Aeroengine blade labyrinth axial displacement measurement system and aeroengine

Abstract

This invention provides an axial displacement measurement system for aero-engine blade fangs, comprising: a sensing device including: a first rectangular core pole; a second rectangular core pole with the same dimensions as the first rectangular core pole and forming an angle α with the first rectangular core pole; a sensing signal output terminal for outputting a capacitance sensing signal; an internal bushing; a housing with a first end face having a normal marking line parallel to the normal direction perpendicular to the radial direction of the blade, and the first and second rectangular core poles being symmetrically distributed along the plane containing the normal marking line; a signal conditioning module configured to: receive the capacitance sensing signal; provide a trigger level signal; and generate a measurement pulse signal based on the capacitance sensing signal and the trigger level signal; and a control module configured to: obtain the axial displacement measurement value δ of the blade fangs based on the pulse width of the measurement pulse signal. This invention enables accurate and efficient measurement of the axial displacement of blade fangs.

Description

Technical Field

[0001] This invention relates primarily to the field of aero-engines, and more particularly to an aero-engine blade axial displacement measurement system and an aero-engine. Background Technology

[0002] Currently, most advanced aero-engine turbine blades employ a crowned structure to improve turbine efficiency and address vibration issues. The crowned blade increases blade rigidity, reduces torsional and bending deformation, and acts as a vibration damper. Furthermore, it reduces air leakage, lowers secondary losses, and improves efficiency. The tip of the crowned blade is typically fitted with sealing serrations to further reduce tip leakage, improve aerodynamic efficiency, and minimize damage and wear when the crowned blade rubs against the casing.

[0003] In actual operating conditions, aero-engines are subjected to many nonlinear excitation sources, such as aerodynamic excitation sources, time-varying temperature loads, and space loads under multi-field coupling. Engine rotors and stator components are prone to deformation or axial movement, directly causing changes in the axial clearances between the casing and rotating parts, the sealing grates and blades, and the moving and stationary blade cascades. How to measure the axial displacement of the grates under space-constrained conditions and decouple it from other influencing factors to achieve accurate measurement has become a problem that needs to be solved. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide an axial displacement measurement system for the cleavage teeth of an aero-engine blade and an aero-engine, so as to realize the accurate measurement of the axial displacement of the cleavage teeth of the aero-engine blade.

[0005] To solve the above-mentioned technical problems, the present invention provides an axial displacement measurement system for aero-engine blade serrations, comprising: a sensing device including: a first rectangular core pole; a second rectangular core pole having the same size as the first rectangular core pole and forming an angle α with the first rectangular core pole; a sensing signal output terminal connected to the first and second rectangular core poles and outputting a capacitance sensing signal; an inner bushing having a first opening and a second opening on a first end face that match the end face shapes of the first and second rectangular core poles; a housing fitted onto the outside of the inner bushing, the first end face of the housing having a normal marking line parallel to the normal direction perpendicular to the radial direction of the blade, and the first and second rectangular core poles being symmetrically distributed along the plane containing the normal marking line; a signal conditioning module configured to: receive the capacitance sensing signal; provide a trigger level signal; and generate a measurement pulse signal based on the capacitance sensing signal and the trigger level signal; and a control module configured to: obtain the axial displacement measurement value δ of the blade serrations based on the pulse width of the measurement pulse signal.

[0006] In one embodiment of the present invention, there is a gap between the first rectangular core electrode and the second rectangular core electrode.

[0007] In one embodiment of the present invention, the capacitance sensing signal has a first low peak value and a second high peak value; the amplitude of the trigger level signal is located between the first low peak value and the second high peak value.

[0008] In one embodiment of the present invention, generating a measurement pulse signal based on the capacitance sensing signal and the trigger level signal includes: when the amplitude of the capacitance sensing signal is less than the amplitude of the trigger level signal, the measurement pulse signal is at a low level; when the amplitude of the capacitance sensing signal is greater than or equal to the amplitude of the trigger level signal, the measurement pulse signal is at a high level.

[0009] In one embodiment of the present invention, obtaining the axial displacement measurement value δ of the blade teeth based on the pulse width of the measurement pulse signal includes:

[0010]

[0011] Where n is a positive integer, k i T(δ) is the calibration coefficient, T(δ) is the pulse width of the pulse signal for measuring axial displacement of the blade teeth, and T(0) is the pulse width of the pulse signal for measuring axial displacement of the blade teeth.

[0012] In one embodiment of the present invention, the sensing device further includes a flange structure, the flange structure being disposed around the outside of the housing and close to the side where the second end face of the housing is located.

[0013] In one embodiment of the present invention, the second end of the built-in bushing has positioning serrations, which cooperate with the second end face of the housing to assemble and position the embossed markings, the first rectangular core pole, and the second rectangular core pole.

[0014] In one embodiment of the present invention, the first rectangular core electrode and the second rectangular core electrode are made of high-temperature alloy.

[0015] The present invention also provides an aero-engine, comprising an aero-engine blade serration axial displacement measurement system as described in any of the preceding claims; a turbine blade; a turbine casing; wherein the radially outer edge of the turbine blade has serrations; the sensing device is mounted on the turbine casing; a first rectangular core pole and a second rectangular core pole face the radially outer edge of the turbine blade; the axial length of the first rectangular core pole and the second rectangular core pole covers the axial displacement range of the aero-engine blade serrations.

[0016] In one embodiment of the present invention, one or more of the sensing devices are provided on the turbine casing corresponding to the outer periphery of the cleavage of each stage of the turbine blade.

[0017] Compared with the prior art, the present invention has the following advantages: The technical solution of this application, through the setting of the sensing device and the corresponding sensing operation process, realizes accurate and efficient measurement of the axial displacement of the toothed grates under the condition of limited circumferential space of the grates. Attached Figure Description

[0018] The accompanying drawings are included to provide a further understanding of this application and form part of this application. The drawings illustrate embodiments of this application and, together with this specification, serve to explain the principles of this application.

[0019] In the attached image:

[0020] Figure 1 This is a partial structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application.

[0021] Figure 2 This is a partial structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application.

[0022] Figure 3 This is a partial structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application.

[0023] Figure 4 This is a first-view overall structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application.

[0024] Figure 5 This is a second-view overall structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application.

[0025] Figure 6 This is a schematic diagram of the composition of an aero-engine blade axial displacement measurement system according to an embodiment of this application.

[0026] Figure 7 This is a schematic diagram of the tooth structure of an aero-engine blade according to an embodiment of this application.

[0027] Figure 8 This is a schematic diagram illustrating the measurement principle of an aero-engine blade axial displacement measurement system according to an embodiment of this application.

[0028] Figure 9 This is a waveform diagram of the capacitance sensing signal, trigger level signal, and measurement pulse signal according to an embodiment of this application.

[0029] Figure 10 This is a schematic diagram of the axial displacement measurement state of the air-to-air engine blade grates according to an embodiment of this application. Detailed Implementation

[0030] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely some examples or embodiments of this application. For those skilled in the art, these drawings can be applied to other similar scenarios without creative effort. Unless obvious from the context or otherwise specified, the same reference numerals in the drawings represent the same structures or operations.

[0031] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0032] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this application. It should also be understood that, for ease of description, the dimensions of the various parts shown in the accompanying drawings are not drawn to actual scale.

[0033] In the description of this application, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is usually based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this application and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this application; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0034] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be construed as limiting the scope of protection of this application.

[0035] The embodiments of this application describe an axial displacement measurement system for the ferrules of an aero-engine blade and an aero-engine.

[0036] Figure 1This is a partial structural schematic diagram of the sensing device of an aero-engine blade serration axial displacement measurement system according to an embodiment of this application. Wherein, Figure 1 Figure (a) shows a schematic diagram of the structure of the first and second rectangular core electrodes of the sensing device. Figure 1 Figure (b) shows a side view of the first end face of the first rectangular core and the second rectangular core of the sensing device.

[0037] Figure 2 This is a partial structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application. Figure 3 This is a partial structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application. Figure 4 This is a first-view overall structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application. Figure 5 This is a second-view overall structural schematic diagram of the sensing device of an aero-engine blade cleat axial displacement measurement system according to an embodiment of this application. Figure 6 This is a schematic diagram of the composition of an aero-engine blade axial displacement measurement system according to an embodiment of this application.

[0038] refer to Figures 1 to 6 The aero-engine blade axial displacement measurement system 600 includes a sensing device 400, a signal conditioning module 501, and a control module 502.

[0039] The sensing device 400 includes a first rectangular core electrode 101, a second rectangular core electrode 102, an inner bushing 201, and a housing 301. The second rectangular core electrode 102 has the same dimensions as the first rectangular core electrode 101 and forms an angle α with the first rectangular core electrode 101. The angle α is greater than zero degrees, for example, 20°, 30°, 50°, or 90°, and may also be an obtuse angle.

[0040] The sensing signal output terminal is connected to the first rectangular core 101 and the second rectangular core 102 and outputs a capacitance sensing signal. The sensing signal output terminal is, for example, provided on the connecting part 103. The first end face 215 of the built-in bushing 201 has a first opening 211 and a second opening 212 that match the end face shapes of the first rectangular core 101 and the second rectangular core 102.

[0041] The housing 301 is fitted onto the outside of the inner bushing 201. The second end face 411 of the housing 301 has a marking line 401. The marking line 401 is parallel to the normal direction perpendicular to the radial direction of the blade, and the first rectangular core pole 101 and the second rectangular core pole 102 are symmetrically distributed along the plane P containing the marking line 401. The first rectangular core pole 101 and the second rectangular core pole 102 are made of high-temperature alloy.

[0042] In some embodiments, a gap exists between the first rectangular core 101 and the second rectangular core 102, for example, in Figure 5 The distance between the closest points of the first rectangular core 101 and the second rectangular core 102 is indicated by the symbol r. The setting of the distance between the first rectangular core 101 and the second rectangular core 102 can improve the distinguishability of changes in the capacitive sensing signal.

[0043] The second end of the built-in bushing 201 has positioning serrations 213, which engage with the second end face 411 of the housing 301 to assemble and position the imprint line 401, the first rectangular core pole 101, and the second rectangular core pole 102. The sensing device 400 also includes, for example, a flange structure 302, which is arranged around the outside of the housing 301 and close to the side where the second end face 411 of the housing 301 is located.

[0044] In some embodiments, the signal conditioning module 501 is configured to perform the following steps: step 521, receiving a capacitance sensing signal; step 522, providing a trigger level signal; step 523, generating a measurement pulse signal based on the capacitance sensing signal and the trigger level signal. The control module 502 is configured to obtain the axial displacement measurement value δ of the blade teeth based on the pulse width of the measurement pulse signal.

[0045] Figure 7 This is a schematic diagram of the tooth structure of an aero-engine blade according to an embodiment of this application. Figure 8 This is a schematic diagram illustrating the measurement principle of an aero-engine blade axial displacement measurement system according to an embodiment of this application. Figure 8 Figure (a) is a schematic diagram showing the comparison between the axial displacement of the comb teeth and the positions of the first and second rectangular core poles. Figure 8 Figure (b) in the figure is a schematic diagram of the measurement pulse signal waveform corresponding to the axial displacement of the comb teeth. Figure 9 This is a waveform diagram of the capacitance sensing signal, trigger level signal, and measurement pulse signal according to an embodiment of this application. Figure 9 Figure (a) in the figure is a schematic diagram of the waveform of the capacitance sensing signal 901. Figure 9 Figure (b) shows a schematic diagram of the comparison waveforms of the capacitance sensing signal 901 and the trigger level signal 902. Figure 9 Figure (c) shows a schematic diagram of the comparison waveforms of the capacitance sensing signal 901 trigger level signal 902 and the measurement pulse signal 903. Figure 9 Figure (d) in the figure is a schematic diagram of the waveform of the measurement pulse signal 903.

[0046] refer to Figures 7 to 9The rotation axis of the turbine blade 700 of the aero-engine is 701, 703, for example, indicating the blade disk. Direction X is the circumferential rotation direction, and direction Y is the circumferential direction. The capacitive sensing signal 901 has a first low peak value amp1 and a second high peak value amp2. Figure 7 The example shows tooth 702 and tooth 704.

[0047] refer to Figure 8 In Figures (a) and (b), when the grating tooth 704 has no axial displacement, the generated measurement pulse signal is u0, with a pulse width of T(0) (or denoted as T0). When the grating tooth undergoes an axial displacement δ1 in the +y direction, the generated measurement pulse signal is u1, with a pulse width of T(δ1) (or denoted as T1), and the grating tooth position is indicated as shown in Figure 704a. When the grating tooth undergoes an axial displacement δ2 in the -y direction, the generated measurement pulse signal is u2, with a pulse width of T(δ2) (or denoted as T2), and the grating tooth position is indicated as shown in Figure 704b.

[0048] The capacitive sensing signal 901 is generated based on the effective facing area of ​​the first rectangular core 101 and the second rectangular core 102 with the grating teeth. The capacitive sensing signal 901 gradually rises from a first low peak value amp1 to a second high peak value amp2, and then gradually decreases from the second high peak value amp2 back to the first low peak value amp1. This cycle repeats as the grating teeth at the blade edge rotate. The amplitude amp3 of the trigger level signal 902 is located between the first low peak value and the second high peak value. The amplitude amp3 of the trigger level signal 902 is, for example, based on the first low peak value amp1 plus m*(amp2-amp1), where the coefficient m is a rational number, such as 0.5, 0.6, 0.7, or 0.8.

[0049] In some embodiments, generating a measurement pulse signal 903 based on a capacitance sensing signal 901 and a trigger level signal 902 includes: when the amplitude of the capacitance sensing signal 901 is less than the amplitude of the trigger level signal 902, the measurement pulse signal 903 is at a low level Q1; when the amplitude of the capacitance sensing signal 901 is greater than or equal to the amplitude of the trigger level signal 902, the measurement pulse signal 903 is at a high level Q2.

[0050] In some embodiments, obtaining the axial displacement measurement value δ of the blade teeth based on the pulse width of the measurement pulse signal 903 includes:

[0051]

[0052] n is a positive integer. k i These are calibration coefficients, or fitting coefficients. T(δ) is the pulse width of the axial displacement measurement pulse signal 903 for the blade teeth. T(0) is the pulse width of the axial displacement measurement pulse signal 903 for the blade teeth.

[0053] For example, when n is 1, δ = k0 + k1*(T(δ) - T(0)). When n is 2, δ = k0 + k1*(T(δ) - T(0)) + k2*(T(δ) - T(0)). 2 The specific value of n and the measurement results of the axial displacement δ of the blade grating teeth are used to determine the calculation method based on factors such as the structure of the grating teeth and the sensor structure, and thus obtain the axial displacement δ of the blade grating teeth.

[0054] Figure 10 This is a schematic diagram of the axial displacement measurement state of the air-to-air engine blade grates according to an embodiment of this application.

[0055] The present invention also provides an aero-engine. The aero-engine includes an aero-engine blade serration axial displacement measuring system 600 as described above, a turbine blade 700, and a turbine casing (not shown). A sensing device 400 is mounted on the turbine casing, specifically, for example, engaging with a corresponding mounting hole opened in the turbine casing. The radially outer edge of the turbine blade has serrations. A first rectangular core pole 101 and a second rectangular core pole 102 face the radially outer edge of the turbine blade. The axial length of the first rectangular core pole 101 and the second rectangular core pole 102 covers the axial displacement range of the aero-engine blade serrations.

[0056] In some embodiments, one or more sensing devices 400 are provided on the turbine casing corresponding to the outer periphery of the grates of each stage turbine blade.

[0057] The aero-engine blade axial displacement measurement system and aero-engine of this application, through the setting of sensing devices and the corresponding sensing operation process, achieve accurate and efficient measurement of the axial displacement of the axial displacement of the blade axial displacement under the condition of limited circumferential space of the blade axial displacement.

[0058] The basic concepts have been described above. Obviously, 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.

[0059] 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.

[0060] Some aspects of this application may be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The aforementioned hardware or software may be referred to as a "data block," "module," "engine," "unit," "component," or "system." The processor may be one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. Furthermore, aspects of this application may be manifested as a computer product located on one or more computer-readable media, including computer-readable program code.

[0061] Similarly, it should be noted that, in order to simplify the description of the present application and thus aid in the understanding of one or more embodiments of the invention, the foregoing description of the embodiments of the present 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 the application requires more features than those mentioned in the claims. In fact, the embodiments contain fewer features than all the features of the single embodiments disclosed above.

[0062] Although this application has been described with reference to specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, any changes or modifications to the above embodiments within the essential spirit of this application will fall within the scope of the claims of this application.

Claims

1. A system for measuring the axial displacement of the blade teeth of an aero-engine, comprising: Sensing device: The sensing device includes: First rectangular core electrode; The second rectangular core pole has the same dimensions as the first rectangular core pole and forms an angle α with the first rectangular core pole; The sensing signal output terminal is connected to the first rectangular core and the second rectangular core, and outputs a capacitance sensing signal; An internal bushing, wherein the first end face of the internal bushing has a first opening and a second opening that match the end face shapes of the first rectangular core pole and the second rectangular core pole. The housing is fitted onto the outside of the inner bushing. The first end face of the housing has a normal marking line. The normal marking line is parallel to the normal direction that is perpendicular to the radial direction of the blade. The first rectangular core pole and the second rectangular core pole are symmetrically distributed along the plane where the normal marking line is located. The signal conditioning module is configured as follows: Receive the capacitance sensing signal; Provide a trigger level signal; A measurement pulse signal is generated based on the capacitance sensing signal and the trigger level signal; The control module is configured to: obtain the axial displacement measurement value δ of the blade teeth based on the pulse width of the measurement pulse signal; The axial displacement measurement value δ of the blade teeth is obtained based on the pulse width of the measurement pulse signal, including: in, n It is a positive integer. For calibration coefficients, The pulse width of the pulse signal used to measure the axial displacement of the blade teeth. The pulse width of the pulse signal is measured when the blade teeth have not undergone axial displacement.

2. The aero-engine blade axial displacement measurement system according to claim 1, characterized in that, There is a gap between the first rectangular core and the second rectangular core.

3. The aero-engine blade axial displacement measurement system according to claim 1, characterized in that, The capacitance sensing signal has a first low peak value and a second high peak value; the amplitude of the trigger level signal is between the first low peak value and the second high peak value.

4. The aero-engine blade axial displacement measurement system according to claim 3, characterized in that, Generating a measurement pulse signal based on the capacitance sensing signal and the trigger level signal includes: When the amplitude of the capacitance sensing signal is less than the amplitude of the trigger level signal, the measurement pulse signal is at a low level; When the amplitude of the capacitance sensing signal is greater than or equal to the amplitude of the trigger level signal, the measurement pulse signal is at a high level.

5. The aero-engine blade axial displacement measurement system according to claim 1, characterized in that, The sensing device also includes a flange structure, which is arranged around the outside of the housing and close to the side where the second end face of the housing is located.

6. The aero-engine blade axial displacement measurement system according to claim 1, characterized in that, The second end of the built-in bushing has positioning serrations, which mate with the second end face of the housing to assemble and position the marking line, the first rectangular core pole, and the second rectangular core pole.

7. The aero-engine blade axial displacement measurement system according to claim 1, characterized in that, The first rectangular core electrode and the second rectangular core electrode are made of high-temperature alloys.

8. An aero-engine, comprising the aero-engine blade axial displacement measurement system as described in any one of claims 1-7; Turbine blades; Turbine casing; in, The turbine blade has serrated outer radial edges; the sensing device is mounted on the turbine casing; the first rectangular core pole and the second rectangular core pole face the outer radial edges of the turbine blade; The lengths of the first and second rectangular core poles in the axial direction cover the axial displacement range of the aero-engine blade teeth.

9. The aero-engine according to claim 8, characterized in that, One or more of the aforementioned sensing devices are provided on the turbine casing corresponding to the outer periphery of the cleavage teeth of each stage of the turbine blades.

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