Aero-engine blade labyrinth axial displacement measuring system and aero-engine

Abstract

The invention provides an aero-engine and a blade labyrinth axial displacement measuring system thereof. The aero-engine comprises a sensing device and a measuring device, wherein the sensing device comprises a first rectangular core pole; the size of the second rectangular core pole is the same as that of the first rectangular core pole, and an included angle alpha is formed between the second rectangular core pole and the first rectangular core pole; the sensing signal output end is used for outputting a capacitance sensing signal; a lining is built in; the first end face of the shell is provided with a normal printing marked line, the normal printing marked line is parallel to the normal direction perpendicular to the radial direction of the blade, and the first rectangular core pole and the second rectangular core pole are symmetrically distributed along the plane where the normal printing marked line is located; the signal conditioning module is configured to receive a capacitance sensing signal; providing a trigger level signal; generating a measurement pulse signal according to the capacitance sensing signal and the trigger level signal; and the control module is configured to obtain an axial displacement measurement value delta of the blade labyrinth based on the pulse width of the measurement pulse signal. According to the invention, the axial displacement of the blade labyrinth can be accurately and efficiently measured.

Description

Technical Field

[0001] The invention mainly relates to the field of aeroengines, and in particular to an aeroengine blade grate axial displacement measurement system and an aeroengine. Background Art

[0002] At present, most advanced aircraft engine turbine blades often use a crown structure to improve turbine efficiency and solve vibration problems. Blade crowns can improve blade rigidity, reduce blade distortion and bending deformation, and play a vibration reduction role. In addition, they can also reduce air leakage, reduce secondary losses, and improve efficiency. The top of the crowned blade is usually sealed with grate teeth to further reduce tip leakage, improve aerodynamic efficiency, and reduce damage and wear when the crowned blade rubs against the casing.

[0003] In actual working conditions, aircraft engines are subjected to many nonlinear excitation sources, such as aerodynamic excitation sources, time-varying temperature loads, and spatial loads under multi-field coupling. The engine rotor and stator components are prone to deformation or axial movement, which directly leads to changes in the axial clearance between the casing and the rotating parts, the sealing grate teeth and the blades, and the dynamic and static blade grids. How to measure the axial displacement of the grate teeth under space-constrained conditions and decouple it from other types of 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 aero-engine blade grate axial displacement measurement system and an aero-engine, so as to realize the accurate measurement of the axial displacement of the aero-engine blade grate.

[0005] In order to solve the above technical problems, the present invention provides an axial displacement measurement system for aero-engine blade grate, comprising: a sensing device: the sensing device comprises: a first rectangular core pole; a second rectangular core pole, which is the same size as the first rectangular core pole and forms an angle α with the first rectangular core pole; a sensing signal output end, which is connected to the first rectangular core pole and the second rectangular core pole and outputs a capacitive sensing signal; a built-in bushing, wherein the first end face of the built-in 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; a shell, which is sleeved on the outside of the built-in bushing, and the first end face of the shell has a French print line, the French print line is parallel to the normal direction perpendicular to the radial direction of the blade, and the first rectangular core pole and the second rectangular core pole are symmetrically distributed along the plane where the French print line is located; a signal conditioning module, which is configured to: receive the capacitive sensing signal; provide a trigger level signal; and generate a measurement pulse signal according to the capacitive sensing signal and the trigger level signal; a control module, which is configured to: obtain the axial displacement measurement value δ of the blade grate 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 pole and the second rectangular core pole.

[0007] In one embodiment of the present invention, the capacitance sensing signal has a first low peak value and a second high peak value; and the amplitude of the trigger level signal is 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 according to 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 grate teeth based on the pulse width of the measurement pulse signal includes:

[0010]

[0011] Where n is a positive integer, k i is the calibration coefficient, T(δ) is the pulse width of the pulse signal when the blade grate teeth undergo axial displacement, and T(0) is the pulse width of the pulse signal when the blade grate teeth do not undergo axial displacement.

[0012] In one embodiment of the present invention, the sensor device further comprises a flange structure, wherein the flange structure is disposed outside the shell and close to a side where the second end surface of the shell is located.

[0013] In one embodiment of the present invention, the second end of the built-in bushing has a positioning serration, and the positioning serration cooperates with the second end surface of the shell to assemble and position the French printing line, the first rectangular core pole and the second rectangular core pole.

[0014] In one embodiment of the present invention, the material of the first rectangular core electrode and the second rectangular core electrode includes a high temperature alloy.

[0015] The present invention also provides an aircraft engine, comprising an aircraft engine blade grate axial displacement measurement system as described in any of the preceding items; a turbine blade; a turbine casing; wherein the radial outer edge of the turbine blade has grate teeth; the sensor device is mounted on the turbine casing; the first rectangular core pole and the second rectangular core pole are facing the radial outer edge of the turbine blade; the lengths of the first rectangular core pole and the second rectangular core pole in the axial direction cover the axial displacement range of the aircraft engine blade grate teeth.

[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 comb teeth of each stage of the turbine blades.

[0017] Compared with the prior art, the present invention has the following advantages: the technical solution of the present application, through the setting of the sensing device and the corresponding sensing operation process, realizes the accurate and efficient measurement of the axial displacement of the comb teeth under the condition that the circumferential space of the comb teeth is limited. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are provided to provide a further understanding of the present application. They are included in and constitute a part of the present application. The accompanying drawings illustrate embodiments of the present application and together with the description serve to explain the principles of the present application.

[0019] In the attached figure:

[0020] Figure 1 It is a partial structural schematic diagram of a sensor device of an aircraft engine blade comb tooth axial displacement measurement system according to an embodiment of the present application.

[0021] Figure 2 It is a partial structural schematic diagram of a sensor device of an aircraft engine blade comb tooth axial displacement measurement system according to an embodiment of the present application.

[0022] Figure 3 It is a partial structural schematic diagram of a sensor device of an aircraft engine blade comb tooth axial displacement measurement system according to an embodiment of the present application.

[0023] Figure 4 It is a schematic diagram of the overall structure of the first perspective of the sensor device of the aircraft engine blade comb axial displacement measurement system of one embodiment of the present application.

[0024] Figure 5 It is a schematic diagram of the overall structure from a second perspective of a sensor device of an aircraft engine blade comb axial displacement measurement system according to an embodiment of the present application.

[0025] Figure 6 It is a schematic diagram of the composition of an aircraft engine blade grate axial displacement measurement system according to an embodiment of the present application.

[0026] Figure 7 It is a schematic diagram of the comb tooth structure of an aircraft engine blade according to an embodiment of the present application.

[0027] Figure 8 It is a schematic diagram of the measurement principle of an aircraft engine blade comb axial displacement measurement system according to an embodiment of the present application.

[0028] Fig. 9 1 is a waveform diagram of a capacitance sensing signal, a trigger level signal, and a measurement pulse signal according to an embodiment of the present application.

[0029] Fig.10 It is a schematic diagram of the axial displacement measurement state of the comb teeth of an aircraft engine blade according to an embodiment of the present application. DETAILED DESCRIPTION

[0030] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for the description of the embodiments. Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. Unless it is obvious from the language environment or otherwise explained, the same reference numerals in the figures represent the same structure or operation.

[0031] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0032] Unless otherwise specifically stated, the relative arrangement of the components and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present application. Meanwhile, it should be understood that for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship.

[0033] In the description of the present application, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction, and therefore cannot be understood as limiting the scope of protection of the present application; the directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0034] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of this application.

[0035] The embodiments of the present application describe an aircraft engine blade grate axial displacement measurement system and an aircraft engine.

[0036] Figure 1This is a partial structural schematic diagram of a sensor device of an aircraft engine blade grate axial displacement measurement system according to an embodiment of the present application. Figure 1 Figure (a) is a schematic diagram of the structure of the first rectangular core electrode and the second rectangular core electrode of the sensor device. Figure 1 Figure (b) is a side view of the first end surface of the first rectangular core pole and the second rectangular core pole of the sensing device.

[0037] Figure 2 It is a partial structural schematic diagram of a sensor device of an aircraft engine blade comb tooth axial displacement measurement system according to an embodiment of the present application. Figure 3 It is a partial structural schematic diagram of a sensor device of an aircraft engine blade comb tooth axial displacement measurement system according to an embodiment of the present application. Figure 4 It is a schematic diagram of the overall structure of the first perspective of the sensor device of the aircraft engine blade comb axial displacement measurement system of one embodiment of the present application. Figure 5 It is a schematic diagram of the overall structure from a second perspective of a sensor device of an aircraft engine blade comb axial displacement measurement system according to an embodiment of the present application. Figure 6 It is a schematic diagram of the composition of an aircraft engine blade grate axial displacement measurement system according to an embodiment of the present application.

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

[0039] The sensor device 400 includes a first rectangular core electrode 101, a second rectangular core electrode 102, a built-in bushing 201 and a housing 301. The second rectangular core electrode 102 has the same size 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, for example, 20°, 30°, 50° or 90°, and can also be an obtuse angle.

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

[0041] The shell 301 is sleeved on the outside of the built-in bushing 201, and the second end surface 411 of the shell 301 has a French marking line 401. The French 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 where the French marking line 401 is located. The material of the first rectangular core pole 101 and the second rectangular core pole 102 includes a high-temperature alloy.

[0042] In some embodiments, there is a gap between the first rectangular core electrode 101 and the second rectangular core electrode 102. Figure 5 The mark in the middle indicates that the gap between the first rectangular core electrode 101 and the second rectangular core electrode 102 at the closest point is r. The setting of the gap between the first rectangular core electrode 101 and the second rectangular core electrode 102 can improve the variation distinction of the capacitance sensing signal.

[0043] The second end of the built-in bushing 201 has a positioning sawtooth 213, and the positioning sawtooth 213 cooperates with the second end surface 411 of the housing 301 to assemble and position the French printing line 401, the first rectangular core pole 101 and the second rectangular core pole 102. The sensor device 400, for example, also includes a flange structure 302, which is arranged outside the housing 301 and close to the side where the second end surface 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 capacitive sensing signal; step 522, providing a trigger level signal; step 523, generating a measurement pulse signal according to the capacitive sensing signal and the trigger level signal. The control module 502 is configured to obtain an axial displacement measurement value δ of the blade grate teeth based on the pulse width of the measurement pulse signal.

[0045] Figure 7 It is a schematic diagram of the comb tooth structure of an aircraft engine blade according to an embodiment of the present application. Figure 8 It is a schematic diagram of the measurement principle of an aircraft engine blade comb axial displacement measurement system according to an embodiment of the present 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 rectangular core pole and the second rectangular core pole. Figure 8 Figure (b) is a schematic diagram of the measurement pulse signal waveform corresponding to the axial displacement of the comb teeth. Fig. 9 : is a waveform diagram of a capacitance sensing signal, a trigger level signal and a measurement pulse signal according to an embodiment of the present application. Fig. 9 FIG. 8 (a) is a schematic diagram of a waveform of a capacitance sensing signal 901 . Fig. 9 FIG. 8( b ) is a schematic diagram showing comparison waveforms of the capacitance sensing signal 901 and the trigger level signal 902 . Fig. 9 FIG. 5( c ) is a schematic diagram showing the comparison waveforms of the capacitance sensing signal 901 , the trigger level signal 902 and the measurement pulse signal 903 . Fig. 9 Figure (d) is a schematic diagram of the waveform of the measurement pulse signal 903.

[0046] refer to Figures 7 to 9The rotation axis of the aircraft engine turbine blade 700 is 701, and 703 is, for example, a blade disk of the blade. Direction X is the circumferential rotation direction, and direction Y is the circumferential direction. The capacitance sensing signal 901 has a first low peak value amp1 and a second high peak value amp2. Figure 7 The comb teeth 702 and the comb teeth 704 are shown as examples.

[0047] refer to Figure 8 In Figures (a) and (b), when the comb teeth 704 do not undergo axial displacement, the generated measurement pulse signal is u0, where the pulse width is T(0) (or T 0 When the grate teeth undergo an axial displacement of δ1 in the +y direction, the generated measurement pulse signal is u1, where the pulse width is T(δ1) (or T 1 ), the position of the grate teeth is indicated by 704a. When the grate teeth undergo an axial displacement δ2 in the -y direction, the generated measurement pulse signal is u2, where the pulse width is T(δ2) (or T 2 ), the comb teeth position is as indicated by 704b.

[0048] The capacitive sensing signal 901 is generated based on the effective facing area of ​​the first rectangular core pole 101 and the second rectangular core pole 102 with the comb teeth. The capacitive sensing signal 901 gradually rises from the first low peak value amp1 to the second high peak value amp2, and then gradually decreases from the second high peak value amp2 to the first low peak value amp1. As the comb teeth at the edge of the blade rotate, the cycle is repeated. The amplitude amp3 of the trigger level signal 902 is 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), and 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 according to 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 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 a high level Q2.

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

[0051]

[0052] n is a positive integer. k iis the calibration coefficient, or fitting coefficient. T(δ) is the pulse width of the blade grate measurement pulse signal 903 when the blade grate undergoes axial displacement. T(0) is the pulse width of the blade grate measurement pulse signal 903 when no axial displacement occurs.

[0053] For example, when n is 1, δ = k 0 +k 1 *(T(δ)-T(0)). When n is 2, δ=k 0 +k 1 *(T(δ)-T(0))+k 2 *(T(δ)-T(0)) 2 The specific value of n and the measurement result of the axial displacement measurement value δ of the blade grate teeth are finally determined according to factors such as the structure of the grate teeth and the structure of the sensor, and the axial displacement measurement value δ of the blade grate teeth is obtained.

[0054] Fig.10 It is a schematic diagram of the axial displacement measurement state of the comb teeth of an aircraft engine blade according to an embodiment of the present application.

[0055] The present invention also provides an aircraft engine. The aircraft engine includes the aircraft engine blade grate axial displacement measurement system 600, turbine blade 700 and turbine casing (not shown in the figure) as described above. The sensor device 400 is mounted on the turbine casing, for example, it is engaged in a corresponding mounting hole opened on the turbine casing. The radial outer edge of the turbine blade has grate teeth. The first rectangular core pole 101 and the second rectangular core pole 102 face the radial outer edge of the turbine blade. The length of the first rectangular core pole 101 and the second rectangular core pole 102 in the axial direction covers the axial displacement range of the aircraft engine blade grate teeth.

[0056] In some embodiments, one or more sensor devices 400 are provided on the turbine casing corresponding to the outer periphery of the grate teeth of each stage of turbine blades.

[0057] The aircraft engine blade comb tooth axial displacement measurement system and aircraft engine of the present application realize accurate and efficient measurement of the comb tooth axial displacement under the condition of limited circumferential space of the comb teeth through the setting of the sensing device and the corresponding sensing operation process.

[0058] The basic concepts have been described above. Obviously, 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 embodiments of the present application.

[0059] 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.

[0060] Some aspects of the present application can be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software can all be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor can 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. In addition, various aspects of the present application may be expressed as a computer product located in one or more computer-readable media, which includes computer-readable program code.

[0061] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus help understand one or more embodiments of the invention, in the above description of the embodiments of this application, multiple features are sometimes combined into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than the features mentioned in the claims. In fact, the features of the embodiments are less than all the features of the single embodiment disclosed above.

[0062] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions may be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the essential spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. An aircraft engine blade grate axial displacement measurement system, include: Sensing device: The sensing device comprises: a first rectangular core pole; A second rectangular core electrode having the same size as the first rectangular core electrode and forming an angle α with the first rectangular core electrode; A sensing signal output terminal, connected to the first rectangular core electrode and the second rectangular core electrode, and outputting a capacitive sensing signal; A built-in bushing, wherein a first end surface of the built-in bushing has a first opening and a second opening that match the end surface shapes of the first rectangular core pole and the second rectangular core pole; A shell is sleeved on the outside of the built-in bushing, wherein a first end surface of the shell has a French marking line, the French marking line is parallel to a normal direction perpendicular to the radial direction of the blade, and the first rectangular core pole and the second rectangular core pole are symmetrically distributed along the plane where the French marking line is located; The signal conditioning module is configured as: receiving the capacitive sensing signal; Provide trigger level signal; generating a measurement pulse signal according to 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 comb teeth based on the pulse width of the measurement pulse signal.

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

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

4. The aircraft engine blade grate axial displacement measurement system according to claim 3, It is characterized in that Generating a measurement pulse signal according to the capacitance sensing signal and the trigger level signal comprises: 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 aircraft engine blade grate axial displacement measurement system according to claim 4, It is characterized in that Based on the pulse width of the measurement pulse signal, the axial displacement measurement value δ of the blade grate teeth is obtained, which includes: where n is a positive integer, and k i is a calibration coefficient, T(δ) is the pulse width of the measurement pulse signal for the axial displacement of the blade labyrinth teeth, and T(0) is the pulse width of the measurement pulse signal when the blade labyrinth teeth do not have axial displacement.

6. The aircraft engine blade grate axial displacement measurement system according to claim 1, It is characterized in that The sensor device further comprises a flange structure, which is arranged outside the shell and close to the side where the second end surface of the shell is located.

7. The aircraft engine blade grate axial displacement measurement system according to claim 1, It is characterized in that The second end of the built-in bushing has a positioning sawtooth, and the positioning sawtooth cooperates with the second end surface of the shell to assemble and position the French printing line, the first rectangular core pole and the second rectangular core pole.

8. The aircraft engine blade grate axial displacement measurement system according to claim 1, It is characterized in that The material of the first rectangular core electrode and the second rectangular core electrode includes a high temperature alloy.

9. An aircraft engine, comprising the aircraft engine blade grate axial displacement measurement system according to any one of claims 1 to 8; Turbine blades; turbine casing; in, The radial outer edge of the turbine blade has comb teeth; the sensor device is installed on the turbine casing; the first rectangular core pole and the second rectangular core pole face the radial outer edge of the turbine blade; The lengths of the first rectangular core pole and the second rectangular core pole in the axial direction cover the axial displacement range of the aircraft engine blade grate teeth.

10. The aircraft engine according to claim 9, It is characterized in that One or more of the sensing devices are arranged on the turbine casing corresponding to the outer periphery of the comb teeth of each stage of the turbine blades.

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