CN115773729A - Device and method for measuring coaxiality of rotor unit in assembly state of aircraft engine - Google Patents

Abstract

The invention relates to a device and a method for measuring the coaxiality of a rotor unit in an assembly state of an aircraft engine. Case switching centering frock mainly includes: the casing switching positioning piece is fixedly connected to the stator casing of the rotor unit and is aligned with the axis of the rotor unit; the rotor switching positioning piece is matched with the rotor unit so as to align the axis of the casing switching positioning piece and the axis of the rotor unit; the central bearing is arranged between the case transfer positioning piece and the rotor transfer positioning piece, so that the case transfer positioning piece and the rotor transfer positioning piece rotate relatively; and the extension rod mounting structure is fixedly connected to the casing switching positioning piece. The tail end of the measuring extension rod is connected with the extension rod mounting structure, the front end of the measuring extension rod extends into the rotor unit, and the length of the measuring extension rod is enough to reach the position of an inner hole cylindrical surface to be measured. The inner hole circle runout of the multi-stage disc shaft part in the rotor unit of the aircraft engine can be measured simultaneously.

Description

Device and method for measuring coaxiality of rotor unit in assembly state of aircraft engine

Technical Field

The invention relates to the technical field of precision assembly of an aeroengine rotor unit, in particular to a device and a method for determining the assembly coaxiality of a rotor by measuring the inner hole circle run-out parameters of multi-stage disc shaft parts of the rotor unit in the assembly state of the aeroengine.

Background

The assembly coaxiality of parts of the rotor unit of the aircraft engine has an important tractive effect in an engine assembly process, is a key index for determining the service performance and the working safety of the engine and a key component for influencing the assembly quality of the whole engine, and is an important influence factor of the assembly clearance of the rotor of the engine. The rotor unit has a large number of parts, a large number of assembling procedures and complex technical requirements, and the assembling coaxiality of the rotor unit is obviously influenced by the assembling deformation of a typical thin-wall structure of parts, which is a key problem at the expense of the assembling quality of the aeroengine. In specific engineering practice, the assembly process of a large number of parts is involved, and the assembly of the parts of the aircraft engine has the characteristics of typical weak rigidity, easy deformation, high technical precision requirement, more quality technical index control links and the like, so that the technical difficulty of accurate regulation and control in the assembly process of the parts of the rotor is greatly increased.

The existing method mainly optimizes the assembly coaxiality of the rotor unit by measuring the mounting edge run-out of each level of parts of the rotor in advance, or simulates the assembly and measurement coaxiality condition of the air compressing assembly and the turbine assembly of the rotor unit in advance, but in the actual engine assembly link, the rotor assembly and the casing assembly are mutually shielded in the assembly process, so that the rotor unit coaxiality measurement work in the whole machine assembly process cannot be carried out to obtain first-hand data, and great difficulty is brought to the quality assessment of the assembly coaxiality of the rotor unit of the engine product in actual production. Therefore, a technical means capable of effectively measuring the coaxiality of the rotor unit in the assembly state of the aero-engine is urgently needed, so that support is provided for mastering and improving the assembly quality of the aero-engine rotor.

Disclosure of Invention

In view of the above problems, the present invention provides a device for measuring the inner hole circle runout of multiple stages of disk shaft parts of an aircraft engine rotor in an assembled state, which can solve the problem of coaxiality assessment of a long-scale aircraft engine rotor unit by synchronously measuring the inner hole circle runout of multiple disk shaft parts of a compressor part and a turbine part in the rotor unit.

In order to realize the purpose, the invention adopts the following technical scheme:

a rotor unit coaxiality measuring device in an assembled state of an aircraft engine comprises:

cartridge receiver switching centering frock, cartridge receiver switching centering frock mainly includes: the casing switching positioning piece is fixedly connected to the stator casing of the rotor unit and is aligned with the axis of the rotor unit; the rotor switching positioning piece is matched with the rotor unit so as to align the axis of the casing switching positioning piece and the axis of the rotor unit; the central bearing is arranged between the case transfer positioning piece and the rotor transfer positioning piece, so that the case transfer positioning piece and the rotor transfer positioning piece rotate relatively; the extension rod mounting structure is fixedly connected to the casing switching positioning piece; and

and measuring the extension rod, wherein the tail end of the measurement extension rod is connected with the extension rod mounting structure, the front end of the measurement extension rod extends into the rotor unit, and the length of the measurement extension rod is enough to reach the position of an inner hole cylindrical surface to be measured.

And an angle encoder is arranged on the central bearing and used for recording the rotation quantity of the inner ring of the central bearing.

Further comprising: the sensor adaptor is installed on the measuring extension rod.

Further comprising: and the displacement sensor is arranged on the sensor adaptor and used for detecting the inner hole circle runout of the part to be measured in a contact or non-contact mode.

The sensor adapter can be adjusted in height according to the position and the diameter of an inner hole of a part to be measured so as to ensure that the displacement sensor is in a measuring condition.

The sensor adaptor is adjusted and fixed manually or by an expansion rod structure driven by a servo motor according to an input instruction.

The measuring device is used for vertical assembly and horizontal assembly of the aircraft engine to measure and evaluate the coaxiality of the rotor unit.

A method for measuring the coaxiality of a rotor unit in an assembled state of an aircraft engine comprises the following steps:

the rotor unit is placed in a vertical state, the position of the rotor rotation axis is determined through the front fulcrum bearing and the rear fulcrum bearing of the rotor unit so as to establish a measurement reference, and the central line of the measurement extension rod is superposed with the rotor rotation central line;

setting a detection scheme according to the size position relation of the parts of the rotor unit, planning a mounting point on the measuring extension rod and adjusting each sensor to a measuring condition;

the measuring device is installed on an engine rotor, a casing switching positioning piece and a rotor unit are fixed and centered, the rotor switching positioning piece is matched with a rear fulcrum bearing of the rotor unit to achieve simulated centering of the rotor unit, a measuring extension rod extends into the rotor unit, and the measuring extension rod is connected with the casing switching positioning piece through an extension rod installation structure to accurately center the measuring extension rod, adjust the position posture and fix the measuring extension rod;

after the installation and adjustment of the measuring device are completed, the displacement sensor is close to the surface of the inner hole of the part to be measured, the rotor unit is slowly rotated at a constant speed, and after the working state of the sensor is stable, the data acquisition equipment starts to record measured data; and

and performing mathematical calculation on the measurement data to obtain the assembly coaxiality deviation of the rotor unit, and checking the assembly quality of the engine rotor.

The measurement data includes time, rotation angle amount and circle run-out data of each measurement inner hole surface.

Obtaining the assembly coaxiality deviation of the rotor unit comprises:

fitting each inner hole run-out measurement data to a circle;

all fitting circles can be drawn in a coordinate system based on time and rotation angle quantity parameters by considering the synchronism of the measured data;

and performing minimum circular envelope on all fitting circles, and finding out diameter data of the enveloped circles as an assembly coaxiality deviation value of the rotor unit.

Due to the adoption of the technical scheme, the invention has the following advantages:

the inner hole circle runout quantity of the multistage disc shaft part inside the aircraft engine rotor unit can be measured simultaneously, and the data can reflect the coaxiality state of the rotor assembly, so that a key technical means is provided for quality evaluation in the assembly process of the aircraft engine rotor unit.

Drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Like reference numerals refer to like parts throughout the drawings. In the drawings:

FIG. 1 is a schematic view of a measuring device according to an embodiment of the present invention;

FIG. 2 is a schematic diagram of a method of using a measurement device in accordance with an embodiment of the present invention; and

FIG. 3 is a schematic diagram of a method for calculating rotor coaxiality based on a plurality of inner hole runout quantities according to an embodiment of the invention.

In the drawings, the reference numerals denote the following:

1. a casing switching and centering tool; 2. measuring the wand; 3. a sensor adaptor; 4. a measuring probe;

5. the case is connected with the positioning piece in a switching way; 6. a center bearing; 7. a rotor switching positioning piece; 8-extension bar mounting structure.

Detailed Description

Exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention can be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

According to some embodiments of the present application, there is provided a rotor unit coaxiality measuring device in an assembled state of an aircraft engine, including:

the machine box switching centering tool mainly comprises a machine box switching positioning piece, a central bearing, a rotor switching positioning piece and an extension rod mounting structure, wherein the machine box switching positioning piece is fixedly connected with a mounting edge of a stator machine box and realizes centering, the rotor switching positioning piece is matched with a rear bearing piece of a rotor unit to realize simulated centering mounting of the rotor unit, the machine box switching positioning piece realizes mutual rotation relation with the rotor switching positioning piece through the central bearing, and the extension rod mounting structure is fixedly connected with the machine box switching positioning piece.

According to some embodiments of the present application, the rear end of the center bearing may be provided with a measuring device, such as an angular encoder, capable of precisely recording the rotation amount of the inner race of the bearing.

The tail end of the measuring extension rod is connected with the casing switching centering tool through an extension rod mounting structure, the front end of the measuring extension rod extends into the casing, the length of the measuring extension rod is enough to reach the position of an inner hole cylindrical surface to be measured, and meanwhile, a plurality of mounting points are distributed on the extension rod and used for mounting a sensor switching piece.

Each sensor adapter is used for mounting a precise displacement sensor which can detect the inner hole circle runout of each disc shaft part in a contact or non-contact mode.

According to some embodiments of the application, each sensor adapter can be adjusted in height according to the position and the diameter of the inner hole of the part to be measured so as to ensure that the sensor is in a good measuring condition.

In some embodiments of the present application, each sensor adapter may be a manually adjustable and fixed mechanism or may be an expandable rod structure driven by a small precision servo motor that is adjusted and fixed according to an input command.

According to some embodiments of the application, the measuring device can be used under the conditions of vertical assembly and horizontal assembly of the aircraft engine to measure and evaluate the coaxiality of the rotor unit, but the typical use environment is the vertical assembly scene of the core engine of the aircraft engine.

Some embodiments of the present application provide a method for measuring the coaxiality of a rotor unit in an assembly state of an aircraft engine, to which the device for measuring the coaxiality of a rotor unit in an assembly state of an aircraft engine is applied, and the method includes the following specific steps:

step 1: and (3) placing the rotor unit in a vertical state, determining the position of a rotor rotation axis through front and rear fulcrum bearings of the rotor unit, establishing a measurement reference, and enabling the central line of the measurement extension rod to coincide with the rotor rotation central line. And (3) formulating a detection scheme according to the size position relation of the parts on the rotor unit assembly drawing, planning a proper mounting point on the measuring extension rod and adjusting each sensor to a good measuring condition.

Step 2: this measuring device of installation on engine rotor, the installation limit of machine casket switching setting element and stator machine casket is fixed and the centering, and rotor switching setting element realizes the simulation centering to rotor unit with the cooperation of rotor unit rear pivot bearing, will measure inside the extension rod stretches into rotor unit, measures the extension rod and passes through extension rod mounting structure and be connected with machine casket switching setting element, to measuring accurate centering of extension rod, adjusting position gesture and fixed.

And step 3: after the installation and the adjustment of the measuring device are completed, each displacement sensor approaches to the surface of the inner hole of the part to be measured, at the moment, the rotor unit is slowly rotated at a uniform speed, and after the working state of the sensor is stable, the sensor can start to record measurement data including time, rotation angle and circle run-out data of each measured inner hole surface through data acquisition equipment.

And 4, step 4: the measured data is mathematically calculated, the assembly coaxiality deviation of the rotor unit can be obtained, and the parameter is an important assessment index of the assembly quality of the engine rotor in the assembly production process.

Examples

According to some embodiments of the present application, as shown in fig. 1, a rotor unit coaxiality measuring device in an assembled state of an aircraft engine is provided, and comprises a casing adapter centering tool 1, a measuring extension rod 2, a sensor adapter 3 and a displacement sensor 4.

Cartridge change centering frock 1 mainly includes four component parts of cartridge change switching setting element 5, central bearing 6, rotor switching setting element 7 and extension rod mounting structure 8, wherein cartridge change switching setting element 5 realizes centering with the installation limit fixed connection of stator cartridge change, rotor switching setting element 7 realizes the installation of the simulation centering to the rotor unit with the supporting part cooperation behind the rotor unit, cartridge change switching setting element 5 realizes the mutual rotation relation through central bearing 6 and rotor switching setting element 7, extension rod mounting structure 8 carries out fixed connection with cartridge change switching setting element 5.

According to some embodiments of the present application, the rear end of the center bearing 6 may be provided with a measuring device, such as an angular encoder, capable of precisely recording the rotation of the inner race of the bearing.

The tail end of the measuring extension rod 2 is connected with a casing switching centering tool 7 through an extension rod mounting structure 8, the front end of the measuring extension rod extends into the engine stator casing, the length of the measuring extension rod is enough to reach the position of an inner hole cylindrical surface to be measured, and meanwhile, a plurality of mounting points are distributed on the extension rod 2 and used for mounting the sensor adapter 3.

Each sensor adaptor 3 is used for mounting a precise displacement sensor 4 which can detect the inner hole circle runout of each disc shaft part in a contact or non-contact mode.

According to some embodiments of the application, each sensor adapter 3 can be height adjusted according to the part bore position and diameter to be measured to ensure that the sensor 4 is in good measurement condition.

According to some embodiments of the present application, each sensor adapter 3 may be a manually adjustable and fixed mechanism or may be a small precision servo motor driven deployable rod structure that is adjusted and fixed according to the input command.

The measuring device can be used under the conditions of vertical assembly and horizontal assembly of the aircraft engine to measure and evaluate the coaxiality of the rotor unit, but the typical use environment is the vertical assembly scene of the core engine of the aircraft engine.

Compared with the prior art, the detection device provided by the invention can simultaneously measure the circular runout of the inner holes of the multi-stage disc shaft parts in the rotor unit of the aircraft engine, and the data can reflect the coaxiality state of the rotor assembly body, so that a key technical means is provided for the quality evaluation of the assembly process of the rotor unit of the aircraft engine, and the problem that the measurement and evaluation of the coaxiality of the rotor unit cannot be completed in the whole assembly process in the prior art is solved.

The following are the operation steps of the method for measuring the coaxiality of the rotor unit in the assembly state of the aircraft engine by applying the measuring device of the embodiment of the invention.

Step 1: and (3) placing the rotor unit in a vertical state, determining the position of a rotor rotation axis through front and rear fulcrum bearings of the rotor unit, establishing a measurement reference, and enabling the central line of the measurement extension rod to coincide with the rotor rotation central line. And (3) making a detection scheme according to the dimensional position relation of the parts on the rotor unit assembly drawing, planning proper mounting points on the measuring extension rod 2 and adjusting each sensor to a good measuring condition.

And 2, step: this measuring device of installation on engine rotor, the installation limit of machine casket switching setting element 5 and stator machine casket is fixed and the centering, and rotor switching setting element 7 realizes the simulation centering to the rotor unit with the cooperation of rotor unit rear pivot bearing, will measure inside extension rod 2 stretches into the rotor unit, measures extension rod 2 and is connected with machine casket switching setting element 5 through extension rod mounting structure 3, to measuring accurate centering of extension rod 2, adjusting position gesture and fixed.

And 3, step 3: after the installation and adjustment of the measuring device are completed, each displacement sensor 4 approaches the surface of the inner hole of the part to be measured, at the moment, the rotor unit is slowly rotated at a uniform speed, and after the working state of the sensor to be measured is stable, the measuring data including time, rotation angle and circular runout data of each measured inner hole surface can be recorded by data acquisition equipment.

And 4, step 4: processing the original data, and performing mathematical calculation according to the following mode to obtain the assembly coaxiality deviation of the rotor unit: firstly, fitting each inner hole run-out measurement data into a circle; secondly, according to the synchronism of the measurement data, all fitting circles can be drawn in a coordinate system based on time and rotation angle quantity parameters; and finally, carrying out minimum circle enveloping on all fitting circles, and finding out diameter data of the enveloping circle, namely the assembly coaxiality deviation value of the rotor unit. The current assembly coaxiality of the rotor unit is an important assessment index of the assembly quality of the engine rotor.

The embodiment provided by the invention provides a special device for precisely measuring the coaxiality of a rotor unit in an engine assembly state, aiming at the problems that an aeroengine assembly structure is complex and the rotor unit and a stator casing are shielded from each other and difficult to measure, and realizes that:

the detection device is convenient to assemble and disassemble, the operating mechanism is simple and simplified, the coaxiality measurement task of multi-stage parts can be quickly completed in a narrow operating space in the rotor unit, and the detection device is low in manufacturing cost, high in assembly efficiency and good in economic benefit;

the detection device can synchronously measure the inner hole circle run-out of the rotor unit disc shaft part, solves the problem that the traditional method cannot carry out the coaxiality measurement work of the rotor unit to obtain first-hand data, and provides a key technical means for quality evaluation in the rotor unit assembling process.

Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (10)

1. A rotor unit coaxiality measuring device in an aircraft engine assembling state is characterized by comprising:

cartridge receiver switching centering frock (1), cartridge receiver switching centering frock (1) mainly includes: the casing switching positioning piece (5) is fixedly connected to the stator casing of the rotor unit, and is aligned with the axis of the rotor unit; the rotor switching positioning piece (7) is matched with the rotor unit to align the axis of the casing switching positioning piece (5) and the axis of the rotor unit; the central bearing (6) is arranged between the casing switching positioning piece (5) and the rotor switching positioning piece (7) to realize the relative rotation of the casing switching positioning piece (5) and the rotor switching positioning piece (7); an extension bar mounting structure (8), said extension bar mounting structure (8) being fixedly connected to said case transfer location (5); and

the tail end of the measuring extension rod (2) is connected with the extension rod mounting structure, the front end of the measuring extension rod (2) extends into the rotor unit, and the length of the measuring extension rod (2) is enough to reach the position of an inner hole cylindrical surface to be measured.

2. Arrangement according to claim 1, characterized in that an angle encoder is mounted on the central bearing (8) for recording the amount of rotation of the inner ring of the central bearing (8).

3. The apparatus for measuring the coaxiality of the rotor unit in the assembled state of the aircraft engine according to claim 1, further comprising: a sensor adaptor (3), the sensor adaptor (3) being mounted on the measuring wand (2).

4. The apparatus for measuring the coaxiality of the rotor unit in the assembled state of the aircraft engine according to claim 3, further comprising: and the displacement sensor is arranged on the sensor adaptor (3) and is used for detecting the inner hole circular runout of the part to be measured in a contact or non-contact mode.

5. The device for measuring the coaxiality of the rotor unit in the assembled state of the aircraft engine according to claim 3, wherein the sensor adapter (3) can be adjusted in height according to the position and the diameter of the inner hole of the component to be measured, so as to ensure that the displacement sensor is in a measuring condition.

6. The device for measuring the coaxiality of a rotor unit in an assembled state of an aircraft engine according to claim 3, wherein the sensor adapter (3) is adjusted and fixed manually or by means of a deployment rod structure driven by a servomotor, according to input commands.

7. The device for measuring the coaxiality of a rotor unit in an assembled state of an aircraft engine according to claim 1, wherein the device is used for vertical assembly and horizontal assembly of the aircraft engine to measure and evaluate the coaxiality of the rotor unit.

8. A method of measuring the coaxiality of a rotor unit in an assembled state of an aircraft engine, using the apparatus for measuring the coaxiality of a rotor unit in an assembled state of an aircraft engine according to any one of claims 1 to 7, comprising:

the rotor unit is placed in a vertical state, the position of the rotor rotation axis is determined through the front fulcrum bearing and the rear fulcrum bearing of the rotor unit so as to establish a measurement reference, and the central line of the measurement extension rod is superposed with the rotor rotation central line;

setting a detection scheme according to the size position relation of the parts of the rotor unit, planning a mounting point on the measuring extension rod and adjusting each sensor to a measuring condition;

the measuring device is installed on an engine rotor, a casing switching positioning piece and a rotor unit are fixed and centered, the rotor switching positioning piece is matched with a rear fulcrum bearing of the rotor unit to achieve simulated centering of the rotor unit, a measuring extension rod extends into the rotor unit, and the measuring extension rod is connected with the casing switching positioning piece through an extension rod installation structure to accurately center the measuring extension rod, adjust the position posture and fix the measuring extension rod;

after the installation and the adjustment of the measuring device are finished, the displacement sensor is enabled to be close to the surface of an inner hole of a part to be measured, the rotor unit is slowly rotated at a constant speed, and after the working state of the sensor is stable, measuring data are recorded through data acquisition equipment; and

and performing mathematical calculation on the measurement data to obtain the assembly coaxiality deviation of the rotor unit, and checking the assembly quality of the engine rotor.

9. The method of claim 8, wherein the measurement data includes time, an amount of rotational angle, and circular run out data for each measured bore surface.

10. The method for measuring the coaxiality of the rotor unit in the assembled state of the aircraft engine as claimed in claim 8, wherein the obtaining of the deviation of the assembled coaxiality of the rotor unit includes:

fitting each inner hole run-out measurement data to a circle;

all fitting circles can be drawn in a coordinate system based on time and rotation angle quantity parameters by considering the synchronism of the measured data;

and performing minimum circle enveloping on all fitting circles, and finding out diameter data of the enveloped circles as an assembly coaxiality deviation value of the rotor unit.

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