Honeycomb sealing structure grinding crack depth measuring device and method

Abstract

A device for measuring the grinding crack depth of a honeycomb sealing structure comprises a substrate and probes, the substrate is provided with a reference surface, and the multiple probes are movably installed on the substrate in the axial direction and are arranged perpendicular to the reference surface. The device can carry out profiling measurement on the surface of the honeycomb sealing structure, avoids pore interference on the surface of the honeycomb sealing structure to measure the depth of a grinding crack, and effectively improves the measurement efficiency and accuracy. The invention further provides a method for measuring the grinding crack depth of the honeycomb sealing structure.

Description

Technical Field

[0001] The invention belongs to the field of aeroengines, and in particular relates to a wear scar depth measuring device and method for a honeycomb sealing structure. Background Art

[0002] Aircraft engines are equipped with multi-stage rotor structures, and there are significant differences in working pressure between rotors. Therefore, it is necessary to set a sealing structure between stages for sealing to prevent the high-pressure airflow of the rear stage from leaking to the front stage or the lubricating oil in the lubricating oil cavity from leaking. The honeycomb-comb tooth sealing structure is a commonly used sealing structure in aircraft engines. The comb tooth structure and the honeycomb structure are used in combination to achieve the sealing effect. In actual working conditions, the tip of the comb tooth often cuts into the honeycomb structure to form wear marks, which will cause significant wear of the honeycomb structure under long-term service and thus cause the sealing effect to decline. Therefore, measuring the wear mark depth of the honeycomb sealing structure is of great significance for evaluating the service life of the sealing structure. However, the surface of the honeycomb sealing structure itself is provided with honeycomb pores. Conventional depth gauges, laser rangefinders, three-coordinate measuring machines, etc. are easy to confuse the depth of the honeycomb pores with the wear mark depth of the honeycomb sealing structure, so it is difficult to provide accurate measurement results. Summary of the invention

[0003] The purpose of the present invention is to provide a wear scar depth measuring device for a honeycomb sealing structure, which can accurately measure the wear scar depth of the honeycomb structure. The present invention also provides a wear scar depth measuring method for a honeycomb sealing structure.

[0004] According to an embodiment of one aspect of the present invention, a wear scar depth measuring device for a honeycomb sealing structure is provided, the device comprising a substrate and probes, the substrate having a measuring reference surface, a plurality of the probes being movably mounted on the substrate along the axial direction and arranged in a straight line perpendicular to the reference surface.

[0005] The linearly arranged probes can profile the honeycomb structure in the measurement area, thereby distinguishing the bottom of the honeycomb structure pores from the wear scar area during measurement, achieving fast and effective measurement and improving the efficiency and accuracy of wear scar measurement.

[0006] Furthermore, in some embodiments, the diameter of the probe is set to 1 / 4-1 / 2 of the maximum width of the pores of the honeycomb structure to be measured. A thinner probe can be smoothly inserted into the bottom of the pores of the honeycomb sealing structure.

[0007] Furthermore, in some embodiments, the gap between the probes is smaller than the wall thickness between the pores of the honeycomb structure to be measured. The probe gap should not be larger than the wall thickness between the pores of the honeycomb structure to avoid the wall of the honeycomb structure being embedded between the probes, resulting in an inability to accurately measure the wear scar depth.

[0008] Furthermore, in some embodiments, the base plate includes two clamping plates, and the probe is clamped between the two clamping plates. The clamping plates can effectively fix the probe and provide damping for the sliding of the probe.

[0009] Furthermore, in some embodiments, a measuring device is provided on the substrate to measure the length of movement of the probe relative to the measurement reference plane. Providing the measuring device on the substrate can quickly measure the depth corresponding to the probe.

[0010] Furthermore, in some embodiments, the measuring device is a mechanical ruler.

[0011] Furthermore, in some embodiments, scale lines are provided on the probe.

[0012] Furthermore, in some embodiments, the measuring device comprises a plurality of the substrates and a plurality of groups of the probes, wherein the probes are arranged in an array. The probe array can perform surface profiling on the honeycomb sealing structure, thereby increasing the measuring range.

[0013] According to another embodiment of the present invention, a method for measuring the wear scar depth of a honeycomb sealing structure is provided, the method comprising the following steps: setting a plurality of measuring points on the sealing surface of the honeycomb sealing structure, so that at least some of the measuring points fall in the area where the wear scars are located, and the spacing between adjacent measuring points does not exceed 1 / 2 of the maximum width of the pores of the honeycomb sealing structure; measuring the distances of the plurality of measuring points relative to the surface of the honeycomb sealing structure, with the maximum value measured being the pore depth of the honeycomb sealing structure, and the value less than the pore depth being the measured wear scar depth. This method can be used to profile and measure the honeycomb sealing structure, and distinguish the bottom of the honeycomb structure pores from the wear scars caused by wear, thereby improving measurement efficiency and accuracy.

[0014] Further, the method adopts the honeycomb structure wear scar depth measuring device in any of the aforementioned embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 Schematic diagram of the structure of a wear scar depth measuring device for a honeycomb sealing structure in one embodiment;

[0016] Figure 2 This is a schematic diagram of an engine sealing structure in one embodiment;

[0017] Figure 3 A schematic diagram of the wear mark structure of the honeycomb sealing structure in one embodiment;

[0018] Figure 4 A schematic diagram of a probe structure in an embodiment;

[0019] Figure 5A schematic diagram of a process for measuring wear marks on a honeycomb sealing structure in one embodiment;

[0020] Figure 6 Schematic diagram of a wear scar depth measuring device for a honeycomb sealing structure after measurement in an embodiment.

[0021] The purpose of the above drawings is to explain the present invention in detail so that those skilled in the art can understand the technical concept of the present invention, but it is not intended to limit the present invention. For the sake of simplicity, the above drawings only schematically illustrate the structures related to the technical features of the present invention, and do not strictly draw the complete device and all details according to the actual scale. DETAILED DESCRIPTION

[0022] The present invention is further described in detail below through specific embodiments in conjunction with the accompanying drawings.

[0023] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present invention. The phrase appearing in various locations in the specification does not necessarily refer to the same embodiment, nor is it limited to mutually exclusive independent or alternative embodiments. Those skilled in the art should be able to understand that the embodiments herein may be combined with other embodiments without causing structural conflicts.

[0024] In the description of this article, unless otherwise clearly specified and limited, the technical terms "installed", "connected", "connected" and the like should be understood in a broad sense, which can be a movable connection, a fixed connection or an integral connection. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of this application can be understood according to specific circumstances.

[0025] In the description of this document, terms indicating orientation or positional relationships, such as "up", "down", "left", "right", "horizontal", "vertical", "height", "length", and "width", are intended to accurately describe the embodiments and simplify the description, but are not intended to limit the parts or structures involved to have a specific orientation, be installed or operate in a specific orientation, and should not be construed as a limitation on the embodiments in this document.

[0026] In the description of this article, the terms "first", "second" and the like are only used to distinguish different objects, and cannot be understood as indicating relative importance or limiting the quantity, specific order or primary and secondary relationship of the described technical features. In the description of this article, the meaning of "plurality" is at least two.

[0027] An embodiment of one aspect of the present invention provides a wear scar depth measuring device for a honeycomb sealing structure.

[0028] In one embodiment, the local structure of the aircraft engine to be inspected is as follows: Figure 2As shown. Among them, 31 is the low-pressure stage rotor blade, 32 is the stator blade, and 33 is the high-pressure stage rotor blade. The low-pressure stage rotor blade 31 is located in the low-pressure chamber 34, and the high-pressure stage rotor blade 33 is located in the high-pressure chamber 35. A sealing structure needs to be provided between the low-pressure chamber 34 and the high-pressure chamber 35 to prevent the high-pressure airflow from leaking to the front stage and causing the engine power to be reduced. Therefore, a grate-honeycomb sealing structure composed of a grate 36 and a honeycomb structure 4 is provided between the low-pressure chamber 34 and the high-pressure chamber 35, wherein the grate 36 rotates with the engine rotor, and the honeycomb structure 4 is installed on the stator blade and remains stationary relative to the casing. During the rotation of the engine, the sealing structure formed between the end of the grate 36 and the honeycomb structure 4 blocks the airflow, preventing the gas in the high-pressure chamber 35 from leaking into the low-pressure chamber 34. However, at the same time, during the rotation of the grate 36, the end of the grate 36 will cut into the surface of the honeycomb structure 4, as shown in FIG. Figure 3 As shown, wear marks 42 are formed on the surface of the honeycomb structure 4. In order to detect the wear state of the honeycomb structure 4, it is necessary to measure the depth d of the wear marks 42 to determine whether the wear affects the normal function of the honeycomb structure 4. However, since the surface of the honeycomb structure 4 is covered with pores 40, conventional measuring tools can easily reach the bottom of the honeycomb structure 4 and measure the overall depth D of the pores 40, which leads to confusion of the measurement data and seriously affects the detection efficiency.

[0029] In order to solve the above problems, an embodiment of one aspect of the present invention provides a wear scar depth measuring device for a honeycomb sealing structure. The structure of the device is as follows: Figure 1 As shown, the device comprises a substrate 1 and probes 2, wherein one side end face of the substrate 1 is a measurement reference surface 10, and a plurality of probes 2 are arranged in a straight line perpendicular to the measurement reference surface 10, and each probe 2 can slide relative to the substrate along its own axis. The device is used to detect the depth of wear marks on the honeycomb sealing structure of an aircraft engine.

[0030] In a preferred embodiment, the diameter of the probe 2 is set to 1 / 4-1 / 2 of the maximum width of the pore 40. In other preferred embodiments, the gap between adjacent probes 2 is smaller than the thickness of the wall 41 forming the pore 40.

[0031] In some preferred embodiments, the substrate 1 is formed by splicing two clamping plates 1a and 1b, and the probe 2 is clamped between the clamping plates 1a and 1b. The clamping surfaces of the clamping plates 1a and 1b may be provided with slideways for mounting the probe 2, and damping is provided for the sliding of the probe 2 to prevent the probe 2 from slipping off. In some embodiments, the substrate 1 may also be provided as a whole, and holes are punched on the reference surface to mount each probe 2.

[0032] In some embodiments, a measuring device is provided on the substrate 1 to measure the sliding distance of each probe 2. In a preferred embodiment, Figure 5As shown, the measuring device is configured as a mechanical scale 11 fixed on the surface of the substrate 1. In a further preferred embodiment, as Figure 4 As shown, the surface of the probe 2 is provided with scale lines 21 to measure the relative position of the probe 2. In other embodiments, an electronic measuring device may be used to measure the position of the probe 2, such as a resistive displacement sensor or a capacitive displacement sensor. In other embodiments, the measuring device may be omitted, and other general measuring tools such as a vernier caliper may be used to measure the position of the probe 2 one by one.

[0033] In some embodiments, a plurality of substrates 1 are provided, and the probes 2 on each substrate 1 are distributed in an array form.

[0034] In a preferred embodiment, if Figure 5 The method of using the wear scar depth measuring device for the honeycomb sealing structure shown is as follows:

[0035] First, the probes 2 are reset to their positions so that the positions of the probes 2 are aligned, and the measuring device is brought close to the honeycomb structure 4 to be measured, with each probe 2 corresponding to one measuring point.

[0036] Next, the measuring device is brought close to the measuring surface of the honeycomb structure 4 until the measuring reference surface 10 is completely flush with the surface of the honeycomb structure 4 , so that each probe 2 can contour the measuring surface.

[0037] Then, the measuring device is taken out vertically, and its status diagram Figure 6 As shown. After the measurement is completed, the probe 2 is in three devices, among which the 2a type probe has the shortest moving distance, and this type of probe penetrates into the pore 40 of the honeycomb structure 4 and abuts against the bottom of the pore 40; the 2b type probe has the longest moving distance and its end is flush with the reference surface, and this type of probe abuts against the unworn wall 41; the moving distance of the 2c type probe is between the 2a type probe and the 2b type probe, and this type of probe contacts the residual wall in the wear scar 42, and its moving distance can reflect the wear scar depth of the honeycomb structure 4. By comparing the scale line 21 on the probe 2c with the reading of the mechanical ruler 11, the specific depth of the wear scar 42 can be obtained.

[0038] In other embodiments, the above method may adopt the wear scar depth measuring device for the honeycomb sealing structure provided in any of the above embodiments.

[0039] In other embodiments, other methods may also be used, such as using a non-contact sensor to measure the sealing surface of the honeycomb structure 40 at multiple measuring points arranged at a spacing not exceeding 1 / 2 of the width of the pore 40, analyzing the data of each measuring point, and comparing the measured value with the distance from the surface of the honeycomb structure 40, where the largest value is the depth D of the pore 40, and the depth d of the wear mark 42 is the depth of the resin less than the pore depth D.

[0040] The purpose of the above embodiments is to further explain the present invention in detail in conjunction with the accompanying drawings so that those skilled in the art can understand the technical concept of the present invention. Within the scope of the claims of the present invention, optimization or equivalent replacement of the involved part structures or method steps shall fall within the protection scope of the present invention.

Claims

1. A wear scar depth measuring device for a honeycomb sealing structure, characterized in that: The invention comprises a substrate and probes, wherein the substrate has a measuring reference surface, and a plurality of probes are movably mounted on the substrate along the axial direction and arranged in a straight line perpendicular to the reference surface.

2. The wear scar depth measuring device for a honeycomb sealing structure according to claim 1, characterized in that: The probe diameter is set to be 1 / 4-1 / 2 of the maximum pore width of the honeycomb sealing structure to be tested.

3. The wear scar depth measuring device for a honeycomb sealing structure according to claim 1 or 2, characterized in that: The gap between the probes is smaller than the wall thickness between the pores of the honeycomb sealing structure to be tested.

4. The wear scar depth measuring device for a honeycomb sealing structure according to claim 1 or 2, characterized in that: The substrate includes two clamping plates, and the probe is clamped between the two clamping plates.

5. The wear scar depth measuring device for a honeycomb sealing structure according to claim 1 or 2, characterized in that: A measuring device is arranged on the substrate to measure the moving length of the probe relative to the measuring reference plane.

6. The wear scar depth measuring device for a honeycomb sealing structure according to claim 5, characterized in that: The measuring device is a mechanical ruler.

7. The wear scar depth measuring device of the honeycomb sealing structure according to claim 6, characterized in that: The probe is provided with scale lines.

8. The wear scar depth measuring device for a honeycomb sealing structure according to claim 1 or 2, characterized in that: It comprises a plurality of the substrates and a plurality of groups of the probes, and the probes are arranged in an array.

9. A method for measuring the wear scar depth of a honeycomb sealing structure, characterized in that: The following steps are involved: A plurality of measuring points are arranged on the sealing surface of the honeycomb sealing structure, so that at least some of the measuring points fall in the area where the wear marks are located, and the distance between adjacent measuring points does not exceed 1 / 2 of the maximum width of the pores of the honeycomb sealing structure; The distances between the multiple measuring points and the surface of the honeycomb sealing structure are measured, and the maximum value measured therein is taken as the pore depth of the honeycomb sealing structure, and the value less than the pore depth is taken as the measured wear scar depth.

10. The method for measuring the wear scar depth of a honeycomb sealing structure according to claim 9, characterized in that: A wear scar depth measuring device for a honeycomb sealing structure as claimed in any one of claims 1 to 8 is used.

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