CN205384081U - A vibration detection device and gas turbine for gas turbine - Google Patents
A vibration detection device and gas turbine for gas turbine Download PDFInfo
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- CN205384081U CN205384081U CN201521129880.9U CN201521129880U CN205384081U CN 205384081 U CN205384081 U CN 205384081U CN 201521129880 U CN201521129880 U CN 201521129880U CN 205384081 U CN205384081 U CN 205384081U
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Abstract
The utility model discloses a vibration detection device and gas turbine for gas turbine. Be used for gas turbine's vibration detection device, including gas turbine's rotor, locate the front end bearing frame of the rotation axis front end of rotor and locate the tail end bearing frame of the rotation axis tail end of rotor, be equipped with on the rotation axis and arrange and be used for the vibration base plate as rotor vibration detection benchmark along rotor shaft circumference, be equipped with the axial vibration sensor that is used for measuring rotor axial vibration on the relative position of vibration base plate, the front end relative position and/or the tail end relative position of rotation axis are equipped with the radial vibration sensor who is used for measuring the vibration of the radial direction of rotor. Through set for the vibration benchmark on the rotation axis of rotor to the vibration benchmark realize rotor week the border rotor shaft to or radial vibration detection, each position through the rotation axis at the rotor sets up the sensor, acquires the concrete position and the concrete direction of vibration, conveniently finds out failure cause. Be applicable to all kinds of gas turbine's vibration detection.
Description
Technical field
This utility model relates to aero-engine detection technique field, especially, relates to a kind of vibration detection device for gas turbine.Additionally, this utility model further relates to a kind of gas turbine including the above-mentioned vibration detection device for gas turbine.
Background technology
Due to the high speed rotating of aero-gas turbine rotor, the vibration values of gas turbine becomes an important Protection parameters of gas turbine, and along with the increase of the time of operation, gas turbine vibration will increase, and is necessary for safeguarding or repairing when vibration exceedes limit value.
The vibration detection scheme of existing gas turbine is: installs vibrating sensor on gas turbine body or bearing block, measures the vibration that gas turbine is overall.Existing metering system can effectively measure the Vibration Condition that combustion engine is overall, but the vibration that particular location causes can not be reflected, accurate direction can not be provided for unit maintenance, go again to look into fault only by after decomposing combustion engine, analyze vibration cause, scheme is complicated and workload is big, and is difficult to find the reason of vibration.
Utility model content
This utility model provides a kind of vibration detection device for gas turbine and gas turbine, to solve the vibration detection scheme of existing gas turbine, it is only capable of measuring the Vibration Condition that combustion engine is overall, concrete vibration position can not be reflected, accurate direction can not be provided for unit maintenance, carrying out progressively looking up the fault after requiring over decomposition combustion engine and analyze vibration cause, scheme is complicated and workload is big, and is difficult to find the technical problem of the reason of vibration.
This utility model provides a kind of vibration detection device for gas turbine, including gas turbine rotor, be located at the front end bearing block of the rotating shaft front end of rotor and be located at the tail end bearing block of rotating shaft tail end of rotor, rotating shaft be provided with along armature spindle circumferentially and for as rotor oscillation detect benchmark vibration substrate, vibration substrate relative position be provided with for measure rotor axial vibration axial vibration sensor；The front end relative position of rotating shaft and/or tail end relative position are provided with the radial vibration sensor for measuring the vibration of rotor radial direction.
Further, axial vibration sensor and/or radial vibration sensor are set to multiple；Multiple axial vibration sensors and/or multiple radial vibration sensor are evenly arranged along the circumference of rotor.
Further, axial vibration sensor and radial vibration sensor are disposed as two or four；Axial vibration sensor is arranged symmetrically with between two along the rotating shaft of rotor, and radial vibration sensor is arranged symmetrically with between two along the rotating shaft of rotor.
Further, radial vibration sensor is laid on rotating shaft along rotor radial；And/or radial vibration sensor is laid on front end bearing block along rotor axial；And/or radial vibration sensor is laid on tail end bearing block along rotor axial.
Further, vibration substrate is located between front end bearing block and tail end bearing block and is integrated making molding with rotating shaft.
Further, axial vibration sensor is laid on vibration substrate along rotor axial.
Further, the immediately preceding end bearing block of vibration substrate is arranged.
Further, axial vibration sensor is on the plate face of the side of vibration real estate forward end bearing block.
Further, radial vibration sensor is on front end bearing block away from the end face of rotor；And/or radial vibration sensor is on tail end bearing block away from the end face of rotor.
According to another aspect of the present utility model, additionally providing a kind of gas turbine, it includes the above-mentioned vibration detection device for gas turbine.
This utility model has the advantages that
This utility model is for the vibration detection device of gas turbine, by setting vibration benchmark on the rotating shaft of rotor, realizes rotor periphery along rotor axial or vibration detection radially vibrating benchmark；Sensor is set by each position at the rotating shaft of rotor, the particular location of vibration and concrete direction can be obtained intuitively, conveniently find out failure cause, it is simple to maintenance and repair.Vibration detection suitable in all kinds of gas turbines.
Sensor is fixed on gas turbine casing or interior fixtures, forms the relative position relation with each position of rotor, thus immediately sensing and transmit the vibration data at each position of rotor, conveniently finds out failure cause, it is simple to maintenance and repair.Vibration detection suitable in all kinds of gas turbines.
Except purpose described above, feature and advantage, this utility model also has other purpose, feature and advantage.Below with reference to figure, this utility model is described in further detail.
Accompanying drawing explanation
The accompanying drawing constituting the part of the application is used for providing being further appreciated by of the present utility model, and schematic description and description of the present utility model is used for explaining this utility model, is not intended that improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the structural representation of the vibration detection device for gas turbine of this utility model preferred embodiment.
Marginal data:
1, rotor；101, rotating shaft；2, front end bearing block；3, tail end bearing block；4, vibration substrate；5, axial vibration sensor；6, radial vibration sensor.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail, but this utility model can be implemented by following the multitude of different ways limiting and covering.
Fig. 1 is the structural representation of the vibration detection device for gas turbine of this utility model preferred embodiment.As shown in Figure 1, the vibration detection device for gas turbine of the present embodiment, including gas turbine rotor 1, be located at the front end bearing block 2 of rotating shaft 101 front end of rotor 1 and be located at the tail end bearing block 3 of rotating shaft 101 tail end of rotor 1, rotating shaft 101 is provided with along rotor 1 axle circumferentially and for the vibration substrate 4 as rotor 1 vibration detection benchmark, and the relative position of vibration substrate 4 is provided with the axial vibration sensor 5 for measuring rotor 1 axial vibration；The front end relative position of rotating shaft 101 and/or tail end relative position are provided with the radial vibration sensor 6 for measuring the vibration of rotor 1 radial direction.This utility model is for the vibration detection device of gas turbine, by setting vibration benchmark on the rotating shaft of rotor, realizes rotor periphery along rotor axial or vibration detection radially vibrating benchmark；Sensor is set by each position at the rotating shaft of rotor, the particular location of vibration and concrete direction can be obtained intuitively, conveniently find out failure cause, it is simple to maintenance and repair.Vibration detection suitable in all kinds of gas turbines.Sensor is fixed on gas turbine casing or interior fixtures, forms the relative position relation with each position of rotor, thus immediately sensing and transmit the vibration data at each position of rotor, conveniently finds out failure cause, it is simple to maintenance and repair.Vibration detection suitable in all kinds of gas turbines.
In the present embodiment, axial vibration sensor 5 and/or radial vibration sensor 6 are set to multiple.Multiple axial vibration sensors 5 and/or multiple radial vibration sensor 6 are evenly arranged along the circumference of rotor 1.Adopt Redundancy Design, will not cause that combustion engine is not normally functioning and depot repair due to a fault of vibrating sensor own.
In the present embodiment, axial vibration sensor 5 and radial vibration sensor 6 are disposed as two.Two axial vibration sensors 5 are arranged symmetrically with along the rotating shaft 101 of rotor 1, and two radial vibration sensors 6 are arranged symmetrically with along the rotating shaft 101 of rotor 1.Adopt Redundancy Design, will not cause that combustion engine is not normally functioning and depot repair due to a fault of vibrating sensor own.
In the present embodiment, alternatively, radial vibration sensor 6 is radially laid on rotating shaft 101 along rotor 1, and radial vibration sensor 6 is axially laid on front end bearing block 2 along rotor 1, and radial vibration sensor 6 is axially laid on tail end bearing block 3 along rotor 1.Alternatively, radial vibration sensor 6 is radially laid on rotating shaft 101 along rotor 1, and radial vibration sensor 6 is axially laid on front end bearing block 2 along rotor 1.Alternatively, radial vibration sensor 6 is axially laid on front end bearing block 2 along rotor 1, and radial vibration sensor 6 is axially laid on tail end bearing block 3 along rotor 1.Alternatively, radial vibration sensor 6 is radially laid on rotating shaft 101 along rotor 1, and radial vibration sensor 6 is axially laid on tail end bearing block 3 along rotor 1.Can according to the architectural feature of rotor 1 and model size, it is determined that the installation position of sensor, so that it is guaranteed that the collection of vibration data and transmission, it is ensured that the accuracy of vibration data, reach at-once monitor vibration data and determine the purpose of vibration position.
In the present embodiment, vibration substrate 4 is located between front end bearing block 2 and tail end bearing block 3 and is integrated making molding with rotating shaft 101.Thus ensureing the structural stability of vibration substrate 4, it is ensured that as the accuracy of the vibration substrate 4 on vibration basis.
In the present embodiment, axial vibration sensor 5 is axially laid on vibration substrate 4 along rotor 1.With the axial vibration data in at-once monitor rotor 1 running.
In the present embodiment, the vibration immediately preceding end bearing block 2 of substrate 4 is arranged.Accurate axially or radially vibration data can be obtained.
In the present embodiment, axial vibration sensor 5 is in vibration substrate 4 on the plate face of the side of front end bearing block 2.Accurate axially or radially vibration data can be obtained.
In the present embodiment, alternatively, on the end face that radial vibration sensor 6 is on front end bearing block 2 away from rotor 1；Radial vibration sensor 6 is on tail end bearing block 3 away from the end face of rotor 1.Alternatively, on the end face that radial vibration sensor 6 is on front end bearing block 2 away from rotor 1.Alternatively, radial vibration sensor 6 is on tail end bearing block 3 away from the end face of rotor 1.Can according to the architectural feature of rotor 1 and model size, it is determined that the installation position of sensor, so that it is guaranteed that the collection of vibration data and transmission, it is ensured that the accuracy of vibration data, reach at-once monitor vibration data and determine the purpose of vibration position.
The gas turbine of the present embodiment, including the above-mentioned vibration detection device for gas turbine.
During enforcement, owing to the root of gas turbine vibration is that rotor high speed rotating produces, directly at the Vibration Condition of gas turbine internal monitoring gas turbine rotor, as shown in Figure 1, two ends radial direction at rotating shaft has two groups to measure vibrating sensor respectively, consider that vibrating sensor is inside gas turbine, owing to vibrating sensor itself is likely to also there will be the factor of fault, so each position vibrating sensor has two (Redundancy Design is standby each other).Wherein front end above-below direction arranges two groups of vibrating sensors, fore-and-aft direction arranges two groups of vibrating sensors (not marking on figure), tail end above-below direction is symmetrically arranged with two groups of vibrating sensors, fore-and-aft direction is provided with two groups of vibrating sensors (not marking on figure), for measuring the vibration in rotor radial direction.
When working due to gas turbine, rotor can be subject to a power backward at axial direction, so also there are two groups of vibrating sensors (Redundancy Design is standby each other) in rotor axial direction, for measuring the vibration in rotor axial direction.
Wherein above-mentioned all vibrating sensors are all magneto-electric vibrating sensor, and measurement is all displacement vibration.Its measured value can pass through controller and show on host computer computer.
The foregoing is only preferred embodiment of the present utility model, be not limited to this utility model, for a person skilled in the art, this utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment of making, equivalent replacement, improvement etc., should be included within protection domain of the present utility model.
Claims (10)
1. the vibration detection device for gas turbine, including gas turbine rotor (1), be located at the front end bearing block (2) of rotating shaft (101) front end of described rotor (1) and be located at the tail end bearing block (3) of rotating shaft (101) tail end of described rotor (1)
It is characterized in that,
Described rotating shaft (101) is provided with and circumferentially and is used for the vibration substrate (4) as described rotor (1) vibration detection benchmark along described rotor (1) axle,
The relative position of described vibration substrate (4) is provided with the axial vibration sensor (5) for measuring described rotor (1) axial vibration；
On the front end relative position of described rotating shaft (101) and/or tail end relative position be provided with for measure described rotor (1) radial direction vibration radial vibration sensor (6).
2. the vibration detection device for gas turbine according to claim 1, it is characterised in that
Described axial vibration sensor (5) and/or described radial vibration sensor (6) are set to multiple；
Multiple described axial vibration sensors (5) and/or multiple described radial vibration sensor (6) are evenly arranged along the circumference of described rotor (1).
3. the vibration detection device for gas turbine according to claim 2, it is characterised in that
Described axial vibration sensor (5) and described radial vibration sensor (6) are disposed as two or four；
Described axial vibration sensor (5) is arranged symmetrically with between two along the described rotating shaft (101) of described rotor (1),
Described radial vibration sensor (6) is arranged symmetrically with between two along the described rotating shaft (101) of described rotor (1).
4. the vibration detection device for gas turbine according to claim 2, it is characterised in that
Described radial vibration sensor (6) is radially laid on described rotating shaft (101) along described rotor (1)；And/or
Described radial vibration sensor (6) is axially laid on described front end bearing block (2) along described rotor (1)；And/or
Described radial vibration sensor (6) is axially laid on described tail end bearing block (3) along described rotor (1).
5. the vibration detection device for gas turbine according to any one of claim 1 to 4, it is characterised in that
Described vibration substrate (4) is located between described front end bearing block (2) and described tail end bearing block (3) and is integrated making molding with described rotating shaft (101).
6. the vibration detection device for gas turbine according to claim 5, it is characterised in that
Described axial vibration sensor (5) is axially laid on described vibration substrate (4) along described rotor (1).
7. the vibration detection device for gas turbine according to claim 6, it is characterised in that
Described vibration substrate (4) is arranged against described front end bearing block (2).
8. the vibration detection device for gas turbine according to claim 7, it is characterised in that
Described axial vibration sensor (5) is in described vibration substrate (4) on the plate face of the side of described front end bearing block (2).
9. the vibration detection device for gas turbine according to any one of claim 1 to 4, it is characterised in that
On the end face that described radial vibration sensor (6) is on described front end bearing block (2) away from described rotor (1)；And/or
On the end face that described radial vibration sensor (6) is on described tail end bearing block (3) away from described rotor (1).
10. a gas turbine, it is characterised in that include the vibration detection device for gas turbine according to any one of claim 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521129880.9U CN205384081U (en) | 2015-12-30 | 2015-12-30 | A vibration detection device and gas turbine for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521129880.9U CN205384081U (en) | 2015-12-30 | 2015-12-30 | A vibration detection device and gas turbine for gas turbine |
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| Publication Number | Publication Date |
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| CN205384081U true CN205384081U (en) | 2016-07-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201521129880.9U Active CN205384081U (en) | 2015-12-30 | 2015-12-30 | A vibration detection device and gas turbine for gas turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113074811A (en) * | 2021-05-11 | 2021-07-06 | 核工业理化工程研究院 | Multi-measuring-point testing device for high-speed rotating equipment |
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2015
- 2015-12-30 CN CN201521129880.9U patent/CN205384081U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113074811A (en) * | 2021-05-11 | 2021-07-06 | 核工业理化工程研究院 | Multi-measuring-point testing device for high-speed rotating equipment |
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