CN203551510U - Magnetic particle testing equipment for aero-engine blade - Google Patents
Magnetic particle testing equipment for aero-engine blade Download PDFInfo
- Publication number
- CN203551510U CN203551510U CN201320639334.4U CN201320639334U CN203551510U CN 203551510 U CN203551510 U CN 203551510U CN 201320639334 U CN201320639334 U CN 201320639334U CN 203551510 U CN203551510 U CN 203551510U
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- Prior art keywords
- blade
- joint
- equipment
- tenon
- holding
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- Expired - Lifetime
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- 239000006249 magnetic particle Substances 0.000 title abstract 6
- 238000007689 inspection Methods 0.000 claims description 61
- 238000009434 installation Methods 0.000 claims description 12
- 238000010276 construction Methods 0.000 claims description 4
- 239000011148 porous material Substances 0.000 claims description 3
- 230000005347 demagnetization Effects 0.000 abstract description 15
- 230000005415 magnetization Effects 0.000 abstract description 12
- 230000035945 sensitivity Effects 0.000 abstract description 8
- 230000000694 effects Effects 0.000 description 10
- 230000007547 defect Effects 0.000 description 9
- 238000000034 method Methods 0.000 description 8
- 230000005389 magnetism Effects 0.000 description 6
- 238000001514 detection method Methods 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
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Abstract
The utility model discloses magnetic particle testing equipment for an aero-engine blade. The equipment comprises an equipment bed body, a magnetizing coil and a device, wherein the magnetizing coil is located on the equipment bed body, and the device is used for enlarging the magnetic particle testing length/diameter ratio of a tested blade; the device mainly comprises a fixing bottom plate, a tenon holding joint, a blade apex holding joint and an extension plate, wherein the fixing bottom plate is used for placing a tooling device on the magnetic particle testing equipment bed body, the tenon holding joint is placed on the fixing bottom plate and is used for holding the tenon end of the tested blade, the blade apex holding joint is used for holding the blade apex end of the tested blade, and the extension plate is placed on the tenon holding joint and is used for enlarging the length/diameter ratio of the tested blade; the mounting direction of the extension plate is opposite to that of the tested blade, the tenon holding joint and the blade apex holding joint are arranged oppositely, either the tenon holding joint or the blade apex holding joint is rotatable, and either the tenon holding joint or the blade apex holding joint is movable. The equipment has the characteristics that the longitudinal magnetization sensitivity is high, the magnetic field intensity for magnetic particle testing is low, the demagnetization is easy, large-sized demagnetization equipment is not required to repeatedly demagnetize, the magnetic particle testing efficiency is high, the applicable range of blade kinds is wide, and the like.
Description
Technical field
The novel blade of aviation engine magnetic inspection technology that relates to of this practicality, more specifically, relates to a kind of equipment for the inspection of blade of aviation engine magnetic.
Background technology
Blade of aviation engine is the very important part of aeromotor, needs block-by-block to carry out magnetic detection (magnetic inspection) before assembling, and will demagnetize after magnetic inspection, to guarantee aeromotor security of operation.Blade of aviation engine magnetic detects and belongs to extraordinary and detect, and the defect that can detect comprises crackle, is mingled with, hairline, folding etc.For ensureing the reliability of magnetic inspection, prevent after part installation because accident appears in defect, need to examine program and standard is carried out magnetic inspection and demagnetization in strict accordance with magnetic.Magnetic inspection is that the stray field producing after utilizing magnetic field to part magnetization attracts magnetic to show the defect that blade exists.Demagnetization refers to that part magnetic examine and rear magnetic is examined to process magnetized part demagnetization.Demagnetization is the work together that must carry out after part magnetic inspection, this be because remanent magnetism can affect the following process of part and pay after use, particularly remanent magnetism can affect the normal work of electronic equipment.In practice, because part demagnetization is dealt with improperly, it is not rarely seen by remanent magnetism, affecting the normal accident of bringing of working of electronic equipment.
In magnetic inspection process, magnetic field intensity is larger, and magnetization effect is just better, and produced simultaneously stray field is also just larger, and the sensitivity of detection is also just higher, and defect also just manifests more clearly.In magnetic inspection, except magnetic field intensity affects magnetic inspection effect, the quality of part longitudinal magnetization effect also seriously restricts magnetic inspection effect, and the quality of part longitudinal magnetization effect depends primarily on the length-diameter ratio of part, the larger magnetization effect of length-diameter ratio is better, and sensitivity is higher, and the demagnetization after the inspection of blade magnetic is also easier, the required demagnetizing field intensity of demagnetizing is also just less, also just lower to the requirement of demagnetizing apparatus.Otherwise still.
Blade of aviation engine of a great variety, length is not of uniform size, and wherein the length-diameter ratio of some part is very little.In the magnetic inspection process of blade, the magnetic field intensity providing due to magnetic spy equipment is enough not large, and the longitudinal magnetization effect of blade is poor, and it is low that magnetic is visited sensitivity, causes defect undetected, detects quality and can not get ensureing, the accident causing because of part defect occurs often.Prior art is in order to overcome the problems referred to above, common way is with providing the magnetic spy equipment of larger magnetic field intensity to carry out magnetic inspection, but this brings problem is demagnetization difficulty, easy residual remanent magnetism, need to use large-scale demagnetizing apparatus to its repeated multiple times demagnetization, to avoid remanent magnetism to produce adverse influence to the use of part.
Utility model content
The problem existing for existing blade magnetic inspection, the novel object of this practicality aims to provide a kind of equipment for the inspection of blade of aviation engine magnetic, low to solve the longitudinal magnetization sensitivity that existing magnetic inspection equipment exists, the blade little for length-diameter ratio carries out magnetic inspection, magnetic field intensity is large, and demagnetization difficulty, need to be used the repeated multiple times demagnetization of large-scale demagnetizing apparatus, magnetic inspection efficiency is low, and the kind that is suitable for blade such as lacks at the problem.
The novel basic thought of this practicality is by a kind of device that can expand detected blade length-diameter ratio is provided, and the magnetic inspection equipment that solves prior art carries out for the little blade of length-diameter ratio the problem that magnetic inspection exists.
The novel equipment for blade of aviation engine magnetic inspection side providing of this practicality, its formation mainly comprises equipment bed body, be arranged on the magnetizing coil on equipment bed body and expand blade magnetic the device of examining length-diameter ratio, described device comprises: for device being placed in to the fixed base plate on magnetic inspection equipment bed body, be placed on fixed base plate and hold joint for the tenon of holding tested blade tenon one end, for the blade tip of holding tested blade tip one end, hold joint, and be placed in tenon and hold joint for increasing the extension plate of tested blade length-diameter ratio, the installation direction of extension plate is contrary with the installation direction of tested blade, tenon is held joint and blade tip and is held joint and be oppositely arranged, both are one of at least for can hold the rotating rotatable joint of holding of tested blade, and both are one of at least for moving the removable joint of holding that regulates installation site with respect to the other side.
In order to realize better goal of the invention, this practicality is novel also can further take following technical measures.Following technical measures can be taked to implement individually, and also capable of being combined taking implemented, and take even in the lump to implement.
In the novel technique scheme of this practicality, preferably described tenon being held to joint design is that rotatable tenon is held joint, described blade tip is held to joint design and hold joint for blade tip movably.Certainly also tenon can be held joint and blade tip hold joint be designed to simultaneously revolution hold joint and be designed to the removable joint of holding simultaneously.Described rotatable tenon is held the connecting structure of holding of joint and is paid the utmost attention to and adopt the draw bail being fixedly connected with blade tenon.Described removable blade tip is held the connecting structure of holding of joint and is paid the utmost attention to adopt and hold structure.The described structure that holds can be held the addendum cone of joint and forms by being fixed on the apical pore on the fixed block of blade tip and forming removable blade tip.
In the novel technique scheme of this practicality, described removable blade tip is held to be designed with between the base of joint and fixed base plate and is made blade tip hold joint relative to tenon, to hold joint and move the guide rail sliding pair that regulates installation site, to adapt to the blade of different length.Described guide rail sliding pair can be considered to be designed to form by being positioned at two guide rails on fixed base plate and being positioned at the slide construction that removable blade tip holds on joint base.Two guide rails that are positioned on fixed base plate are preferably guide-track groove, and being positioned at the slide construction that removable blade tip holds on joint base is two protruding rails.In blade magnetic when inspection,, removable blade tip is fixed on fixed base plate by set bolt after holding joint and moving into place by guide rail sliding pair.
In the novel technique scheme of this practicality, in order to reduce the weight of device, described fixed base plate can design some for alleviating the hole of fixed base plate weight; Described mobile blade tip is held on the supporting plate of joint and is designed some holes of holding joint weight for alleviating mobile blade tip.
The novel equipment for the inspection of blade of aviation engine magnetic providing of this practicality, by the device of its specially designed expansion blade magnetic inspection length-diameter ratio, at tenon, hold joint the plate face direction extension plate contrary with tested direction blade is set, increased the magnetic inspection length of tested blade, expanded the length-diameter ratio of blade, thereby solved existing blade magnetic inspection equipment completely, the longitudinal magnetization weak effect existing for the blade magnetic inspection of leaflet footpath ratio, magnetic inspection sensitivity is low, easily cause defect undetected, detect quality and can not get ensureing, the accident problem causing because of part defect occurs often.Because the device of the novel expansion blade magnetic inspection length-diameter ratio of this practicality has improved blade longitudinal magnetization sensitivity, make to detect the magnetic field intensity that equal length-diameter ratio blade needs little, it is easy that magnetic inspection retreats magnetic-capacity, avoided remanent magnetism to produce adverse influence to the use of part, and the blade after demagnetization does not need to use large-scale demagnetizing apparatus to magnetic inspection carries out repeated multiple times demagnetization, greatly reduce demagnetization difficulty, improved magnetic inspection work efficiency.
The novel equipment for the inspection of blade of aviation engine magnetic providing of this practicality, blade magnetic inspection equipment compared to prior art sums up has following very outstanding technique effect:
1) reliability: the device of the special expansion blade magnetic inspection length-diameter ratio arranging has increased the magnetic inspection length-diameter ratio of tested blade, has strengthened the magnetization effect of blade longitudinal magnetization, has improved magnetic inspection sensitivity, has effectively prevented the undetected of defect, has guaranteed the quality detecting.
2) high efficiency: the blade tenon joint that expands blade magnetic inspection length-diameter ratio device is rotatable tenon joint, can realize the detection of whole blade after tested blade one-step installation, clamps mounting parts after not needing blade to be changed to face more again, has improved the efficiency of work.
3) versatility: to the blade of different size of the same type, can change tenon and hold joint, only need to regulate tenon to hold bayonet socket on joint can to realize the clamping of blade part.For the different blade of length, by removable blade tip, hold joint mobile adjusting position on fixed base plate guide-track groove, can realize the clamping of part.
4) reliability, maintainability, safety and human factors: the various parts of this device are all simple mechanical apparatus, are easy for installation and maintenance, and the difficulty of maintenance and cost are all lower, and be not easy infringement.
Accompanying drawing explanation
Fig. 1 is the main TV structure schematic diagram for blade of aviation engine magnetic inspection equipment.
Fig. 2 is the plan structure schematic diagram for blade of aviation engine magnetic inspection equipment.
In above-mentioned accompanying drawing, the object of each shown by reference numeral sign is respectively: 1-fixed base plate; 2-blade tip is held joint; 3-tenon is held joint; 4-extension plate; 5-fixed block; 6-is detected blade; 7 guide-track grooves; 8-magnetizing coil.
Embodiment
Below in conjunction with accompanying drawing explanation, provide the novel embodiment of this practicality, and be further described this practicality is novel by embodiment, so that people understand this practicality is more easily novel.But it needs to be noted; the novel embodiment of this practicality is not limited to the described form of embodiment below; those skilled in the art is not in the situation that paying creative work; also can design easily other embodiment; therefore the embodiment of embodiment given below should be interpreted as to the protection domain that this practicality is novel, protection domain novel this practicality is limited in to given embodiment.
Embodiment 1
The equipment for the inspection of blade of aviation engine magnetic of the present embodiment, its structure as depicted in figs. 1 and 2, it forms mainly by equipment bed body, be arranged on the magnetizing coil 8 on equipment bed body and expand blade magnetic the device formation of examining length-diameter ratio, wherein said device comprises: for device being placed in to the fixed base plate 1 on magnetic inspection equipment bed body, be placed on fixed base plate and hold joint 3 for the tenon of holding tested blade tenon one end, for the blade tip of holding tested blade tip one end, hold joint 2, and be placed in the extension plate 4 that tenon holds on joint for increasing tested blade magnetic inspection length-diameter ratio and form, the installation direction of extension plate is contrary with the installation direction of tested blade, tenon is held joint and blade tip and is held joint and be oppositely arranged.It is that rotatable tenon is held joint that described tenon is held joint, and it holds connecting structure is the draw bail being fixedly connected with blade tenon.Described blade tip is held joint and is held joint for blade tip movably, and blade tip is held the connecting structure of holding of joint and held the addendum cone of joint and form by being fixed on the apical pore on the fixed block 5 of blade tip and forming mobile blade tip; The moving structure that blade tip is held joint is guide rail sliding pair between base and fixed base plate, and sliding pair forms by being positioned at two guide-track grooves on fixed base plate 7 and being positioned at two protruding rails that removable blade tip holds on joint base.Described fixed base plate 1 and described removable blade tip are held on the supporting plate of joint and are designed with some holes for alleviator weight.When blade 6 carries out magnetic inspection, be suspended from magnetizing coil 8.The length of described extension plate 4 is greater than the length of tested blade, makes the length-diameter ratio of blade magnetic inspection be greater than 2.
Claims (10)
1. the equipment for the inspection of blade of aviation engine magnetic, comprise equipment bed body and be arranged on the magnetizing coil on equipment bed body, it is characterized in that being provided with the device that expands blade magnetic inspection length-diameter ratio, this device mainly comprises: for device being placed in to the fixed base plate (1) on magnetic inspection equipment bed body, be placed on fixed base plate and hold joint (3) for the tenon of holding tested blade (6) tenon one end, for the blade tip of holding tested blade tip one end, hold joint (2), and be placed in tenon and hold joint for increasing the extension plate (4) of tested blade length-diameter ratio, the installation direction of extension plate is contrary with the installation direction of tested blade, tenon is held joint and blade tip and is held joint and be oppositely arranged, both are one of at least for can hold the rotating rotatable joint of holding of tested blade, and both are one of at least for moving the removable joint of holding that regulates installation site with respect to the other side.
2. the equipment for the inspection of blade of aviation engine magnetic according to claim 1, is characterized in that it is the rotatable joint of holding that tenon is held joint, and it is that removable blade tip is held joint that blade tip is held joint.
3. the equipment for the inspection of blade of aviation engine magnetic according to claim 2, is characterized in that it is fixed connection structure that described rotatable tenon is held the connecting structure of holding of joint.
4. the equipment for blade of aviation engine magnetic inspection according to claim 2, what it is characterized in that described removable blade tip holds joint holds connecting structure for holding structure.
5. the equipment for blade of aviation engine magnetic inspection according to claim 4, holds structure and holds the addendum cone of joint and form by being fixed on the apical pore on the fixed block of blade tip and forming mobile blade tip described in it is characterized in that.
6. the equipment for blade of aviation engine magnetic inspection according to claim 2, is characterized in that described removable blade tip is held between joint base and fixed base plate (1) to be designed with guide rail sliding pair.
7. the equipment for blade of aviation engine magnetic inspection according to claim 6, is characterized in that described guide rail sliding pair holds the slide construction matching with two guide rails on joint base and form by being positioned at two guide rails on fixed base plate and being positioned at removable blade tip.
8. the equipment for blade of aviation engine magnetic inspection according to claim 7, two guide rails that it is characterized in that being positioned on fixed base plate are two guide-track grooves, being positioned at the slide construction that removable blade tip holds on joint base is two protruding rails.
9. according to the equipment for the inspection of blade of aviation engine magnetic one of claim 1 to 8 Suo Shu, it is characterized in that described fixed base plate (1) is designed with some for alleviating the hole of fixed base plate weight.
10. according to the equipment for blade of aviation engine magnetic inspection one of claim 1 to 8 Suo Shu, it is characterized in that described blade tip is held on the supporting plate of joint (2), to be designed with some holes of holding joint weight for alleviating blade tip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320639334.4U CN203551510U (en) | 2013-10-16 | 2013-10-16 | Magnetic particle testing equipment for aero-engine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320639334.4U CN203551510U (en) | 2013-10-16 | 2013-10-16 | Magnetic particle testing equipment for aero-engine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203551510U true CN203551510U (en) | 2014-04-16 |
Family
ID=50469607
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320639334.4U Expired - Lifetime CN203551510U (en) | 2013-10-16 | 2013-10-16 | Magnetic particle testing equipment for aero-engine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203551510U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104181224A (en) * | 2014-05-06 | 2014-12-03 | 北京理工大学 | Engine turbine blade flaw ACFM (Alternating Current Field Measurement) excitation platform |
| CN105388209A (en) * | 2015-12-21 | 2016-03-09 | 中核核电运行管理有限公司 | High-sensitivity fluorescent magnetic particle examination equipment for turbine blades |
| CN106710783A (en) * | 2016-12-10 | 2017-05-24 | 无锡银联齿轮传动机械有限公司 | Movable demagnetizing pressure plate assembly of machine for cleaning handle tubes before plating |
| CN106783014A (en) * | 2016-12-10 | 2017-05-31 | 无锡银联齿轮传动机械有限公司 | The handle pipe demagnetization mechanism of handle pipe cleaning before copper plating machine |
| CN103529119B (en) * | 2013-10-16 | 2017-05-31 | 成都发动机（集团）有限公司 | Improve the device of magnetic testing sensitivity of aviation engine blade |
-
2013
- 2013-10-16 CN CN201320639334.4U patent/CN203551510U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103529119B (en) * | 2013-10-16 | 2017-05-31 | 成都发动机（集团）有限公司 | Improve the device of magnetic testing sensitivity of aviation engine blade |
| CN104181224A (en) * | 2014-05-06 | 2014-12-03 | 北京理工大学 | Engine turbine blade flaw ACFM (Alternating Current Field Measurement) excitation platform |
| CN105388209A (en) * | 2015-12-21 | 2016-03-09 | 中核核电运行管理有限公司 | High-sensitivity fluorescent magnetic particle examination equipment for turbine blades |
| CN106710783A (en) * | 2016-12-10 | 2017-05-24 | 无锡银联齿轮传动机械有限公司 | Movable demagnetizing pressure plate assembly of machine for cleaning handle tubes before plating |
| CN106783014A (en) * | 2016-12-10 | 2017-05-31 | 无锡银联齿轮传动机械有限公司 | The handle pipe demagnetization mechanism of handle pipe cleaning before copper plating machine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140416 |
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| CX01 | Expiry of patent term |