Method and device for measuring relative runout between rotor and stator of aeroengine

Abstract

The present disclosure relates to a method and device for measuring the relative runout between a stator and a rotor of an aero-engine. The measurement method includes: establishing a first coordinate system for the stator unit body, and measuring a first coordinate data set of at least one stage of the first mating part of the stator in the stator unit body; establishing a second coordinate system for the rotor unit body, and measuring a second coordinate data set of at least one stage of the second mating part of the rotor in the rotor unit body; assembling the stator unit body and the rotor unit body, establishing a third coordinate system for the stator unit body that is consistent with the first coordinate system, and establishing a fourth coordinate system for the rotor unit body that is consistent with the second coordinate system; rotating the rotor unit body in the assembled body, and establishing a dynamic rotor coordinate system of the rotor unit body in real time based on the fourth coordinate system; according to the pose relationship between the first coordinate system and the dynamic rotor coordinate system and the third coordinate system, converting both the first coordinate data set and the second coordinate data set to the third coordinate system, and calculating the relative runout between at least one stage of the rotor and the stator.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aeroengine measurement, and particularly to a method and device for measuring the relative runout between the rotating and stationary components of an aeroengine. Background Art

[0002] The engine assembly process is a very important link, which has a direct impact on the product reliability. The relative runout between the rotating and stationary components after assembly in the engine is an important parameter input for measuring the rubbing amount between the rotating and stationary components and the change amount of the relative clearance between the rotating and stationary components during the rotor movement process, and is the key data that needs to be detected during the overall engine assembly process.

[0003] In order to obtain the rubbing amount between the rotating and stationary components, the traditional detection method measures the clearance between the rotor blades and the stator coating, and between the rotor labyrinth and the stator honeycomb by using a feeler gauge. However, the obvious drawback of this method is that it can only measure a limited number of local measuring points and all are static data.

[0004] Or, in order to obtain the relative change amount between the rotating and stationary components, the traditional detection method uses the runout of the rotor blades in the rotor unit state, the runout of the stator coating in the stator unit state, and then combines the clearance between the rotating and stationary components. However, the obvious disadvantage of this method is that it ignores the assembly state of the rotating and stationary components, resulting in a large error. Summary of the Invention

[0005] Embodiments of the present disclosure provide a method and device for measuring the relative runout between the rotating and stationary components of an aeroengine, which can improve the objectivity and accuracy of measuring the relative runout between the rotating and stationary components of an aeroengine.

[0006] According to the first aspect of the present disclosure, there is provided a method for measuring the relative runout between the rotating and stationary components of an aeroengine, including:

[0007] Establish a first coordinate system for a separate stator unit body, and measure a first coordinate data set of at least one stage of stator's first mating part in the stator unit body, where the first mating part is used to form a working clearance with a second mating part on the corresponding stage of the rotor;

[0008] Establish a second coordinate system for a separate rotor unit body, and measure a second coordinate data set of at least one stage of rotor's second mating part in the rotor unit body;

[0009] Assemble the stator unit body and the rotor unit body, establish a third coordinate system for the stator unit body that is consistent with the first coordinate system, and establish a fourth coordinate system for the rotor unit body that is consistent with the second coordinate system;

[0010] Rotate the rotor unit body in the assembly, and establish a dynamic rotor coordinate system of the rotor unit body in real time based on the fourth coordinate system;

[0011] According to the pose relationship between the first coordinate system and the third coordinate system, and the pose relationship between the dynamic rotor coordinate system and the third coordinate system, both the first coordinate data set and the second coordinate data set are converted to the third coordinate system, and the relative runout between at least one stage of the rotor and the stator is calculated.

[0012] In some embodiments, establishing a first coordinate system for the stator unit body includes:

[0013] Set a reference hole or a reference installation tooling on the stator unit body to provide at least three target installation points outside the stator unit body;

[0014] Install the first targets at the at least three target installation points one by one;

[0015] Measure the coordinates of the at least three first targets and establish the first coordinate system;

[0016] Alternatively, establishing a second coordinate system for the rotor unit body includes:

[0017] Set a reference hole or a reference installation tooling on the rotor unit body to provide at least three target installation points outside the rotor unit body;

[0018] Install the second targets at the at least three target installation points one by one;

[0019] Measure the coordinates of the at least three second targets to establish the second coordinate system.

[0020] In some embodiments, rotating the rotor unit body in the assembly to establish the dynamic rotor coordinate system of the rotor unit body based on the fourth coordinate system in real time includes:

[0021] In the assembly, use the coordinates of at least three second targets corresponding to the fourth coordinate system as the initial positions;

[0022] Rotate the rotor unit body and measure the coordinates of at least three second targets in real time to establish the dynamic rotor coordinate system of the rotor unit body.

[0023] In some embodiments, the first mating part is a stator coating, the stator coating is conical, and measuring the first coordinate data set of the first mating part of at least one stage of the stator in the stator unit body includes:

[0024] Select different cross-sections on the stator coating of at least one stage of the stator;

[0025] Measure the coordinates of multiple points in the circumferential direction on the inner surface of the stator coating using the laser scanning method on each cross-section;

[0026] Form the first coordinate data set with the coordinates of each point on different cross-sections.

[0027] In some embodiments, the second mating part is a rotor blade, and the second coordinate data set for measuring the second mating part of at least one stage of the rotor includes:

[0028] Using the spherical measurement method to find the tip positions of the rotor blades in the circumferential direction of at least one stage of the rotor, and obtaining the coordinates of the tip positions of each rotor blade to form a second coordinate data set.

[0029] In some embodiments, according to the pose relationship between the first coordinate system and the third coordinate system, and the pose relationship between the dynamic rotor coordinate system and the third coordinate system, converting both the first coordinate data set and the second coordinate data set to the third coordinate system includes:

[0030] Calculating the first pose matrix between the first coordinate system and the third coordinate system;

[0031] Calculating the second pose matrix between the dynamic rotor coordinate system and the third coordinate system;

[0032] Multiplying the first coordinate data set by the first pose matrix to convert it into a data set in the third coordinate system;

[0033] Multiplying the second coordinate data set by the second pose matrix to convert it into a data set in the third coordinate system.

[0034] In some embodiments, the first mating part is a stator coating and the second mating part is a rotor blade. Converting both the first coordinate data set and the second coordinate data set to the third coordinate system and calculating the relative runout between a certain stage of the rotor and the stator includes:

[0035] At a specific moment when the rotor unit rotates, calculating the minimum distance between the tip of a single rotor blade in a certain stage of the rotor and the scanning points of the stator coating as the distance between the tip and the stator coating at the specific moment;

[0036] Forming a set of clearance change amounts between a single rotor blade and the stator coating in sequence according to the distances between the tip and the stator coating at each specific moment during the rotation of the rotor unit;

[0037] Successively obtaining the sets of clearance change amounts of all rotor blades in a certain stage of the rotor.

[0038] In some embodiments, it further includes:

[0039] Calculating the sets of clearance change amounts of all rotor blades in all stages of the rotor.

[0040] In some embodiments, it further includes:

[0041] Calculating the change range of the working clearance between at least one stage of the rotor and the stator based on the relative runout between at least one stage of the rotor and the stator; and / or

[0042] Calculate the relative eccentricity between the rotor and the stator according to the relative runout between at least one stage of the rotor and the stator.

[0043] In some embodiments, the first mating part is the stator coating, and the second mating part is the rotor blade; and / or the first mating part is the stator honeycomb, and the second mating part is the rotor labyrinth.

[0044] According to a second aspect of the present disclosure, there is provided an aero-engine rotor-stator relative runout measuring device, including:

[0045] At least three first targets, corresponding to the stator unit body, configured to establish a first coordinate system for the individual stator unit body; and after the stator unit body and the rotor unit body are assembled, establish a third coordinate system consistent with the first coordinate system;

[0046] At least three second targets, corresponding to the rotor unit body, configured to establish a second coordinate system for the individual rotor unit body, and after the stator unit body and the rotor unit body are assembled, establish a fourth coordinate system consistent with the second coordinate system, and when the rotor unit body rotates in the assembly, establish a dynamic rotor coordinate system of the rotor unit body in real time based on the fourth coordinate system;

[0047] A first measuring component, configured to measure a first coordinate data set of at least one stage of the stator in the stator unit body, and the first mating part is used to form a working gap with the second mating part on the corresponding stage of the rotor;

[0048] A second measuring component, configured to measure a second coordinate data set of at least one stage of the rotor in the rotor unit body; and

[0049] A controller, configured to convert both the first coordinate data set and the second coordinate data set to the third coordinate system according to the pose relationship between the first coordinate system and the third coordinate system, and the pose relationship between the dynamic rotor coordinate system and the third coordinate system, and calculate the relative runout between at least one stage of the rotor and the stator.

[0050] The aero-engine rotor-stator relative runout measuring method according to the embodiments of the present disclosure takes into account the assembly error between the rotor and the stator, can also measure the runout of the second mating part during the entire rotation of the rotor unit body, and is also convenient for measuring the runout of multiple second mating parts (for example, rotor blades) of a certain stage of the rotor in the circumferential direction, and can also measure the mating conditions between multiple stages of the rotor and the stator. Therefore, the measurement result can more objectively reflect the runout situation after the actual assembly of the rotor and the stator, improve the accuracy of the measurement result, and thus improve the assembly accuracy of the aero-engine. Description of the Drawings

[0051] The accompanying drawings described herein are used to provide a further understanding of the present disclosure, and constitute a part of this application. The schematic embodiments of the present disclosure and their descriptions are used to explain the present disclosure, and do not constitute an improper limitation of the present disclosure. In the drawings:

[0052] Figure 1 is a schematic structural diagram of the matching between the rotating and stationary components in the aero-engine of the present disclosure;

[0053] Figure 2 is a schematic diagram for establishing a coordinate system and performing measurements on the compressor stator unit;

[0054] Figure 3 is a schematic diagram for establishing a coordinate system and performing measurements on the compressor rotor unit;

[0055] Figure 4 is a schematic diagram for measuring the combined state of the compressor rotor and stator;

[0056] Figure 5 is a schematic flowchart of some embodiments of the method for measuring the relative runout between the rotating and stationary components of the aero-engine of the present disclosure;

[0057] Figure 6 is a schematic diagram of the module composition of some embodiments of the device for measuring the relative runout between the rotating and stationary components of the aero-engine of the present disclosure. Detailed Embodiments

[0058] The following details the present disclosure. In the following paragraphs, different aspects of the embodiments are more specifically defined. Each aspect so defined can be combined with any other one or more aspects, unless clearly stated otherwise. In particular, any feature considered to be preferred or advantageous can be combined with any other one or more features considered to be preferred or advantageous.

[0059] The terms "first", "second", etc. used in the present disclosure are only for convenience of description to distinguish different components with the same name, and do not indicate a sequence or primary-secondary relationship.

[0060] In the description of the present invention, it should be understood that the orientation or positional relationships indicated by the terms "inner", "outer", "upper", "lower", "left", and "right" are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention, rather than indicating or implying that the device referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the protection scope of the present invention.

[0061] Such as Figure 1As shown, an aero-engine compressor includes a stator unit 10 and a rotor unit 20. The stator unit 10 is provided with multiple stages of stators along the axial direction of the aero-engine, and the rotor unit 20 is provided with multiple stages of rotors along the axial direction of the aero-engine. The multiple stages of stators and the multiple stages of rotors are arranged in one-to-one correspondence, and a working gap is formed between the stator and the rotor of the corresponding stage. Specifically, a first mating part is provided on a certain stage of the stator, and a second mating part is provided on the rotor of the corresponding stage. The first mating part is used to form a working gap with the second mating part on the rotor of the corresponding stage.

[0062] For example, as Figure 1 shown, the first mating part is the stator coating 12, and the second mating part is the rotor blade 21. The stator coating 12 is provided on the inner wall of the stator casing 11; and / or the first mating part is the stator honeycomb 14, and the second mating part is the rotor labyrinth 22.

[0063] Based on the above structure, the present disclosure provides a method for measuring the relative runout between the rotor and stator of an aero-engine. In some embodiments, as Figure 5 shown, the measuring method includes:

[0064] Step 110, as Figure 2 shown, establish a first coordinate system O xyz ( J S 1～3 ) for the separate stator unit 10, and measure the first coordinate data set of the first mating part of at least one stage of the stator in the stator unit 10. The first coordinate system is the stator coordinate system; wherein, the first mating part is used to form a working gap with the second mating part on the rotor of the corresponding stage.

[0065] Step 120, as Figure 3 shown, establish a second coordinate system O uvw ( d R 1～3 ) for the separate rotor unit 20, and measure the second coordinate data set of the second mating part of at least one stage of the rotor in the rotor unit 20. The second coordinate system O uvw ( d R 1～3 ) is the rotor coordinate system.

[0066] Step 130, as Figure 4 shown, assemble the stator unit 10 and the rotor unit 20, and establish a third coordinate system O xyz ( J S 1～3 ) that is consistent with the first coordinate system O xyz ( z S 1～3 ) for the stator unit 10, and establish a third coordinate system O uvw ( d R1～3 ) Consistent fourth coordinate system O uvw ( Z R 1～3 );The third coordinate system O xyz ( z S 1～3 ) is established in the same way as the first coordinate system O xyz ( J S 1～3 ) The fourth coordinate system O uvw ( Z R 1～3 ) is established in the same way as the second coordinate system O uvw ( d R 1～3 ) is the same.

[0067] Step 140: Rotate the rotor unit body 20 in the assembly to establish the dynamic rotor coordinate system Oi of the rotor unit body 20 in real time based on the fourth coordinate system O uvw ( Z R 1～3 ). uvw ( Z R 1～3 ).

[0068] Step 150: According to the pose relationship between the first coordinate system O xyz ( J S 1～3 ) and the third coordinate system O xyz ( z S 1～3 ), and the pose relationship between the dynamic rotor coordinate system Oi uvw ( Z R 1～3 ) and the third coordinate system O xyz ( z S 1～3 ), convert both the first coordinate data set and the second coordinate data set to the third coordinate system O xyz ( z S 1～3 ) and calculate the relative runout between at least one stage of the rotor and the stator.

[0069] Among them, the execution order of Step 110 and Step 120 can be interchanged, and Steps 130 - 150 are executed in sequence. Before assembling the stator unit body 10 and the rotor unit body 20, first measure the coordinates of the first mating part in the first coordinate system of the stator unit body 10 alone, and measure the coordinates of the second mating part in the second coordinate system of the rotor unit body 20, so that it is easy to measure the coordinates of the mating parts.

[0070] Next, rotate the rotor after assembly. Taking the third coordinate system of the stator as a reference, the dynamic change amount of the fourth coordinate system relative to the third coordinate system is detected in real time, so as to obtain the distance change relationship between the first mating part and the second mating part in the assembled state, that is, the clearance change amount between the rotor and the stator.

[0071] This method takes into account the assembly error between the rotor and the stator, can also measure the runout of the second mating part during the entire rotation of the rotor unit body, and is also convenient for measuring the runout of multiple second mating parts (for example, rotor blades 21) in the circumferential direction of a certain stage of the rotor, and can also measure the mating condition between multiple stages of the rotor and the stator. Therefore, the measurement result can more objectively reflect the runout condition after the actual assembly of the rotor and the stator, and improve the accuracy of the measurement result.

[0072] In some embodiments, as Figure 2 shown, establishing the first coordinate system for the stator unit body 10 in step 110 includes:

[0073] Step 110A: Set reference holes or reference installation tooling on the stator unit body 10 to provide at least three target installation points outside the stator unit body 10; for example, set three target installation points, and the three target installation points are not collinear;

[0074] Step 110B: Install the first targets at the at least three target installation points one by one;

[0075] Step 110C: Measure the coordinates of the at least three first targets and establish the first coordinate system O xyz ( J S 1～3 )。

[0076] In this embodiment, by setting target installation points outside the stator unit body 10, the first coordinate system can be conveniently and accurately established by measuring the coordinate positions of the first targets.

[0077] In some embodiments, establishing the second coordinate system for the rotor unit body 20 in step 120 includes:

[0078] Step 120A: Set reference holes or reference installation tooling on the rotor unit body 20 to provide at least three target installation points outside the rotor unit body 20; for example, set three target installation points, and the three target installation points are not collinear;

[0079] Step 120B: Install the second targets at the at least three target installation points one by one;

[0080] Step 120C: Measure the coordinates of the at least three second targets to establish the second coordinate system O uvw ( d R 1～3 )。

[0081] In this embodiment, by providing a target mounting point outside the rotor unit body 20, the second coordinate system can be conveniently and accurately established by measuring the coordinate positions of the second targets.

[0082] In some embodiments, in step 140, the rotor unit body 20 is rotated in the assembly, and a dynamic rotor coordinate system Oi of the rotor unit body 20 is established in real time based on the fourth coordinate system. uvw ( Z R 1～3 ) includes:

[0083] Step 140A: In the assembly, use the coordinates of at least three second targets corresponding to the fourth coordinate system as the initial positions.

[0084] Step 140B: Rotate the rotor unit body 20, and measure the coordinates of at least three second targets in real time to establish a dynamic rotor coordinate system Oi of the rotor unit body 20. uvw ( Z R 1～3 ).

[0085] In this embodiment, when the rotor is rotated in the assembled state, with the third coordinate system of the stator as the reference, the dynamic change amount of the fourth coordinate system relative to the third coordinate system is detected in real time, and this change amount is reflected in the form of the coordinates of the second targets. Since the second coordinate data set of the second mating part in the rotor unit body 20 has been measured in the second coordinate system, and the dynamic rotor coordinate system has been obtained based on the fourth coordinate system after assembly, the coordinates of the second mating part in the dynamic rotor coordinate system can thus be obtained. Thereby, the distance change relationship between the first mating part and the second mating part in the assembled state, that is, the clearance change amount between the rotor and the stator, can be obtained.

[0086] In some embodiments, as Figure 2 shown, the first mating part is the stator coating 12, and the stator coating 12 is conical. The first coordinate data set for measuring the first mating part of at least one stage of the stator in the stator unit body 10 in step 110 includes:

[0087] Step 110D: Select different cross-sections on the stator coating 12 of at least one stage of the stator.

[0088] Step 110E: Use the laser scanning method to measure the coordinates of multiple circumferential points on the inner surface of the stator coating 12 on each cross-section; for example, select 1 to m cross-sections, and select 1 to n points in each cross-section.

[0089] Step 110F: Form a first coordinate data set with the coordinates of the points on different cross-sections.

[0090] Since the stator coating 12 is conical, by obtaining different cross-sections and selecting the coordinates of multiple points within each cross-section, the coordinate situation of the stator coating 12 can be more comprehensively reflected to calculate the distance from the tip of the rotor blade 21.

[0091] In some embodiments, the second mating part is the rotor blade 21, and the second coordinate data set for measuring the second mating part of at least one stage of the rotor in step 120 includes:

[0092] Using the spherical measurement method to find the tip positions of the circumferential rotor blades 21 of at least one stage of the rotor and obtaining the coordinates of the tip positions of the rotor blades 21 to form a second coordinate data set.

[0093] Since the end of the rotor blade 21 is an inclined structure, by measuring to find the tip position, the working gap between the rotor blade 21 and the stator coating 12 can be more accurately reflected.

[0094] In some embodiments, in step 150, according to the pose relationship between the first coordinate system and the third coordinate system, and the pose relationship between the dynamic rotor coordinate system and the third coordinate system, converting both the first coordinate data set and the second coordinate data set to the third coordinate system includes:

[0095] Step 150A, calculate the first pose matrix T0 between the first coordinate system O xyz ( J S 1～3 ) and the third coordinate system O xyz ( z S 1～3 ), T0 = F(O xyz ( z S 1～3 ), O xyz ( J S 1～3 ));

[0096] Step 150B, calculate the second pose matrix T1i between the dynamic rotor coordinate system Oi uvw ( Z R 1～3 ) and the third coordinate system O xyz ( z S 1～3 ), T1i = F(O xyz ( z S 1～3 ) · Oi uvw ( Z R 1～3 ));

[0097] Step 150C, multiply the first coordinate data set by the first pose matrix T0 to convert it into a data set in the third coordinate system;

[0098] Step 150D: Multiply the second coordinate data set by the second pose matrix T1i to convert it into a data set in the third coordinate system.

[0099] This embodiment can accurately convert the first coordinate data set and the second coordinate data set to the coordinate system after assembly through coordinate system changes. Thus, the converted coordinate data obtained from the first coordinate data set and the second coordinate data set in the coordinate system of the assembly can consider the influence of assembly errors, and thus accurately measure the runout of the rotor-stator.

[0100] In some embodiments, the first mating part is the stator coating 12, and the second mating part is the rotor blade 21. In step 150, both the first coordinate data set and the second coordinate data set are converted to the third coordinate system, and calculating the relative runout between a certain stage of the rotor and the stator includes:

[0101] Step 150E: At a specific moment when the rotor unit 20 rotates, calculate the minimum distance between the tip of a single rotor blade 21 in a certain stage of the rotor and the scanning points of the stator coating 12 as the distance between the tip and the stator coating 12 at the specific moment.

[0102] Step 150F: Arrange the distances between the tip of the rotor blade 21 and the stator coating 12 at each specific moment during the rotation of the rotor unit 20 in sequence to form a set of clearance change amounts between a single rotor blade 21 and the stator coating 12.

[0103] Step 150G: Sequentially obtain the sets of clearance change amounts of all rotor blades 21 in a certain stage of the rotor.

[0104] This embodiment can conveniently obtain the clearance change amounts of all rotor blades 21 in a certain stage of the rotor relative to the stator coating 12 to measure the runout of all rotor blades 21 in the circumferential direction, providing a more accurate basis for the assembly of the rotor-stator.

[0105] In some embodiments, step 150 further includes:

[0106] Step 150H: Calculate the sets of clearance change amounts of all rotor blades 21 in all stages of the rotor.

[0107] This embodiment can obtain the sets of clearance change amounts of all rotor blades 21 in all stages of the rotor, which can reflect the runout of the rotor blades 21 in all stages of the rotor, more accurately reflect the assembly situation of the rotor, and prevent the rotor from deflecting axially.

[0108] In some embodiments, the measurement method of the present disclosure further includes:

[0109] Step 160: Calculate the change range of the working clearance between at least one stage of the rotor and the stator based on the relative runout between at least one stage of the rotor and the stator; and / or

[0110] Step 170: Calculate the relative eccentricity between the rotor and the stator according to the relative runout between at least one stage of the rotor and the stator.

[0111] In this embodiment, the change range of the working clearance between the rotor and the stator and the relative eccentricity can also reflect the assembly condition of the rotor and the stator, thereby improving the assembly accuracy.

[0112] The measurement method of the above embodiment of the present disclosure can measure the change amount of the relative clearance between the rotor and the stator during the movement of the rotor, fully consider the topography characteristics at the measurement position of the rotor and the stator, and can measure the runout of the rotor tip relative to the stator coating under the assembled state of the rotor and the stator. Moreover, it realizes the calculation of the clearance between the rotor and the stator based on the scanned points, thereby measuring the rubbing amount and rubbing state between the rotor and the stator, improving the assembly detection accuracy of the engine, and thus improving the assembly qualification rate of the engine.

[0113] Secondly, the present disclosure provides a measurement device for the relative runout of the rotor and the stator of an aeroengine, as Figure 6 shown. In some embodiments, it includes: at least three first targets, at least three second targets, a first measurement component 30, a second measurement component 40, and a controller 50.

[0114] Among them, at least three first targets are correspondingly arranged with the stator unit body 10, and are configured to establish a first coordinate system for the individual stator unit body 10; and after the stator unit body 10 and the rotor unit body 20 are assembled, a third coordinate system consistent with the first coordinate system is established. For example, at least three target installation points can be provided in the precision holes at the rear installation edge of the stator unit body 10 or by designing precision tools for installing the first targets one by one.

[0115] At least three second targets are correspondingly arranged with the rotor unit body 20, and are configured to establish a second coordinate system for the individual rotor unit body 20, and after the stator unit body 10 and the rotor unit body 20 are assembled, a fourth coordinate system consistent with the second coordinate system is established, and when the rotor unit body 20 rotates in the assembly, a dynamic rotor coordinate system of the rotor unit body 20 is established in real time based on the fourth coordinate system; for example, at least three target installation points can be provided by pasting or designing precision tools at the rear end of the rotor unit body 20, and the second targets are installed one by one.

[0116] The first measurement component 30 is configured to measure the first coordinate data set of at least one stage of the stator in the stator unit body 10 at the first mating part, where the first mating part is used to form a working clearance with the second mating part on the corresponding stage of the rotor; for example, the first measurement component 30 can be a laser scanning component, which can provide line laser and receive the light spot through a target ball.

[0117] The second measuring component 40 is configured to measure the second coordinate data set of the second mating part of at least one stage of the rotor unit body 20; for example, the second measuring component 40 can be a measuring ball head that can receive light spots.

[0118] The controller 50 is configured to convert both the first coordinate data set and the second coordinate data set to the third coordinate system according to the pose relationship between the first coordinate system and the third coordinate system, and the pose relationship between the dynamic rotor coordinate system and the third coordinate system, and calculate the relative runout between at least one stage of the rotor and the stator.

[0119] This embodiment can utilize the coordinates of the first mating part in the first coordinate system, the coordinates of the second mating part in the second coordinate system, and rotate the rotor in the assembled state. Taking the third coordinate system of the stator as the reference, the dynamic change amount of the fourth coordinate system relative to the third coordinate system can be detected in real time. This change amount is reflected in the form of target coordinates, so that the distance change relationship between the first mating part and the second mating part in the assembled state, that is, the clearance change amount between the rotor and the stator, can be obtained.

[0120] This method takes into account the assembly error between the rotor and the stator, can also measure the runout of the second mating part during the entire rotation process of the rotor unit body, and is also convenient for measuring the runout of multiple second mating parts (for example, rotor blades 21) of a certain stage of the rotor in the circumferential direction, and can also measure the mating situation between multiple stages of the rotor and the stator. Therefore, the measurement result can more objectively reflect the runout situation after the actual assembly of the rotor and the stator, and improve the accuracy of the measurement result.

[0121] The following takes the measurement and calculation of the relative runout between the ninth and tenth stages of the rotor and the stator of an aeroengine as an example to describe the process of the entire measurement method, combined with Figures 1 to 4 , the specific operation process is as shown in the figure:

[0122] 1. Objective: Measure and calculate the relative runout between the ninth and tenth stages of the compressor rotor and the stator, and finally obtain Figure 4 The relative clearance change data P9 1～q and P10 1～q (i.e., relative runout) of the tip A of each rotor blade 21 shown and the corresponding stator coating 12. Furthermore, the clearance change amount between each rotor blade 21 and the stator coating 12 on the inner wall of the stator casing 11 can be calculated, and the rubbing amount and rubbing state can be analyzed.

[0123] 2. Stator unit body measurement:

[0124] 1) Provide target installation points with precision holes on the rear mounting edge of the stator unit body 10 or design precision tools, and install the first targets one by one, and measure multiple first targets to obtain coordinates J S 1～3 (at least three first targets are installed) to establish the first coordinate system Oxyz ( J S 1～3 ) as shown in Figure 2 ;

[0125] 2) Using the scanning measurement method, obtain the coordinates of the scanning points on the conical surface of the two-stage coating shown in Figure 2 and record them as J P9J 1～m,1～n and J P10J 1～m,1～n . Obtain the coordinates of the scanning points in the first coordinate system. By analogy, the scanning coordinates of the stator coatings 12 of other stages of stators can be obtained to form the first coordinate dataset.

[0126] 3. Measurement of the rotor unit:

[0127] 1) Stick or design precision tools at the rear end of the rotor unit 20 to provide target installation points, and install the second targets one by one. Measure the target coordinates d R 1～3 and establish the second coordinate system O uvw ( d R 1～3 ) as shown in Figure 3 .

[0128] 2) Using the spherical measurement method, obtain the coordinates of the tip A of each rotor blade 21 of the two-stage rotor in the second coordinate system d P9D 1～q and d P10D 1～q (q represents that there are q rotor blades 21 at this stage). By analogy, the coordinates of the tips of the rotor blades 21 of other stages can be obtained to form the second coordinate dataset.

[0129] 4. Measurement after the engine rotor unit 20 and the stator unit 10 are assembled:

[0130] 1) Install the target by using the precision holes on the rear installation edge of the stator unit 10 or designing precision tools to provide target installation points, and install the first targets one by one. Use the coordinates of each first target z S 1～3 to establish the third coordinate system O xyz ( z S 1～3 ) in the combined state of the rotor and stator as shown in Figure 3 . This third coordinate system is consistent with the first coordinate system.

[0131] 2) Stick or design precision tool placement points at the rear end of the rotor unit 20, and install the second targets one by one. Use the measured coordinates of the second targets Z R 1～3, establish the fourth coordinate system O in the combined state of the rotating and stationary components uvw ( Z R 1～3 ).

[0132] 3) Rotate the rotor unit 20 and monitor in real time the coordinates of the second target at the rear end of the rotor unit 20 Z Ri 1～3 (expressed as the target coordinates of the rotor coordinate system established at the i-th moment), and establish the dynamic rotor coordinate system Oi uvw ( Z R 1～3 ).

[0133] Note: The method and sequence for establishing the coordinate system in the assembled state must be consistent with those of the rotor unit 20 and the stator unit 10. When the rotor unit 20 rotates, the coordinate information of the three targets can be collected in real time and synchronized, and then the coordinate system is established.

[0134] 5. Algorithm for calculating the relative runout data or relative clearance change amount between the rotor and stator:

[0135] 1) Transfer the scan point coordinates in the first coordinate system O xyz ( J S 1～3 ) to the third coordinate system O in the assembly xyz ( z S 1～3 ). Let T0 be the first pose matrix between the first coordinate system O xyz ( J S 1～3 ) and the third coordinate system O xyz ( z S 1～3 ):

[0136] T0 = F(O xyz ( z S 1～3 ), O xyz ( J S 1～3 )) (1)

[0137] Z P9J 1～m,1～n = T0 · J P9J 1～m,1～n (2)

[0138] Z P10J 1～m,1～n = T0 · J P10J 1～m,1～n (3)

[0139] 2) Obtain the dynamic rotor coordinate system Oi uvw ( ZR 1～3 )With respect to the third coordinate system O in the assembly xyz ( z S 1～3 )Pose relationship:

[0140] T1i = F(O xyz ( z S 1～3 )·Oi uvw ( Z R 1～3 )) (4)

[0141] 3) Next, taking the relative runout of the tip A of the x-th rotor blade 21 of the 9th-stage rotor with respect to the stator coating 12 as an example for calculation, the relative runout data set P9 of the tip A with respect to the stator coating 12 is obtained x :

[0142] P9 x = Set(min(|(T1i * d P9D x ) - Z P9J 1～m,1～n |)) (5)

[0143] In the formula, |(T1i * d P9D x ) - Z P9J x,1～n | represents the distance between two points;

[0144] min(|(T1i * d P9D x ) - Z P9J 1～m,1～n |) represents selecting the minimum distance among the distances between the tip A of the rotor blade and all the scanned points of the stator coating 12 as the distance between the tip A of the rotor blade at the current i-th position of the dynamic rotor coordinate system and the stator coating 12;

[0145] Set(min(|(T1i * d P9D x ) - Z P9J 1～m,1～n |)) means putting the distances between the tip A of the rotor blade and the stator coating 12 generated by all the dynamic rotor coordinate systems into a set in the order of positions. This set is the data set of the relative clearance change amount between the tip A of the x-th blade of the 9th-stage rotor and the stator coating 12, and it is also the runout data set.

[0146] 4) According to formula (5), the relative runout data sets of the tip A of all the rotor blades 21 of the 9th and 10th stages with respect to the stator coating 12 can be obtained, that is, the relative clearance data sets P9 1～q and P10 1～q .

[0147] 6. Rotor-stator radial clearance calculation algorithm:

[0148] According to P9 1～q and P10 1～q the change range of the rotor-stator radial clearance can be calculated as min(P9 1～q ) ~ max(P9 1～q ) and min(P10 1～q ) ~ max(P10 1～q ).

[0149] 7. Using this method, the change data set and clearance value of the radial clearance between the rotor labyrinth 22 and the stator honeycomb 14 can be obtained. At the same time, the relative eccentricity between the rotor and the stator can be obtained using this runout value.

[0150] The above has introduced in detail a method and device for measuring the relative runout between the rotor and the stator of an aeroengine provided by the present disclosure. Specific embodiments are used herein to elaborate on the principle and implementation manner of the present disclosure. The description of the above embodiments is only used to help understand the method and its core idea of the present disclosure. It should be noted that for those of ordinary skill in the art in this technical field, without departing from the principle of the present disclosure, several improvements and modifications can still be made to the present disclosure, and these improvements and modifications also fall within the protection scope of the claims of the present disclosure.

Claims

1. A method for measuring the relative runout between the rotating and stationary components of an aeroengine, characterized in that Including: Establish a first coordinate system for a separate stator unit body (10), and measure a first coordinate data set of at least one stage of the first mating part of the stator in the stator unit body (10), wherein the first mating part is used to form a working gap with a second mating part on the corresponding stage of the rotor; Establish a second coordinate system for a separate rotor unit body (20), and measure a second coordinate data set of the second mating part of at least one stage of the rotor in the rotor unit body (20); Assemble the stator unit body (10) and the rotor unit body (20), establish a third coordinate system for the stator unit body (10) that is consistent with the first coordinate system, and establish a fourth coordinate system for the rotor unit body (20) that is consistent with the second coordinate system; Rotate the rotor unit body (20) in the assembly, and based on the fourth coordinate system, establish a dynamic rotor coordinate system of the rotor unit body (20) in real time; According to the pose relationship between the first coordinate system and the third coordinate system, and the pose relationship between the dynamic rotor coordinate system and the third coordinate system, convert both the first coordinate data set and the second coordinate data set to the third coordinate system, and calculate the relative runout amount between at least one stage of the rotor and the stator.

2. The method for measuring the relative runout of the rotating and static parts of an aeroengine according to claim 1, wherein: Establishing a first coordinate system for the stator unit body (10) includes: Set a reference hole or a reference installation tooling on the stator unit body (10) to provide at least three target installation points outside the stator unit body (10); Install first targets at the at least three target installation points one by one; Measure the coordinates of at least three first targets, and establish the first coordinate system; Alternatively, establishing a second coordinate system for the rotor unit body (20) includes: Set a reference hole or a reference installation tooling on the rotor unit body (20) to provide at least three target installation points outside the rotor unit body (20); Install second targets at the at least three target installation points one by one; Measure the coordinates of at least three second targets to establish the second coordinate system.

3. The method for measuring the relative runout between the rotating and stationary components of an aeroengine according to claim 2, wherein Rotating the rotor unit body (20) in the assembly and establishing a dynamic rotor coordinate system of the rotor unit body (20) in real time based on the fourth coordinate system includes: In the assembly, use the coordinates of at least three second targets corresponding to the fourth coordinate system as the initial position; Rotate the rotor unit body (20), and measure the coordinates of at least three second targets in real time to establish a dynamic rotor coordinate system of the rotor unit body (20).

4. The method for measuring the relative jump between the rotating and stationary components of an aeroengine according to claim 1, wherein The first mating part is a stator coating (12), the stator coating (12) is conical, and measuring a first coordinate data set of at least one stage of the first mating part of the stator in the stator unit body (10) includes: Select different cross-sections on the stator coating (12) of at least one stage of the stator; Measure the coordinates of multiple circumferential points on the inner surface of the stator coating (12) by using the laser scanning method on each cross-section; Form the first coordinate data set with the coordinates of each point on different cross-sections.

5. The method for measuring the relative runout between the rotating and stationary components of an aeroengine according to claim 1, wherein The second mating part is the rotor blade (21). The second coordinate data set for measuring the second mating part of at least one stage of the rotor includes: Finding the tip positions of the rotor blades (21) in the circumferential direction of at least one stage of the rotor using a spherical measurement method, and obtaining the coordinates of the tip positions of the rotor blades (21) to form the second coordinate data set.

6. The method for measuring the relative runout between the rotating and stationary components of an aeroengine according to claim 1, wherein According to the pose relationship between the first coordinate system and the third coordinate system, and the pose relationship between the dynamic rotor coordinate system and the third coordinate system, converting the first coordinate data set and the second coordinate data set to the third coordinate system includes: Calculating a first pose matrix between the first coordinate system and the third coordinate system; Calculating a second pose matrix between the dynamic rotor coordinate system and the third coordinate system; Multiplying the first coordinate data set by the first pose matrix to convert it into a data set in the third coordinate system; Multiplying the second coordinate data set by the second pose matrix to convert it into a data set in the third coordinate system.

7. The method for measuring the relative runout between the rotating and stationary components of an aeroengine according to claim 1, characterized in that, The first mating part is the stator coating (12), and the second mating part is the rotor blade (21). Converting the first coordinate data set and the second coordinate data set to the third coordinate system and calculating the relative runout between a certain stage of the rotor and the stator includes: At a specific moment when the rotor unit (20) rotates, calculating the minimum distance between the tip of a single rotor blade (21) in a certain stage of the rotor and the scanning points of the stator coating (12) as the distance between the tip and the stator coating (12) at the specific moment; Forming a set of clearance change amounts between the tip of a single rotor blade (21) and the stator coating (12) at each specific moment during the rotation of the rotor unit (20) in sequence; Successively obtaining the sets of clearance change amounts of all the rotor blades (21) in a certain stage of the rotor.

8. The method for measuring the relative runout between the rotating and stationary components of an aeroengine according to claim 7, characterized in that, Further includes: Calculating the sets of clearance change amounts of all the rotor blades (21) in all stages of the rotor.

9. The method for measuring the relative runout between the rotating and stationary components of an aeroengine according to claim 1, wherein, Further includes: Calculating the change range of the working clearance between the at least one stage of the rotor and the stator according to the relative runout between the at least one stage of the rotor and the stator; and / or Calculating the relative eccentricity between the rotor and the stator according to the relative runout between the at least one stage of the rotor and the stator.

10. The method for measuring the relative runout between the rotating and stationary components of an aeroengine according to claim 1, wherein, The first mating part is the stator coating (12), and the second mating part is the rotor blade (21); and / or the first mating part is the stator honeycomb (14), and the second mating part is the rotor labyrinth (22).

11. An aero-engine stator-rotor relative runout measuring device, characterized in that Includes: At least three first targets, correspondingly arranged with the stator unit (10), configured to establish a first coordinate system for the separate stator unit (10); and after the stator unit (10) and the rotor unit (20) are assembled, establishing a third coordinate system consistent with the first coordinate system; At least three second targets, which are correspondingly arranged with respect to the rotor unit body (20), are configured to establish a second coordinate system for the individual rotor unit body (20), and after the stator unit body (10) and the rotor unit body (20) are assembled, establish a fourth coordinate system consistent with the second coordinate system, and when the rotor unit body (20) is rotated in the assembly, establish a dynamic rotor coordinate system of the rotor unit body (20) in real time based on the fourth coordinate system; A first measuring component (30), which is configured to measure a first coordinate data set of a first mating part of at least one stage of stator in the stator unit body (10), wherein the first mating part is used to form a working gap with a second mating part on the corresponding stage of rotor; A second measuring component (40), which is configured to measure a second coordinate data set of the second mating part of at least one stage of rotor of the rotor unit body (20); and A controller (50), which is configured to convert both the first coordinate data set and the second coordinate data set to the third coordinate system according to the pose relationship between the first coordinate system and the third coordinate system, and the pose relationship between the dynamic rotor coordinate system and the third coordinate system, and calculate the relative runout amount between at least one stage of rotor and stator.

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