Device and method for measuring abrasion loss of working blade of low-pressure turbine

Abstract

The invention provides a low-pressure turbine working blade abrasion loss measuring device and method, and the device comprises a pedestal, a movable blade fixing seat mechanism is fixed on the pedestal, and a tenon of a to-be-measured blade is fixed on the movable blade fixing seat mechanism and extends towards the exterior of the pedestal; the measurement fixing mechanism is mounted on the base and is arranged opposite to the movable blade fixing seat mechanism, and the measurement fixing mechanism can move along the base; the measuring device is installed on the measuring fixing mechanism, and the blade tip of the blade to be measured is aligned with the measuring device; the adjusting mechanism is installed on the movable blade fixing seat mechanism and is used for adjusting the tenon fixation degree of the blade to be measured. The measuring tool has high universality, and the process cost can be effectively reduced. The blade tip abrasion loss of the movable blade is indirectly evaluated in a polar radius measuring mode, the polar radius of each angle of the movable blade is obtained, and therefore more state data of the engine can be analyzed.

Description

Technical Field

[0001] The invention relates to the field of engine assembly, and in particular to a device and a method for measuring the wear of a low-pressure turbine working blade. Background Art

[0002] Figure 1 Schematic diagram of the engine low-pressure turbine structure.

[0003] like Figure 1 As shown, the low-pressure turbine is composed of a multi-stage rotor and a multi-stage stator, including a first-stage disk 10 to an N-stage disk 20, and a double-layer comb 31 is provided on the rotor blade 30. A stepped honeycomb 41 is provided on the stator outer ring 40, and the comb 31 and the honeycomb 41 form a blade tip sealing structure, which can effectively prevent gas leakage and improve the work efficiency of the low-pressure turbine.

[0004] When the engine is working, the comb teeth 31 are embedded in the honeycomb 41, and the blade tips of the moving blades 30 will be worn during the rotation of the rotor. Therefore, after the engine has been working for a certain period of time, the wear amount of the blade tips of each level of moving blades needs to be measured, and the blades need to be replaced according to the wear amount.

[0005] Since the blades of each stage of the low-pressure turbine are of different lengths and numerous, the accuracy of blade positioning directly affects the measurement results of blade tip wear. The versatility of the measuring tool can directly reduce process costs.

[0006] The wear measurement of low-pressure turbine blades in the prior art has the following problems:

[0007] 1. Only applicable to the measurement of the polar radius of a single blade.

[0008] Second, the same measuring tool cannot measure the wear of different stages of low-pressure turbine blades, and the process cost is high.

[0009] In view of this, the inventor of the present application has designed a low-pressure turbine blade wear measurement device and a measurement method in order to overcome the above-mentioned technical problems. Summary of the invention

[0010] The technical problem to be solved by the present invention is to overcome the defects of low-pressure turbine blade wear accuracy and high process cost in the prior art, and to provide a low-pressure turbine blade wear measurement device and method.

[0011] The present invention solves the above technical problems through the following technical solutions:

[0012] A low-pressure turbine blade wear measurement device, characterized in that the low-pressure turbine blade wear measurement device comprises: a base,

[0013] A moving blade fixing seat mechanism, wherein the moving blade fixing seat mechanism is fixed on the base, and a tenon of a blade to be measured is fixed on the moving blade fixing seat mechanism and extends toward the outside of the base;

[0014] A measuring and fixing mechanism, which is installed on the base, arranged opposite to the moving blade fixing seat mechanism, and can move along the base;

[0015] A measuring device, wherein the measuring device is mounted on the measuring fixture, and the tip of the blade to be measured is aligned with the measuring device;

[0016] An adjusting mechanism is installed on the moving blade fixing seat mechanism and is used to adjust the tenon fixing degree of the blade to be tested.

[0017] According to one embodiment of the present invention, the moving blade fixing seat mechanism includes a blade adapter seat and a moving blade fixing seat, the blade adapter seat is fixed on the base, and the moving blade fixing seat is fixed on the blade adapter seat.

[0018] According to one embodiment of the present invention, the adjustment mechanism includes an adjusting bolt, a tenon is provided on the outer wall surface of the moving blade fixing seat, the adjusting bolt passes through the tenon from the inner wall surface of the moving blade fixing seat, the tenon of the blade to be measured is installed in the tenon, and the contact between the tenon and the tenon is adjusted by the adjusting bolt.

[0019] According to one embodiment of the present invention, the measuring and fixing mechanism comprises a plurality of guide rods, an engine axis simulation seat and a rotating rod, the two ends of the guide rods are respectively fixed above the base through a first support, the engine axis simulation seat is penetrated on the guide rods and can move along the guide rods;

[0020] One end of the rotating rod is connected to the engine axis simulation seat, and the other end extends toward a direction close to the moving blade fixing seat mechanism.

[0021] According to one embodiment of the present invention, the measuring and fixing mechanism further comprises a screw, which is arranged on the base via a second support and penetrates into the engine axis simulation seat to lock the engine axis simulation seat.

[0022] According to an embodiment of the present invention, the measuring device is mounted on the other end of the rotating rod and is located close to the tip of the blade to be measured.

[0023] According to one embodiment of the present invention, the measuring device is a micrometer.

[0024] According to an embodiment of the present invention, the micrometer is mounted on the rotating rod via a fixed gauge clamp.

[0025] The present invention also provides a method for measuring the wear of a low-pressure turbine blade, which is characterized in that the method adopts the low-pressure turbine blade wear measuring device as described above, and the method comprises the following steps:

[0026] S1. Place the Nth-stage moving blade on the moving blade fixing seat, and adjust the bolts so that the tenon and the tenon groove of the blade to be tested coincide with each other in theoretical contact center;

[0027] S2, rotating the screw to adjust the engine axis simulation seat to the theoretical axis position of the blade of this stage under the engine working state (Kn=Ln+a);

[0028] S3. Adjust the measuring device so that the distance between the measuring device and the rotation axis is equal to the theoretical polar radius of the working blade of this stage;

[0029] S4. The measuring device is reset to zero and the fixing mechanism of the measuring device is rotated so that the measuring device sweeps along the comb tooth cylindrical surface of the blade tip of the blade to be measured. The displayed value of the measuring device is the blade tip wear amount.

[0030] According to one embodiment of the present invention, the step S4 further includes the following steps:

[0031] S5. Replace the blade to be tested, and make the tenon of the blade to be tested fully contact with the tenon groove of the moving blade fixing seat by adjusting the bolt. The displayed change of the measuring device is the tip wear amount of the blade to be tested.

[0032] According to one embodiment of the present invention, the step S5 further includes the following steps:

[0033] S6. Recalibrate the measuring device on another grate tooth of the blade at the same level using a standard blade, and repeat the above steps S1 to S5 to complete the wear measurement of all blades at this level.

[0034] The positive and progressive effects of the present invention are:

[0035] The low-pressure turbine blade wear measurement device and method of the present invention have the following advantages:

[0036] 1. The measuring tool has high versatility and can effectively reduce process costs.

[0037] Second, by measuring the polar radius, the tip wear of the moving blades can be indirectly evaluated, and the polar radius of the moving blades at various angles can be obtained, thereby analyzing more status data of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always represent the same features, wherein:

[0039] Figure 1 Schematic diagram of the engine low-pressure turbine structure.

[0040] Figure 2 It is a stereoscopic diagram of the wear measurement device for low-pressure turbine working blades of the present invention.

[0041] Figure 3 It is a front view of the low-pressure turbine working blade wear measurement device of the present invention.

[0042] Figure 4 It is a stereoscopic view of the low-pressure turbine working blade wear measurement device of the present invention in a measuring state.

[0043] Figure 5 It is a front view of the low-pressure turbine working blade wear measurement device of the present invention in the measuring state.

[0044] Figure 6 for Figure 5 Longitudinal section view of .

[0045] Figure 7 It is a schematic diagram of adjusting the blade polar radius in the tenon groove of the low-pressure turbine working blade wear measurement device of the present invention.

[0046] [Reference Signs]

[0047] Level 10

[0048] N-level disk 20

[0049] Rotor blades 30

[0050] Comb teeth 31

[0051] Outer ring 40

[0052] Honeycomb 41

[0053] Base 100

[0054] Moving blade fixing seat mechanism 200

[0055] Measuring fixture 300

[0056] Measuring device 400

[0057] Adjustment mechanism 500

[0058] Blade to be tested 600

[0059] Tenon 610

[0060] Tip 620

[0061] Blade adapter 210

[0062] Moving blade fixing seat 220

[0063] Adjusting bolt 510

[0064] Mortise and tenon 221

[0065] Guide rod 310

[0066] Engine axis simulation seat 320

[0067] Rotating rod 330

[0068] The first support 311

[0069] Screw 340

[0070] Fixed watch clip 700

[0071] Second support 342 DETAILED DESCRIPTION

[0072] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0073] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to preferred embodiments of the present invention, examples of which are shown in the accompanying drawings. Wherever possible, the same reference numerals will be used throughout the drawings to represent the same or similar parts.

[0074] Furthermore, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the present invention specification may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this document.

[0075] Furthermore, it is required that the present invention be understood not only by the actual terms used but also by the meanings connoted by each term.

[0076] like Figures 2 to 7As shown, the present invention discloses a low-pressure turbine blade wear measurement device, which includes: a base 100, a moving blade fixing seat mechanism 200, a measuring fixing mechanism 300, a measuring device 400 and an adjusting mechanism 500. Among them, the moving blade fixing seat mechanism 200 is fixed on the base 100, and the tenon 610 of the blade 600 to be measured is fixed on the moving blade fixing seat mechanism 200 and extends toward the outside of the base 100. The measuring fixing mechanism 300 is installed on the base 100, arranged opposite to the moving blade fixing seat mechanism 200, and the measuring fixing mechanism 300 can move along the base 100. The measuring device 400 is installed on the measuring fixing mechanism 300, and the blade tip 620 of the blade 600 to be measured is aligned with the measuring device 400. The adjusting mechanism 500 is installed on the moving blade fixing seat mechanism 200, and is used to adjust the fixing degree of the tenon 610 of the blade 600 to be measured.

[0077] Preferably, the moving blade fixing seat mechanism 200 includes a blade adapter 210 and a moving blade fixing seat 220. The blade adapter 210 is fixed to the base 100 (for example, fixed to the base 100 by bolts), and the moving blade fixing seat 220 is fixed to the blade adapter 210 for fixing the blades. The moving blade fixing seat is fixed to the blade adapter by bolts.

[0078] Further preferably, the adjustment mechanism 500 includes an adjustment bolt 510, which is used to tighten the tenon of the blade to be tested so that the theoretical contact center of the tenon and the tenon groove of the blade coincides (such as Figure 7 A tenon groove 221 is provided on the outer wall surface of the moving blade fixing seat 220, and the adjusting bolt 510 is inserted into the tenon groove 221 from the inner wall surface of the moving blade fixing seat 220. The tenon 610 of the blade 600 to be tested is installed in the tenon groove 221, and the contact between the tenon 610 and the tenon groove 221 is adjusted by the adjusting bolt 510.

[0079] In addition, the measurement fixing mechanism 300 includes a plurality of guide rods 310, an engine axis simulation seat 320 and a rotating rod 330. The two ends of the guide rod 310 are respectively fixed on the upper side of the base 100 through the first support 311, and fixed on the base 100 through nuts, so as to guide the engine axis simulation seat 320 to move in a straight line and prevent the follower screw 340 from rotating.

[0080] The engine axis simulation seat 320 is passed through the guide rod 310 and can move along the guide rod 310. One end of the rotating rod 330 is connected to the engine axis simulation seat 320, and the other end extends toward the direction close to the moving blade fixing seat mechanism 200.

[0081] The rotating rod 330 is used to fix the gauge clamp 700, adjust the distance between the measuring device (such as a micrometer) and the rotation axis, and drive the measuring device (such as a micrometer) to rotate around the axis to measure the multi-angle polar radius of the moving blade comb teeth.

[0082] The measurement fixing mechanism 300 also includes a screw 340, which is arranged on the base 100 through a second support 342, and the screw 340 penetrates into the engine axis simulation seat 320 to lock the engine axis simulation seat 320. The screw 340 is used to push the engine axis simulation seat 320 to move radially, simulate the rotation axis of each level of blades, and is fixed to the engine axis simulation seat 320 through a limit pin 341, and is connected to the base 100 through a thread.

[0083] The measuring device 400 is installed on the other end of the rotating rod 330, and is located near the tip 620 of the blade 600 to be measured. The measuring device 400 may be a micrometer.

[0084] For example, the micrometer (ie, the measuring device 400) is mounted on the rotating rod 330 via a fixed dial clamp 700. The fixed dial clamp 700 is used to connect the micrometer and the rotating rod 330 to adjust the measuring height and measuring radius of the micrometer.

[0085] The present invention also provides a method for measuring the wear of low-pressure turbine blades, which uses the low-pressure turbine blade wear measuring device as described above to indirectly evaluate the blade wear by measuring the values ​​of the blade pole radius at each stage. The measuring method comprises the following steps:

[0086] Step S1: When measuring the wear of the Nth-stage moving blade, place the Nth-stage moving blade on the moving blade fixing seat, and adjust the bolts so that the tenon of the blade to be measured coincides with the theoretical contact center of the tenon groove (e.g. Figure 7 shown).

[0087] Step S2, rotating the screw rod to adjust the engine axis simulation seat to the theoretical axis position of the blade of this stage when the engine is in working state (Kn=Ln+a).

[0088] Step S3, adjusting the measuring device so that the distance between the measuring device and the rotation axis is equal to the theoretical polar radius of the working blade of this stage.

[0089] Adjust the micrometer so that the distance between the micrometer head and the rotation axis is Rn (the theoretical polar radius of the working blade of this stage), reset the micrometer to zero, and rotate the micrometer fixing mechanism so that the micrometer head sweeps along the cylindrical surface of the blade tip comb teeth to be measured. The displayed value is the blade tip wear.

[0090] Step S4, reset the measuring device to zero, rotate the fixing mechanism of the measuring device, so that the measuring device sweeps along the comb tooth cylindrical surface of the blade tip of the blade to be measured, and the displayed value of the measuring device is the blade tip wear amount.

[0091] Preferably, the step S4 further includes the following steps:

[0092] Step S5, replace the blade to be measured, and make the tenon of the blade to be measured fully contact with the tenon groove of the moving blade fixing seat by adjusting the bolt. The displayed change of the measuring device is the tip wear amount of the blade to be measured.

[0093] Further preferably, the step S5 further includes the following steps:

[0094] Step S6, recalibrate the measuring device on another comb tooth of the blade at the same level by using a standard blade, repeat the above steps S1 to S5, and complete the wear measurement of all blades at this level.

[0095] According to the above steps, after the engine is working, the blades are worn and the radial size becomes smaller. Therefore, when setting the theoretical polar radius of each level of moving blades (Rna upper grate teeth\Rnb lower grate teeth), it is necessary to ensure that the micrometer is under pressure (pre-set pressure gauge value). When measuring the wear of the blade to be measured, the pop-up amount of the micrometer head is the wear of the moving blade grate teeth;

[0096] By adjusting the bolt to tighten the blade tenon, the blade tenon and the tenon groove theoretical contact center are made to coincide, thereby achieving a high degree of identity in the installation of each blade to be measured and improving the measurement accuracy.

[0097] During the measurement, the dial gauge fixing structure can rotate along the theoretical rotation axis to enable the dial gauge head to sweep across the cylindrical surface of the blade tip grate. After one clamping, the polar radius of the blade grate can be measured at multiple angles. Based on the polar radius values ​​at multiple positions, it can be determined whether the low-pressure turbine rotor has eccentric wear, and then the deviation between the turbine rotor and the stator axis during engine operation can be analyzed.

[0098] The engine axis simulation seat can be adjusted radially to simulate the rotation center axis of each level of working blades under the working state of the engine. The micrometer can be adjusted radially and axially on its fixing mechanism to change the measurement size and height, so as to measure the tip grate polar radius of blades at different positions of different levels of blades and evaluate the grate wear of moving blades from multiple angles. The same measuring tool can measure the wear of multiple levels of blades, which can significantly reduce the process cost.

[0099] The present invention designs a process and tool suitable for measuring the tip wear of a multi-stage low-pressure turbine working blade, which indirectly evaluates the blade wear by measuring the polar radius values ​​of each stage of the moving blade. During measurement, the theoretical contact center plane between the blade tenon and the tenon groove is used as the reference, and the engine axis simulation seat can be adjusted radially to simulate the rotation center axis of each stage of the working blade under the working state of the engine. The fixing mechanism for fixing the micrometer can rotate around the center axis to realize the micrometer head sweeping along the cylindrical surface of the moving blade grate teeth, thereby obtaining the polar radius value of each stage of the moving blade grate teeth, and the difference between the measured value and the theoretical value (the displayed value) is the tip wear. The measuring tool can simulate the rotation axis of each stage of the moving blade and the theoretical polar radius of each stage of the moving blade grate teeth, has high versatility, and reduces the measurement cost.

[0100] In summary, the low-pressure turbine blade wear measurement device and method of the present invention have the following advantages:

[0101] 1. The measuring tool has high versatility and can effectively reduce process costs.

[0102] Second, by measuring the polar radius, the tip wear of the moving blades can be indirectly evaluated, and the polar radius of the moving blades at various angles can be obtained, thereby analyzing more status data of the engine.

[0103] For those skilled in the art, the above invention disclosure is only used as an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary implementation of the present application.

[0104] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0105] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus facilitate the understanding of one or more embodiments of the invention, in the foregoing description of the embodiments of this application, multiple features are sometimes grouped into one embodiment, drawing, or description thereof. However, this disclosure method does not mean that the subject matter of this application requires more features than those mentioned in the claims. In fact, the features of an embodiment are less than all the features of a single embodiment disclosed above.

[0106] Although the specific embodiments of the present invention are described above, it should be understood by those skilled in the art that these are only examples, and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. A low-pressure turbine blade wear measurement device, characterized in that: The low-pressure turbine blade wear measurement device comprises: a base, A moving blade fixing seat mechanism, wherein the moving blade fixing seat mechanism is fixed on the base, and a tenon of a blade to be measured is fixed on the moving blade fixing seat mechanism and extends toward the outside of the base; A measuring and fixing mechanism, which is installed on the base, arranged opposite to the moving blade fixing seat mechanism, and can move along the base; A measuring device, wherein the measuring device is mounted on the measuring fixture, and the tip of the blade to be measured is aligned with the measuring device; An adjusting mechanism is installed on the moving blade fixing seat mechanism and is used to adjust the tenon fixing degree of the blade to be tested.

2. The low-pressure turbine blade wear measurement device according to claim 1, characterized in that: The moving blade fixing seat mechanism comprises a blade adapter seat and a moving blade fixing seat, the blade adapter seat is fixed on the base, and the moving blade fixing seat is fixed on the blade adapter seat.

3. The low-pressure turbine blade wear measurement device according to claim 2, characterized in that: The adjustment mechanism includes an adjusting bolt, and a tenon is provided on the outer wall surface of the moving blade fixing seat. The adjusting bolt passes through the tenon from the inner wall surface of the moving blade fixing seat, and the tenon of the blade to be measured is installed in the tenon, and the contact between the tenon and the tenon is adjusted by the adjusting bolt.

4. The low-pressure turbine blade wear measurement device according to claim 3, characterized in that: The measuring and fixing mechanism comprises a plurality of guide rods, an engine axis simulation seat and a rotating rod, the two ends of the guide rods are respectively fixed above the base through a first support, and the engine axis simulation seat is passed through the guide rods and can move along the guide rods; One end of the rotating rod is connected to the engine axis simulation seat, and the other end extends toward a direction close to the moving blade fixing seat mechanism.

5. The low-pressure turbine blade wear measurement device according to claim 4, characterized in that: The measuring and fixing mechanism also includes a screw rod, which is arranged on the base through a second support and penetrates into the engine axis simulation seat to lock the engine axis simulation seat.

6. The low-pressure turbine blade wear measurement device according to claim 4, characterized in that: The measuring device is mounted on the other end of the rotating rod and is located near the tip of the blade to be measured.

7. The low-pressure turbine blade wear measurement device according to claim 6, characterized in that: The measuring device is a dial gauge.

8. The low-pressure turbine blade wear measurement device according to claim 7, characterized in that: The micrometer is mounted on the rotating rod through a fixed dial clamp.

9. A method for measuring the wear of low-pressure turbine blades, characterized in that: The measuring method adopts the low-pressure turbine blade wear measurement device according to any one of claims 1 to 8, and the measuring method comprises the following steps: S1. Place the Nth-stage moving blade on the moving blade fixing seat, and adjust the bolts so that the tenon and the tenon groove of the blade to be tested coincide with each other in theoretical contact center; S2, rotating the screw to adjust the engine axis simulation seat to the theoretical axis position of the blade of this stage under the engine working state (Kn=Ln+a); S3. Adjust the measuring device so that the distance between the measuring device and the rotation axis is equal to the theoretical polar radius of the working blade of this stage; S4. The measuring device is reset to zero and the fixing mechanism of the measuring device is rotated so that the measuring device sweeps along the comb tooth cylindrical surface of the blade tip of the blade to be measured. The displayed value of the measuring device is the blade tip wear amount.

10. The method for measuring the wear of low-pressure turbine blades according to claim 9, characterized in that: The step S4 further includes the following steps: S5. Replace the blade to be tested, and make the tenon of the blade to be tested fully contact with the tenon groove of the moving blade fixing seat by adjusting the bolt. The displayed change of the measuring device is the tip wear amount of the blade to be tested.

11. The method for measuring the wear of low-pressure turbine blades according to claim 10, characterized in that: The step S5 further includes the following steps: S6. Recalibrate the measuring device on another grate tooth of the blade at the same level using a standard blade, and repeat the above steps S1 to S5 to complete the wear measurement of all blades at this level.

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