Low-pressure turbine blade wear measuring device and measuring method

Abstract

The application provides a low-pressure turbine working blade wear measurement device and a measurement method, which comprises a base, a blade fixing seat mechanism fixed on the base, a tenon of a blade to be measured fixed on the blade fixing seat mechanism and extending towards the outside of the base, a measurement fixing mechanism installed on the base, arranged opposite to the blade fixing seat mechanism and capable of moving along the base, a measurement device installed on the measurement fixing mechanism, a blade tip of the blade to be measured aligned with the measurement device, and an adjusting mechanism installed on the blade fixing seat mechanism and used for adjusting the tenon fixing degree of the blade to be measured. The measuring tool has higher universality and can effectively reduce the process cost. The blade tip wear of the blade is indirectly evaluated by measuring the polar radius, the polar radius of each angle of the blade is obtained, and more state data of the engine can be analyzed.

Description

Technical Field

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

[0002] Figure 1 This is a schematic diagram of the low-pressure turbine structure of the engine.

[0003] like Figure 1 As shown, the low-pressure turbine consists of a multi-stage rotor and a multi-stage stator, including a first-stage disk 10 to an Nth-stage disk 20. The rotor blades 30 are provided with double-layered grates 31. The stator outer ring 40 is provided with stepped honeycomb 41. The grates 31 and the honeycomb 41 form a blade tip sealing structure, which can effectively prevent gas leakage and improve the working efficiency of the low-pressure turbine.

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

[0005] Since the blades of low-pressure turbines vary in length and are numerous, the accuracy of blade positioning directly affects the measurement results of blade tip wear. The versatility of the measuring tools can directly reduce process costs.

[0006] The existing technology for measuring wear of low-pressure turbine blades has the following problems:

[0007] 1. This method is only applicable to the measurement of the polar radius of a single blade.

[0008] Second, the same measuring instrument cannot measure the wear of different levels of low-pressure turbine blades, resulting in high process costs.

[0009] In view of this, the inventors of this application have designed a device and method for measuring the wear of low-pressure turbine blades 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 accuracy and high process cost in the measurement results of low-pressure turbine blades at all levels in the prior art, and to provide a device and method for measuring the wear of low-pressure turbine working blades.

[0011] The present invention solves the above-mentioned technical problems through the following technical solution:

[0012] A device for measuring the wear of low-pressure turbine blades, characterized in that the device comprises: a base;

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

[0014] A measurement fixing mechanism is installed on the base, is arranged opposite to the movable blade fixing seat mechanism, and is movable along the base;

[0015] A measurement device is installed on the measurement fixing mechanism, and a blade tip of the blade to be measured is aligned with the measurement device;

[0016] An adjusting mechanism is installed on the movable blade fixing seat mechanism and is used for adjusting the fixing of the tenon of the blade to be measured.

[0017] According to an embodiment of the present application, the movable blade fixing seat mechanism comprises a blade adapter and a movable blade fixing seat, the blade adapter is fixed on the base, and the movable blade fixing seat is fixed on the blade adapter.

[0018] According to an embodiment of the present application, the adjusting mechanism comprises an adjusting bolt, a tenon groove is formed on an outer side wall surface of the movable blade fixing seat, the adjusting bolt penetrates into the tenon groove from an inner side wall surface of the movable blade fixing seat, the tenon of the blade to be measured is installed into the tenon groove, and the contact between the tenon and the tenon groove is adjusted by the adjusting bolt.

[0019] According to an embodiment of the present application, the measurement fixing mechanism comprises a plurality of guide rods, an engine axis simulation seat and a rotating rod, two ends of the guide rod are respectively fixed above the base through a first support, the engine axis simulation seat is arranged on the guide rod and is movable along the guide rod;

[0020] One end of the rotating rod is connected with the engine axis simulation seat, and the other end extends towards the movable blade fixing seat mechanism.

[0021] According to an embodiment of the present application, the measurement fixing mechanism further comprises a screw rod, the screw rod is arranged on the base through a second support, and the screw rod penetrates into the engine axis simulation seat and is used for locking the engine axis simulation seat.

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

[0023] According to an embodiment of the present application, the measurement device is a micrometer.

[0024] According to an embodiment of the present application, the micrometer is installed on the rotating rod through a fixed gauge clamp.

[0025] The present invention also provides a method for measuring the wear of low-pressure turbine blades, characterized in that the method employs the low-pressure turbine blade wear measuring device described above, and the method includes the following steps:

[0026] S1. Place the Nth stage moving blade on the moving blade fixing seat, and adjust the bolts to make the tenon of the blade to be tested coincide with the theoretical contact center of the mortise and tenon.

[0027] S2. Rotate the screw to adjust the engine axis simulation seat to the theoretical axis position of the blade of this stage under engine operating conditions (Kn=Ln+a);

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

[0029] S4. Zero the measuring device, rotate the fixing mechanism of the measuring device so that the measuring device sweeps along the toothed cylindrical surface of the blade tip 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 is followed by the following step:

[0031] S5. Replace the blade to be tested. Adjust the bolts to make the tenon of the blade to be tested fully contact the tenon groove of the moving blade fixing seat. The change displayed by the measuring device is the blade tip wear of the blade to be tested.

[0032] According to one embodiment of the present invention, step S5 is followed by the following steps:

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

[0034] The positive and progressive effects of this invention are as follows:

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

[0036] First, the measuring instruments have high versatility, which can effectively reduce process costs.

[0037] Second, by indirectly assessing the tip wear of the moving blade by measuring the extreme radius, the extreme radius of the moving blade at various angles can be obtained, thereby enabling the analysis of more state data of the engine. Attached Figure Description

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

[0039] Figure 1 This is a schematic diagram of the low-pressure turbine structure of the engine.

[0040] Figure 2 This is a perspective view of the low-pressure turbine blade wear measurement device of the present invention.

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

[0042] Figure 4 This is a perspective view of the low-pressure turbine blade wear measuring device of the present invention in the measuring state.

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

[0044] Figure 6 for Figure 5 A longitudinal sectional view.

[0045] Figure 7 This is a schematic diagram of the blade radius adjustment within the tenon groove in the low-pressure turbine blade wear measurement device of the present invention.

[0046] [Attached image labels]

[0047] Level 10

[0048] N-level disk 20

[0049] Rotor blade 30

[0050] 31 teeth

[0051] Outer Ring 40

[0052] Honeycomb 41

[0053] Base 100

[0054] Moving blade fixing seat mechanism 200

[0055] Measuring fixing mechanism 300

[0056] Measuring device 400

[0057] Adjustment mechanism 500

[0058] 600 blades to be tested

[0059] Tenon 610

[0060] Leaf Tip 620

[0061] Blade adapter 210

[0062] 220 moving blade mounting base

[0063] Adjusting bolt 510

[0064] Mortise and tenon 221

[0065] Guide rod 310

[0066] Engine shaft simulation mount 320

[0067] Rotary rod 330

[0068] First support 311

[0069] Screw 340

[0070] Fixed watch clip 700

[0071] Second support 342 Detailed Implementation

[0072] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0073] Embodiments of the invention will now be described in detail with reference to the accompanying drawings. Preferred embodiments of the invention will now be described in detail, examples of which are shown in the drawings. Wherever possible, the same reference numerals will be used in all the drawings to denote the same or similar parts.

[0074] Furthermore, although the terminology used in this invention is selected from commonly known and used terms, some terms mentioned in this specification may have been selected by the applicant in his or her judgment, and their detailed meanings are explained in the relevant sections of the description herein.

[0075] Furthermore, the invention should be understood not only through the actual terminology used, but also through the meaning implied by each term.

[0076] like Figures 2 to 7As shown, this invention discloses a device for measuring the wear of low-pressure turbine blades, comprising: a base 100, a moving blade fixing mechanism 200, a measuring fixing mechanism 300, a measuring device 400, and an adjusting mechanism 500. The moving blade fixing mechanism 200 is fixed to the base 100, and the tenon 610 of the blade 600 to be measured is fixed to the moving blade fixing mechanism 200, extending outwards towards the base 100. The measuring fixing mechanism 300 is mounted on the base 100, arranged opposite to the moving blade fixing mechanism 200, and is movable along the base 100. The measuring device 400 is mounted 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 mounted on the moving blade fixing 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 seat 210 and a moving blade fixing seat 220. The blade adapter seat 210 is fixed to the base 100 (e.g., fixed to the base 100 by bolts), and the moving blade fixing seat 220 is fixed to the blade adapter seat 210 for fixing the blade. The moving blade fixing seat is fixed to the blade adapter seat by bolts.

[0078] More preferably, the adjusting mechanism 500 includes an adjusting bolt 510 for tightening the tenon of the blade to be tested, so as to achieve the theoretical contact center of the blade tenon and the mortise (e.g., Figure 7 (Structure shown). A tenon 221 is provided on the outer wall of the moving blade fixing seat 220, and an adjusting bolt 510 passes through the tenon 221 from the inner wall of the moving blade fixing seat 220. The tenon 610 of the blade to be tested 600 is installed into the tenon 221, and the contact between the tenon 610 and the tenon 221 is adjusted by adjusting the adjusting bolt 510.

[0079] In addition, the measuring and fixing mechanism 300 includes multiple guide rods 310, an engine shaft simulation seat 320, and a rotating rod 330. The two ends of the guide rods 310 are respectively fixed above the base 100 by the first support 311 and fixed to the base 100 by nuts, which is used to guide the engine shaft simulation seat 320 to move in a straight line and prevent it from rotating with the screw 340.

[0080] The engine shaft simulation mount 320 is mounted on the guide rod 310 and can move along the guide rod 310. One end of the rotating rod 330 is connected to the engine shaft simulation mount 320, and the other end extends toward the blade fixing mechanism 200.

[0081] The rotating rod 330 is used to fix the gauge clamp 700, adjust the distance between the measuring device (e.g., dial indicator) and the rotating axis, and drive the measuring device (e.g., dial indicator) to rotate around the axis to measure the multi-angle polar radius of the moving blade teeth.

[0082] The measuring and fixing mechanism 300 also includes a screw 340, which is arranged on the base 100 via a second support 342. The screw 340 passes through 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, simulating the rotation axis of each stage of the blades. It is fixed to the engine axis simulation seat 320 by a limit pin 341 and is threadedly connected to the base 100.

[0083] The measuring device 400 is mounted on the other end of the rotating rod 330, located near the tip 620 of the blade 600 to be measured. The measuring device 400 is preferably a dial indicator.

[0084] For example, the dial indicator (i.e., measuring device 400) is mounted on the rotating rod 330 via a fixing clamp 700. The fixing clamp 700 is used to connect the dial indicator and the rotating rod 330, enabling adjustment of the dial indicator's measuring height and measuring radius.

[0085] This invention also provides a method for measuring the wear of low-pressure turbine blades. The method uses the low-pressure turbine blade wear measuring device described above to indirectly assess blade wear by measuring the polar radius of each stage of the moving blades. The measurement method includes the following steps:

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

[0087] Step S2: Rotate the screw to adjust the engine axis simulation seat to the theoretical axis position of the blade of that stage under engine operating conditions (Kn=Ln+a).

[0088] Step S3: Adjust the measuring device so that the distance between the measuring device and the rotation axis is the theoretical extreme radius of the working blade of that stage.

[0089] Adjust the dial indicator so that the distance between the dial indicator head and the rotation axis is Rn (the theoretical extreme radius of the working blade of this stage). Zero the dial indicator and rotate the dial indicator fixing mechanism so that the dial indicator head sweeps along the cylindrical surface of the blade tip tooth to be measured. The displayed value is the blade tip wear amount.

[0090] Step S4: Zero the measuring device and rotate the fixing mechanism of the measuring device so that the measuring device sweeps along the toothed cylindrical surface of the blade tip. The displayed value of the measuring device is the blade tip wear amount.

[0091] Preferably, the step S4 is followed by the following step:

[0092] Step S5: Replace the blade to be tested. Adjust the bolts to ensure that the tenon of the blade to be tested is in full contact with the tenon groove of the moving blade fixing seat. The change displayed by the measuring device is the blade tip wear of the blade to be tested.

[0093] More preferably, step S5 is followed by the following steps:

[0094] Step S6: Recalibrate the measuring device on another tooth of the same grade of blade using the standard blade. Repeat steps S1 to S5 to complete the wear measurement of all blades in this grade.

[0095] According to the above steps, since the blades are worn after the engine is running, the radial dimension will decrease. Therefore, when setting the theoretical extreme radius of each stage of moving blades (Rna upper layer grate tooth\Rnb lower layer grate tooth), it is necessary to ensure that the dial indicator is under pressure (preset pressure gauge value). When measuring the wear of the blade to be measured, the amount of the dial indicator head popping out is the wear of the moving blade grate tooth.

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

[0097] During measurement, the dial indicator's fixed structure can rotate along the theoretical rotation axis, allowing the dial indicator head to sweep across the cylindrical surface of the moving blade's tip teeth. After a single setup, the extreme radius of the moving blade's teeth can be measured at multiple angles. Based on the extreme radius values ​​at multiple locations, it can be determined whether there is uneven wear on the low-pressure turbine rotor, and further analyze the deviation between the turbine rotor and the stator axis during engine operation.

[0098] The engine axis simulation mount can be adjusted radially to simulate the rotation center axis of each stage of the working blades under engine operating conditions. The dial indicator can be adjusted radially and axially on its fixed mechanism to change the measurement size and height, enabling the measurement of the extreme radius of the blade tip teeth at different positions of different stages of blades, and multi-angle evaluation of the wear of the moving blade teeth. The same measuring instrument can measure the wear of multiple stages of blades, which can significantly reduce the process cost.

[0099] This invention designs a process and tool suitable for measuring the tip wear of multi-stage low-pressure turbine blades. It indirectly assesses blade wear by measuring the extreme radius of each stage of the moving blades. During measurement, the theoretical contact center plane between the blade tenon and the tenon groove is used as a reference. The engine axis simulation base can be adjusted radially to simulate the rotation center axis of each stage of the working blades under engine operating conditions. The fixing mechanism for the dial indicator can rotate around this center axis, allowing the dial indicator head to sweep along the cylindrical surface of the moving blade teeth, thereby obtaining the extreme radius value of each moving blade tooth in each stage. The difference between the measured value and the theoretical value (displayed value) is the tip wear. This measuring tool can simulate the rotation axis of each stage of the moving blades and the theoretical extreme radius of each stage of the moving blade teeth, exhibiting high versatility and reducing measurement costs.

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

[0101] First, the measuring instruments have high versatility, which can effectively reduce process costs.

[0102] Second, by indirectly assessing the tip wear of the moving blade by measuring the extreme radius, the extreme radius of the moving blade at various angles can be obtained, thereby enabling the analysis of more state data of the engine.

[0103] For those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application and therefore remain within the spirit and scope of the exemplary embodiments of this application.

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

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

[0106] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A method for measuring the wear of low-pressure turbine blades, characterized in that, The measurement method uses a low-pressure turbine blade wear measurement device. The low-pressure turbine blade wear measuring device includes: a base, A moving blade fixing mechanism is fixed on the base, and the tenon of the blade to be tested is fixed on the moving blade fixing mechanism and extends outward toward the base; A measuring and fixing mechanism is mounted on the base and arranged opposite to the moving blade fixing mechanism, and the measuring and fixing mechanism is movable along the base; the measuring and fixing mechanism includes multiple guide rods, an engine shaft simulation seat, and a rotating rod, the two ends of the guide rods are respectively fixed above the base by first supports, the engine shaft simulation seat passes through the guide rods and is movable along the guide rods; one end of the rotating rod is connected to the engine shaft simulation seat, and the other end extends toward the moving blade fixing mechanism; A measuring device is mounted on the measuring fixing mechanism, and the tip of the blade to be measured is aligned with the measuring device; An adjustment mechanism is installed on the moving blade fixing seat mechanism to adjust the tenon fixing degree of the blade to be tested. By tightening the tenon positioning surface of the blade to be tested, the tenon positioning surface is made to fully contact the tenon groove of the moving blade fixing seat, so that the theoretical contact center of the blade tenon and the tenon groove coincides. The method for measuring the wear of low-pressure turbine blades includes the following steps: S1. Place the Nth stage moving blade on the moving blade fixing seat, and adjust the bolts to make the tenon of the blade to be tested coincide with the theoretical contact center of the mortise and tenon. S2. Rotate the screw to adjust the engine axis simulation seat to the theoretical axis position of the blade of this stage under the engine working condition (Kn=Ln+a). S3. Adjust the measuring device so that the distance between the measuring device and the rotation axis is the theoretical extreme radius of the working blade of this stage; S4. Zero the measuring device, rotate the fixing mechanism of the measuring device so that the measuring device sweeps along the toothed cylindrical surface of the blade tip to be measured. The displayed value of the measuring device is the blade tip wear amount.

2. The method for measuring the wear of low-pressure turbine blades as described in claim 1, characterized in that, 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.

3. The method for measuring the wear of low-pressure turbine blades as described in claim 2, characterized in that, The adjustment mechanism includes an adjustment bolt. A tenon groove is provided on the outer wall of the moving blade fixing seat. The adjustment bolt passes through the tenon groove from the inner wall of the moving blade fixing seat. The tenon of the blade to be tested is installed into the tenon groove. The contact between the tenon and the tenon groove is adjusted by the adjustment bolt.

4. The method for measuring the wear of low-pressure turbine blades as described in claim 1, characterized in that, The measuring and fixing mechanism also includes a screw, which is arranged on the base via a second support and passes through the engine shaft simulation seat to lock the engine shaft simulation seat.

5. The method for measuring the wear of low-pressure turbine blades as described in claim 1, characterized in that, The measuring device is mounted on the other end of the rotating rod, located near the tip of the blade to be measured.

6. The method for measuring the wear of low-pressure turbine blades as described in claim 5, characterized in that, The measuring device is a dial indicator.

7. The method for measuring the wear of low-pressure turbine blades as described in claim 6, characterized in that, The dial indicator is mounted on the rotating rod via a fixed clamp.

8. The method for measuring the wear of low-pressure turbine blades as described in claim 1, characterized in that, Following step S4, the following steps are also included: S5. Replace the blade to be tested. Adjust the bolts to make the tenon of the blade to be tested fully contact the tenon groove of the moving blade fixing seat. The change displayed by the measuring device is the blade tip wear of the blade to be tested.

9. The method for measuring the wear of low-pressure turbine blades as described in claim 8, characterized in that, Following step S5, the following steps are also included: S6. Recalibrate the measuring device on another tooth of the same grade of blade using the standard blade, and repeat steps S1 to S5 to complete the wear measurement of all blades in this grade.

Images