Method for measuring coaxiality of rotor fulcrum in whole engine assembly state of aero-engine

Abstract

The application relates to a method for measuring the coaxiality of a rotor support point of an aero-engine, comprising the following steps: step one, establishing a reference coordinate system with the first support point in the first casing as the 0 point and the axial direction of the aero-engine as the x axis; installing a first target, a second target and a third target outside the first casing and measuring the coordinates of the three targets in the reference coordinate system; step two, assembling the aero-engine into a whole machine, installing a fourth target on the first support point and a fifth target on the second support point; step three, measuring the positions of the first target, the second target and the third target outside the casing of the aero-engine to reacquire the reference coordinate system; and step four, measuring the coordinates of the second support point in the reference coordinate system and calculating the coaxiality of the first support point and the second support point according to the position of the second support point in the reference coordinate system.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engine detection, in particular to a method for measuring the coaxiality of a rotor fulcrum in the whole assembly state of an aero-engine. BACKGROUND

[0002] In the assembly process of an aero-engine, an important detection data is the coaxiality or concentricity of the two fulcrums of the engine rotor 2. For example, the coaxiality between the two fulcrums supporting the compressor rotor before and after, as shown in the figure, the coaxiality between the two fulcrums refers to the deflection of the second fulcrum B fixedly installed in the turbine interstage casing 2 relative to the first fulcrum A fixedly installed in the fan casing 1. The purpose of obtaining this type of detection item (fulcrum coaxiality) is to obtain the inclination state of the rotating axis of the rotor 2 relative to the stator casing after the rotor 2 is installed, so as to facilitate the subsequent analysis of the flow channel between the rotor and the stator, the analysis of the rotor-stator rubbing amount and the assembly performance analysis, etc., and therefore the detection of the fulcrum concentricity is particularly necessary. Figure 1

[0003] The current method for detecting this position in the field of aero-engines is to not assemble the engine rotor, and to assemble all the stator casings together, as shown in the figure, the stator casing assembly is installed to the precision turntable, and the coaxiality P of the fulcrum B is measured by taking A1 and A2 of the fulcrum A as the reference. However, this method has the following disadvantages: Figure 2

[0004] 1) The stator casing assembly state is inconsistent with the whole assembly state of the engine;

[0005] 2) The stator casing assembly state does not consider the installation state of the fulcrum bearing and the influence of the bearing radial clearance on the support state;

[0006] 3) The influence of the rotor assembly on the coaxiality of the fulcrum is not considered. SUMMARY

[0007] The present application aims to provide a method for measuring the coaxiality of the rotor fulcrum in the whole assembly state of an aero-engine, so as to improve the problem that the result of the coaxiality measurement of the rotor fulcrum is different from that in the whole assembly state in the related art.

[0008] According to an aspect of an embodiment of the present application, a method for measuring the coaxiality of the rotor fulcrum of an aero-engine is provided, comprising:

[0009] Step one, taking the first fulcrum in the first casing as the 0 point and taking the axis direction of the aero-engine as the x axis to establish a reference coordinate system, installing a first target, a second target and a third target outside the first casing, and measuring the coordinates of the three targets in the reference coordinate system;

[0010] ​​Step two, assembling the aero-engine into an entire machine, installing the fourth target on the first fulcrum and installing the fifth target on the second fulcrum, wherein assembling the aero-engine into an entire machine comprises installing a first end of a rotor of the aero-engine on the first fulcrum and installing a second end of the rotor on the second fulcrum in a second casing;

[0011] Step three, measuring the positions of the first target, the second target and the third target outside the casing of the aero-engine to reacquire the reference coordinate system;

[0012] Step four, measuring the coordinates of the second fulcrum in the reference coordinate system and calculating the coaxiality of the first fulcrum and the second fulcrum according to the position of the second fulcrum in the reference coordinate system.

[0013] In some embodiments, in step 3, the positions of the first target, the second target and the third target are measured by a first measuring device located outside the casing of the aero-engine and between the first end and the second end of the rotor.

[0014] In some embodiments, in step four,

[0015] the position of the second fulcrum is measured by a second measuring device located outside the casing and at the second end of the rotor,

[0016] the position of the second fulcrum measured by the second measuring device is converted into coordinates in the reference coordinate system through the relative positional relationship of the first measuring device and the second measuring device.

[0017] In some embodiments, step four further comprises:

[0018] the position of the first fulcrum is measured by a third measuring device located outside the casing and at the first end of the rotor,

[0019] the position of the first fulcrum measured by the third measuring device is converted into coordinates in the reference coordinate system through the relative positional relationship of the first measuring device and the third measuring device.

[0020] In some embodiments,

[0021] the measuring of the position of the second fulcrum by the second measuring device comprises real-time detection of the circumferential scanning points of Q2 during rotation of the rotor, denoted as Q2 1～n ;

[0022] the measuring of the position of the first fulcrum by the third measuring device comprises real-time detection of the circumferential scanning points of Q1 during rotation of the rotor, denoted as Q1 1～n .

[0023] In some embodiments, the calculation of the coaxiality of the first fulcrum and the second fulcrum according to the position of the second fulcrum in the reference coordinate system comprises:

[0024] The line vector of the line connecting the first fulcrum and the second fulcrum can be obtained by using an axis fitting algorithm: S = Fit( Z Q1 1～n , Z Q2 1～n ), wherein Fit() is a fitting algorithm, and S is a line vector parameter of the line connecting the first fulcrum and the second fulcrum in the reference coordinate system;

[0025] The coaxiality Δ of the fulcrum B relative to the fulcrum A is calculated:

[0026] α = Cross(S, [0, 0, 1] T )

[0027] Δ = h·sin(α).

[0028] In some embodiments, the first target, the second target and the third target.

[0029] By applying the technical solution of the present application, the coaxiality of the first fulcrum and the second fulcrum is measured after the engine is completely assembled, thereby improving the problem that the coaxiality measurement result of the rotor fulcrum in the related art is different from the assembly state of the whole machine.

[0030] Other features and advantages of the present application will become apparent from the following detailed description of exemplary embodiments thereof, with reference to the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0031] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the related art, the drawings needed to be used in the embodiments or the related art description will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0032] Figure 1 A structural schematic diagram of an existing aviation engine is shown;

[0033] Figure 2 A concentricity detection method schematic diagram of two fulcrums of an existing aviation engine for supporting a rotor is shown;

[0034] Figure 3 A structural schematic diagram of establishing a reference coordinate system in a rotor fulcrum coaxiality measurement method of an embodiment of the present application is shown;

[0035] Figure 4 A detector device layout diagram in a rotor fulcrum coaxiality measurement method of an embodiment of the present application is shown;

[0036] Figure 5 A diagram showing the coaxiality of a rotor pivot point of an embodiment of the application;

[0037] Figure 6 A flowchart showing a method of measuring the coaxiality of a rotor pivot point of an embodiment of the application. DETAILED DESCRIPTION

[0038] The technical solutions in the embodiments of the application will be apparently and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only a part of the embodiments of the application, rather than all the embodiments of the application. The following description of at least one exemplary embodiment is only illustrative in nature and in no way limits the application and its application or use. Based on the embodiments in the application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the scope of protection of the application.

[0039] The embodiment provides a method for measuring the coaxiality of a rotor pivot point of an aero-engine. As shown in the figure, Figure 6 the method for measuring the coaxiality of a rotor pivot point of an aero-engine comprises:

[0040] Step one, taking the first pivot point A in the first casing 1 as the 0 point and taking the axial direction of the aero-engine as the x axis to establish a reference coordinate system, installing a first target, a second target and a third target outside the first casing 1, and measuring the coordinates of the three targets in the reference coordinate system, referring to Figure 3 ;

[0041] Step two, assembling the aero-engine into a whole machine, installing a fourth target Q1 on the first pivot point A and installing a fifth target Q2 on the second pivot point B, wherein assembling the aero-engine into a whole machine comprises installing the first end of the rotor 3 of the aero-engine on the first pivot point A and installing the second end of the rotor 3 on the second pivot point B in the second casing 2, referring to Figure 4 ;

[0042] Step three, measuring the positions of the first target, the second target and the third target outside the casing of the aero-engine to re-establish a reference coordinate system. In some embodiments, the new coordinate system is different from the original coordinate system, and the positions of the first target, the second target and the third target in the new coordinate system and the original coordinate system can be used to determine the positions of the original points of the new coordinate system and the original coordinate system.

[0043] Step four, measuring the coordinates of the second pivot point B in the reference coordinate system, and calculating the coaxiality of the first pivot point A and the second pivot point B according to the position of the second pivot point B in the reference coordinate system, referring to Figure 5 .

[0044] In step 3, the positions of the first target, the second target and the third target are measured by the first measuring device 5 located outside the casing of the aero-engine and between the first end and the second end of the rotor 3.

[0045] In step 4, first, the position of the second fulcrum B is measured by the second measuring device 6 located outside the casing and at the second end of the rotor 3, and then the position of the second fulcrum B measured by the second measuring device 6 is converted into coordinates in the reference coordinate system through the relative position relationship between the first measuring device 5 and the second measuring device 6.

[0046] Step 4 also includes measuring the position of the first fulcrum A by the third measuring device 4 located outside the casing and at the first end of the rotor 3,

[0047] The position of the first fulcrum A measured by the third measuring device 4 is converted into coordinates in the reference coordinate system through the relative position relationship between the first measuring device 5 and the third measuring device 4.

[0048] The second measuring device 6 measures the position of the second fulcrum B includes real-time detection of the circumferential scanning point of the Q2 point during the rotation of the rotor, denoted as Q2 1～n ;

[0049] The third measuring device 4 measures the position of the first fulcrum A real-time detects the circumferential scanning point of the Q1 point during the rotation of the rotor, denoted as Q1 1～n .

[0050] According to the position of the second fulcrum B in the reference coordinate system, the coaxiality of the first fulcrum A and the second fulcrum B is calculated, including:

[0051] Using the axis fitting algorithm, the line vector of the connecting line of the first fulcrum A and the second fulcrum B can be obtained: S = Fit( Z Q1 1～n , Z Q2 1～n ), wherein Fit() is a fitting algorithm, and S is a line vector parameter of the connecting line of the first fulcrum A and the second fulcrum B in the reference coordinate system;

[0052] The coaxiality Δ of the fulcrum B relative to the fulcrum A is calculated:

[0053] α = Cross(S, [0, 0, 1] T ) 2

[0054] Δ = h·sin(α).

[0055] The measurement method of the fulcrum axis of the engine rotor in the whole assembly state is introduced by taking the implementation process of the high-pressure rotor fulcrum axis as an example, as follows:

[0056] 1. Use equipment such as a laser tracker or iGPS to establish a reference coordinate system at position A, the first pivot point of the fan casing. Figure 3 As shown, in order to enable this coordinate system to be identified outside the casing, at least three fixed targets are installed outside the first casing. J P 1～3 Measure the target coordinates, and then quickly establish this reference coordinate system O by identifying the target point coordinates of the external target. xyz ( J P 1～3 ).

[0057] 2. With the engine in its complete state, attach at least one fixed target Q1 and Q2 at the front and rear ends of the rotor, respectively. Figure 4 As shown, if it is difficult to directly paste the target at this position, an adapter tool can be designed and manufactured. The adapter tool is required to be fixed together with the rotor. During the rotation of the rotor, there should be no relative movement between the tool and the rotor. Then, the target is pasted onto the adapter tool.

[0058] 3. Establish a survey station, in Figure 4 The first measuring device 5, the second measuring device 6, and the third measuring device 4 are set up at the locations shown. The three measuring devices can monitor each other and acquire the data collected by each other.

[0059] 4. First measuring device 5 measures the overall assembly status of the machine. First casing 1 has at least three fixed targets mounted on its exterior. Z P1~3, re-establish the reference coordinate system O xyz ( Z P 1～3 ).

[0060] 5. Rotate Figure 4 The rotor shown is monitored in real time by measuring station U, with point Q1 being the circumferential scanning point during rotor rotation, denoted as Q1. 1～n Measurement station W detects the circumferential scanning point Q2 in real time during rotor rotation, denoted as Q2. 1～n Using the coordinate system established by measuring station V and the positions of measuring stations U and W monitored by measuring station V, all Q1 and Q2 scanning points can be transformed to the reference coordinate system O. xyz ( Z P 1～3 You can get it by following the instructions below. Z Q1 1～n and Z Q2 1～n .

[0061] 5. Using the axis fitting algorithm, the axis line vector can be obtained:

[0062] S = Fit( Z Q1 1～n ,Z Q2 1～n )

[0063] In the formula, Fit() is a fitting algorithm, which can be solved by the following formula

[0064] S is the linear vector parameter of the axis in the reference coordinate system.

[0065]

[0066] In the formula, f1, f2, g1, g2 are least squares to be solved

[0067] O2 is the center vector point coordinate formed by the rear end rotation

[0068] O1 is the center vector point coordinate formed by the front end rotation

[0069] 6. The support point axis of the whole machine assembly state can be obtained by formula 1, and the coaxiality Δ of the support point B relative to the support point A is calculated by using the support point axis:

[0070] α=Cross(S,[0,0,1] T )

[0071] △=h·sin(α)

[0072] In the formula, α is the included angle between the support point axis and the z-axis of the reference coordinate system, and see Figure 5 ;

[0073] h is the axial distance between the two support points, see Figure 5 .

[0074] 7. All targets are removed, and the measurement is completed.

[0075] Solution / technical innovation point:

[0076] 1. The targets are pasted outside the unit body (such as a fan case) at the reference support point, a coordinate system is established at the reference support point, and the position detection of the reference coordinate system is led out to the outside of the fan case;

[0077] 2. The rotation center of the front end and the rear end of the rotor is measured at the same time, and the rotation axis of the engine is obtained by using the algorithm;

[0078] 3. The measurement data of the front and rear rotation centers of the rotor are in the reference support point coordinate system, and the coaxiality of the front and rear support points can be obtained by using the algorithm.

[0079] The beneficial effects of the present application:

[0080] 1. A method for providing the coaxiality of the front and rear support points in the formal assembly state is provided, which breaks the shackles of the traditional method;

[0081] 2. The installation state of the bearing and the radial clearance of the bearing are comprehensively considered, and the obtained result is more in line with the actual situation;

[0082] 3. The influence factor of the assembly state of the rotor unit on the coaxiality of the fulcrum is comprehensively considered;

[0083] 4. The assembly quality evaluation precision of the engine is improved;

[0084] 5. Effective data of engine data analysis is provided.

[0085] The above are only exemplary embodiments of the present application, and are not used to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A method for measuring the coaxiality of the rotor support of an aero-engine, characterized in that, include: Step 1: Establish a reference coordinate system with the first fulcrum (A) inside the first casing (1) as the 0 point and the axis of the aero-engine as the x-axis. Install the first target, the second target and the third target on the outside of the first casing (1) and measure the coordinates of the three targets in the reference coordinate system. Step 2: Assemble the aircraft engine into a complete machine, install the fourth target (Q1) on the first fulcrum (A), and install the fifth target (Q2) on the second fulcrum (B). The assembly of the aircraft engine into a complete machine includes installing the first end of the rotor (3) of the aircraft engine on the first fulcrum (A) and installing the second end of the rotor (3) on the second fulcrum (B) inside the second casing (2). Step 3: Measure the positions of the first target, the second target, and the third target outside the casing of the aero-engine to re-establish the reference coordinate system; Step four: Measure the coordinates of the second fulcrum (B) in the reference coordinate system, and calculate the coaxiality of the first fulcrum (A) and the second fulcrum (B) based on the position of the second fulcrum (B) in the reference coordinate system.

2. The method for measuring the coaxiality of the rotor support of an aero-engine according to claim 1, characterized in that, In step 3, the positions of the first target, the second target and the third target are measured using a first measuring device (5) located outside the casing of the aero-engine and between the first end and the second end of the rotor (3).

3. The method for measuring the coaxiality of the rotor support of an aero-engine according to claim 2, characterized in that, In step four, The position of the second fulcrum (B) is measured using a second measuring device (6) located outside the casing and at the second end of the rotor (3). By using the relative positional relationship between the first measuring device (5) and the second measuring device (6), the position of the second fulcrum (B) measured by the second measuring device (6) is converted into coordinates in the reference coordinate system.

4. The method for measuring the coaxiality of the rotor support of an aero-engine according to claim 3, characterized in that, Step four also includes: The position of the first fulcrum (A) is measured using a third measuring device (4) located outside the casing and at the first end of the rotor (3). By using the relative positional relationship between the first measuring device (5) and the third measuring device (4), the position of the first fulcrum (A) measured by the third measuring device (4) is converted into coordinates in the reference coordinate system.

5. The method for measuring the coaxiality of the rotor support point of an aero-engine according to claim 4, characterized in that, The second measuring device (6) measures the position of the second fulcrum (B) by real-time detection of the circumferential scanning point Q2 during rotor rotation, denoted as Q2. 1~n ; The third measuring device (4) measures the position of the first fulcrum (A) and detects the circumferential scanning point Q1 during the rotor rotation in real time, denoted as Q1. 1~n .

6. The method for measuring the coaxiality of the rotor support point of an aero-engine according to claim 5, characterized in that, The calculation of the coaxiality of the first support point (A) and the second support point (B) based on the position of the second support point (B) in the reference coordinate system includes: Using the axis fitting algorithm, the line vector connecting the first fulcrum (A) and the second fulcrum (B) can be obtained: S = Fit( Z Q1 1~n , Z Q2 1~n In the formula, Fit() is the fitting algorithm, and S is the line vector parameter of the line connecting the first support point (A) and the second support point (B) in the reference coordinate system. Calculate the coaxiality Δ of fulcrum B relative to fulcrum A: α=Cross(S,[0,0,1] T ) △ = h·sin(α).

7. The method for measuring the coaxiality of the rotor support of an aero-engine according to claim 1, characterized in that, in, The first target, the second target, and the third target.

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