CN110095240B - Auxiliary loading device for rigidity test of turbine engine case - Google Patents
Auxiliary loading device for rigidity test of turbine engine case Download PDFInfo
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- CN110095240B CN110095240B CN201810089471.2A CN201810089471A CN110095240B CN 110095240 B CN110095240 B CN 110095240B CN 201810089471 A CN201810089471 A CN 201810089471A CN 110095240 B CN110095240 B CN 110095240B
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- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0041—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining deflection or stress
- G01M5/005—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining deflection or stress by means of external apparatus, e.g. test benches or portable test systems
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Abstract
The invention aims to provide an auxiliary loading device for a rigidity test of a turbine engine casing, which can be used for loading tension-compression, bending and torsional rigidity tests. The loading disc is provided with a loading center which is coaxial with the tested casing; the upper end of the upper switching section is connected with the loading disc, and the lower end of the upper switching section is used for being connected with the upper end of the tested casing; the upper end of the lower switching section is used for connecting the lower end of the tested casing; the grounding disc is used for being fixed on the foundation and is connected with the lower end of the lower connecting section; the vertical actuating cylinders are arranged in the vertical direction, one ends of the vertical actuating cylinders are respectively connected to vertical loading points of the loading disc, and the vertical loading points are symmetrically distributed by taking a loading center as a center; the horizontal actuating cylinders are arranged in the horizontal direction, one end of each horizontal actuating cylinder is connected to a horizontal loading point on the loading disc, the horizontal loading points are arranged in the diameter direction of the loading disc, one horizontal loading point is positioned in the loading center, and the rest horizontal loading points are symmetrically distributed by taking the loading center as the center; the support beam is used for mounting the horizontal actuating cylinder.
Description
Technical Field
The invention relates to a turbine engine test device, in particular to an auxiliary loading device for realizing a turbine engine casing rigidity test.
Background
The stator casing of the aero-engine is a framework of the engine, the casing is mostly designed to be a thin-wall cylinder structure along with the development of high rotating speed and high thrust-weight ratio of the aero-engine, the rigidity is weak, the rigidity of the casing has great influence on the supporting rigidity and critical rotating speed of a rotor, the rigidity of the casing can also influence the arrangement of vibration measuring points of the whole engine, and along with the development of a finite element technology, the finite element analysis of parts and the whole engine is widely applied to engineering practice, but the model check and calibration of a finite element model are necessary to be carried out on the basis of rigidity characteristic test data, so the rigidity test of the casing is necessary to obtain the rigidity characteristic of the casing.
The rigidity test of the aeroengine case comprises tension and compression rigidity, bending rigidity and torsional rigidity test, the aeroengine case is mostly of a thin-wall cylinder structure, and an auxiliary loading device is needed to realize loading when the rigidity test is carried out.
The auxiliary loading device for the rigidity test is less in disclosure at present and is not suitable for an aeroengine casing structure. Therefore, an auxiliary loading device suitable for the rigidity test of the aero-engine casing needs to be designed for carrying out the rigidity test.
Disclosure of Invention
The invention aims to provide an auxiliary loading device for a rigidity test of a turbine engine casing, which can be used for loading tension-compression, bending and torsional rigidity tests.
In the auxiliary loading device for the rigidity test of the turbine engine casing, the loading disc is provided with a loading center which is coaxial with the tested casing; the upper end of the upper switching section is connected with the loading disc, and the lower end of the upper switching section is used for being connected with the upper end of the tested casing; the upper end of the lower switching section is used for connecting the lower end of the tested casing; the grounding disc is used for being fixed on the foundation and is connected with the lower end of the lower connecting section; the plurality of vertical actuating cylinders are arranged in the vertical direction, one ends of the plurality of vertical actuating cylinders are respectively connected to vertical loading points of the loading disc, and the vertical loading points are symmetrically distributed by taking the loading center as the center; the horizontal actuating cylinders are arranged in the horizontal direction, one end of each horizontal actuating cylinder is connected to a horizontal loading point on a loading disc, the horizontal loading points are arranged in the diameter direction of the loading disc, one horizontal loading point is positioned in the loading center, and the rest horizontal loading points are symmetrically distributed by taking the loading center as the center; the support beam is used for mounting the horizontal actuating cylinder.
In one embodiment, the vertical load points are respectively arranged on two diameters of the load disc perpendicular to each other with the load center as a center, and are used for connecting with the vertical actuating cylinders.
In one embodiment, the support beam is mounted on a guide rail and can be horizontally moved to adjust the position.
In one embodiment, the vertical ram includes a threaded adapter that is secured by a nut through a hole at the vertical load point.
In one embodiment, the horizontal ram includes a threaded adapter, and a loading tab is disposed at the horizontal loading point, the adapter being connected to the loading tab.
In one embodiment, the vertical ram or the horizontal ram includes a base, a cylinder coupled to the base, a force sensor coupled to an upper end of the cylinder, a ram extension extending upward from the force sensor, and a threaded adapter coupled to the ram extension.
In one embodiment, to ensure that the tensile and compressive loads applied to the case are equal when the bending stiffness test is loaded, the force of the vertical ram that is subjected to the tensile load needs to be added to the weight of the load plate and the vertical ram, and the force of the vertical ram that is subjected to the compressive load needs to be subtracted from the weight of the load plate and the vertical ram.
The beneficial effect of the aforesaid scheme:
1. the auxiliary loading device is suitable for the rigidity test of the aero-engine casing structure.
2. The auxiliary loading of the tension-compression, bending and torsional rigidity tests of the aero-engine casing structure can be respectively carried out.
3. And loading the bending moment and the torque into the force.
4. In order to ensure the loading correctness of axial tension and compression rigidity and bending rigidity load, the vertical actuating cylinders are uniformly and symmetrically distributed along the loading disc.
5. In order to ensure that the loading load action point in the torsional rigidity and lateral (vertical) rigidity tests is in the circle center of the loading disc, the loading action surfaces of the three loading lugs are positioned on the diameter of the loading disc, the two actuating cylinders in the torsional rigidity tests are symmetrically distributed, and the loading actuating cylinders in the lateral (vertical) rigidity tests are positioned at the circle center of the loading disc. Therefore, only one side of each actuator cylinder is designed with a test support beam, and the parallelism of the two actuator cylinders is easy to keep consistent.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a perspective view of a turbine engine case stiffness test auxiliary loading device;
FIG. 2 is a front view of a turbine engine case stiffness test auxiliary loading device;
FIG. 3 is a perspective view of a loading tray;
FIG. 4 is a top view of a load tray;
FIG. 5 is a front view of the ram;
fig. 6 is a number diagram of load points on a load tray.
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.
It is to be noted that the drawings are designed solely as examples and are not to scale and should not be construed as limiting the scope of the invention as it may be practiced otherwise than as specifically claimed.
As shown in fig. 1 and 2, the auxiliary loading device for the turbine engine casing stiffness test comprises an upper transition section 2 connected with the upper end of a tested casing 1, a lower transition section 3 connected with the lower end of the tested casing 1, a grounding disc 4 (preferably with a radial T-shaped slot disc) fixed on a foundation, a # 1 actuator cylinder 5, a # 2 actuator cylinder 6, a # 3 actuator cylinder 7, a # 4 actuator cylinder 8, a # 5 actuator cylinder 9, a # 6 actuator cylinder 10, a # 7 actuator cylinder 11, a loading disc 12, a test support beam 13 and a support beam moving guide rail 14. The 1# actuator cylinder 5, the 2# actuator cylinder 6, the 3# actuator cylinder 7, and the 4# actuator cylinder 8 are vertical actuator cylinders arranged in the vertical direction. The 5# ram 9, the 6# ram 10, and the 7# ram 11 are horizontal rams and are arranged in the horizontal direction. The tested casing 1 is fixed on a grounding disc 4 through a lower switching section 3 and is connected with a loading disc 12 through an upper switching section. The loading disc 12, the upper connecting section 2, the tested casing 1, the lower connecting section 3 and the grounding disc 4 are connected through bolts and the like. The test carriage beam 13 is movable on the guide rails 14 and the 5# -7 # rams 9, 10, 11 are movable on the test carriage beam 13.
As shown in fig. 5, each ram has substantially the same structure, including a base 27, a barrel 28, a force sensor 29, a ram extension 30, and a threaded adapter 31. The adapter at the top of the actuating cylinder is provided with threads, so that the actuating cylinder can be conveniently connected with other structures. The base 27 may be supported directly on the foundation or connected to the support beam 13. The cylinder 28 is fitted to the base 27 and is hydraulically driven. The ram extension 30 extends upwardly from a force sensor 29. the force sensor 29 may be provided as part of the cylinder 28 for sensing the force output by the ram. The upper end of the ram extension 30 is connected to an adapter 31.
The 1# -4 # rams 5, 6, 7, 9 are connected to the load plate 12 via their extensions 30, and the 5# -7 # rams 9, 10, 11 are connected to the load plate 12 via their extensions.
As shown in fig. 1, the origin of coordinates is the center of the loading tray 12, the X-axis is the positive direction of the casing in the direction from the vertical direction to the outside, the Y-axis is the positive direction of the casing in the direction from the lateral direction to the right, and the Z-axis is the positive direction of the casing in the axial direction.
As shown in fig. 3, 4, and 6, the loading tray 12 is provided with: the connecting bolt hole for the 1# actuator cylinder and the loading disc 15, the connecting bolt hole for the 2# actuator cylinder and the loading disc 16, the connecting bolt hole for the 3# actuator cylinder and the loading disc 17, the connecting bolt hole for the 4# actuator cylinder and the loading disc 18, the loading lug 19 of the 5# actuator cylinder, the loading lug 20 of the 6# actuator cylinder, the loading lug 21 of the 7# actuator cylinder, the connecting bolt hole for the 5# actuator cylinder and the loading lug 22, the connecting bolt hole for the 6# actuator cylinder and the loading lug 23, the connecting bolt hole for the 7# actuator cylinder and the loading lug 24, the hoisting hole for the loading disc 25 and the connecting bolt hole for the adapter section and the loading disc. And a hoisting hole 25 is further formed in the loading disc 12, so that hoisting is facilitated. In order to ensure the loading correctness of the axial tension and compression stiffness and the bending stiffness load, the 1# -4 # actuating cylinders 5, 6, 7 and 8 are uniformly and symmetrically distributed along the loading disc 12, for example, the 1# -3 # actuating cylinders 5 and 7 are positioned on the Y axis and symmetrically distributed, and the 2# -4 # actuating cylinders 6 and 8 are positioned on the Y axis and symmetrically distributed. In order to ensure that the loading load acting point in the torsional rigidity and lateral (vertical) rigidity tests is at the circle center of the loading disc 12, the loading acting surfaces of the three loading lugs 20, 21 and 19 are positioned on the diameter of the loading disc 12, the 5# actuator cylinder 9 and the 7# actuator cylinder 11 are positioned on the Y axis and are symmetrically distributed, and the 6# actuator cylinder 10 is positioned at the circle center of the loading disc 12. Therefore, only one side of each actuator cylinder is designed with a test support beam, and the parallelism of the two actuator cylinders is easy to keep consistent.
The following brief description of the implementation process for the case stiffness test loading is made with reference to the accompanying drawings:
the loading process of the Z-direction (axial) tension and compression stiffness of the casing comprises the following steps: the 1#, 2#, 3#, and 4# actuators simultaneously perform Z-direction (axial) tension or compression, and apply Z-direction tension or compression loads, and the loads applied by the four actuators are the same.
The loading process of the X-direction (vertical) tension and compression rigidity of the casing is as follows: the 6# ram is stretched or compressed in the X direction (vertical direction) and a tensile or compressive load in the X direction is applied. If a Y-direction (lateral) rigidity test is carried out, the casing or the loading disc can be rotated by 90 degrees for loading and testing.
1# actuator cylinder 5, 2# actuator cylinder 6, 3# actuator cylinder 7, 4# actuator cylinder 8, 5# actuator cylinder 9, 6# actuator cylinder 10, 7# actuator cylinder 11
The loading process of the bending rigidity of the casing in the X direction (vertical direction) comprises the following steps: the two symmetric rams 1# and 3# are axially tensioned and compressed, respectively, for example, the 1# ram applies a tensile load, the 3# ram applies a compressive load, or the two rams may be switched. To ensure that the tensile and compressive loads applied to the receiver are equal, the force of the ram in the tensile load needs to be added to the weight of the load plate and ram, and the force of the ram in the compressive load needs to be subtracted from the weight of the load plate and ram.
The loading process of the Y-direction (lateral) bending stiffness of the casing comprises the following steps: the two symmetric cylinders 2# and 4# are respectively stretched and compressed along the axial direction, for example, the 2# cylinder applies tensile load, the 4# cylinder applies compressive load, or the two cylinders can be exchanged, and the loads are equal. To ensure that the tensile and compressive loads applied to the receiver are equal, the force of the ram in the tensile load needs to be added to the weight of the load plate and ram, and the force of the ram in the compressive load needs to be subtracted from the weight of the load plate and ram.
The loading process of the torsional rigidity of the casing in the Z direction (axial direction) comprises the following steps: the two symmetric rams 5# and 7# are respectively stretched and compressed along the X direction (lateral direction), for example, the 5# ram applies a tensile load, the 7# ram applies a compressive load, or the two rams apply the same load.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (7)
1. Turbine engine machine casket rigidity test assists loading device, its characterized in that includes:
the loading disc is provided with a loading center which is coaxial with the tested casing;
the upper end of the upper switching section is connected with the loading disc, and the lower end of the upper switching section is used for being connected with the upper end of the tested casing;
the upper end of the lower switching section is used for connecting the lower end of the tested casing;
the grounding disc is fixed on the foundation and connected with the lower end of the lower connecting section;
the vertical actuating cylinders are arranged in the vertical direction, one ends of the vertical actuating cylinders are respectively connected to vertical loading points of the loading disc, the vertical loading points corresponding to the vertical actuating cylinders are circumferentially and symmetrically distributed by taking the loading center as the center, and the two symmetrical vertical actuating cylinders are respectively stretched and compressed along the axial direction so as to realize the bending rigidity loading process of the casing in the vertical direction or the lateral direction;
the horizontal actuating cylinders are arranged in the horizontal direction, one end of each horizontal actuating cylinder is connected to a horizontal loading point on a loading disc, the horizontal loading points are arranged in the diameter direction of the loading disc, one horizontal loading point is located at the loading center, the other horizontal loading points are symmetrically distributed by taking the loading center as the center, and the two symmetrical horizontal actuating cylinders are stretched and compressed respectively to provide an axial torsional rigidity loading process; and
and the support beam is used for mounting the horizontal actuating cylinder.
2. The turbine engine case stiffness test auxiliary loading device according to claim 1, wherein the vertical loading points are respectively arranged centering on the loading center in two diameter directions in which the loading discs are perpendicular to each other, for connecting with the vertical actuator cylinder.
3. The turbine engine case stiffness test auxiliary loading device according to claim 1, wherein the bracket beam is mounted on a guide rail and can be horizontally moved to adjust the position.
4. The turbine engine case stiffness test auxiliary loading unit of claim 1, wherein the vertical ram includes a threaded adapter that is secured by a nut through a hole at the vertical loading point.
5. The turbine engine case stiffness test auxiliary loading device as claimed in claim 1, wherein the horizontal actuator cylinder comprises a threaded adapter, a loading tab is disposed at the horizontal loading point, and the adapter is connected with the loading tab.
6. The turbine engine case stiffness test auxiliary loading unit of claim 1, wherein the vertical ram or the horizontal ram includes a base, a cylinder coupled to the base, a force sensor coupled to an upper end of the cylinder, a ram extension extending upwardly from the force sensor, and a threaded adapter coupled to the ram extension.
7. The turbine engine case stiffness test auxiliary loading device of claim 1, wherein in order to ensure equal tensile and compressive loads are applied to the case during bending stiffness test loading, the force of the vertical ram that is subject to tensile load needs to be added to the weight of the loading plate and the vertical ram, and the force of the vertical ram that is subject to compressive load needs to be subtracted from the weight of the loading plate and the vertical ram.
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| CN201810089471.2A CN110095240B (en) | 2018-01-30 | 2018-01-30 | Auxiliary loading device for rigidity test of turbine engine case |
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| CN201810089471.2A CN110095240B (en) | 2018-01-30 | 2018-01-30 | Auxiliary loading device for rigidity test of turbine engine case |
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| CN110095240B true CN110095240B (en) | 2020-12-15 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110514428B (en) * | 2019-09-24 | 2021-03-26 | 中国人民解放军空军工程大学 | Bidirectional loading test platform for aviation connection structure test piece |
| CN111157250B (en) * | 2020-01-06 | 2021-11-19 | 中国航发沈阳发动机研究所 | Stress application barrel structure strength tester for axisymmetric thrust vector complex load |
| 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 |
| CN112985787B (en) * | 2021-02-01 | 2022-10-28 | 中国航发沈阳发动机研究所 | Card installing mechanism for high-temperature test of case |
| CN112945533B (en) * | 2021-02-06 | 2023-01-17 | 中国航发沈阳发动机研究所 | Combined loading device and method for aeroengine parts |
| CN116026695A (en) * | 2021-04-01 | 2023-04-28 | 中国航发常州兰翔机械有限责任公司 | Application method of aeroengine casing pressure test tool |
| CN115266347B (en) * | 2022-07-27 | 2023-05-16 | 中国航发沈阳发动机研究所 | Aeroengine turbine rear casing static strength test device |
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| JP2988372B2 (en) * | 1996-05-13 | 1999-12-13 | 三菱自動車工業株式会社 | Piston test equipment for internal combustion engines |
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