CN213600346U - Aeroengine main shaft strength test device - Google Patents
Aeroengine main shaft strength test device Download PDFInfo
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- CN213600346U CN213600346U CN202023025060.9U CN202023025060U CN213600346U CN 213600346 U CN213600346 U CN 213600346U CN 202023025060 U CN202023025060 U CN 202023025060U CN 213600346 U CN213600346 U CN 213600346U
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Abstract
An object of the utility model is to provide an aeroengine main shaft intensity test device can improve the experimental accuracy of main shaft intensity. The device for testing the strength of the main shaft of the aircraft engine for achieving the purpose comprises an outer frame of the device, a testing unit group, two torque actuating units, two fulcrum units and two axial force actuating units. The test unit group comprises a fan disc simulation piece, a fan shaft simulation piece and a main shaft test piece, wherein two torque actuating units are respectively connected with the fan disc simulation piece and the device outer frame, the main shaft test piece is supported by the two fulcrum units in the device outer frame, the first axial force actuates the unit connecting device outer frame and the main shaft test piece, and the second axial force actuates the unit connecting device outer frame and the fan disc simulation piece. One of the first axial force actuating unit and the second axial force actuating unit is connected with the test unit group through the lever unit.
Description
Technical Field
The utility model relates to an aeroengine main shaft intensity test device.
Background
The main shaft of the aircraft engine comprises a fan shaft, a low-vortex shaft (referred to as a main shaft) and the like, is one of the most important force transmission components of the aircraft engine, and is designed, manufactured, verified and maintained by an aircraft engine owner manufacturer as a life-limiting component according to the structural failure safety level and the airworthiness regulation requirements of a civil aircraft engine, and the safety of the aircraft engine directly influences the safe flight of the whole engine or even an airplane. As one of main structures for bearing the falling load of the blades of the aircraft engine, the strength test verification of the main shaft is one of the projects which must be completed by the airworthiness regulation of the civil aircraft engine.
Because the main shaft is complex in stress and limited in space, the main shaft can bear transverse force, bending moment and axial force in different directions besides torque. However, in the prior art, a plurality of loads are applied simultaneously in a limited space, and the interference among the loads is difficult to completely eliminate. Meanwhile, the more the load is applied, the larger the synchronism error applied by the load is, which has a great influence on the accuracy of the spindle strength test. Therefore, a more accurate loading method and device are needed, which can eliminate the interference among the loads, reduce the synchronization error applied by the loads as much as possible, and make the test result more accurate and reliable.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aeroengine main shaft intensity test device can improve the experimental accuracy of main shaft intensity.
In order to achieve the above object, the aircraft engine spindle strength testing device comprises a device outer frame and:
the test unit group comprises a fan disc simulation piece, a fan shaft simulation piece and a main shaft test piece which are sequentially connected with one another;
two torque actuating units, which are respectively connected with the fan disc simulation piece and the device outer frame at two sides;
the first fulcrum unit supports the spindle test piece in the device outer frame at one side and limits the spindle test piece to move along the axial direction and the radial direction of the spindle test piece;
the second fulcrum unit supports the spindle test piece in the device outer frame at the other side and limits the radial movement of the spindle test piece;
the first axial force actuating unit is connected with the device outer frame and the spindle test piece; and
a second axial force actuating unit connecting the device outer frame and the fan disk simulation member;
one of the first axial force actuating unit and the second axial force actuating unit is connected with the test unit group through a lever unit.
In one or more embodiments, the lever unit is hinged at both ends to the first axial force actuation unit and the apparatus outer frame, respectively, and at a middle portion to an end portion of the spindle test piece.
In one or more embodiments, the fan disk simulation element is connected to the fan shaft simulation element by a first adapter sleeve tooth, and the fan shaft simulation element is connected to the spindle test element by a second adapter sleeve tooth.
In one or more embodiments, the main shaft test piece penetrates through one end behind the second adapter sleeve tooth and is supported in the fan shaft simulation piece through a first thrust bearing.
In one or more embodiments, the first fulcrum unit includes a first fulcrum bearing and an axial limiting portion annularly arranged on the periphery of the second adapter sleeve tooth, and the first fulcrum bearing and the axial limiting portion jointly limit the movement of the spindle test piece along the axial direction of the spindle test piece;
the second fulcrum unit comprises a second fulcrum bearing, and the second fulcrum bearing and the first fulcrum bearing jointly limit the movement of the main shaft test piece along the radial direction of the main shaft test piece.
In one or more embodiments, the two torque actuation units are respectively flexibly connected with the fan disk simulation piece on two sides.
In one or more embodiments, the two torque actuation units are connected to the fan disc simulation member at both sides by wire ropes, respectively.
In one or more embodiments, a second thrust bearing is provided at a connection of the second axial force actuation unit and the fan disc simulation.
In one or more embodiments, an included angle exists between a connecting line of the two torque actuating units and the connecting position of the fan disk simulation piece and a connecting line of the two torque actuating units and the connecting position of the device outer frame.
The utility model discloses an advance effect includes following one or combination:
1) by using the lever unit, the first or second axial force action unit can apply large load by using a small actuator, and the requirement of hardware equipment is reduced.
2) The mode that two actuators staggered in the axial direction and eccentric carry out unequal-size loading at two ends of a test unit group is utilized, and two torques are utilized to actuate the unit to accurately apply main shaft bending moment, torque and transverse force, so that the test result is more accurate and reliable, the test tool is reduced, and the test control difficulty is reduced.
3) The actuator and the torque are flexibly connected through the rope, so that the problem of force arm change caused by a large torsion angle during hard connection is solved, and the loading precision is ensured.
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 shows a schematic front view of an embodiment of an aircraft engine spindle strength testing apparatus;
FIG. 2 shows a schematic top view of one embodiment of an aircraft engine spindle strength testing apparatus;
FIG. 3 shows a schematic partial cross-sectional view of an embodiment of an aircraft engine spindle strength testing apparatus.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present disclosure. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
It should be noted that, where used, the following description of upper, lower, left, right, front, rear, top, bottom, positive, negative, clockwise, and counterclockwise are used for convenience only and do not imply any particular fixed orientation. In fact, they are used to reflect the relative position and/or orientation between the various parts of the object.
It should be noted that these and other figures are given by way of example only and are not drawn to scale, and should not be construed as limiting the scope of the invention as it is actually claimed. Further, the conversion methods in the different embodiments may be appropriately combined.
For providing one kind can carry out more accurate experimental device to the main shaft intensity test, the utility model provides an aeroengine main shaft intensity test device, as fig. 1 shows the front schematic view under this aeroengine main shaft intensity test device's an embodiment, fig. 2 shows the schematic view of overlooking under this aeroengine main shaft intensity test device's an embodiment, fig. 3 shows the schematic view of partly cut-out under this aeroengine main shaft intensity test device's an embodiment.
The aero-engine spindle strength testing device comprises a device outer frame, wherein it can be understood that, in order to facilitate explanation of the utility model, fig. 1 to 3 only show the main body part of the testing device, and the outer frame part of the testing device is omitted, the device main body part shown in fig. 1 to 3 is arranged in the device outer frame not shown in the figure, and the device outer frame can be an existing bearing frame.
The aeroengine main shaft strength testing device further comprises a testing unit group 1, two torque actuating units 2, a first fulcrum unit 3, a second fulcrum unit 4, a first axial force actuating unit 5 and a second axial force actuating unit 6.
The test unit group 1 includes a fan disk simulating member 10, a fan shaft simulating member 11, and a main shaft testing member 12, which are connected to each other in this order as shown in the drawing. The fan disc simulation piece 10 and the fan shaft simulation piece 11 are simulation pieces manufactured by simulating structures of a fan disc and a fan shaft in the whole aircraft of the aircraft engine, so that the precision of a main shaft test performed by a test device is ensured.
The two torque actuating units 2 are respectively connected with the fan shaft simulation piece 11 and the device outer frame at two sides, and in the test process, the two torque actuating units 2 respectively apply loads to the fan shaft simulation piece 11 at two sides.
The first fulcrum unit 3 supports one side of the spindle test piece 12 in the apparatus outer frame, and restricts the movement of the spindle test piece 12 in the axial direction and the radial direction thereof. It is to be understood that the axial direction referred to herein means the axial direction of the spindle test piece 12, and the radial direction means the direction from the center of the spindle test piece 12 toward the outer peripheral wall surface.
The second fulcrum unit 4 supports the other side of the spindle test piece 12 in the apparatus outer frame, that is, the first fulcrum unit 3 and the first fulcrum unit 3 support the spindle test piece 12 on both sides, respectively. The second fulcrum unit 4 restricts the movement of the spindle test piece 12 in the radial direction thereof.
The first axial force actuating unit 5 is respectively connected with the device outer frame and the spindle test piece 12, and in the test process, the first axial force actuating unit 5 applies an axial load to the spindle test piece 12.
The second axial force actuating unit 6 is respectively connected with the device outer frame and the fan disc simulation piece 10, and in the test process, the second axial force actuating unit 6 applies axial load to the fan disc simulation piece 10.
The first axial force actuating unit 5 is connected with the spindle test piece 12 in the test unit group 1 through the lever unit 7, and in the test process, the first axial force actuating unit 5 applies load to the spindle test piece 12 through the lever unit 7, so that the lever principle is utilized to apply large load to the small actuator, and the requirements of hardware equipment are reduced. At the same time, the first axial force actuation unit 5 and the second axial force actuation unit 6 are axially offset by the manner of connection of the lever unit 7.
The loading method by using the test device comprises the following steps:
the two torque actuators 2 provide loads F1 and F2, the second axial force actuator 6 provides an axial force F3, and the first axial force actuator 5 provides an axial force F4.
The torque borne by the test unit group 1 is as follows: and T is (F1+ F2) multiplied by D/2, wherein D is the moment arm size of F1 and F2, and the torque moment arm size D can be adjusted according to the rated load of the actuator.
Transverse force: and on the basis of ensuring that the test torque meets the requirement, the FR is equal to | F1-F2|, and the magnitudes of F1 and F2 can be adjusted according to the magnitude of the transverse force required by the test.
Bending moment: t is FR L, on the basis of guaranteeing that experimental moment of torsion and transverse force satisfy the demand, L is the arm of force size of transverse force FR, can adjust the size of moment of bending moment arm of force L according to experimental required moment of bending.
Axial force: FA1 ═ F3; axial force: FA2 ═ F4 × (S1+ S2)/S1, where S1 is the distance from the joint of the lever unit 7 and the spindle test piece 12 to the joint of the lever unit 7 and the apparatus outer frame, and S2 is the distance from the joint of the lever unit 7 and the spindle test piece 12 to the joint of the first axial force actuation unit 5 and the lever unit 7.
Therefore, except for the two axial forces FA1 and FA2, the torque, the bending moment and the transverse force load are all adjusted through F1 and F2, the interference problem and the synchronization problem which possibly exist when the bending moment, the torque and the transverse force are independently loaded are eliminated, the test control is simplified, the test tools are reduced, and the test loading accuracy is improved.
Through utilizing two to stagger in the axial, the mode that eccentric actuator carries out not equidimension loading at test unit 1's both ends, utilize two moments of torsion to actuate unit 2 accuracy and apply main shaft bending moment, moment of torsion and transverse force simultaneously, make the test result more accurate reliable, reduced experimental frock simultaneously, reduced the experimental control degree of difficulty.
In an embodiment different from the one shown in the figure, the second axial force actuation unit 6 may also be connected to the fan disk simulation 10 in the test unit group 1 via a lever unit.
Although one embodiment of the aircraft engine spindle strength testing apparatus is described above, in other embodiments of the aircraft engine spindle strength testing apparatus, the aircraft engine spindle strength testing apparatus may have more details in many respects than the above-described embodiments, and at least some of the details may have various variations. At least some of these details and variations are described below in several embodiments.
In one embodiment of the aircraft engine spindle strength testing apparatus, the lever unit 7 is connected to the first axial force actuation unit 5 and the apparatus frame at both ends, respectively, as shown in the figure, and is hinged to the end of the spindle test piece 12 at the middle portion 70. In one embodiment, the lever unit 7 is connected to the device housing by a connection socket 71.
In one embodiment of the aircraft engine spindle strength testing device, the fan disk simulation piece 10 is connected with the fan shaft simulation piece 11 through the first adapting sleeve tooth 8, and the fan shaft simulation piece 11 is connected with the spindle test piece 12 through the second adapting sleeve tooth 9, so that the sequential assembly connection of the components in the test unit group 1 is completed.
In one embodiment of the aircraft engine spindle strength testing device, one end of the spindle test piece 12, which passes through the second adapter sleeve tooth 9, is supported in the fan shaft simulation piece 11 through a first thrust bearing 13. The first thrust bearing 13 can bear axial force, and the main shaft test piece 12 and the fan shaft simulation piece 11 are ensured to be kept connected along the axial direction.
In one embodiment of the aircraft engine spindle strength testing device, the first fulcrum unit 3 includes a first fulcrum bearing 31 and an axial limiting portion 32 annularly disposed on the outer periphery of the second adapter sleeve gear 9, and the first fulcrum bearing 31 and the axial limiting portion 32 jointly limit the movement of the spindle test piece 12 along the axial direction thereof. The second fulcrum unit 4 includes a second fulcrum bearing 41, and the second fulcrum bearing 41 restricts the movement of the main shaft test piece 12 in the radial direction thereof in cooperation with the first fulcrum bearing 31.
In one embodiment of the aircraft engine spindle strength testing device, two torque actuation units 2 are flexibly connected with the fan disc simulation piece 10. Specifically, as shown in fig. 2, the two torque actuation units 2 are connected to the fan disk simulation 10 through wire ropes 21, respectively. The actuator and the torque are flexibly connected through the rope, so that the problem of force arm change caused by a large torsion angle during hard connection is solved, and the loading precision is ensured.
In one embodiment of the aircraft engine spindle strength testing device, a second thrust bearing 14 is arranged at the joint of the second axial force actuation unit 6 and the fan disc simulation piece 10, and the second thrust bearing 14 can bear axial force to ensure that the fan disc simulation piece 10 and the second axial force actuation unit 6 are kept connected in the axial direction.
In one embodiment of the aircraft engine spindle strength testing device, as shown in fig. 2, an included angle exists between a connecting line of the two torque actuating units 2 and the fan disc simulation piece 10 and a connecting line of the two torque actuating units 2 and the device outer frame, so that the two torque actuating units 2 apply torque to the fan disc simulation piece 10 in the testing process.
The utility model discloses an advance effect includes following one or combination:
by using the lever unit, the first or second axial force action unit can apply large load by using a small actuator, and the requirement of hardware equipment is reduced.
2) The mode that two actuators staggered in the axial direction and eccentric carry out unequal-size loading at two ends of a test unit group is utilized, and two torques are utilized to actuate the unit to accurately apply main shaft bending moment, torque and transverse force, so that the test result is more accurate and reliable, the test tool is reduced, and the test control difficulty is reduced.
3) The actuator and the torque are flexibly connected through the rope, so that the problem of force arm change caused by a large torsion angle during hard connection is solved, and the loading precision is ensured.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.
Claims (9)
1. The utility model provides an aeroengine main shaft intensity test device which characterized in that, includes the device frame and:
the test unit group comprises a fan disc simulation piece, a fan shaft simulation piece and a main shaft test piece which are sequentially connected with one another;
two torque actuating units, which are respectively connected with the fan disc simulation piece and the device outer frame at two sides;
the first fulcrum unit supports the spindle test piece in the device outer frame at one side and limits the spindle test piece to move along the axial direction and the radial direction of the spindle test piece;
the second fulcrum unit supports the spindle test piece in the device outer frame at the other side and limits the radial movement of the spindle test piece;
the first axial force actuating unit is connected with the device outer frame and the spindle test piece; and
a second axial force actuating unit connecting the device outer frame and the fan disk simulation member;
one of the first axial force actuating unit and the second axial force actuating unit is connected with the test unit group through a lever unit.
2. The aircraft engine spindle strength test device according to claim 1, wherein the lever unit is hinged at both ends to the first axial force actuation unit and the device outer frame, respectively, and at a middle portion to an end portion of the spindle test piece.
3. The aircraft engine spindle strength test apparatus of claim 1, wherein the fan disk simulating member and the fan shaft simulating member are connected by a first adapter sleeve tooth, and the fan shaft simulating member and the spindle testing member are connected by a second adapter sleeve tooth.
4. The aircraft engine spindle strength test device of claim 3, wherein the spindle test piece passes through one end behind the second adapter sleeve tooth and is supported in the fan shaft simulation piece through a first thrust bearing.
5. The aircraft engine spindle strength test device according to claim 3, wherein the first fulcrum unit comprises a first fulcrum bearing and an axial limiting part annularly arranged on the periphery of the second adapter sleeve tooth, and the first fulcrum bearing and the axial limiting part jointly limit the spindle test piece to move along the axial direction of the spindle test piece;
the second fulcrum unit comprises a second fulcrum bearing, and the second fulcrum bearing and the first fulcrum bearing jointly limit the movement of the main shaft test piece along the radial direction of the main shaft test piece.
6. The aircraft engine spindle strength testing apparatus of claim 1, wherein two torque actuation units are respectively flexibly connected to the fan disc simulation member at both sides.
7. The aircraft engine spindle strength test device of claim 6, wherein two torque actuation units are connected to the fan disc simulation member at two sides respectively through steel cables.
8. The aircraft engine spindle strength testing device of claim 1, wherein a second thrust bearing is disposed at a junction of the second axial force actuation unit and the fan disc simulation member.
9. The aircraft engine spindle strength test device according to claim 1, wherein an included angle exists between a connecting line of the two torque actuation units and the fan disc simulation piece and a connecting line of the two torque actuation units and the device outer frame.
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| CN202023025060.9U CN213600346U (en) | 2020-12-14 | 2020-12-14 | Aeroengine main shaft strength test device |
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| CN202023025060.9U CN213600346U (en) | 2020-12-14 | 2020-12-14 | Aeroengine main shaft strength test device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114112356A (en) * | 2021-11-22 | 2022-03-01 | 中国航发沈阳发动机研究所 | Aeroengine propeller shaft strength test device |
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2020
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114112356A (en) * | 2021-11-22 | 2022-03-01 | 中国航发沈阳发动机研究所 | Aeroengine propeller shaft strength test device |
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