CN203534813U - Aircraft engine casing intensity test simulation loading redundant force elimination device - Google Patents
Aircraft engine casing intensity test simulation loading redundant force elimination device Download PDFInfo
- Publication number
- CN203534813U CN203534813U CN201320672217.8U CN201320672217U CN203534813U CN 203534813 U CN203534813 U CN 203534813U CN 201320672217 U CN201320672217 U CN 201320672217U CN 203534813 U CN203534813 U CN 203534813U
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- inner chamber
- casing
- annular
- flange
- base
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model relates to an aircraft engine casing intensity test simulation loading redundant force elimination device. The casing is provided with an inner chamber body and an outer chamber body. The outer chamber is provided with an outer chamber upper flange, an outer chamber lower flange and a middle flange. The inner chamber is provided with an inner chamber upper flange, an inner chamber lower flange that extend outside the outer chamber, a base, an annular piston and an annular outer pipe. The outer chamber lower flange and the inner chamber lower flange are sealingly and fixedly disposed on the base. The outer chamber upper flange is fixedly connected with the annular outer pipe. The middle position of the base is fixedly hinged to a pull bar pasting through the inner chamber. The upper end of the pull bar is sleeved with the annular piston. The annular piston is sealingly connected with the inwall of the annular outer pipe. The base is connected with the pull bar, the pull bar is connected with the annular piston, the annular piston is connected with the annular outer pipe, the annular outer pipe is connected with the casing, and the casing is sealingly fixed with the base, so that an internal force closed loop is formed, and superfluous force generated by the casing in a test process is eliminated.
Description
Technical field
The utility model relates to aircraft engine casing strength test simulation loading redundant force cancellation element, belongs to aircraft engine technical field.
Background technology
Along with the development of China's aeronautical technology, the aviation industry of China has been obtained huge progress, yet relates to engine technology aspect, is but a weakness always, is subject to blockade on new techniques abroad.The casing of engine is one of important foundation part of aircraft engine, and the quality of its performance has fatal impact to the running quality of engine, therefore the performance test of aircraft engine casing is just seemed to particularly important.
Because the casing of aircraft engine is generally thin-wall annular part, each cavity is distributed on different surface levels, requires to test under different pressure, that proof strength tests to carry out smoothly difficulty very big.Strength test for casing in prior art adopts the interior mode loading of pressing conventionally, be the cavity two ends that casing is clamped in fixture sealing, adopt large-tonnage servo-cylinder respectively toward the interior injection liquid force feed compressing of interior outer chamber casing simultaneously, by obtaining the mode of the pressure reduction of inside and outside hydraulic oil, obtain the intensity of casing, this mode is comparatively backward undoubtedly, stressing conditions that can only simple analog casing, not only need to guarantee that between different cavitys, string pressure can not occur causes damage to casing, the load range of simulation loading is less simultaneously, is difficult to meet the demand of high strength test.
A kind of aircraft engine casing strength test analog loading device is provided for this reason, by the mode of outside multiple spot mechanical compression, has carried out the stressing conditions of analog synthesis casing, but the mode of mechanical compression often causes the inside of casing to produce redundant force.
Utility model content
The purpose of this utility model is to overcome the problem of above-mentioned prior art, and a kind of aircraft engine casing strength test simulation loading redundant force cancellation element is provided, its can Elimination test process in the inner redundant force producing of casing.
The purpose of this utility model is to be achieved through the following technical solutions:
Aircraft engine casing strength test simulation loading redundant force cancellation element, this casing has inner chamber body and outer chamber, described outer chamber has exocoel upper flange, exocoel lower flange and intermediate flange, described inner chamber body has inner chamber upper flange and the inner chamber lower flange that protrudes out described outer chamber, comprise base, annular piston and annular outer tube, described exocoel lower flange and the sealing of described inner chamber lower flange are fixedly installed on described base, and described exocoel upper flange is fixedly connected with described annular outer tube; The centre position of the described base pull bar that runs through described inner chamber body that is fixedly hinged, described pull bar upper end is arranged with annular piston, and described annular piston is connected with the inner wall sealing of described annular outer tube.
Aircraft engine casing strength test simulation loading redundant force cancellation element described in the utility model, this casing has inner chamber body and outer chamber, described outer chamber has exocoel upper flange, exocoel lower flange and intermediate flange, described inner chamber body has inner chamber upper flange and the inner chamber lower flange that protrudes out described outer chamber, comprise base, annular piston and annular outer tube, described exocoel lower flange and the sealing of described inner chamber lower flange are fixedly installed on described base, and described exocoel upper flange is fixedly connected with described annular outer tube; The centre position of the described base pull bar that runs through described inner chamber body that is fixedly hinged, described pull bar upper end is arranged with annular piston, and described annular piston is connected with the inner wall sealing of described annular outer tube.By base, be connected with pull bar, pull bar is connected with annular piston, and annular piston is connected with annular outer tube, and annular outer tube is connected with casing, and casing is fixed with base seal again, thereby has formed internal force closed loop, has eliminated the inner redundant force producing of casing in process of the test.
Accompanying drawing explanation
Fig. 1 is the perspective view of the simulation loading balance device of aircraft engine casing strength test while being connected with erecting frame;
Fig. 2 removes the perspective view after erecting frame in Fig. 1;
Fig. 3 is that Fig. 2 removes the cut-open view after servo-cylinder.
Embodiment
According to drawings and embodiments the utility model is described in further detail below.
As shown in Figure 1 to Figure 3, the simulation loading balance method of aircraft engine casing strength test, this casing 10 has inner chamber body 1 and outer chamber 2, outer chamber 2 has exocoel upper flange 21, exocoel lower flange 22 and intermediate flange 23, inner chamber body 1 has inner chamber upper flange 11 and the inner chamber lower flange 12 that protrudes out outer chamber 2, intermediate flange 23 has symmetrical the first loading boss 231 and second and loads boss 232, the central shaft of casing of take is X-axis, the first line direction that loads boss and the second loading boss is Y-axis, the horizontal vertical line of take with Y-axis in same level is Z axis, fixedly casing 10, exocoel upper flange 21 applies respectively X axis power F1, symmetrical torsional forces F2 and the F3 tangent with exocoel upper flange 21, the Y-axis side force F4 radially applying along exocoel upper flange 21, inner chamber upper flange 11 applies respectively X axis power F5, with the tangent symmetrical torsional forces F6 of inner chamber upper flange 11 and F7, along the Y-axis side force F8 radially applying and the Z axis side force F9 of inner chamber upper flange 11, first loads boss 231 applies respectively along center flange 23 Y-axis side force F10 radially and the Z axis side force F11 tangent with center flange 23, second loads boss 232 applies respectively along center flange 23 Y-axis side force F12 radially and the Z axis side force F13 tangent with center flange 23, in the same way, all X axis power, symmetrical torsional forces, Y-axis side force and Z axis side force are provided by servo-cylinder respectively the Z axis side force F13 at the Z axis side force F11 at the first loading bench 231 places and the second loading bench place 232.The X axis power F5 that inner chamber upper flange 11 applies comprises symmetrical X axis component F5a and F5b.
As shown in Figure 1 to Figure 3, the simulation loading balance device of aircraft engine casing strength test, this casing 10 has inner chamber body 1 and outer chamber 2, outer chamber 2 has exocoel upper flange 21, exocoel lower flange 22 and intermediate flange 23, inner chamber body 1 has inner chamber upper flange 11 and the inner chamber lower flange 12 that protrudes out outer chamber 2, intermediate flange 23 has symmetrical the first loading boss 231 and second and loads boss 232, the central shaft of casing 10 of take is X-axis, the first line direction that loads boss 231 and the second loading boss 232 is Y-axis, the horizontal vertical line of take with Y-axis in same level is Z axis, exocoel lower flange 21 and 12 sealings of inner chamber lower flange are fixedly installed on base 3, exocoel upper flange 21 is fixedly connected with annular outer tube 4, exocoel upper flange 21 is arranged with respectively and loads connected unit 41a along Y direction with the junction of annular outer tube 4, 41b, the centre position of base 3 pull bar 5 that runs through inner chamber body 1 that is fixedly hinged, inner chamber upper flange 11 is fixedly connected with annular inner tube 6, and the edge of annular inner tube 6 has upwards protruded out support division 61, and the top of abutting part 61 is fixedly connected with clip plate 7, between clip plate 7 and pull bar 5, have gap, pull bar 5 upper ends are arranged with annular piston 8, and annular piston 8 is connected with the inner wall sealing of annular outer tube 4, clip plate 7 along Y direction and Z-direction respectively symmetry protruded out connecting portion 71a, 71b, 71c, 71d, connecting portion 71a, 71b, 71c, 71d run through and extend annular outer tube 4, on clip plate 7, symmetry is installed with installation base 72, and annular outer tube 4 tops are fixedly connected with outer plate 9, and the position of the corresponding installation base 72 of outer plate 9 is provided with opening, the centre position, top of outer plate 9 is along the X-direction servo-cylinder S1 that is fixedly hinged, in order to F1 to be provided, two connect loading bench 41a, 41b along Z-direction be oppositely fixedly hinged respectively servo-cylinder S2, S3, in order to F2, F3 to be provided, one of them connects loading bench 31a along the Y direction servo-cylinder S4 that is fixedly hinged, in order to F4 to be provided, installation base 72 is along X-direction be fixedly hinged servo-cylinder S5a, S5b, in order to F5a, F5b to be provided, two connecting portion 71a, 71b that are positioned at Y direction are along Z-direction be oppositely fixedly hinged servo-cylinder S6, S7, in order to F6, F7 to be provided, one of them connecting portion 71a that is positioned at Y direction is along the Y direction servo-cylinder S8 that is fixedly hinged, in order to F8 to be provided, one of them connecting portion 71c that is positioned at Z-direction is along the Z-direction servo-cylinder S9 that is fixedly hinged, in order to F9 to be provided, first loads boss 231 respectively along Y direction and Z-direction be fixedly hinged servo-cylinder S10, S11, in order to F10, F11 to be provided, second loads boss 232 respectively along Y direction and Z-direction be fixedly hinged servo-cylinder S12, S13, and in order to F10, F11 to be provided, first loads boss 231 and second loads servo-cylinder S11 that boss 232 arranges along Z-direction and S13 in the same way.
This aircraft engine casing strength test simulation loading redundant force cancellation element comprises base, pull bar, annular piston and annular outer tube, annular piston 8 is connected with base 3 by pull bar 5, annular piston 8 is connected with annular outer tube 4, annular outer tube 4 is connected with casing 10, casing 10 is fixing with base 3 sealings again, thereby formed internal force closed loop, eliminated generation redundant force.
The foregoing is only explanation embodiment of the present utility model; be not limited to the utility model; for a person skilled in the art; all within spirit of the present utility model and principle; any modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (1)
1. aircraft engine casing strength test simulation loading redundant force cancellation element, this casing has inner chamber body and outer chamber, described outer chamber has exocoel upper flange, exocoel lower flange and intermediate flange, described inner chamber body has inner chamber upper flange and the inner chamber lower flange that protrudes out described outer chamber, it is characterized in that, comprise base, annular piston and annular outer tube, described exocoel lower flange and the sealing of described inner chamber lower flange are fixedly installed on described base, and described exocoel upper flange is fixedly connected with described annular outer tube; The centre position of the described base pull bar that runs through described inner chamber body that is fixedly hinged, described pull bar upper end is arranged with annular piston, and described annular piston is connected with the inner wall sealing of described annular outer tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320672217.8U CN203534813U (en) | 2013-10-29 | 2013-10-29 | Aircraft engine casing intensity test simulation loading redundant force elimination device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320672217.8U CN203534813U (en) | 2013-10-29 | 2013-10-29 | Aircraft engine casing intensity test simulation loading redundant force elimination device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203534813U true CN203534813U (en) | 2014-04-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320672217.8U Withdrawn - After Issue CN203534813U (en) | 2013-10-29 | 2013-10-29 | Aircraft engine casing intensity test simulation loading redundant force elimination device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203534813U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103604589A (en) * | 2013-10-29 | 2014-02-26 | 无锡市海航电液伺服系统有限公司 | Strength-test analog-loading redundant-force eliminating device for cartridge receiver of aircraft engine |
-
2013
- 2013-10-29 CN CN201320672217.8U patent/CN203534813U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103604589A (en) * | 2013-10-29 | 2014-02-26 | 无锡市海航电液伺服系统有限公司 | Strength-test analog-loading redundant-force eliminating device for cartridge receiver of aircraft engine |
| CN103604589B (en) * | 2013-10-29 | 2018-06-05 | 无锡市海航电液伺服系统股份有限公司 | The extra force eliminating device of aircraft engine casing strength test simulation loading |
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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 | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140409 Effective date of abandoning: 20180605 |