating shaft; one end of the motor shaft is sleeved in the through hole and is in sliding fit along the axial direction;

when the motor is assembled, the hollow rotating shaft 3 is controlled to move towards one side far away from the motor shaft 1, so that the elastic component 2 is in a stretching state, and at the moment, the relative position of the hollow rotating shaft 3 and the motor shaft 1 is locked through the disengaging device 5, so that the elasticity is in the stretching state when the motor starts to rotate; when the motor shaft 1 rotates, one end of the motor shaft 1, which is far away from the hollow rotating shaft 3, is coaxially connected in a transmission way, the other end of the motor shaft 1 is sleeved in the hollow rotating shaft 3 and is connected in a transmission way, and the hollow rotating shaft 3 is driven to rotate under the condition that the motor shaft 1 rotates; the turbojet engine connecting shaft is connected with the hollow rotating shaft 3 through a spline, and meanwhile, the turbojet engine connecting shaft and the hollow rotating shaft are in sliding fit along the axis of the hollow rotating shaft 3, and the turbojet engine connecting shaft rotates under the condition that the hollow rotating shaft 3 rotates so as to drive the turbojet engine to rotate; along with the increase of the rotating speed, when the rotating speed reaches the starting rotating speed of the turbojet engine, the separation device 5 is separated from the hollow rotating shaft 3 under the action of centrifugal force, and at the moment, the elastic component 2 is restored to the initial state to drive the hollow rotating shaft 3 to slide towards one side close to the motor shaft 1; so that the connecting shaft of the turbojet engine is separated from the hollow connecting shaft; the turbojet engine is brought to the working speed by the hollow rotating shaft 3, so that the turbojet engine can work independently.

In some possible embodiments, to effectively achieve that the elastic component 2 is in a stretched state; the separation device 5 comprises a hinge seat 51 arranged on the outer side of the hollow rotating shaft 3 and a separation assembly hinged with the hinge seat 51 and clamped with the hollow rotating shaft 3;

the disengagement assembly is arranged on the side of the hinge base 51 remote from the motor shaft 1.

The hinge seat 51 is arranged at the outer side of the hollow rotating shaft 3, and the separation assembly is hinged with the hinge seat 51; when elastic component 2 is in free state, break away from subassembly and hollow rotating shaft 3 and do not connect to, when elastic component 2 is in tensile state, break away from the subassembly and will be used for guaranteeing that elastic component 2 is in tensile state all the time, only when the rotation at the turbojet engine reaches the operating requirement, break away from the subassembly under the effect of centrifugal force and adopt and the separation of hollow rotating shaft 3, thereby make hollow rotating shaft 3 move to one side that is close to motor shaft 1 under elastic component 2's drive, make hollow rotating shaft 3 and the separation of turbojet engine external shaft 4, thereby make the turbojet engine normally work.

In some possible embodiments, in order to effectively achieve the connection of the disengagement assembly with the hollow rotating shaft 3;

the disengaging assembly comprises a disengaging rod 52, a clamping rod 53 and a clamping groove 31, wherein one end of the disengaging rod 52 is connected with the hinge seat 51, the clamping rod 53 is arranged on one side of the disengaging rod 52 close to the hollow rotating shaft 3, and the clamping groove 31 is matched with the clamping rod 53 and is arranged on the hollow rotating shaft 3;

the clamping groove 31 is communicated with the inside of the hollow rotating shaft 3; the hinge base 51 is disposed between the disengagement lever 52 and the motor shaft 1.

As shown in fig. 2, the release lever 52 is disposed along the axial direction of the hollow rotating shaft 3, and has one end hinged to the hinge base 51 and a free end located on the side of the hinge base 51 away from the motor shaft 1.

When the spring is in a stretching state, the clamping rod 53 penetrates through the clamping groove 31 to enter the hollow rotating shaft 3 and is abutted against one side of the motor shaft 1 close to the turbojet engine connecting shaft, so that the elastic component 2 is prevented from being incapable of keeping the stretching state;

in some possible embodiments, in order to effectively ensure that the turbojet engine reaches the working rotating speed, the centrifugal force is utilized to overcome the magnetic force, so that the separation component is separated from the hollow rotating shaft 3;

the disengaging device 5 further comprises a magnetic component and a first mounting groove 32 which is arranged on the hollow rotating shaft 3 and used for mounting the magnetic component; the release rod 52 is arranged corresponding to the first mounting groove 32.

The magnetic component is arranged in the first mounting groove 32, and when the elastic component 2 is in a stretching state, the release rod 52 rotates towards one side close to the hollow rotating shaft 3 along the hinge point, so that the clamping rod 53 is ensured to pass through the clamping groove 31 to be abutted against the motor shaft 1;

the first mounting groove 32 is formed in the outer side of the hollow rotating shaft 3, the magnetic component is mounted in the first mounting groove 32 and provides magnetic force to magnetically attract the separation rod 52, so that the separation rod 52 and the clamping rod 53 are prevented from being separated from the hollow rotating shaft 3 due to the action of centrifugal force when the turbojet engine does not reach a normal rotating speed;

in some possible embodiments, the release rod 52 is provided with a second installation groove along the length direction thereof, and the second installation groove is internally provided with a magnetic component; the first mounting groove 32 and the second mounting groove are arranged in a one-to-one correspondence mode.

A second mounting groove is formed in the disengaging rod 52, and a magnetic assembly is mounted in the second mounting groove and has the same function as the first mounting groove 32 and the magnetic assembly;

preferably, the magnetic component is a magnet.

In some possible embodiments, as shown in fig. 2, 4 and 5, the clamping rod 53 has an arc-shaped structure, and the opening of the arc-shaped structure is arranged on the side far away from the motor shaft 1.

In some possible embodiments, in order to effectively ensure the connection of the disengaging device 5 and the hollow rotating shaft 3, the hollow rotating shaft 3 is uniformly stressed;

the separation devices 5 are arranged in a plurality of groups and are uniformly arranged along the circumferential direction of the hollow rotating shaft 3.

Preferably, as shown in fig. 3 and 6, the number of the disengaging devices 5 is three;

in some possible embodiments, in order to effectively realize the installation of the elastic component 2 and the hollow rotating shaft 3;

the motor shaft 1 comprises a shaft seat and a connecting shaft rod which is coaxially connected with the shaft seat and sleeved in the hollow rotating shaft 3; the connecting shaft lever is connected with the hollow rotating shaft 3 through a spline.

The shaft seat is used for being connected with a driving motor to realize the fixation of the connecting shaft rod; the turbojet engine external shaft 4 is connected with a turbine engine to realize the fixation of the turbojet engine external shaft 4; the hollow rotating shaft 3 slides along the axial direction of the elastic component 2, and the hollow rotating shaft 3 rotates under the driving of the driving motor and drives the external shaft 4 of the turbojet engine to rotate, so that the turbojet engine rotates.

Preferably, the motor shaft 1 is of a T-shaped structure, the large end of the motor shaft is a shaft seat, and the small end of the motor shaft is a connecting shaft rod; the hollow rotating shaft 3 is sleeved on the outer side of the connecting shaft rod and connected through a spline, and the hollow rotating shaft and the connecting shaft rod can be in sliding fit in the axial direction; an annular cavity is formed between the shaft seat and the hollow rotating shaft 3, and the elastic component 2 is installed in the annular cavity and is respectively connected with the shaft seat and the hollow rotating shaft 3.

The elastic component 2 is mainly used for realizing the elastic connection between the motor shaft 1 and the hollow rotating shaft 3 and providing elastic acting force for the hollow connecting shaft; can be a compression spring, a disc spring, a plate spring and the like.

In some possible embodiments, in order to make the assembly of the elastic assembly 2 simpler and more convenient; the elastic component 2 is a spring, and two ends of the elastic component are respectively connected with the shaft seat and the hollow rotating shaft 3.

In some possible embodiments, as shown in fig. 5, when the elastic component 2 is in a free state, the end of the motor shaft 1 close to the turbojet engine external shaft 4 is at a distance D from the turbojet engine external shaft 4, and the side of the clamping groove 31 close to the motor shaft 1 is at a distance E from the turbojet engine external shaft 4, where E > D.

As shown in fig. 2, when the spring is in a stretched state, one end of the connecting shaft rod, which is far away from the shaft seat, and one side of the clamping groove 31, which is close to the motor shaft 1 side, are on the same plane, and the two form an abutting surface, and the clamping rod 53 passes through the clamping groove 31, enters the hollow of the hollow rotating shaft 3, and abuts against one end of the connecting shaft rod, which is far away from the motor shaft 1; the hollow rotating shaft 3 is prevented from sliding along the axial direction thereof when the spring is in a stretching state.

The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.