CN110966054A - Easily-ground layer and preparation method thereof - Google Patents
Easily-ground layer and preparation method thereof Download PDFInfo
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- CN110966054A CN110966054A CN201811156070.0A CN201811156070A CN110966054A CN 110966054 A CN110966054 A CN 110966054A CN 201811156070 A CN201811156070 A CN 201811156070A CN 110966054 A CN110966054 A CN 110966054A
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- layer
- abradable
- worn
- wear detection
- wear
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
- G01N27/02—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating impedance
- G01N27/04—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating impedance by investigating resistance
- G01N27/041—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating impedance by investigating resistance of a solid body
Abstract
The invention relates to an easily-ground layer and a preparation method thereof. The easily-abraded layer is suitable for an aeroengine, the aeroengine comprises a signal circuit, a plurality of abrasion detection layers are formed on the easily-abraded layer along the direction of an abrasion path, conductive wires are arranged in the abrasion detection layers, and the conductive wires are connected to the signal circuit; in the wearing process of the easily-worn layer, the wearing detection layer gradually wears to cause the disconnection of the conductive wire, and the signal circuit detects the resistance value change of the conductive wire to indicate the wearing state of the easily-worn layer. The invention provides an easily-abraded layer, which can conveniently detect the abrasion degree of the easily-abraded layer, thereby avoiding serious accidents caused by abrasion of the easily-abraded layer and improving the safety performance.
Description
Technical Field
The invention relates to the field of aero-engine structure design, in particular to an easily-abraded layer and a preparation method thereof.
Background
With the continuous development of science and technology, the clearance between the rotor and the stator of some rotary machines is smaller and smaller, because the clearance has important influence on the performance of equipment, once the clearance becomes smaller, the rotor is more likely to collide and rub with the stator, and this kind of collision and rub between rotor and the stator is very unfavorable for the safe operation of equipment. In order to avoid serious adverse influence caused by collision and abrasion, the easy-abrasion block is widely applied between the rotor and the stator, when the rotor and the stator are collided and abraded, the easy-abrasion block is gradually abraded, before the easy-abrasion block is completely abraded, the rotor and the stator cannot cause safety influence due to collision and abrasion, and therefore the easy-abrasion block is widely applied. In particular in the field of aircraft engines for structural design of aircraft, abradable layers are applied in a plurality of places between the rotor and the stator.
The easy-to-wear layer belongs to a quick-wear part, if the easy-to-wear layer is worn more and is not found, once the metal between the rotor and the stator is rubbed, the operation safety of the equipment is seriously influenced. Therefore, wear information of the abradable layer is very important, but obtaining such information is very difficult, mainly because wear information is usually obtained by visual inspection. In order to see the wear of the wearing layer, it is necessary to disassemble equipment, such as complex equipment like aircraft engines, which is very difficult to disassemble. If the abrasion information of the abrasion layer cannot be checked in time, the safety hazard still exists in the aircraft engine.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides the easily-abraded layer, which can conveniently detect the abrasion degree of the easily-abraded layer, thereby avoiding serious accidents caused by abrasion of the easily-abraded layer and improving the safety performance.
The easily-abraded layer comprises a signal circuit, a plurality of abrasion detection layers are formed on the easily-abraded layer along the direction of an abrasion path, conductive wires are arranged in the abrasion detection layers, and the conductive wires are connected to the signal circuit;
in the wearing process of the easily-worn layer, the wearing detection layer gradually wears to cause the conductive wire to be disconnected, and the signal circuit detects the resistance value change of the conductive wire to indicate the wearing state of the easily-worn layer.
According to one embodiment of the invention, the conductive filaments are embedded in the abradable layer.
According to one embodiment of the invention, several of the wear detection layers are at different thicknesses of the abradable layer.
According to one embodiment of the invention, the conductive filaments of several of the wear detection layers are connected in parallel into the signal circuit.
According to one embodiment of the invention, the abradable layer is disposed between a casing and a rotor blade of the aircraft engine.
The present invention also provides a method of preparing an abradable layer having a plurality of wear detection layers, the method comprising:
step S1: adhering a conductive wire to a substrate;
step S2: a groove is formed in the easy-to-wear layer of the easy-to-wear block along the direction perpendicular to the wear path;
step S3: inserting the substrate into the trench;
step S4: and sealing the groove by using a sealant.
According to one embodiment of the invention, the substrate is an abradable insulating sheet.
The invention also provides another method for preparing the easily-abraded layer, wherein the easily-abraded layer is provided with a plurality of abrasion detection layers, the method comprises the steps of forming each abrasion detection layer of the easily-abraded layer in a spraying mode, placing the conductive wires when each easily-abraded layer is sprayed to a set thickness, continuing spraying to bury the conductive wires, and forming the abrasion detection layers.
The easily-abraded layer and the preparation method thereof provided by the invention have the advantages that the structure is compact, the preparation is convenient, the easily-abraded layer is connected into a signal circuit, the abrasion degree of the easily-abraded layer can be conveniently detected, so that serious accidents caused by abrasion of the easily-abraded layer are avoided, and the safety performance is improved.
It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the invention as claimed.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principle of the invention. In the drawings:
FIG. 1 illustrates a state diagram of the use of an abradable layer in accordance with one embodiment of the invention.
FIG. 2 shows a schematic structural view of a portion of an abradable layer of one embodiment of the invention.
Fig. 3 shows a schematic flow chart of a method for preparing an abradable layer according to an embodiment of the invention.
Fig. 4 shows a schematic structural view of an abradable layer of one embodiment of the present invention.
Wherein the figures include the following reference numerals:
Second wear detection layer 203 third wear detection layer 204
Fourth wear detection layer 205 fifth wear detection layer 206
Second conductive yarn 209 third conductive yarn 210
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
In the description of the present application, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are used for convenience of description and simplicity of description only, and in the case of not making a reverse description, these directional terms do not indicate and imply that the device or element being referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore, should not be considered as limiting the scope of the present application; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of protection of the present application is not to be construed as being limited. Further, although the terms used in the present application are selected from publicly known and used terms, some of the terms mentioned in the specification of the present application may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Further, it is required that the present application is understood not only by the actual terms used but also by the meaning of each term lying within.
FIG. 1 illustrates a state diagram of the use of an abradable layer in accordance with one embodiment of the invention. As shown in the drawing, in the field of aircraft engines designed for aircraft construction, a stator blade 102 is provided on a stator gate 101, an abradable layer 200 is provided between a rotor blade 103 and the stator blade 102, and an abradable layer 200 is also provided between the stator gate 101 and the rotor blade 103. It is understood that the abradable layer 200 may be disposed around the stator gate 101, generally in the shape of a ring. During the operation of the aircraft engine, the rotor blade 103 and the stator gate 101 and the stator blade 102 rotate relatively, and the easy-to-wear layer 200 maintains the clearance between the rotor blade 103 and the stator gate 101 and the stator blade 102. When the aircraft engine runs for a period of time, gaps between some rotor blades 103 and the stator gate 101 and the stator blades 102 become smaller, and once the gaps become smaller, the rotor blades 103 rub against the abradable layer 200, so that the abradable layer 200 is abraded. When the easily-abraded layer 200 is completely abraded, the rotor blade 103, the stator gate 101 and the stator blade 102 are abraded, so that the normal operation of the space engine is affected, and severe adverse effects are caused.
FIG. 2 shows a schematic structural view of a portion of an abradable layer of one embodiment of the invention. Illustrated is a portion of the abradable layer 200. The abradable layer 200 forms a number of wear detection layers 201 in the direction of the wear path. The abradable layer 200 in this embodiment has 3 wear detection layers 201, and on the wear path from far to near are a first wear detection layer 202, a second wear detection layer 203, and a third wear detection layer 204, respectively. The abradable layer 200 may also include a fourth abradable layer 205 and a fifth abradable layer 206. Within each wear detection layer 201 is a conductive filament 207, schematically labeled as conductive filaments 207 disposed on the first to third wear detection layers 202 to 204. Therein, a first conductive thread 208 is provided within the first wear detection layer 202, a second conductive thread 209 is provided within the second wear detection layer 203, and a third conductive thread 210 is provided within the third wear detection layer 204. It is readily understood that the fourth abradable layer 205 and the fifth abradable layer 206 may have similar structures and will not be described in detail.
Conventionally, an aircraft engine includes signal circuitry. The conductive filaments 207 of each wear detection layer 201 can be connected to the signal circuit to form a loop.
In the operation process of the aircraft engine, as the gap between the stator blade 102 and the rotor blade 103 is reduced, the easily-abraded layer 200 is abraded, and the abrasion detection layer 201 is gradually abraded to break the conductive wire 207. The signal circuit is capable of detecting a change in resistance of the conductive filaments 207 to indicate the wear state of the abradable layer 200. It should be noted that a person skilled in the art can design such a signal circuit, which can detect the change of the resistance value of the conductive wire 207 by the principle of the present invention, and therefore, more details about the signal circuit are not described in detail herein. The signal circuit may be arranged outside the aircraft engine's engine brake, in other words, the conductive wire 207 may extend out of the engine brake. The easily-worn layer 200 and the signal circuit equivalently form a wear sensor, so that the wear condition of the easily-worn layer 200 can be conveniently detected on line, the gap distance between the stator casing 101, the stator blade 102 and the rotor blade 103 is displayed, direct collision between the stator casing 101 and the stator blade 102 is avoided, and the safety performance is improved.
As shown, the wear process of the abradable layer 200 is generally outside-in, from the first abradable layer 202 to the fifth abradable layer 206, assuming the distal first wear detection layer 202 is in the initial position of wear. When the abradable layer 200 is not in use or before the first wear detection layer 202 is unworn, the first conductive filament 208 is intact, and the signal circuit will indicate that the resistance value of the first conductive filament 208 of the first wear detection layer 202 is at a minimum or in an unworn state. When the first wear detection layer 202 is worn, the first conductive wires 208 are broken, and the signal circuit detects that the corresponding resistance value is greatly increased and indicates that the easily-worn layer 200 is slightly worn, i.e., the first wear detection layer 202 is worn. When the second wear detection layer 203 is worn and the second conductive wires 209 are broken, the signal circuit detects that the corresponding resistance value continues to increase greatly and indicates moderate wear of the easily-worn layer 200, that is, the second wear detection layer 203 is worn. When the third wear detection layer 204 is worn, the third conductive wire 210 is damaged and disconnected, and the signal circuit detects that the corresponding resistance value continues to be increased greatly and indicates that the easily-worn layer 200 is heavily worn, that is, the third easily-worn layer 204 is worn. At this time, corresponding maintenance work, such as repairing and replacing the abradable layer 200, is required. If the fourth easy-to-wear layer 205 or the fifth easy-to-wear layer 206 is worn, the signal circuit can send out a serious alarm to remind a worker to process as soon as possible so as to avoid accidents.
Preferably, the conductive filaments 207 are embedded within the wear detection layer 201. The conductive filaments 207 may be arranged in any routing manner within the abradable layer 201, such as in an S-shaped arrangement.
Preferably, the thickness of each of the abradable layers 201 is the same, i.e., the thickness of each of the first wear detection layer 202, the second wear detection layer 203, the third wear detection layer 204, the fourth wear detection layer 205, and the fifth wear detection layer 206 is the same. The wear degree reflected by the signal circuit is uniformly increased. More preferably, adjacent conductive filaments 207 are spaced apart the same distance.
Preferably, the electrical characteristics of the conductive filaments 207 of the plurality of abradable layers 201 are the same. Conventionally, the conductive filaments 207 in each of the abradable layers 201 have the same resistance value.
Preferably, the conductive wires 207 of the plurality of easily-worn layers 201 are connected to the signal circuit in a parallel manner, so that the signal circuit can conveniently detect which easily-worn layer 203 the easily-worn block 200 is worn to, and the corresponding operation is conveniently performed by a worker.
Fig. 3 shows a schematic flow chart of a method for preparing an abradable layer according to an embodiment of the invention. FIG. 4 shows a schematic structural diagram of a wear detection layer of one embodiment of the present invention. Referring to fig. 3 and 4, a method 300 of preparing an abradable layer 200, the abradable layer 200 having a plurality of wear detection layers 201, the method 300 comprising:
step S1: the conductive wires 207 are adhered to the substrate 211, and two cut-off portions of the conductive wires 207 are exposed outside the substrate 211, thereby facilitating subsequent connection with a signal circuit.
Step S2: grooves 212 are opened in the wear detection layer 201 of the abradable layer 200 in a direction perpendicular to the wear path. The groove 212 may also be understood as a slot that opens on the wear detection layer 201, as long as the substrate 211 can be accommodated. In practice, a groove 212 may be formed in each wear detection layer 201 of the abradable layer 200.
Step S3: substrate 211 is inserted into trench 212.
Step S4: the trench 212 is sealed with a sealant.
The easy-to-wear layer 200 can be conveniently manufactured by the preparation method 300 so as to satisfy the condition that the conductive wire 207 is provided in each easy-to-wear layer 201.
Preferably, the substrate 211 is an abrasion-prone insulating sheet.
The present invention also provides another method of making the abradable layer 200. The abradable layer 200 has a number of wear detection layers 201. The preparation method includes forming each wear detection layer 201 of the easily-wearable layer 200 by spraying. Specifically, the easily abradable layer 200 is manufactured by spraying, another wear detection layer 201 is sprayed on one wear detection layer 201, and the wear detection layers 201 of the easily abradable layer 200 are manufactured by lamination. In the process of spray forming each wear detection layer 201, when the conductive wire 207 is sprayed to a set thickness, the conductive wire 207 is placed on the spraying material, the spraying is continued to bury the conductive wire 207 in the spraying material, and the spraying is continued to form an easily-worn layer 201 with the conductive wire 207. The easily-abraded layer 200 can be also easily manufactured by the manufacturing method so as to satisfy the condition that the conductive wire 207 is provided in each wear detection layer 201 of the easily-abraded layer 200.
It will be apparent to those skilled in the art that various modifications and variations can be made to the above-described exemplary embodiments of the present invention without departing from the spirit and scope of the invention. Thus, it is intended that the present invention cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents.
Claims (8)
1. An easily-abraded layer is suitable for an aeroengine and comprises a signal circuit, wherein a plurality of abrasion detection layers are formed on the easily-abraded layer along the direction of an abrasion path, conductive wires are arranged in the abrasion detection layers, and the conductive wires are connected to the signal circuit;
in the wearing process of the easily-worn layer, the wearing detection layer gradually wears to cause the conductive wire to be disconnected, and the signal circuit detects the resistance value change of the conductive wire to indicate the wearing state of the easily-worn layer.
2. The abradable layer of claim 1, wherein the conductive filaments are embedded within the abradable layer.
3. The abradable layer of claim 1, wherein a number of the wear detection layers are disposed at different thicknesses of the abradable layer.
4. The abradable layer of claim 1, wherein the conductive filaments of several of the wear detection layers are connected in parallel to the signal circuit.
5. The abradable layer of claim 1, wherein the abradable layer is disposed within a case of the aircraft engine between the case and a rotor blade.
6. A method of making an abradable layer having a plurality of wear detection layers, the method comprising:
step S1: adhering a conductive wire to a substrate;
step S2: a groove is formed in the wear detection layer of the easily-worn layer along the direction perpendicular to the wear path;
step S3: inserting the substrate into the trench;
step S4: and sealing the groove by using a sealant.
7. The abradable layer of claim 6, wherein the substrate is an abradable insulation sheet.
8. A method for preparing an easily-worn layer is provided with a plurality of wear detection layers, and comprises the steps of forming each wear detection layer of the easily-worn layer in a spraying mode, placing conductive wires when the easily-worn layer is sprayed to a set thickness, and continuing spraying to bury the conductive wires to form the wear detection layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811156070.0A CN110966054A (en) | 2018-09-30 | 2018-09-30 | Easily-ground layer and preparation method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811156070.0A CN110966054A (en) | 2018-09-30 | 2018-09-30 | Easily-ground layer and preparation method thereof |
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| CN110966054A true CN110966054A (en) | 2020-04-07 |
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| CN201811156070.0A Pending CN110966054A (en) | 2018-09-30 | 2018-09-30 | Easily-ground layer and preparation method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112343855A (en) * | 2021-01-08 | 2021-02-09 | 中国航发上海商用航空发动机制造有限责任公司 | Aeroengine and method for evaluating blade tip clearance of aeroengine on wing |
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| US20060056960A1 (en) * | 2002-09-23 | 2006-03-16 | Siemens Westinghouse Power Corporation | Apparatus and method of detecting wear in an abradable coating system |
| US20090243585A1 (en) * | 2008-03-25 | 2009-10-01 | General Electric Company | Systems for inspection of shrouds |
| WO2010135011A1 (en) * | 2009-05-21 | 2010-11-25 | Siemens Energy, Inc. | Sensor for quantifying increasing reduction wear on a surface |
| US9939247B1 (en) * | 2016-12-05 | 2018-04-10 | United Technologies Corporation | Embedded sensor for in-situ monitoring of blade tip incursion |
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| US20030020496A1 (en) * | 2000-07-06 | 2003-01-30 | Eyraud Jean-Louis | Play measuring sensor by multiple depth abrasion |
| US20050158511A1 (en) * | 2002-09-23 | 2005-07-21 | Siemens Westinghouse Power Corporation | Wear monitoring system with embedded conductors |
| US20060056960A1 (en) * | 2002-09-23 | 2006-03-16 | Siemens Westinghouse Power Corporation | Apparatus and method of detecting wear in an abradable coating system |
| US20090243585A1 (en) * | 2008-03-25 | 2009-10-01 | General Electric Company | Systems for inspection of shrouds |
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| US9939247B1 (en) * | 2016-12-05 | 2018-04-10 | United Technologies Corporation | Embedded sensor for in-situ monitoring of blade tip incursion |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112343855A (en) * | 2021-01-08 | 2021-02-09 | 中国航发上海商用航空发动机制造有限责任公司 | Aeroengine and method for evaluating blade tip clearance of aeroengine on wing |
| CN112343855B (en) * | 2021-01-08 | 2021-03-26 | 中国航发上海商用航空发动机制造有限责任公司 | Aeroengine and method for evaluating blade tip clearance of aeroengine on wing |
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Application publication date: 20200407 |