CN216669269U - Aeroengine high-pressure rotor dynamic stress measuring system with switching device - Google Patents
Aeroengine high-pressure rotor dynamic stress measuring system with switching device Download PDFInfo
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- CN216669269U CN216669269U CN202220313737.9U CN202220313737U CN216669269U CN 216669269 U CN216669269 U CN 216669269U CN 202220313737 U CN202220313737 U CN 202220313737U CN 216669269 U CN216669269 U CN 216669269U
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Abstract
The utility model provides an aeroengine high-pressure rotor dynamic stress measuring system with a switching device, which comprises: the switching device is connected with the slip ring structure and a rotor-stator structure of the high-pressure compressor; the switching device comprises a double-fulcrum supporting structure and a flexible compensation structure, the double-fulcrum supporting structure is installed on a rotor shaft of the slip ring structure, one end of the flexible compensation structure is connected with the end of the rotor shaft of the slip ring structure, and the other end of the flexible compensation structure is connected with the rotor shaft of the high-pressure compressor. The utility model can meet the flexible switching function of the slip ring system of the core engine of the aeroengine and an engine structure, avoids the influence of eccentricity of the engine and a slip ring rotor, avoids the adverse effect caused by transient pulling or impact of the engine rotor, provides larger bearing capacity by the bearing with double pivots and ensures the stable operation of the slip ring rotor.
Description
Technical Field
The utility model relates to the field of testing of aircraft engines, in particular to a system for measuring dynamic stress of a high-pressure rotor of an aircraft engine with a switching device.
Background
In the test of the aero-engine, the dynamic stress measurement of the rotor is an important parameter for monitoring the safety of the aero-engine, and the rotor safety is an important guarantee for the reliability of the engine. The dynamic stress measurement technology can truly reflect the deformation condition of rotor vibration in test run, and is an important basis for ensuring the sufficient strength design of the engine blade.
At present, the main domestic method for measuring the dynamic stress of the rotor is to use a slip ring structure, and the slip ring structure has the advantages of low manufacturing cost, simple structure, mature technology and the like. The method has the disadvantages that the contact type measurement requires a stable rotor and stator running structure, the environmental requirement is high, and the running noise is reduced as much as possible. And the more the measuring point quantity, the bigger the volume, the more unstable the structure, the more complicated the design supporting structure.
The current slip ring in China has simple structure, mostly within 20 measuring points, and the volume is less, can use flexible structure as compensation usually. Common mechanisms such as a small-sized coupling for switching an engine rotor have small compensation eccentricity and short sustainable operation time.
In the prior art, in order to carry out a dynamic stress test of a high-pressure rotor of an aircraft engine, a slip ring structure is used, but the following difficulties exist in connection with the engine:
firstly, high pressure rotor rotational speed is high, and the measurement station is more to lead to whole sliding ring structure longer, and the eccentricity of operation in-process rotor is big, can produce destructive influence to the sliding ring, and sliding ring bearing capacity is not enough, and inside brush silk scatters, can lead to the signal to take place the confusion.
And secondly, during the operation of the engine, the relative movement of the rotor and the stator can produce transient pulling or impact on the slip ring rotor, so that the slip ring rotor and the cooling structure are damaged.
And thirdly, oil gas at the position of the engine close to the bearing cavity is large, so that interference on the slip ring electric signal is easy to generate.
Fourthly, hot gas at the axle center of the engine can damage the slip ring structure.
Fifthly, the rotor state of the switching structure is difficult to be clear in the test process.
In view of the above, the present inventors have devised a system for measuring dynamic stress of a high-pressure rotor of an aircraft engine with an adapter device, in order to overcome the above technical problems.
SUMMERY OF THE UTILITY MODEL
The utility model aims to overcome the defects that a slip ring structure is used for connecting an engine in a high-pressure rotor stress test in the prior art, and the dynamic stress measuring system with a switching device for the high-pressure rotor of the aeroengine is provided.
The utility model solves the technical problems through the following technical scheme:
the utility model provides a take switching device's aeroengine high pressure rotor dynamic stress measurement system which characterized in that, the aeroengine high pressure rotor dynamic stress measurement system who takes switching device includes: the switching device is connected with the slip ring structure and a rotor-stator structure of the high-pressure compressor;
the switching device comprises a double-fulcrum supporting structure and a flexible compensation structure, the double-fulcrum supporting structure is installed on a rotor shaft of the slip ring structure, one end of the flexible compensation structure is connected with the end of the rotor shaft of the slip ring structure, and the other end of the flexible compensation structure is connected with the rotor shaft of the high-pressure compressor.
According to one embodiment of the utility model, the dual-fulcrum support structure is a dual ball bearing.
According to one embodiment of the utility model, the double ball bearing is a thrust ball bearing or a deep groove ball bearing.
According to one embodiment of the utility model, the flexible compensation structure is a bellows.
According to one embodiment of the utility model, a rotating sleeve is arranged in the double ball bearing.
According to one embodiment of the present invention, a continuous rectangular sealing structure is provided on an inner wall surface of the rotating sleeve.
According to one embodiment of the utility model, a gradual-change aperture structure is arranged inside the axis of the rotor shaft of the slip ring structure and used for sealing the lead.
According to one embodiment of the utility model, the bearing seat of the double ball bearing is provided with at least one first opening for arranging a temperature sensor, said first opening being located at the bearing location of the double ball bearing.
According to one embodiment of the utility model, the flattened area of the bearing seat is provided with a second opening, and a vibration measuring point is arranged in the second opening.
According to one embodiment of the utility model, the mounting location of the bellows is separated from the bearing cavity by a sealing disc.
The positive progress effects of the utility model are as follows:
the aeroengine high-pressure rotor dynamic stress measuring system with the switching device, disclosed by the utility model, has the advantages that the switching structure of the slip ring system is designed by combining the engine structure according to the characteristics of the slip ring structure, and the following advantages can be realized:
the flexible switching function of a slip ring system of an aircraft engine core machine and an engine structure can be met, and the influence of eccentricity of an engine and a slip ring rotor is avoided.
Two, designed two fulcrum bearing structure, the rear end has used the bellows, but its unique flexible extending structure can transmit the engine moment of torsion, avoids pulling or the impact harmful effects that bring of engine rotor transient state again, and the bearing of two fulcrums provides great bearing capacity, has guaranteed the steady operation of sliding ring rotor.
And thirdly, before the original labyrinth seal structure, a labyrinth seal mode is used in the middle of the double-fulcrum bearing, so that oil gas in a bearing cavity is isolated.
Fourthly, a sealing glue structure is designed at the axis, and the hot air environment is isolated.
And fifthly, the temperature monitoring near the bearing and the vibration monitoring structural design are realized in real time structurally.
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 like reference numerals denote like features throughout the several views, wherein:
fig. 1 is a schematic structural diagram of a dynamic stress measurement system of a high-pressure rotor of an aircraft engine with a switching device.
Fig. 2 is a schematic structural diagram of a slip ring structure in the aeroengine high-pressure rotor dynamic stress measurement system with the adapter device.
FIG. 3 is a schematic structural diagram of a bellows in the aeroengine high-pressure rotor dynamic stress measurement system with the adapter device.
Fig. 4 is a schematic view of the installation of the rotating shaft, the bellows and the rotor shaft of the high-pressure compressor in the dynamic stress measuring system of the high-pressure rotor of the aircraft engine with the adapter device.
Fig. 5 is a schematic view of the installation of the rotating shaft sleeve in the dynamic stress measuring system of the high-pressure rotor of the aircraft engine with the adapter device.
FIG. 6 is a schematic layout view of a sealing structure in the aircraft engine high-pressure rotor dynamic stress measuring system with the adapter device.
Fig. 7 is a schematic structural diagram of a colloid sealing area in the dynamic stress measurement system of the high-pressure rotor of the aircraft engine with the adapter device.
FIG. 8 is a schematic structural diagram of an isolation cavity and a bearing cavity in the dynamic stress measurement system of the high-pressure rotor of the aircraft engine with the adapter device.
FIG. 9 is a schematic layout diagram of temperature measuring points in the dynamic stress measuring system for the high-pressure rotor of the aircraft engine with the adapter device.
FIG. 10 is a schematic layout diagram of vibration measuring points in the aeroengine high-pressure rotor dynamic stress measuring system with the adapter device.
[ reference numerals ]
Double-fulcrum support structure 20
Graded aperture structure 12
Bearing cavity A
Isolation chamber B
First opening 22
Lead hole 71
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
Further, although the terms used in the present invention are selected from publicly known and used terms, some of the terms mentioned in the description of the present invention may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein.
Furthermore, it is required that the present invention is understood, not simply by the actual terms used but by the meaning of each term lying within.
The utility model discloses a dynamic stress measurement system of a high-pressure rotor of an aeroengine with a switching device. The device is used for a switching device of a slip ring structure and a front shaft end rotor-stator structure of a high-pressure compressor. Because the high-pressure rotor of the engine core machine can not avoid the eccentricity of the rotor in the rotating process, and the slip ring rotor structure is a long rod type structure, the slip ring rotor structure needs to keep stable rotating operation, and the electric signals of the rotor can be transmitted to a vehicle platform in a contact mode, so that an intermediate switching structure is needed, and the influence of the eccentricity of the rotor on the slip ring rotor and the signal transmission can be eliminated.
As shown in fig. 1 to 4, the utility model discloses a system for measuring dynamic stress of a high-pressure rotor of an aircraft engine with a switching device, which comprises: the device comprises a slip ring structure 10, a high-pressure compressor and a switching device, wherein the switching device is connected with the slip ring structure 10 and a rotor-stator structure of the high-pressure compressor.
The switching device comprises a double-fulcrum supporting structure 20 and a flexible compensation structure 30, wherein the double-fulcrum supporting structure 20 is installed on a rotor shaft 11 of a slip ring structure 10, one end of the flexible compensation structure 30 is connected with the end of the rotor shaft 11 of the slip ring structure 10, and the other end of the flexible compensation structure 30 is connected with a rotor shaft 40 of a high-pressure compressor.
Preferably, the flexible compensation structure 30 may employ a bellows.
According to the switching device, two thrust ball bearings are designed on the rotor shaft 11 of the slip ring structure 10 to support the rotor, and the double ball bearings can bear larger axial and radial loads, so that the relative gap variation of the rotor and the stator can be controlled, and the fixation of the rotor structure of the slip ring is ensured. In the middle of the connection with the engine, the connection mode is shown in fig. 2, a structure of a corrugated pipe is selected, and two ends of the corrugated pipe can be connected with a structure C in a welding mode, as shown in fig. 3 and 4, and the corrugated pipe can be used for transmitting engine torque.
During the acceleration and deceleration process of the engine, the slip ring rotor can be pulled and compressed, and the unique stretchable and compressible structure of the corrugated pipe can sufficiently compensate the influence brought by the engine rotor and can assist the small coupler of the slip ring system to provide dynamic compensation for the rotor.
Preferably, the dual fulcrum support structure 20 may employ dual ball bearings. The double ball bearing may preferably be a thrust ball bearing or a deep groove ball bearing.
As shown in fig. 5 and 6, a rotating sleeve 50 may be provided in the double ball bearing. A continuous rectangular seal structure 51 is provided on the inner wall surface of the rotary sleeve 50.
In a small space in the middle of the double-bearing structure design, a rotating shaft sleeve 50 for installing and fixing a bearing is utilized, a continuous rectangular sealing structure 51 is designed in the middle, gaps between rotors and stators can be designed, lubricating oil leaking out of a first grate seal of a rear-end engine can be sealed to a certain extent, and lubricating oil is prevented from entering a sliding ring structure at the front end to cause signal failure. Simultaneously, the stator part contact structure is provided with a sealing ring to seal oil gas, and the middle sealing ring also plays a role in adjusting axial clearance.
As shown in fig. 7, a gradual-change aperture structure 12 is provided inside the axial center of the rotor shaft 11 of the slip ring structure 10, and is used for sealing the lead. The structure is convenient for sealing the lead, and the colloid can be limited within the reduced inner diameter.
As shown in fig. 8, the bellows (i.e., the compliance compensation structure 30) is installed in a position separated from the bearing chamber a by a seal disk 60, forming a separate bearing chamber a and a separate chamber B. Particularly, the designed installation position of the corrugated pipe is separated from the right bearing cavity A through the sealing disc 60, so that the influence of the connection damage of the corrugated pipe on the bearing cavity A of the engine is avoided, and the safety during structural instability is ensured.
As shown in fig. 9 and 10, the bearing seat 21 of the double ball bearing is provided with at least one first opening 22 for arranging a temperature sensor to form a temperature measuring point. The first bore 22 is located at the bearing location of the double ball bearing.
In addition, a second opening 23 is provided in the flattened area of the bearing seat 21, and vibration measuring points are arranged in the second opening 23. The support plate 70 may further have a lead hole 71 for passing a lead therethrough.
Holes (namely, a first hole 22) are formed in the front bearing position and the rear bearing position of the bearing seat 21 and used for arranging galvanic couple to measure temperature, holes (namely, lead holes 71) are formed in the outer supporting disk 70, lead wires of the sensors are led out, the bearing can be used for health monitoring in the test process, meanwhile, vibration measuring points can be fixedly placed on the bearing seat 21 in a flattened area through the holes (namely, a second hole 22), and real-time monitoring is conducted as shown in fig. 10, so that the safety of the structure is guaranteed.
According to the structural description, the flexible compensation structure designed by the utility model mainly comes from the corrugated pipe, the elastic structure can compensate most of the eccentricity between the two rotors, and the corrugated pipe can provide larger deformation due to the shorter length of the corrugated pipe, so that the modification mode can greatly reduce the axial size after modification and save space for the engine.
The system for measuring the dynamic stress of the high-pressure rotor of the aircraft engine with the switching device fully considers the stability of a transmission signal according to the slip ring structure and the structural characteristics of the engine, and the switching structure of the slip ring device is designed, so that the switching structure of the slip ring device mounted at the shaft end of the high-pressure rotor for meeting the requirements of an aircraft engine test piece can be met. The utility model adopts the double-pivot supporting structure with larger bearing capacity, compensates larger eccentricity of the rotor except the compensation capacity of the small-sized coupler in a switching mode of the corrugated pipe, and can avoid the adverse effect on the slip ring rotor caused by the transient pulling and the impact of the axial direction of the rotor due to the special flexible structure of the corrugated pipe. A continuous rectangular sealing structure is arranged in the middle of the double-bearing structure, so that oil-gas interference caused by a bearing cavity of an engine is avoided, and stability of transmission signals is guaranteed. In addition, the utility model also designs a bearing temperature monitoring structure, so that the safety of the device rotor is ensured, and simultaneously designs an axis sealing structure, thereby avoiding the influence of hot gas of the axis on the front end slip ring, and meeting the mounting structure requirement of the slip ring and the test requirement of the dynamic stress of the rotor of the aircraft engine.
In summary, the aeroengine high-pressure rotor dynamic stress measurement system with the switching device of the utility model can realize the following advantages by combining the engine structure design switching structure according to the characteristics of the slip ring structure:
the flexible switching function of a slip ring system of an aircraft engine core machine and an engine structure can be met, and the influence of eccentricity of an engine and a slip ring rotor is avoided.
Two, designed two fulcrum bearing structure, the rear end has used the bellows, but its unique flexible extending structure can transmit the engine moment of torsion, avoids pulling or the impact harmful effects that bring of engine rotor transient state again, and the bearing of two fulcrums provides great bearing capacity, has guaranteed the steady operation of sliding ring rotor.
And thirdly, before the original labyrinth seal structure, a labyrinth seal mode is used in the middle of the double-fulcrum bearing, so that oil gas in a bearing cavity is isolated.
Fourthly, a sealing glue structure is designed at the axis, and the hot air environment is isolated.
And fifthly, the temperature monitoring near the bearing and the vibration monitoring structural design are realized in real time structurally.
While specific embodiments of the utility model have been described above, it will be understood by those skilled in the art that these are by way of example only, and that the scope of the utility model is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the utility model, and these changes and modifications are within the scope of the utility model.
Claims (10)
1. The utility model provides a take aeroengine high pressure rotor dynamic stress measurement system of switching device which characterized in that, aeroengine high pressure rotor dynamic stress measurement system of taking switching device includes: the switching device is connected with the slip ring structure and a rotor-stator structure of the high-pressure compressor;
the switching device comprises a double-fulcrum supporting structure and a flexible compensation structure, the double-fulcrum supporting structure is installed on a rotor shaft of the slip ring structure, one end of the flexible compensation structure is connected with the end of the rotor shaft of the slip ring structure, and the other end of the flexible compensation structure is connected with the rotor shaft of the high-pressure compressor.
2. The aircraft engine high pressure rotor dynamic stress measurement system with adapter device of claim 1, wherein said dual fulcrum support structure is a dual ball bearing.
3. The aeroengine high-pressure rotor dynamic stress measurement system with the adapter device according to claim 2, wherein the double-ball bearing is a thrust ball bearing or a deep groove ball bearing.
4. The system for measuring the dynamic stress of the high-pressure rotor of the aircraft engine with the adapter device according to claim 1, wherein the flexible compensation structure adopts a corrugated pipe.
5. The system for measuring the dynamic stress of the high-pressure rotor of the aircraft engine with the adapter device as claimed in claim 2, wherein a rotating shaft sleeve is arranged in the double-ball bearing.
6. The system for measuring the dynamic stress of the high-pressure rotor of the aircraft engine with the adapter device as claimed in claim 5, wherein a continuous rectangular sealing structure is provided on the inner wall surface of the rotating shaft sleeve.
7. The system for measuring the dynamic stress of the high-pressure rotor of the aircraft engine with the adapter device as claimed in claim 1, wherein a gradual-change aperture structure is arranged inside the axis of the rotor shaft of the slip ring structure and used for sealing the lead.
8. The system for measuring the dynamic stress of the high-pressure rotor of the aircraft engine with the adapter device according to claim 2, wherein at least one first opening is provided in the bearing seat of the double-ball bearing for arranging a temperature sensor, and the first opening is located at the bearing position of the double-ball bearing.
9. The system for measuring the dynamic stress of the high-pressure rotor of the aircraft engine with the adapter device as claimed in claim 8, wherein the flattened area of the bearing seat is provided with a second opening, and a vibration measuring point is arranged in the second opening.
10. The aeroengine high-pressure rotor dynamic stress measurement system with the adapter device according to claim 4, wherein the installation position of the corrugated pipe is separated from the bearing cavity by a sealing disc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220313737.9U CN216669269U (en) | 2022-02-16 | 2022-02-16 | Aeroengine high-pressure rotor dynamic stress measuring system with switching device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220313737.9U CN216669269U (en) | 2022-02-16 | 2022-02-16 | Aeroengine high-pressure rotor dynamic stress measuring system with switching device |
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| Publication Number | Publication Date |
|---|---|
| CN216669269U true CN216669269U (en) | 2022-06-03 |
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|---|---|---|---|
| CN202220313737.9U Active CN216669269U (en) | 2022-02-16 | 2022-02-16 | Aeroengine high-pressure rotor dynamic stress measuring system with switching device |
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|---|---|
| CN (1) | CN216669269U (en) |
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- 2022-02-16 CN CN202220313737.9U patent/CN216669269U/en active Active
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