Vibration data detection system for gas turbine

Abstract

The utility model discloses a vibration data detection system used for a gas turbine, comprising a vibration data detection mechanism, the vibration data detection mechanism comprises a fixing member, and the fixing member is fixedly installed on a bearing pedestal housing connected with a gas turbine rotor; the connecting piece is detachably and fixedly connected to the fixing piece; the eddy current sensor is detachably and fixedly connected to the connecting piece, and the gap between the detection end of the eddy current sensor and the gas turbine rotor is adjustable.

Description

Technical Field

[0001] The utility model relates to the technical field of gas turbine detection, in particular to a vibration data detection system for a gas turbine. Background Art

[0002] As key equipment in industry and power generation, gas turbines are crucial for their operational stability and efficiency. During operation, gas turbines are subject to various forces, such as airflow and mechanical forces. The combined effects of these forces can cause vibration. If not monitored and controlled, excessive vibration can lead to mechanical failure, shorten equipment life, and even cause safety incidents. Therefore, regular vibration monitoring can promptly identify potential problems, prevent significant losses, and ensure long-term stable equipment operation.

[0003] Vibration data measurement includes radial and axial vibration data. If the vibration value of the equipment exceeds the standard, it indicates an internal fault in the rotating machinery. The change in radial vibration amplitude is the most important indicator of rotor deviation. Many faults in rotating machinery, such as broken rotor blades, imbalance due to rotor surface fouling, rotor misalignment, support bearing wear, rotor shaft cracks, and rotor and stator blade rubbing, can be detected by measuring vibration amplitude and frequency.

[0004] The rotor is a key component of rotating machinery, and its operating state determines its proper function. Gas turbine rotors are connected to ball bearings. Generally, ball bearings have a small clearance, while oil film bearings have a larger clearance, ranging from 0.01 to 0.02 mm. This results in a significant difference in the relative vibration of the rotor shaft and the bearing housing.

[0005] In the existing vibration detection of the rotor, the detection unit is fixedly installed on the bearing seat housing. There is a certain gap between the detection end of the detection unit and the outer surface of the rotor. It is a non-contact detection method. However, the detection unit and the bearing seat housing are mostly fixedly connected. The gap between the detection end of the detection unit and the outer surface of the rotor is not convenient to adjust. The gap between the detection end of the detection unit and the rotor is a key parameter that directly affects the measurement accuracy and reliability. This gap must be maintained within a certain range to ensure that the sensor reading has good linearity and accuracy. Too large or too small a gap may cause measurement errors or failure of the detection unit. Utility Model Content

[0006] In order to solve the above technical problems, the utility model provides a vibration data detection system for a gas turbine.

[0007] The technical solutions adopted in this utility model are as follows:

[0008] A vibration data detection system for a gas turbine comprises: a vibration data detection mechanism, the vibration data detection mechanism comprising: a fixing member fixedly mounted on a bearing housing connected to a gas turbine rotor; a connecting member detachably and fixedly connected to the fixing member; and an eddy current sensor detachably and fixedly connected to the connecting member, wherein the gap between a detection end of the eddy current sensor and the gas turbine rotor is adjustable.

[0009] The fixing part includes: a fixing part, which is annular in structure and fixedly mounted on a bearing seat housing connected to the gas turbine rotor; a connecting part, which is annular in structure and consistent with the inner diameter of the fixing part, the connecting part is vertically fixedly connected to the fixing part, the gas turbine rotor passes through the connecting part, and the connecting part is arranged to coincide with the center line of the gas turbine rotor.

[0010] There are two connecting pieces, and the two connecting pieces are vertically distributed.

[0011] The connecting piece includes: a connecting pipe, the outer wall of which is provided with an external thread; a self-locking nut, a connecting hole is opened on the connecting part, the self-locking nut is fixedly connected in the connecting hole, and the connecting pipe is threadedly connected to the self-locking nut; a self-locking nut, which is fixedly connected to one end of the connecting pipe located in the connecting part, and the inner diameter of the self-locking nut is smaller than the inner diameter of the connecting pipe.

[0012] The eddy current sensor includes: a probe shell, the outer wall of the probe shell is provided with two external threads, the probe shell is threadedly connected to the two self-locking nuts and extends into the connecting pipe; a detection probe, the detection probe is fixedly connected to one end of the probe shell; and an output shielded cable, the output shielded cable passes through the probe shell and is electrically connected to the detection probe.

[0013] The vibration data detection system for a gas turbine further includes a controller electrically connected to the eddy current sensor.

[0014] The vibration data detection system for a gas turbine further includes a DCS system host computer, and the DCS system host computer is electrically connected to the controller.

[0015] Beneficial effects of the utility model:

[0016] The utility model is used in a vibration data detection system for a gas turbine. The eddy current sensor is threadedly connected to the second self-locking nut, thereby facilitating adjustment of the gap between the end of the detection probe and the rotor surface. In addition, a connecting pipe is threadedly connected to the first self-locking nut, and the gap between the end of the detection probe and the rotor surface can also be adjusted through the connecting pipe, with various adjustment methods. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is an overall schematic diagram of the connection between the vibration data detection mechanism and the bearing seat housing;

[0018] Figure 2 It is a planar schematic diagram of the connection between the vibration data detection mechanism and the bearing seat housing;

[0019] Figure 3 Schematic diagram of the overall structure of the fixing parts;

[0020] Figure 4 Schematic diagram of the overall structure of the connector;

[0021] Figure 5 It is a structural diagram of the eddy current sensor;

[0022] Figure 6 This is the connection block diagram between the eddy current sensor, controller and DCS system host computer.

[0023] Description of reference numerals:

[0024] 1-Fixer; 2-Connector; 3-Eddy current sensor; 4-Fixer; 5-Connector; 6-Connecting pipe; 7-External thread 1; 8-Internal thread; 9-Self-locking nut 1; 10-Probe housing; 11-External thread 2; 12-Detection probe; 13-Output shielded cable; 14-Controller; 15-DCS system host computer. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0026] like Figures 1-6 As shown, a vibration data detection system for a gas turbine according to an embodiment of the present invention may include a vibration data detection mechanism, which may include a fixing member 1, a connecting member 2 and an eddy current sensor 3, wherein the fixing member 1 is fixedly mounted on a bearing seat housing connected to the gas turbine rotor; the connecting member 2 is detachably fixedly connected to the fixing member 1; the eddy current sensor 3 is detachably fixedly connected to the connecting member 2, and the gap between the detection end of the eddy current sensor 3 and the gas turbine rotor is adjustable.

[0027] In the embodiment of the present invention, the eddy current sensor 3 is an electromechanical conversion device that converts mechanical vibration, displacement, and rotational speed into electrical signals. It applies high-frequency alternating current to the coil at the end of the sensor. When the measured rotor gap changes, the oscillator frequency changes accordingly, thereby indirectly obtaining the relative displacement of the object's vibration. There is no direct mechanical contact between the eddy current sensor 3 and the rotor surface, and it has a very wide operating frequency range (0~10Hz).

[0028] In one embodiment of the present invention, Figure 1 and Figure 3 As shown, the fixing member 1 may include a fixing portion 4 and a connecting portion 5, the fixing portion 4 is annular in structure and is fixedly mounted on a bearing seat housing connected to the gas turbine rotor. Exemplarily, the fixing portion 4 and the bearing seat housing are fixedly connected by bolts (anti-vibration and anti-loosening bolts), welding, etc.; the connecting portion 5 is annular in structure and is consistent with the inner diameter of the fixing portion 4. The connecting portion 5 is vertically fixedly connected to the fixing portion 4. Exemplarily, the connecting portion 5 and the fixing portion 4 are fixedly connected by welding, the gas turbine rotor passes through the connecting portion 5, and the connecting portion 5 is arranged to coincide with the center line of the gas turbine rotor.

[0029] In one embodiment of the present invention, Figure 1 、 Figure 2 and Figure 4 As shown, there are two connecting members 2, and the two connecting members 2 are vertically distributed.

[0030] Specifically, the connecting member 2 may include a connecting pipe 6, a self-locking nut 9 and a self-locking nut 8, wherein the outer wall of the connecting pipe 6 is provided with an external thread 7; a connecting hole is provided on the connecting portion 5, the self-locking nut 9 is fixedly connected in the connecting hole, and the connecting pipe 6 is threadedly connected to the self-locking nut 9; the self-locking nut 8 is fixedly connected to one end of the connecting pipe 6 located in the connecting portion 5, and the inner diameter of the self-locking nut 8 is smaller than the inner diameter of the connecting pipe 6.

[0031] In one embodiment of the present invention, Figure 5 As shown, the eddy current sensor 3 includes a probe housing 10, a detection probe 12 and an output shielded cable 13, wherein the outer wall of the probe housing 10 is provided with an external thread 11, the probe housing 10 is threadedly connected to the self-locking nut 8 and extends into the connecting pipe 6; the detection probe 12 is fixedly connected to one end of the probe housing 10; the output shielded cable 13 passes through the probe housing 10 and is electrically connected to the detection probe 12.

[0032] It should be understood that the self-locking nut has the function of preventing loosening and vibration. The use of the self-locking nut to connect the connecting pipe 6 and the eddy current sensor 3 can prevent the connecting pipe 6 and the eddy current sensor 3 from loosening and falling off.

[0033] In one embodiment of the present invention, Figure 6 As shown, the vibration data detection system for a gas turbine further includes a controller 14 and a DCS system host computer 15 . The controller 14 is electrically connected to the eddy current sensor 3 , and the DCS system host computer 15 is electrically connected to the controller 14 .

[0034] When the rotor is running, the gap between the end of the detection probe 12 of the eddy current sensor 3 and the surface of the rotating shaft changes, and the AC signal output by the eddy current sensor 3 changes accordingly. The eddy current sensor 3 transmits the detected data to the controller 14, and the controller 14 then transmits the data to the DCS system host computer 15. The DCS system host computer 15 can calculate the gap change value based on the signal change, that is, the vibration value. By observing the changing trend of the vibration value, the operating status and potential faults of the equipment can be predicted.

[0035] According to the vibration data detection system for a gas turbine according to an embodiment of the present invention, the eddy current sensor 3 is threadedly connected to the self-locking nut 2 8, thereby facilitating adjustment of the gap between the end of the detection probe 12 and the rotor surface. In addition, the gap between the end of the detection probe 12 and the rotor surface can also be adjusted through the connecting pipe 6, which is threadedly connected to the self-locking nut 1 9, and the adjustment method is diverse.

[0036] Throughout this specification, reference to terms such as "one embodiment," "some embodiments," "examples," "specific examples," or "some examples" means that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0037] The above-described embodiments merely represent several implementation methods of the present invention. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that a person skilled in the art would be able to make various modifications and improvements without departing from the concept of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be determined by the appended claims.

Claims

1. A vibration data detection system for a gas turbine, characterized in that: include: A vibration data detection mechanism, the vibration data detection mechanism comprising: A fixing member, wherein the fixing member is fixedly mounted on a bearing housing connected to a gas turbine rotor; a connecting member, the connecting member being detachably fixedly connected to the fixing member; and An eddy current sensor is detachably and fixedly connected to the connecting piece, and the gap between the detection end of the eddy current sensor and the gas turbine rotor is adjustable.

2. The vibration data detection system for a gas turbine according to claim 1, characterized in that: The fixing member includes: A fixing portion, which is an annular structure and is fixedly mounted on a bearing housing connected to a gas turbine rotor; The connecting part has an annular structure and is consistent with the inner diameter of the fixing part. The connecting part is vertically fixedly connected to the fixing part. The gas turbine rotor passes through the connecting part. The connecting part is arranged to coincide with the center line of the gas turbine rotor.

3. The vibration data detection system for a gas turbine according to claim 2, characterized in that: There are two connecting pieces, and the two connecting pieces are vertically distributed.

4. The vibration data detection system for a gas turbine according to claim 3, characterized in that: The connecting piece includes: A connecting pipe, wherein the outer wall of the connecting pipe is provided with an external thread 1; A self-locking nut 1, wherein a connecting hole is provided on the connecting portion, the self-locking nut 1 is fixedly connected in the connecting hole, and the connecting pipe is threadedly connected to the self-locking nut 1; A second self-locking nut is fixedly connected to one end of the connecting pipe located in the connecting portion, and the inner diameter of the second self-locking nut is smaller than the inner diameter of the connecting pipe.

5. The vibration data detection system for a gas turbine according to claim 4, characterized in that: The eddy current sensor comprises: A probe housing, wherein the outer wall of the probe housing is provided with a second external thread, the probe housing is threadedly connected to the second self-locking nut and extends into the connecting pipe; A detection probe, the detection probe being fixedly connected to one end of the probe housing; An output shielded cable passes through the probe housing and is electrically connected to the detection probe.

6. The vibration data detection system for a gas turbine according to claim 5, characterized in that: It also includes a controller, which is electrically connected to the eddy current sensor.

7. The vibration data detection system for a gas turbine according to claim 6, characterized in that: It also includes a DCS system host computer, which is electrically connected to the controller.

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