CN103592111A - Simulation load balancing method and device for aircraft engine crankcase strength tests - Google Patents
Simulation load balancing method and device for aircraft engine crankcase strength tests Download PDFInfo
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- CN103592111A CN103592111A CN201310520444.3A CN201310520444A CN103592111A CN 103592111 A CN103592111 A CN 103592111A CN 201310520444 A CN201310520444 A CN 201310520444A CN 103592111 A CN103592111 A CN 103592111A
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Abstract
The invention relates to a simulation load balancing method and device for aircraft engine crankcase strength tests. According to the method, X-axis force, symmetrical torque force, Y-axis lateral force and Z-axis lateral force are provided for different positions of a crankcase through a servo oil cylinder, and thus the stress conditions of the crankcase are synthesized. The method is reliably verified due to the fact that the device is provided with the servo oil cylinder, an annular outer pipe, an annular inner pipe, an annular piston, a pull rod, an inner pressing plate and an outer pressing plate. With the simulation load balancing method and device for aircraft engine crankcase strength tests, the stress conditions of the crankcase can be effectively simulated, the simulated loaded load range is wide, and thus the requirements of high-strength tests are met.
Description
Technical field
The simulation loading balance method and the device that the present invention relates to the strength test of a kind of aircraft engine casing, belong 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.
Summary of the invention
The object of the invention is to overcome the problem of above-mentioned prior art, simulation loading balance method and the device of the strength test of a kind of aircraft engine casing are provided, it can realize the stressing conditions of effective simulation casing, and the load range of simulation loading is larger simultaneously, can meet the demand of high strength test.
The object of the invention is to be achieved through the following technical solutions:
The simulation loading balance method of aircraft engine casing strength test, 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, described intermediate flange has symmetrical the first loading boss and second and loads boss, the central shaft of casing of take is X-axis, the described first line direction that loads boss and described the second loading boss is Y-axis, the horizontal vertical line of take with Y-axis in same level is Z axis, fixing described casing, described exocoel upper flange applies respectively X axis power, the symmetrical torsional forces tangent with described exocoel upper flange, the Y-axis side force radially applying along described exocoel upper flange, described inner chamber upper flange applies respectively X axis power, with the tangent symmetrical torsional forces of described inner chamber upper flange, along the Y-axis side force radially applying and the Z axis side force of described inner chamber upper flange, described first loads boss applies respectively along described center flange Y-axis side force radially and the Z axis side force tangent with described center flange, described second loads boss applies respectively along described center flange Y-axis side force radially and the Z axis side force tangent with described center flange, 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 at the Z axis side force at described the first loading bench place and described the second loading bench place.
Further, the X axis power that described inner chamber upper flange applies comprises symmetrical X axis component.
The simulation loading balance device of aircraft engine casing strength test, 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, described intermediate flange has symmetrical the first loading boss and second and loads boss, the central shaft of casing of take is X-axis, the described first line direction that loads boss and described the second loading boss is Y-axis, the horizontal vertical line of take with Y-axis in same level is Z axis, described exocoel lower flange and the sealing of described inner chamber lower flange are fixedly installed on base, described exocoel upper flange is fixedly connected with annular outer tube, the junction of described exocoel upper flange and described annular outer tube is arranged with respectively loading connected unit along Y direction, the centre position of the described base pull bar that runs through described inner chamber body that is fixedly hinged, described inner chamber upper flange is fixedly connected with annular inner tube, and the edge of described annular inner tube has upwards protruded out support division, and the top of described abutting part is fixedly connected with clip plate, between described clip plate and described pull bar, have gap, 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, described clip plate along Y direction and Z-direction respectively symmetry protruded out connecting portion, described connecting portion runs through and extends described annular outer tube, on described clip plate, symmetry is installed with installation base, and described annular outer tube top is fixedly connected with outer plate, and the position of the corresponding described installation base of described outer plate is provided with opening, the centre position, top of described outer plate is along the X-direction servo-cylinder that is fixedly hinged, and two connect loading bench along the Z-direction servo-cylinder that is oppositely fixedly hinged respectively, and one of them connects loading bench along the Y direction servo-cylinder that is fixedly hinged, described installation base is along the X-direction servo-cylinder that is fixedly hinged, two connecting portions that are positioned at Y direction are along the Z-direction servo-cylinder that is oppositely fixedly hinged, one of them connecting portion that is positioned at Y direction is along the Y direction servo-cylinder that is fixedly hinged, and one of them connecting portion that is positioned at Z-direction is along the Z-direction servo-cylinder that is fixedly hinged, described first loads boss respectively along Y direction and the Z-direction servo-cylinder that is fixedly hinged, described second loads boss respectively along Y direction and the Z-direction servo-cylinder that is fixedly hinged, and described first loads boss and described second loads servo-cylinder that boss arranges along described Z-direction in the same way.
Further, described annular piston is provided with the through hole that matches with described abutting part, and described abutting part runs through described through hole and is connected with described clip plate.
Further, described servo-cylinder and erecting frame are fixedly hinged.
Simulation loading balance method and the device of aircraft engine casing of the present invention strength test, the method is by adopting servo-cylinder to provide respectively X axis power, symmetrical torsional forces, Y-axis side force and Z axis side force to the diverse location of casing, thus the stressing conditions of synthetic casing; This device is by the setting of servo-cylinder, annular outer tube, annular inner tube, annular piston, pull bar, clip plate and outer plate, thus reliable authentication the method.Simulation loading balance method and the device of the strength test of this aircraft engine casing, realized the stressing conditions of effective simulation casing, and the load range of simulation loading is larger simultaneously, met the demand of high strength test.
Accompanying drawing explanation
Fig. 1 is the perspective view of the simulation loading balance device of aircraft engine casing of the present invention 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 present invention is described in further detail below.
As shown in Figure 1 to Figure 3, the simulation loading balance method of the aircraft engine casing strength test described in the embodiment of the present invention, 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, fixing described 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.
The foregoing is only explanation embodiments of the present invention; be not limited to the present invention, for a person skilled in the art, within the spirit and principles in the present invention all; any modification of doing, be equal to replacement, improvement etc., within protection scope of the present invention all should be included in.
Claims (5)
1. the simulation loading balance method of aircraft engine casing strength test, 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, described intermediate flange has symmetrical the first loading boss and second and loads boss, the central shaft of casing of take is X-axis, the described first line direction that loads boss and described the second loading boss is Y-axis, the horizontal vertical line of take with Y-axis in same level is Z axis, it is characterized in that, fixing described casing,
Described exocoel upper flange apply respectively X axis power, with the tangent symmetrical torsional forces of described exocoel upper flange, the Y-axis side force radially applying along described exocoel upper flange;
Described inner chamber upper flange applies respectively X axis power, with the tangent symmetrical torsional forces of described inner chamber upper flange, along the Y-axis side force radially applying and the Z axis side force of described inner chamber upper flange;
Described first loads boss applies respectively along described center flange Y-axis side force radially and the Z axis side force tangent with described center flange;
Described second loads boss applies respectively along described center flange Y-axis side force radially and the Z axis side force tangent with described center flange;
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 at the Z axis side force at described the first loading bench place and described the second loading bench place.
2. the simulation loading balance method of aircraft engine casing as claimed in claim 1 strength test, is characterized in that, the X axis power that described inner chamber upper flange applies comprises symmetrical X axis component.
3. the simulation loading balance device of aircraft engine casing strength test, 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, described intermediate flange has symmetrical the first loading boss and second and loads boss, the central shaft of casing of take is X-axis, the described first line direction that loads boss and described the second loading boss is Y-axis, the horizontal vertical line of take with Y-axis in same level is Z axis, it is characterized in that, described exocoel lower flange and the sealing of described inner chamber lower flange are fixedly installed on base,
Described exocoel upper flange is fixedly connected with annular outer tube, and the junction of described exocoel upper flange and described annular outer tube is arranged with respectively loading connected unit along Y direction; The centre position of the described base pull bar that runs through described inner chamber body that is fixedly hinged, described inner chamber upper flange is fixedly connected with annular inner tube, and the edge of described annular inner tube has upwards protruded out support division, and the top of described abutting part is fixedly connected with clip plate; Between described clip plate and described pull bar, have gap, 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;
Described clip plate along Y direction and Z-direction respectively symmetry protruded out connecting portion, described connecting portion runs through and extends described annular outer tube; On described clip plate, symmetry is installed with installation base, and described annular outer tube top is fixedly connected with outer plate, and the position of the corresponding described installation base of described outer plate is provided with opening;
The centre position, top of described outer plate is along the X-direction servo-cylinder that is fixedly hinged, and two connect loading bench along the Z-direction servo-cylinder that is oppositely fixedly hinged respectively, and one of them connects loading bench along the Y direction servo-cylinder that is fixedly hinged;
Described installation base is along the X-direction servo-cylinder that is fixedly hinged, two connecting portions that are positioned at Y direction are along the Z-direction servo-cylinder that is oppositely fixedly hinged, one of them connecting portion that is positioned at Y direction is along the Y direction servo-cylinder that is fixedly hinged, and one of them connecting portion that is positioned at Z-direction is along the Z-direction servo-cylinder that is fixedly hinged;
Described first loads boss respectively along Y direction and the Z-direction servo-cylinder that is fixedly hinged; Described second loads boss respectively along Y direction and the Z-direction servo-cylinder that is fixedly hinged, and described first loads boss and described second loads servo-cylinder that boss arranges along described Z-direction in the same way.
4. the simulation loading balance device of aircraft engine casing as claimed in claim 3 strength test, is characterized in that, described annular piston is provided with the through hole that matches with described abutting part, and described abutting part runs through described through hole and is connected with described clip plate.
5. the simulation loading balance device of aircraft engine casing as claimed in claim 4 strength test, is characterized in that, described servo-cylinder and erecting frame are fixedly hinged.
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| CN201310520444.3A CN103592111B (en) | 2013-10-29 | 2013-10-29 | The simulation loading balance method and device of aircraft engine casing strength test |
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| CN107063695A (en) * | 2017-04-26 | 2017-08-18 | 中国燃气涡轮研究院 | A kind of aeroengine combustor buring room water-cooled casing reinforcement structure |
| CN109211497A (en) * | 2018-07-11 | 2019-01-15 | 中国航发沈阳发动机研究所 | A kind of full stator fulcrum dynamic stiffness test exciting force loading device of engine |
| CN110095240A (en) * | 2018-01-30 | 2019-08-06 | 中国航发商用航空发动机有限责任公司 | Turbogenerator casing stiffness test secondary load device |
| CN110726541A (en) * | 2019-10-15 | 2020-01-24 | 中国航发沈阳发动机研究所 | Large-bypass-ratio aero-engine intermediate casing strength test device |
| CN112630055A (en) * | 2021-03-09 | 2021-04-09 | 天津航天瑞莱科技有限公司 | Aeroengine case thermal-static coupling test system |
| CN112798437A (en) * | 2020-12-28 | 2021-05-14 | 中国航发沈阳发动机研究所 | Intermediate casing test load loading device |
| CN112945533A (en) * | 2021-02-06 | 2021-06-11 | 中国航发沈阳发动机研究所 | Combined loading device and method for aeroengine parts |
| CN114001966A (en) * | 2021-11-11 | 2022-02-01 | 中国船舶重工集团公司第七0三研究所 | Test bed for starting and performance test of gas turbine casing |
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| CN112798437A (en) * | 2020-12-28 | 2021-05-14 | 中国航发沈阳发动机研究所 | Intermediate casing test load loading device |
| CN112798437B (en) * | 2020-12-28 | 2024-01-02 | 中国航发沈阳发动机研究所 | Intermediate case test load loading device |
| CN112945533A (en) * | 2021-02-06 | 2021-06-11 | 中国航发沈阳发动机研究所 | Combined loading device and method for aeroengine parts |
| CN112630055A (en) * | 2021-03-09 | 2021-04-09 | 天津航天瑞莱科技有限公司 | Aeroengine case thermal-static coupling test system |
| CN114001966A (en) * | 2021-11-11 | 2022-02-01 | 中国船舶重工集团公司第七0三研究所 | Test bed for starting and performance test of gas turbine casing |
| CN114001966B (en) * | 2021-11-11 | 2023-12-08 | 中国船舶重工集团公司第七0三研究所 | Test bed for starting and performance test of fuel engine casing |
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