Combustion control pressure fluctuation probe for combustion engine

Abstract

The utility model discloses gas turbine combustion control pressure fluctuation probe belongs to sensor technical field, including detection head, protective housing, cooling mechanism and mounting mechanism, the spiral cooling pipe is set in protective housing inner wall, the inside of spiral cooling pipe is provided with the flow guide component that is composed of flow cone, flow vane and spiral flow vane axle, cooling liquid impact flow vane drives spiral flow vane axle rotation, forms spiral liquid flow in spiral cooling pipe, and the heat exchange is strengthened, the mounting mechanism is through the sliding fit of limiting sliding block and limiting groove and the lock of the through setting of plug shaft and lock nut, realizes the multidirectional location of probe Fixed, the utility model discloses through the spin flow guide intensification cooling, effectively avoids the overheating damage of probe, improves the work reliability, and the installation structure simplifies the installation process, and the firm fixed, the strong anti -vibration ability, guarantees the measurement stability.

Description

Technical Field

[0001] This utility model relates to the field of sensor technology, and in particular to a pressure fluctuation probe for combustion control of gas turbines. Background Technology

[0002] As a key power equipment, the combustion stability inside the combustion chamber of a gas turbine is directly related to the safety and efficiency of the entire machine. In order to achieve accurate monitoring and timely control of the combustion state, pressure fluctuation probes need to be installed in high-temperature and high-pressure areas such as the combustion chamber to collect pressure pulsation signals in real time during the combustion process.

[0003] However, the working environment of the probe is extremely harsh, with the temperature in the combustion chamber often reaching thousands of degrees Celsius. This extreme high temperature poses a severe test to the precision sensing elements inside the probe. Existing probe cooling methods usually employ simple cooling jackets or internal flow channel designs. The convective heat transfer efficiency of this structure is relatively limited. When facing the huge thermal radiation and thermal convection generated by the gas turbine operating at high load, the cooling effect is often insufficient, which can easily lead to excessively high probe operating temperature. This not only affects the accuracy of the measurement signal but also greatly shortens the probe's service life and may even cause the probe to burn out.

[0004] In addition, gas turbines generate severe mechanical vibrations during operation. If the pressure fluctuation probes installed on the combustion chamber are not securely fixed, they will shift or loosen in the vibrating environment. Existing installation mechanisms are often complex in structure and cumbersome in installation process, requiring a lot of time for alignment and tightening. Some traditional fixing methods are prone to loosening of fasteners or installation displacement under the strong vibration impact of the gas turbine. This not only leads to distortion of the pressure fluctuation signals collected by the probe, affecting the judgment of the combustion control system, but may also cause safety accidents such as probe detachment, resulting in insufficient reliability.

[0005] Therefore, this invention proposes a gas turbine combustion control pressure fluctuation probe to address the shortcomings of existing technologies. Utility Model Content

[0006] In view of the problems existing in the gas turbine combustion control pressure fluctuation probe, such as low heat exchange efficiency due to simple cooling structure, easy overheating damage at high temperature, complex installation and fixing method, insufficient stability, and susceptibility to vibration, this utility model aims to provide a gas turbine combustion control pressure fluctuation probe with improved structure that can effectively solve the above problems.

[0007] This utility model provides a gas turbine combustion control pressure fluctuation probe, including: a probe head, and a protective shell surrounding the probe head, and a cooling mechanism disposed in the protective shell; the cooling mechanism includes a cooling water tank, a spiral cooling pipe disposed in the inner wall of the protective shell, and a flow guiding component disposed inside the spiral cooling pipe.

[0008] The flow guiding assembly includes a flow guiding cone, a flow guiding impeller, a helical flow guiding blade shaft, and a bearing housing for supporting the helical flow guiding blade shaft.

[0009] Furthermore, the spiral cooling pipe is spirally wound around the inner wall of the protective shell; the guide vane is coaxially fixed to the spiral guide vane shaft, and the spiral guide vane shaft is rotatably installed inside the spiral cooling pipe through the bearing seat; the guide cone is disposed at the coolant inlet end of the spiral cooling pipe and is directly opposite the guide vane.

[0010] Preferably, the gas turbine combustion control pressure fluctuation probe further includes a cooling water tank and a return water pipe. The cooling water tank supplies coolant to the coolant inlet end of the spiral cooling pipe via a pipeline, and the return water pipe connects the coolant outlet end of the spiral cooling pipe to the cooling water tank.

[0011] Preferably, the outer edge of the bearing housing makes rolling contact with the inner wall of the spiral cooling pipe, so that the bearing housing can rotate along the inner wall of the spiral cooling pipe when the spiral guide vane shaft rotates.

[0012] Preferably, the bottom of the protective housing is connected to a mounting block, and the gas turbine combustion control pressure fluctuation probe further includes a mounting mechanism for fixing the mounting block, the mounting mechanism including a fixing seat.

[0013] Preferably, the inner wall of the fixing seat is provided with a limiting groove, and the outer wall of the mounting block is correspondingly provided with a limiting slider, the limiting slider being slidably engaged with the limiting groove.

[0014] Preferably, the mounting mechanism further includes a insertion shaft, and both the fixing seat and the mounting block are provided with through holes for the insertion shaft to pass through.

[0015] Preferably, the mounting mechanism further includes a connecting plate, and the insertion shaft is disposed at both ends of the connecting plate.

[0016] Preferably, the mounting mechanism further includes a lock nut, which is threaded onto the end of the insert shaft.

[0017] This utility model has the following beneficial effects:

[0018] 1. This utility model, by setting a spiral cooling pipe on the inner wall of the protective shell, and setting a spin-guided flow assembly composed of a guide cone, a guide paddle, and a spiral guide vane shaft inside the spiral cooling pipe, causes the coolant to form a forced spiral flow in the spiral pipe, which synergistically enhances heat transfer. This solves the problem of simple probe cooling structure and low heat transfer efficiency in the prior art, which leads to the probe being prone to overheating and damage in high-temperature environments. It achieves the technical effect of efficient cooling and reliable protection of the probe, and significantly improves the working reliability and service life of the probe under harsh working conditions.

[0019] 2. This utility model solves the problems of complex probe installation, insufficient fixation stability, and easy loosening under vibration in the prior art, which affect measurement accuracy. It achieves the technical effects of simplifying the installation process and improving work efficiency. It also achieves all-round stable fixation of the probe, enhances the device's anti-vibration ability, and ensures long-term stability and measurement accuracy. Attached Figure Description

[0020] Figure 1 This is a three-dimensional view of the gas turbine combustion control pressure fluctuation probe proposed in this utility model;

[0021] Figure 2 This is a split view of the probe head of the gas turbine combustion control pressure fluctuation probe proposed in this utility model;

[0022] Figure 3 This is an exploded view of the installation mechanism of the gas turbine combustion control pressure fluctuation probe proposed in this utility model;

[0023] Figure 4 This is a schematic diagram of the spiral cooling tube of the gas turbine combustion control pressure fluctuation probe proposed in this utility model.

[0024] Figure 5 This is a schematic diagram of the cooling mechanism of the gas turbine combustion control pressure fluctuation probe proposed in this utility model.

[0025] Legend:

[0026] 1. Probe head; 2. Cooling mechanism; 201. Cooling water tank; 202. Spiral cooling pipe; 203. Return water pipe; 204. Bearing housing; 205. Guide vane; 206. Spiral guide vane shaft; 207. Guide cone; 3. Installation mechanism; 301. Fixing base; 302. Limiting slider; 303. Limiting groove; 304. Insert shaft; 305. Connecting plate; 306. Anti-loosening nut; 4. Protective shell; 5. Mounting block. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions in the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model.

[0028] Example:

[0029] Please refer to Figure 1 The gas turbine combustion control pressure fluctuation probe includes a probe head 1, a cooling mechanism 2, a mounting mechanism 3, a protective shell 4, and a mounting block 5. The probe head 1 is located in the internal cavity of the protective shell 4, which surrounds the probe head 1 and provides structural protection. The cooling mechanism 2 is located on the inner wall of the protective shell 4 and is used to cool the protective shell 4 and the probe head 1 inside. The mounting block 5 is fixedly connected to the bottom of the protective shell 4. The mounting mechanism 3 is used to detachably fix the mounting block 5, thereby achieving a stable installation of the entire gas turbine combustion control pressure fluctuation probe.

[0030] like Figure 2 , Figure 4 and Figure 5 As shown, the cooling mechanism 2 includes a cooling water tank 201, a spiral cooling pipe 202, a return water pipe 203, a bearing seat 204, a guide vane 205, a spiral guide vane shaft 206, and a guide cone 207. The spiral cooling pipe 202 is spirally wound around the inner wall of the protective shell 4. The cooling water tank 201 is connected to the coolant inlet end of the spiral cooling pipe 202 through a pipe. The return water pipe 203 is connected to the coolant outlet end of the spiral cooling pipe 202 and the cooling water tank 201 to form a cooling circulation loop.

[0031] like Figure 3 As shown, the installation mechanism 3 includes a fixed base 301, a limiting slider 302, a limiting groove 303, a plug shaft 304, a connecting plate 305, and a lock nut 306. The fixed base 301 is used to accommodate the installation block 5. The limiting slider 302 is set on the outer wall of the installation block 5. The limiting groove 303 is opened on the inner wall of the fixed base 301. The limiting slider 302 and the limiting groove 303 are slidably engaged. The plug shaft 304 is fixedly connected to both ends of the connecting plate 305. The plug shaft 304 is used to pass through the fixed base 301 and the installation block 5. The lock nut 306 is used to lock the plug shaft 304.

[0032] Please refer to Figure 2 , Figure 4 and Figure 5The spiral cooling pipe 202 is internally equipped with a flow guiding assembly, which includes a flow guiding cone 207, a flow guiding impeller 205, a spiral flow guiding blade shaft 206, and a bearing seat 204. The flow guiding cone 207 is integrally formed at the coolant inlet end of the spiral cooling pipe 202 and faces the incoming flow direction, used to initially disperse the incoming coolant. The flow guiding impeller 205 is coaxially and fixedly connected to the spiral flow guiding blade shaft 206. The spiral flow guiding blade shaft 206 is rotatably mounted inside the spiral cooling pipe 202 through the bearing seat 204. The outer edge of the bearing seat 204 rolls in contact with the inner wall of the spiral cooling pipe 202, thereby supporting the rotation of the spiral flow guiding blade shaft 206. The bearing housing 204 itself can also rotate along the inner wall of the spiral cooling pipe 202. In the assembled state, the guide vane 205 faces the guide cone 207 and rotates due to the impact of the dispersed coolant, which in turn drives the spiral guide vane shaft 206 to rotate at high speed. The rotation of the spiral guide vane shaft 206 will agitate the coolant in the spiral cooling pipe 202 to form a spiral liquid flow. This forced internal spiral liquid flow works in conjunction with the spiral structure of the spiral cooling pipe 202 itself to greatly increase the contact time and heat exchange area between the coolant and the pipe wall, and significantly improve the heat exchange efficiency, thereby forming a highly efficient heat insulation protection layer for the protective shell 4 and the internal probe head 1.

[0033] As a preferred embodiment, to construct a complete cooling cycle, please refer to... Figure 5 The gas turbine combustion control pressure fluctuation probe also includes a cooling water tank 201 and a return water pipe 203. The cooling water tank 201 supplies coolant to the inlet end of the spiral cooling pipe 202 via a pipeline. The return water pipe 203 connects the outlet end of the spiral cooling pipe 202 to the cooling water tank 201. The cooling water tank 201 recools the recovered coolant.

[0034] As a preferred embodiment, to achieve stable rotation of the flow guiding component, please refer to... Figure 4 and Figure 5 The outer edge of the bearing housing 204 makes rolling contact with the inner wall of the spiral cooling pipe 202, so that the bearing housing 204 can rotate synchronously along the inner wall of the spiral cooling pipe 202 when the spiral guide vane shaft 206 rotates, thereby reducing rotational resistance.

[0035] As a preferred embodiment, for secure installation of the device, please refer to... Figure 1 and Figure 3 The bottom of the protective shell 4 is fixedly connected to the mounting block 5. The gas turbine combustion control pressure fluctuation probe also includes a mounting mechanism 3. The mounting mechanism 3 includes a fixed base 301. The mounting block 5 is pluggably installed in the mounting cavity of the fixed base 301.

[0036] As a preferred embodiment, in order to achieve forward and backward directional limiting during installation, please refer to... Figure 3The inner wall of the fixed base 301 is symmetrically provided with limiting grooves 303, and the outer wall of the mounting block 5 is integrally formed with a limiting slider 302 that slides in cooperation with the limiting groove 303. The limiting slider 302 slides precisely into the limiting groove 303.

[0037] As a preferred embodiment, to achieve locking in the left-right and up-down directions during installation, please refer to... Figure 3 The mounting mechanism 3 also includes a shaft 304, a connecting plate 305, and a locking nut 306. The two side walls of the fixing seat 301 and the interior of the mounting block 5 are provided with through holes for the shaft 304 to pass through. The connecting plate 305 is integrally fixedly connected to one end of the shaft 304. The shaft 304 passes through the through holes of the fixing seat 301 and the mounting block 5. The locking nut 306 is threaded to the end of the shaft 304 and is used to lock the mounting block 5 in the fixing seat 301.

[0038] Working principle: When the probe 1 needs to be cooled while operating in the combustion chamber, the cooling mechanism 2 comes into play. Since the spiral cooling pipe 202 is spirally wound around the inner wall of the protective shell 4 and surrounds the probe 1, when the coolant in the cooling water tank 201 flows through the spiral cooling pipe 202 and the guide vane 205, the guide cone 207 disperses the coolant. The spiral guide vane shaft 206 rotates under the influence of the dispersed coolant. When the spiral guide vane shaft 206 and the guide vane 205 rotate, they drive the bearing seat 204 to rotate within the spiral cooling pipe 202. The inner wall of 2 rotates, and the rotation of the spiral guide vane shaft 206 generates a spiral coolant flow. The spiral cooling pipe 202 and the spiral coolant flow inside it work together to increase the contact time and heat exchange area between the coolant and the protective shell 4, preventing external heat from entering the probe head 1 and forming a protective layer to prevent the probe head 1 from overheating and being damaged. The coolant flows through the spiral cooling pipe 202 and is transported back to the cooling water tank 201 through the return water pipe 203. The cooling water tank 201 cools the coolant and completes the coolant circulation.

[0039] Furthermore, when it is necessary to fix the protective shell 4, the mounting block 5 at the bottom of the protective shell 4 is first inserted into the inner wall of the fixing base 301. During this process, the limiting slider 302 slides along the inner wall of the limiting groove 303. The limiting slider 302 and the limiting groove 303 cooperate to limit the front and rear directions of the probe head 1. After insertion, the insertion shafts 304 at both ends of the connecting plate 305 are inserted into the inner wall of the fixing base 301 and pass through the mounting block 5. After completion, the anti-loosening nut 306 is screwed into the insertion shaft 304, which completes the limitation of the probe head 1 in the left, right and up and down directions. Through the coordinated action of various components in the mounting mechanism 3, the probe head 1 is fixed in all directions, which simplifies the process of fixing the probe head 1 and improves work efficiency.

Claims

1. Gas turbine combustion control pressure fluctuation probe, which includes: The probe head (1) and the protective housing (4) surrounding the probe head (1); Cooling mechanism (2) provided in the protective housing (4); Its features are, The cooling mechanism (2) includes a cooling water tank (201), and the inner wall of the protective shell (4) is provided with a spirally wound spiral cooling pipe (202); The spiral cooling pipe (202) is provided with a flow guiding assembly inside, which includes a flow guiding cone (207), a flow guiding blade (205), a spiral flow guiding blade shaft (206), and a bearing seat (204) for supporting the spiral flow guiding blade shaft (206); The guide vane (205) is coaxially fixed to the spiral guide vane shaft (206), and the spiral guide vane shaft (206) is rotatably mounted in the spiral cooling pipe (202) through the bearing seat (204); The guide cone (207) is located at the coolant inlet end of the spiral cooling pipe (202) and is directly opposite the guide paddle (205).

2. The gas turbine combustion control pressure fluctuation probe according to claim 1, characterized in that, The gas turbine combustion control pressure fluctuation probe also includes a cooling water tank (201) and a return water pipe (203). The cooling water tank (201) supplies coolant to the coolant inlet end of the spiral cooling pipe (202) via a pipeline. The return water pipe (203) connects the coolant outlet end of the spiral cooling pipe (202) to the cooling water tank (201).

3. The gas turbine combustion control pressure fluctuation probe according to claim 1, characterized in that, The outer edge of the bearing housing (204) makes rolling contact with the inner wall of the spiral cooling pipe (202) so that the bearing housing (204) can rotate along the inner wall of the spiral cooling pipe (202) when the spiral guide vane shaft (206) rotates.

4. The gas turbine combustion control pressure fluctuation probe according to claim 1, characterized in that, The bottom of the protective shell (4) is connected to a mounting block (5), and the gas turbine combustion control pressure fluctuation probe also includes a mounting mechanism (3) for fixing the mounting block (5), the mounting mechanism (3) including a fixing seat (301).

5. The gas turbine combustion control pressure fluctuation probe according to claim 4, characterized in that, The inner wall of the fixed base (301) is provided with a limiting groove (303), and the outer wall of the mounting block (5) is provided with a limiting slider (302), which slides in the limiting groove (303).

6. The gas turbine combustion control pressure fluctuation probe according to claim 4, characterized in that, The mounting mechanism (3) also includes a insert shaft (304), and both the fixing seat (301) and the mounting block (5) are provided with through holes for the insert shaft (304) to pass through.

7. The gas turbine combustion control pressure fluctuation probe according to claim 6, characterized in that, The mounting mechanism (3) further includes a connecting plate (305), and the insertion shaft (304) is disposed at both ends of the connecting plate (305).

8. The gas turbine combustion control pressure fluctuation probe according to claim 6, characterized in that, The mounting mechanism (3) also includes a lock nut (306), which is threaded to the end of the insert shaft (304).

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