CN105043673A - Airplane starter rotor sealing performance testing tool - Google Patents
Airplane starter rotor sealing performance testing tool Download PDFInfo
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- CN105043673A CN105043673A CN201510483042.XA CN201510483042A CN105043673A CN 105043673 A CN105043673 A CN 105043673A CN 201510483042 A CN201510483042 A CN 201510483042A CN 105043673 A CN105043673 A CN 105043673A
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- rotor
- hole
- inflator
- fixed head
- connecting link
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Abstract
The invention discloses an airplane starter rotor sealing performance testing tool, comprising a pedestal, a transversely-arranged fixed plate, a plurality of vertically-arranged connection rods, a vertically-arranged air feeding cylinder, and a sealing sheet. A rotor to be tested is installed on pedestal; the transversely-arranged fixed plate is arranged above the pedestal; a hole is formed in the middle portion of the fixed plate; the bottom ends of the connection rods are connected to the pedestal and the top ends of the connection rods are connected to the fixed plate; the middle portion of the air-feeding cylinder is provided with three-stage stepped holes passing through the upper side and the lower side; the apertures of the three-stage stepped holes are gradually increased from the top to the bottom; the small hole on the top is provided with an internal thread and is connected to a vertically-arranged air inflation connector provided with an external thread; the air inflation connector passes through and projects out of the hole formed in the middle of the fixed plate, and the air-feeding cylinder is claimed between the fixed plate and the rotor; the sealing sheet is positioned inside the big hole on the bottom; the center of the sealing sheet is provided with a through hole which has a conical groove matched with the stepped conical surface . The airplane starter rotor sealing energy testing tool is used for testing the sealing of the starter rotor.
Description
Technical field
The present invention 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.
Summary of the invention
The object of this invention is to provide a kind of easy, reliable starter armature sealing property test fixture, can the sealing property of testing rotor effectively.
The object of the invention is to take 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 is to have 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, advantage of the present invention is:
The present invention 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 invention;
Fig. 3 is application cut-open view of the present invention;
Fig. 4 is the vertical view of Fig. 3;
Fig. 5 is the cut-open view that the present invention adds inflator;
Fig. 6 is the schematic diagram of connecting link of the present invention;
Fig. 7 is the schematic diagram of base of the present invention;
Fig. 8 is the D-D cut-open view in Fig. 7;
Fig. 9 is the schematic diagram of fixed head of the present invention;
Figure 10 is the schematic diagram of diaphragm seal of the present invention;
Figure 11 is the A-A cut-open view in Fig. 8.
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 invention will be further described.
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 invention: when using the present invention 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.
The above embodiment of the present invention is not limiting the scope of the present invention; embodiments of the present invention are not limited thereto; all this kind is according to foregoing of the present invention; according to ordinary technical knowledge and the customary means of this area; do not departing under the present invention's above-mentioned basic fundamental thought prerequisite; to the amendment of other various ways that said structure of the present invention is made, replacement or change, all should drop within protection scope of the present invention.
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 is to have 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 |
|---|---|---|---|
| CN201510483042.XA CN105043673B (en) | 2015-08-07 | 2015-08-07 | A kind of airplane starter rotor seal performance test frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510483042.XA CN105043673B (en) | 2015-08-07 | 2015-08-07 | A kind of airplane starter rotor seal performance test frock |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105043673A true CN105043673A (en) | 2015-11-11 |
| CN105043673B CN105043673B (en) | 2017-08-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510483042.XA Active CN105043673B (en) | 2015-08-07 | 2015-08-07 | A kind of airplane starter rotor seal performance test frock |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106706233A (en) * | 2016-12-25 | 2017-05-24 | 重庆德运模具制造有限公司 | Hole-by-hole airtightness verification tool for multiple blind holes on part |
| CN109084941A (en) * | 2018-07-12 | 2018-12-25 | 广东井得电机有限公司 | A kind of starter leakage detection apparatus |
| CN111546280A (en) * | 2020-04-23 | 2020-08-18 | 广州飞机维修工程有限公司 | Aircraft starting drive assembly equipment frock of obturating |
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| JP2004279088A (en) * | 2003-03-13 | 2004-10-07 | Sumitomo Wiring Syst Ltd | Inspecting device |
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2015
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106706233A (en) * | 2016-12-25 | 2017-05-24 | 重庆德运模具制造有限公司 | Hole-by-hole airtightness verification tool for multiple blind holes on part |
| CN106706233B (en) * | 2016-12-25 | 2023-03-31 | 重庆完镁镁制品有限公司 | Hole-by-hole air tightness inspection tool for multiple blind holes in part |
| CN109084941A (en) * | 2018-07-12 | 2018-12-25 | 广东井得电机有限公司 | A kind of starter leakage detection apparatus |
| CN111546280A (en) * | 2020-04-23 | 2020-08-18 | 广州飞机维修工程有限公司 | Aircraft starting drive assembly equipment frock of obturating |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105043673B (en) | 2017-08-22 |
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