CN204881989U - Aircraft starter armature sealing performance test fixture - Google Patents
Aircraft starter armature sealing performance test fixture Download PDFInfo
- Publication number
- CN204881989U CN204881989U CN201520591732.2U CN201520591732U CN204881989U CN 204881989 U CN204881989 U CN 204881989U CN 201520591732 U CN201520591732 U CN 201520591732U CN 204881989 U CN204881989 U CN 204881989U
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- CN
- China
- Prior art keywords
- rotor
- hole
- inflator
- fixed head
- base
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- Withdrawn - After Issue
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Abstract
The utility model provides an aircraft starter armature sealing performance test fixture, the frock includes a base, await measuring the examination the rotor arrange in on the base, the fixed plate of a horizontal setting, fixed plate are located the top of base, and the centre of fixed plate is seted up porosely, the connecting rod of many vertical settings, the bottom of connecting rod is connected with the base, and the top is connected with the fixed plate, a vertical setting add the inflator, tertiary shoulder hole that the middle part that adds the inflator is had a perfect understanding about offering, change from small to big according to top -down's order in the aperture of tertiary shoulder hole, the top aperture is equipped with the internal thread to the gas -charging connection that has an external screw thread through internal thread and a vertical setting is connected, and the gas -charging connection passes the hole of offering and stretches out in the middle of the fixed plate, add the inflator clamping between fixed plate and rotor, a gasket, the gasket is located the bottom is downthehole greatly, and the center department of gasket has a through -hole, and the through -hole has the toper groove with the ladder conical surface looks adaptation of rotor axle journal. The utility model discloses can test the sealing performance of starter armature.
Description
Technical field
The utility model relates to a kind of airplane starter rotor seal performance test frock.
Background technology
Airplane starter, full name air turbine starter, for starting aircraft engine.Starter is as rotary machine part, its main parts size comprises rotor, guides, bearing and driving shaft etc., wherein starter armature is core component, and its principle of work is: by introducing the high speed stamping gas impact rotor blade rotor driven High Rotation Speed of starter.Armature spindle end is provided with gear and gear set is meshed, and by gear set transmission driver output axle, thus provides startup required driving torque to engine, starts aircraft engine and rotates.
Existing starter armature as shown in Figure 1, the blade of starter armature 9 one end and impeller are in the work condition environment in dry air chamber, the gear that the other end is installed and gear set are in lubricating cavity, and rotor high-speed rotates, therefore the sealing of rotor 9 under high-speed motion is very crucial, its sealing property often determines the performance and used life of starter, the sealing of rotor 9 adopts the mode of installing diaphragm seal, utilize the step conic 91 of rotor journal to be sealed and matched with sealing sheet, and step conic 91 smooth finish of rotor journal is the key determining sealing property.In sum, effectively judge that the sealing property of rotor is the basic guarantee of whole starter repair quality.
Utility model content
The purpose of this utility model is to provide a kind of easy, reliable starter armature sealing property test fixture, can the sealing property of testing rotor effectively.
The purpose of this utility model takes following technical scheme to be achieved:
A kind of airplane starter rotor seal performance test frock, is characterized in that: described frock comprises
One base, rotor to be tested is placed on described base, and the axle journal of rotor is step conic;
The fixed head of one horizontally set, described fixed head is positioned at the top of described base, and the centre of fixed head is offered porose;
The many connecting links vertically arranged, the bottom of described connecting link is connected with described base, and top is connected with described fixed head;
One vertically arrange add inflator, the described middle part adding inflator offers three grades of shoulder holes of up/down perforation, change from small to big according to top-down order in the aperture of three grades of shoulder holes, wherein, the hole being positioned at top is top aperture, the hole being positioned at middle part is stage casing connecting hole, the hole being positioned at bottom is bottom macropore, top aperture is provided with internal thread, and being connected with externally threaded gas-charging connection of vertically being arranged by internal thread and, gas-charging connection stretches out through the hole offered in the middle of fixed head, gas-charging connection is used for being connected with source of the gas, described aerating jacket casing cartridge rotor, after suit, the step conic of rotor is positioned at described bottom macropore, described adds inflator clip between fixed head and rotor, add the upper end of inflator, lower end respectively with described fixed head and rotor inconsistent,
One diaphragm seal, described diaphragm seal is positioned at described bottom macropore, and the center of diaphragm seal has through hole, and through hole has the taper groove suitable with the step conic of rotor journal, diaphragm seal cover is sleeved on the axle journal of rotor by taper groove, realizes the sealing between diaphragm seal and rotor;
Described frock is inflated to adding in inflator by gas-charging connection, by detecting the sealing property adding inflator and judge between diaphragm seal and rotor in the Leakage Gas situation of bottom macropore.
The hole wall of described stage casing connecting hole vertically offers a ventilation vertical slot.
The ladder place at macropore place, described bottom is also provided with an annular seal groove, for placing O-ring seal.
Described base having a groove or shoulder hole, avoiding it freely to offset for placing described adding inflator thus limit the position adding inflator.
One end of described connecting link is provided with external thread, the end of the other end is provided with threaded hole, the two ends of described fixed head have connecting hole in the corresponding position, one end with described connecting link, one end of described connecting link is passed described connecting hole and is fixedly connected with fixed head by connecting link with nut, described base has counterbore in the other end corresponding position with described connecting link, and a screw is fixedly connected with the other end threaded hole of connecting link through described counterbore.
The bottom surface of described base is provided with four tapped blind holes, and four supporting legs are threaded in described tapped blind hole for supporting described base respectively by its upper end.
Described base is made up of phenolics.
Compared with prior art, the utility model has the advantages that:
The utility model can carry out corresponding improvement to the size adding inflator, and realize the starter armature sealing property of test Multiple Type, frock is durable, can disassembled and assembled freely, upgrading repacking and to repair maintenance process simple and convenient.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft rotor in prior art;
Fig. 2 is cut-open view of the present utility model;
Fig. 3 is application cut-open view of the present utility model;
Fig. 4 is the vertical view of Fig. 3;
Fig. 5 is the cut-open view that the utility model adds inflator;
Fig. 6 is the schematic diagram of the utility model connecting link;
Fig. 7 is the schematic diagram of the utility model base;
Fig. 8 is the D-D cut-open view in Fig. 7;
Fig. 9 is the schematic diagram of the utility model fixed head;
Figure 10 is the schematic diagram of the utility model diaphragm seal;
Figure 11 is the A-A cut-open view in Figure 10.
In figure: 1-adds inflator, 11-tri-grades of shoulder holes, 12-top aperture, 13-bottom macropore, 14-stage casing connecting hole, 15-ventilates vertical slot, 16-seal groove, 2-fixed head, 3-base, 31-shoulder hole, 32-counterbore, 33-tapped blind hole, 34-supporting leg, 4-connecting link, 41-external thread, 42-threaded hole, 5-diaphragm seal, 51-through hole, 52-taper groove, 6-nut, 7-screw, 8-gas-charging connection, 9-rotor, 91-step conic, 10-O-ring seal.
Embodiment
Below in conjunction with accompanying drawing, by embodiment, the utility model is described in further detail.
As shown in Fig. 2 to 11, a kind of airplane starter rotor seal performance test frock, described frock comprises a base 3, and rotor 9 to be tested is placed on described base, and the axle journal of rotor 9 is step conic 91, the fixed head 2 of one horizontally set, described fixed head 2 is positioned at the top of described base 3, and the centre of fixed head 2 is offered porose, the many connecting links 4 vertically arranged, the bottom of described connecting link 4 is connected with described base 3, and top is connected with described fixed head 2, one vertically arrange add inflator 1, the described middle part adding inflator 1 offers three grades of shoulder holes 11 of up/down perforation, change from small to big according to top-down order in the aperture of three grades of shoulder holes 11, wherein, the hole being positioned at top is top aperture 12, the hole being positioned at middle part is stage casing connecting hole 14, the hole being positioned at bottom is bottom macropore 13, top aperture is provided with internal thread, and being connected with externally threaded gas-charging connection 8 of vertically being arranged by internal thread and, gas-charging connection 8 stretches out through the hole offered in the middle of fixed head 2, gas-charging connection 8 is for being connected with source of the gas, described adds inflator 1 rotor bushing 9, after suit, the step conic 91 of rotor 9 is positioned at described bottom macropore 13, described adds inflator 1 clip between fixed head 2 and rotor 9, add the upper end of inflator 1, lower end respectively with described fixed head 2 and rotor 9 inconsistent, the hole wall of stage casing connecting hole 14 vertically offers a ventilation vertical slot 15 to be passed through for allowing gas, one diaphragm seal 5, described diaphragm seal 5 is positioned at described bottom macropore 13, the center of diaphragm seal 5 has through hole 51, through hole 51 has the taper groove 52 suitable with the step conic of rotor journal, diaphragm seal 5 overlaps and is sleeved on the axle journal of rotor by taper groove 52, realize the sealing between diaphragm seal 5 and rotor 9, the ladder place at bottom macropore 13 place is also provided with an annular seal groove 16, for placing the sealing that O-ring seal 10 is strengthened rotor 9 and added between inflator 1, base 3 has a shoulder hole 31, avoid it freely to offset for placing described adding inflator 1 thus limit the position adding inflator, base 3 is made up of phenolics and can be avoided causing cut or damage to rotor 9, described frock is inflated to adding in inflator 1 by gas-charging connection 8, by detecting the sealing property adding inflator and judge between diaphragm seal 5 and rotor 9 in the Leakage Gas situation of bottom macropore 13.Rotor to be arranged in three grades of shoulder holes and to seal with diaphragm seal, and upper end connects with gas-charging connection and not only can realize sealing but also can inflating simultaneously, thus three grades of shoulder holes are become a seal cavity.
One end of described connecting link 4 is provided with external thread 41, the end of the other end is provided with threaded hole 42, the two ends of described fixed head 2 have connecting hole in the corresponding position, one end with described connecting link 4, connecting link 4 is also fixedly connected with fixed head 2 with nut 6 through described connecting hole by one end of described connecting link 4, described base 3 has counterbore 32 in the other end corresponding position with described connecting link 4, one screw 7 is fixedly connected with the other end threaded hole 42 of connecting link 4 through described counterbore 32, the bottom surface of described base 3 is provided with four tapped blind holes 33, article four, supporting leg 34 is threaded in described tapped blind hole 33 for supporting described base 3 respectively by its upper end.
Use principle of the present utility model: when using the utility model to carry out rotor seal performance test, the first step: first the screw that connecting link is connected with base is unloaded, being inserted into from the macropore direction, bottom of three grades of shoulder holes by the rotor of airplane starter adds in three grades of shoulder holes of inflator again, after plug-in mounting completes, the step conic of rotor journal and the taper groove place of diaphragm seal are sealed and matched, then the screw that connecting link is connected with base screwed on and tighten, the screw that the nut of connecting link and fixed head connection or base and connecting link at this moment can be regulated to connect and the elasticity between adjustable fixed head and base, thus the rotor of airplane starter is closely fixed on to add in inflator completes sealing, second step: the gas-charging connection added on inflator is connected with the tracheae of source of the gas, then to adding inflator insufflation gas, because the bottom macropore adding inflator three grades of shoulder holes coordinates with rotor seal, add in inflator can produce air pressure so gas enters into, at this moment tester can add by checking inflator can judge rotor sealing property in the Leakage Gas situation of three grades of shoulder hole bottom macropores, the three grades of shoulder hole bottom macropores adding inflator also can be positioned in water again to adding inflator insufflation gas by tester in addition, can judge that the sealing property of rotor seems more directly perceived according to the degree of bubble like this.
Above-described embodiment of the present utility model is not the restriction to the utility model protection domain; embodiment of the present utility model is not limited thereto; all this kind is according to foregoing of the present utility model; according to ordinary technical knowledge and the customary means of this area; do not departing under the utility model above-mentioned basic fundamental thought prerequisite; to the amendment of other various ways that the utility model said structure is made, replacement or change, all should drop within protection domain of the present utility model.
Claims (7)
1. an airplane starter rotor seal performance test frock, is characterized in that: described frock comprises
One base, rotor to be tested is placed on described base, and the axle journal of rotor is step conic;
The fixed head of one horizontally set, described fixed head is positioned at the top of described base, and the centre of fixed head is offered porose;
The many connecting links vertically arranged, the bottom of described connecting link is connected with described base, and top is connected with described fixed head;
One vertically arrange add inflator, the described middle part adding inflator offers three grades of shoulder holes of up/down perforation, change from small to big according to top-down order in the aperture of three grades of shoulder holes, wherein, the hole being positioned at top is top aperture, the hole being positioned at middle part is stage casing connecting hole, the hole being positioned at bottom is bottom macropore, top aperture is provided with internal thread, and being connected with externally threaded gas-charging connection of vertically being arranged by internal thread and, gas-charging connection stretches out through the hole offered in the middle of fixed head, gas-charging connection is used for being connected with source of the gas, described aerating jacket casing cartridge rotor, after suit, the step conic of rotor is positioned at described bottom macropore, described adds inflator clip between fixed head and rotor, add the upper end of inflator, lower end respectively with described fixed head and rotor inconsistent,
One diaphragm seal, described diaphragm seal is positioned at described bottom macropore, and the center of diaphragm seal has through hole, and through hole has the taper groove suitable with the step conic of rotor journal, diaphragm seal cover is sleeved on the axle journal of rotor by taper groove, realizes the sealing between diaphragm seal and rotor;
Described frock is inflated to adding in inflator by gas-charging connection, by detecting the sealing property adding inflator and judge between diaphragm seal and rotor in the Leakage Gas situation of bottom macropore.
2. airplane starter rotor seal performance test frock according to claim 1, is characterized in that: the hole wall of described stage casing connecting hole vertically offers a ventilation vertical slot.
3. airplane starter rotor seal performance test frock according to claim 1, is characterized in that: the ladder place at macropore place, described bottom is also provided with an annular seal groove, for placing O-ring seal.
4. airplane starter rotor seal performance test frock according to claim 1, is characterized in that: described base has a groove or shoulder hole, avoids it freely to offset for placing described adding inflator thus limit the position adding inflator.
5. according to the arbitrary described airplane starter rotor seal performance test frock of Claims 1-4, it is characterized in that: one end of described connecting link is provided with external thread, the end of the other end is provided with threaded hole, the two ends of described fixed head have connecting hole in the corresponding position, one end with described connecting link, one end of described connecting link is passed described connecting hole and is fixedly connected with fixed head by connecting link with nut, described base has counterbore in the other end corresponding position with described connecting link, one screw is fixedly connected with the other end threaded hole of connecting link through described counterbore.
6. airplane starter rotor seal performance test frock according to claim 5, it is characterized in that: the bottom surface of described base is provided with four tapped blind holes, four supporting legs are threaded in described tapped blind hole for supporting described base respectively by its upper end.
7. airplane starter rotor seal performance test frock according to claim 6, is characterized in that: described base is made up of phenolics.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520591732.2U CN204881989U (en) | 2015-08-07 | 2015-08-07 | Aircraft starter armature sealing performance test fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520591732.2U CN204881989U (en) | 2015-08-07 | 2015-08-07 | Aircraft starter armature sealing performance test fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204881989U true CN204881989U (en) | 2015-12-16 |
Family
ID=54826351
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520591732.2U Withdrawn - After Issue CN204881989U (en) | 2015-08-07 | 2015-08-07 | Aircraft starter armature sealing performance test fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204881989U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043673A (en) * | 2015-08-07 | 2015-11-11 | 广州飞机维修工程有限公司 | Airplane starter rotor sealing performance testing tool |
| CN112670922A (en) * | 2020-10-30 | 2021-04-16 | 沪东中华造船(集团)有限公司 | Temporary sealing method for ship air tightness detection cable penetration piece |
-
2015
- 2015-08-07 CN CN201520591732.2U patent/CN204881989U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043673A (en) * | 2015-08-07 | 2015-11-11 | 广州飞机维修工程有限公司 | Airplane starter rotor sealing performance testing tool |
| CN105043673B (en) * | 2015-08-07 | 2017-08-22 | 广州飞机维修工程有限公司 | A kind of airplane starter rotor seal performance test frock |
| CN112670922A (en) * | 2020-10-30 | 2021-04-16 | 沪东中华造船(集团)有限公司 | Temporary sealing method for ship air tightness detection cable penetration piece |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20151216 Effective date of abandoning: 20170822 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20151216 Effective date of abandoning: 20170822 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |