阅读说明：本技术 一种航空发动机垂直自动装配对中装置及其使用方法 (Vertical automatic assembly centering device for aero-engine and use method thereof ) 是由 程云勇 林昇 冶文广 窦浩 田怡然 蔺田苗 范欣欣 于 2021-08-20 设计创作，主要内容包括：本发明公开了一种航空发动机垂直自动装配对中监测装置及其使用方法,利用高精度的多自由度转运小车和激光对中仪以解决装配精度及人工成本高的问题,通过自动调节实现航空发动机自动化装配。本发明提供的装置及其使用方法适用于航空发动机的自动装配,解决了航空发动机装配过程中因人为因素所导致的发动机磕碰、装配质量不稳定等情况,不仅提高了装配效率,而且减少了因发动机磕碰、装配质量不稳定现象所导致发动机无法正常进行试车等情况,降低了人工成本。(The invention discloses a vertical automatic assembly centering monitoring device for an aero-engine and a using method thereof, which solve the problems of high assembly precision and high labor cost by utilizing a high-precision multi-degree-of-freedom transfer trolley and a laser centering instrument and realize automatic assembly of the aero-engine through automatic adjustment. The device and the using method thereof provided by the invention are suitable for automatic assembly of the aircraft engine, and solve the problems of engine collision, unstable assembly quality and the like caused by human factors in the assembly process of the aircraft engine, so that the assembly efficiency is improved, the conditions that the engine cannot be normally tested and the like caused by the phenomena of the engine collision and the unstable assembly quality are reduced, and the labor cost is reduced.)

1. The utility model provides a perpendicular automatic assembly centering device of aeroengine which characterized in that:

a rotor unit body (2) and receivers 1(4) and 2(3) in the holes thereof;

a rotor adjusting platform (1) for suspending and positioning the rotor unit body (2);

the multi-degree-of-freedom assembling trolley (7) and an intermediate case (6) assembled on the multi-degree-of-freedom assembling trolley, and a tilt angle sensor (5) is installed on the end face of the intermediate case (6);

a laser transmitter (8) is located on an attitude corrector (9), the attitude corrector (9) being secured within the aperture of the intermediate housing (6) by a transmitter clamp (10);

the rotor adjusting platform (1) is connected with the rotor unit body (2) through a suspension device, the receiver (1), (4) and the receiver (2), (3) are located at the axial center position in a hole of the rotor unit body (2), the emitter clamp (10) is fixed in the hole of the intermediary case (6) and the axis of the hole is coincident, the inclination angle sensor (5) is fixed on the end face of the intermediary case (6) and is horizontally aligned with the intermediary case (6), and the axis of the hole of the intermediary case (6) is coincident with the axis of the hole of the multi-degree-of-freedom assembly trolley (7).

2. The use method of the vertical automatic assembly centering device for the aircraft engine as claimed in claim 1, characterized by comprising the following steps:

step 1, horizontally adjusting an intermediary casing (6);

step 2, calibrating the central hole axis of the intermediate casing (6);

and 3, measuring and adjusting the axis deviation of the rotor unit body (2).

3. Use according to claim 2, characterized in that: in the step 1, the specific step of adjusting the level of the intermediary casing (6) comprises:

1) measuring the inclination angle between the matching end surface of the intermediary case (6) and the horizontal plane according to an inclination angle sensor (5) arranged on the intermediary case (6);

2) the posture of the middle machine box (6) is adjusted through the multi-degree-of-freedom assembly trolley (7).

4. Use according to claim 2, characterized in that: in the step 2, the specific steps of the center hole axis calibration of the intermediate casing (6) comprise:

1) installing a laser transmitter (8) on a central hole of an intermediate casing (6), and installing receivers 1(4) and 2(3) on holes of a rotor unit body (2), wherein the receivers 1(4) are penetrable receivers, and reading a set of four-axis data of the laser through the receivers 1 (4);

2) the intermediate case (6) is rotated by 180 degrees through the multi-degree-of-freedom assembly trolley (7), four-axis data of the receiver 2(3) are read, two groups of data are averaged, and the deviation between the laser transmitter (8) and the axis of the intermediate case (6) is obtained;

3) and adjusting the laser attitude through an attitude corrector under the laser emitter (8), and repeating the steps until the two groups of data are consistent if the adjusted laser attitude does not meet the axis coincidence condition.

5. Use according to claim 2, characterized in that: in the step 3, the specific steps of measuring and adjusting the axis deviation of the rotor unit body (2) comprise:

1) after the axis of the central hole is calibrated, the deviation (the distance from the measuring position of the laser to the center of the receiver) between the straight line of the laser transmitter (8) and the axis of the central hole of the rotor unit body (2) can be measured;

2) adjusting the position of the rotor unit body (2) through the rotor adjusting platform (1) according to the deviation measured in the step;

3) and judging whether the coaxial situation of the laser transmitter (8) and the hole axis of the rotor unit body (2) meets the deviation requirement, if not, repeating deviation measurement and adjustment, and if so, finishing the centering process.

Technical Field

The invention belongs to the field of assembly processes related to the application of an aircraft engine assembly technology, and relates to a vertical automatic assembly device of an aircraft engine and a use method thereof.

Background

Modern aircraft engines are generally designed by adopting unit bodies in order to improve assembly and disassembly efficiency and reduce aircraft engine refitting and maintenance cost. Each engine has its own specific assembly process, according to the technical requirements of the aircraft engine in terms of configuration state, design maintenance, etc. The quality and efficiency of the complete machine assembly of the aero-engine have important influences on the service life, the performance and the reliability of the aero-engine and the production efficiency of the aero-engine. In the whole assembly process of the aircraft engine, the accurate installation between the main unit bodies is one of the core factors influencing the performance, service life, reliability and the like of the aircraft engine, and is one of the process difficulties in the assembly process of the engine.

In the traditional assembly process, an assembler places a heating rod in a matching hole according to a process procedure to reach a specific temperature and then takes out the heating rod, immediately places a shaft part at a position to be assembled, and uses a torque amplifier to carry out manual installation. Because the main body portion of the engine moves between stations during assembly, there is more alignment and leveling work than in conventional spot assembly processes. There are several artifacts that can cause the quality of the assembly to float during this process. In order to reduce the operations of the assembly personnel and at the same time improve the assembly accuracy, an aircraft engine automatic assembly line has become a necessary trend for the assembly of future aircraft engines.

Disclosure of Invention

The invention provides a vertical automatic assembly device of an aero-engine and a using method thereof, aiming at the problems that the assembly quality of the aero-engine is large due to artificial factors in the assembly process of the traditional aero-engine and the manual assembly may cause collision in the assembly process of the aero-engine.

The invention adopts the following technical scheme: an aircraft engine vertical automatic assembly device, includes:

a rotor unit body and a receiver I and a receiver II in the holes of the rotor unit body;

a rotor adjusting platform for suspending and positioning the rotor unit;

the multi-degree-of-freedom assembling trolley is assembled on the intermediate casing, and the inclination angle sensor is installed on the end face of the intermediate casing;

a laser transmitter located on a posture corrector fixed in the intermediate casing hole by a transmitter clamp;

the rotor adjusting platform is connected with the rotor unit body through the suspension device, the first receiver and the second receiver are located at the axial center position in the hole of the rotor unit body, the transmitter clamp is installed in the intermediate casing hole, the axis of the hole is coincident, the inclination angle sensor is fixed on the end face of the intermediate casing and is horizontally aligned with the intermediate casing, and the axis of the intermediate casing hole is coincident with the axis of the hole of the multi-degree-of-freedom assembly trolley.

Furthermore, the centering laser instrument consists of a laser transmitter, a receiver I and a receiver II, and the reading of the receiver is obtained by the laser beam transmitted by the laser transmitter.

Furthermore, the rotor adjusting platform and the multi-degree-of-freedom assembling trolley form a motion control part, the rotor adjusting platform controls the rotor unit body to adjust in a plane mode, and the multi-degree-of-freedom assembling trolley controls the multi-degree-of-freedom space movement of the intermediate casing.

According to the second technical scheme, the use method of the vertical automatic assembly centering monitoring device for the aircraft engine comprises the following steps:

step 1, horizontally adjusting an intermediary casing;

step 2, calibrating the central hole axis of the intermediate casing;

and 3, measuring and adjusting the axial deviation of the rotor unit.

In step 1, the specific step of adjusting the intermediary casing horizontally includes:

1) measuring the inclination angle of the matching end surface of the intermediary case and the horizontal plane according to an inclination angle sensor arranged on the intermediary case;

2) the posture of the intermediary casing is adjusted through the multi-degree-of-freedom assembly trolley.

In step 2, the specific step of calibrating the central hole axis of the intermediate casing includes:

1) installing a laser transmitter on a central hole of an intermediate casing, and installing a receiver I and a receiver II on a hole of a rotor unit body, wherein the receiver I is a penetrating receiver, and a group of four-axis data of laser is read through the receiver I;

2) rotating the intermediate casing by 180 degrees through the multi-degree-of-freedom assembly trolley, reading four-axis data of the second receiver, and averaging the two sets of data to obtain the deviation between the laser transmitter and the axis of the intermediate casing;

3) and adjusting the laser attitude through an attitude corrector under the laser emitter, and repeating the steps until the two groups of data are consistent if the adjusted laser attitude does not meet the axis coincidence condition.

In step 3, the specific steps of measuring and adjusting the axis deviation of the rotor unit body include:

1) after the axis of the central hole is calibrated, the deviation between the straight line of the laser transmitter and the axis of the central hole of the rotor unit body can be measured (the distance from the laser measuring position to the center of the receiver);

2) adjusting the position of the rotor unit body through the rotor adjusting platform according to the deviation measured in the step;

3) and judging whether the coaxial condition of the laser transmitter and the axis of the rotor unit body hole meets the deviation requirement, if not, repeating the deviation measurement and adjustment, and if so, finishing the centering process.

The invention has the beneficial effects that: the device for monitoring vertical automatic assembly and centering of the aero-engine and the using method thereof are suitable for automatic assembly of the aero-engine, solve the problems of engine collision, unstable assembly quality and the like caused by human factors in the assembly process of the aero-engine, improve the assembly efficiency, reduce the problems that the engine cannot be normally tested and the like caused by the phenomena of the engine collision and the unstable assembly quality, and reduce the labor cost.

Drawings

FIG. 1 is a schematic assembly relationship diagram of an aircraft engine vertical automatic assembly centering monitoring device according to the present invention.

FIG. 2 is a flow chart of the algorithm of the present invention.

The system comprises a rotor adjusting platform 1, a rotor unit 2, a receiver II 3, a receiver I4, a tilt angle sensor 5, an intermediate casing 6, a multi-degree-of-freedom assembling trolley 7, a laser transmitter 8, an attitude corrector 9 and a transmitter clamp 10.

Detailed Description

The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

The invention provides a vertical automatic assembly centering monitoring device of an aircraft engine, which comprises a rotor unit body 2, a receiver I4 and a receiver II 3 in a hole of the rotor unit body, a rotor adjusting platform 1 for suspending and positioning the rotor unit body 2, a multi-degree-of-freedom assembly trolley 7 and an intermediate casing 6 assembled on the multi-degree-of-freedom assembly trolley, wherein an inclination angle sensor 5 is installed on the end surface of the intermediate casing 6, a laser transmitter 8 is positioned on an attitude corrector 9, and the attitude corrector 9 is fixed in the hole of the intermediate casing 6 by a transmitter clamp 10, as shown in figure 1.

The invention also provides a using method of the device for monitoring vertical automatic assembly centering of the aircraft engine, as shown in fig. 2, the method of the invention is applied to automatically centering the aircraft engine, and the following steps are executed:

(1) the method comprises the following steps of horizontally adjusting the intermediate casing 6 to be parallel to the lower end face of the rotor unit body 2:

1) measuring the inclination angle between the matching end surface of the intermediary case 6 and the horizontal plane according to an inclination angle sensor 5 arranged on the intermediary case 6;

2) the posture of the intermediary casing is adjusted through the multi-degree-of-freedom assembly trolley.

(2) The method comprises the following steps of calibrating the central hole axis of the intermediate casing 6, and determining the adjusting reference of the rotor unit body 2, wherein the method comprises the following specific steps:

1) installing a laser transmitter 8 on a central hole of an intermediary casing 6, and installing a receiver I4 and a receiver II 3 on holes of a rotor unit body 2, wherein the receiver is a penetrating receiver, and reading a group of four-axis data of laser through the receiver I;

2) the intermediate casing 6 is rotated by 180 degrees through the multi-degree-of-freedom assembly trolley 7, four-axis data of the receiver II 3 are read, and two groups of data are averaged to obtain the deviation between the axis of the laser transmitter 8 and the axis of the intermediate casing 6;

3) and adjusting the laser attitude through an attitude corrector 9 below the laser emitter 8, and repeating the steps until the two groups of data are consistent if the adjusted laser attitude does not meet the axis coincidence condition.

(3) The method specifically comprises the following steps of measuring and adjusting the axis deviation of the rotor unit body 2:

1) after the axis of the central hole is calibrated, the deviation between the straight line of the laser transmitter 8 and the axis of the central hole of the rotor unit body 2 can be measured (the distance from the laser measuring position to the center of the receiver);

2) adjusting the position of the rotor unit body 2 through the rotor adjusting platform 1 according to the deviation measured in the step;

3) and judging whether the coaxial condition of the laser transmitter 8 and the hole axis of the rotor unit body 2 meets the deviation requirement, if not, repeating deviation measurement and adjustment, and if so, finishing the centering process.

Examples

A vertical automatic assembly centering monitoring device for an aircraft engine is characterized in that a rotor adjusting platform 1 is connected with a rotor unit body 2 through a suspension device, a receiver I4 and a receiver II 3 are located at the axial center position in a hole of the rotor unit body 2, a laser emitter 8 is located on an attitude corrector 9, the reading of the receiver is obtained through a laser beam emitted by the laser emitter 8, the attitude corrector 9 is fixed in the hole of an intermediary case 6 through an emitter clamp 10, the emitter clamp 10 is installed in the hole of the intermediary case 6, the hole axis of the emitter clamp coincides with that of the emitter clamp, an inclination angle sensor 5 is installed on the end face of the intermediary case 6 and is horizontally aligned with the intermediary case 6, a multi-freedom degree assembling trolley 7 is installed on the intermediary case 6, the hole axis of the intermediary case 6 coincides with the hole axis of the multi-freedom degree assembling trolley 7, the rotor adjusting platform 1 controls the plane adjustment of the rotor unit body 2, and the multi-freedom degree assembling trolley 7 controls the spatial movement of the intermediary case 6.

As shown in the flow chart of the engine centering process shown in fig. 2, the levelness of the intermediary case 6 is adjusted by using the data obtained by the tilt sensor 5 until the levelness is adjusted to be horizontal to the end face of the rotor unit body 2, then the central hole axis of the intermediary case 6 is determined to be parallel to the hole axis of the rotor unit body 2 by using the laser centering instrument, and then the rotor adjusting platform 1 is controlled to make the central hole axis of the intermediary case 6 coincide with the hole axis of the rotor unit body 2.