Bearing cavity temperature measurement lead structure

Abstract

The application relates to the field of aviation gas turbine engine lubricating systems, and relates to a bearing cavity temperature measurement lead structure. A containing cavity is formed on the inner ring surface of a labyrinth ring, a temperature measurement chip is arranged in the containing cavity, the temperature measurement chip can work normally at a suitable temperature, a lead hole is formed to lead out a temperature measurement lead connected with the temperature measurement chip, the temperature measurement lead is connected with a temperature sensor and is placed at a measurement point, the temperature sensor collects signals at the measurement point, transmits the signals to the temperature measurement chip through the temperature measurement lead, and stores and processes the signals, after the measurement is completed, the temperature measurement chip is removed to export data, the measurement is convenient and stable, and a battery is arranged on the temperature measurement chip to ensure stable power supply of the temperature measurement chip.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aviation gas turbine engine lubrication system, and particularly relates to a bearing cavity temperature measurement lead structure. BACKGROUND

[0002] The aviation gas turbine engine lubrication system is an important component of the aviation gas turbine engine, and mainly undertakes the lubrication work of the high and low pressure rotor fulcrum bearings, transmission gears and other components of the engine. The inner ring of the rolling bearing between the rotating shafts is supported on the high rear shaft neck, and the outer ring is supported on the low pressure turbine shaft. The main function is to support the relative motion of the high and low pressure turbine rotors, and to ensure the stable work of the high and low pressure turbine rotors of the aviation engine. Since the bearing is in a high temperature environment (the bearing cavity temperature can reach 200℃), the speed is high (the DN value is as high as 3X10 6 , the bearing roller speed reaches more than 200000 rpm), the design of the structure at this place will directly affect the safety of the aviation gas turbine engine. At present, the rolling bearing between the rotating shafts of a certain type of engine has occurred many times. The failure seriously affects the development progress of the type. In order to reduce the risk of bearing damage, it is urgent to measure the temperature at the bearing.

[0003] In order to ensure the reliable work and long service life of the bearing, the bearing must be fully cooled and lubricated, and the temperature distribution of the main bearing of the engine must be measured and analyzed to evaluate the cooling and lubrication effect of the bearing. At present, there are few ways to evaluate the cooling and lubrication effect of the bearing. The test equipment, measurement environment and test space conditions are limited. The main parameters monitored by the oil system include oil supply temperature, pressure, and oil return temperature and pressure of each cavity. The trend of oil return temperature is used to determine whether the heat generation of each cavity is normal, but it cannot directly determine whether the bearing is fully cooled and lubricated. During the operation of the engine, the inner and outer rings of the rolling bearing between the rotating shafts are in a high speed rotating state. The temperature of the inner ring of the bearing cannot be measured by the conventional contact lead method, and a non-direct lead measurement method must be used for measurement, so as to further analyze the temperature distribution of the rolling bearing between the rotating shafts of the engine, and to ensure the safe and reliable work of the bearing.

[0004] There are many non-direct lead temperature measurement schemes at present, including non-contact temperature measurement such as infrared temperature measurement and optical fiber temperature measurement, and wireless transmission temperature measurement scheme. At present, the infrared and optical fiber temperature measurement are limited by the size of the measurement equipment, and cannot be applied to the temperature measurement of the inner ring of the rolling bearing between the rotating shafts. The wireless transmission temperature measurement cannot effectively transmit the measured signal in the bearing cavity to the outside of the engine, and cannot complete the measurement. Therefore, a new structure scheme needs to be designed to stably measure the temperature of the inner ring of the rotor bearing. SUMMARY

[0005] The purpose of the present application is to provide a bearing cavity temperature measurement lead structure to solve the problem that it is difficult to effectively measure the temperature in the bearing cavity in the prior art.

[0006] The technical solution of the present application is: a bearing cavity temperature measurement lead structure, comprising a high-pressure turbine shaft, a low-pressure turbine shaft, a cylindrical roller bearing arranged between the high-pressure turbine shaft and the low-pressure turbine shaft, and a labyrinth ring arranged between the high-pressure turbine shaft and the low-pressure turbine shaft, wherein the inner ring surface of the labyrinth ring is provided with a containing cavity, the containing cavity is provided with a shell connected with the labyrinth ring, and the shell is provided with a measurement chip; the labyrinth ring is provided with a lead hole, the measurement chip is provided with a temperature measurement lead, the temperature measurement lead is led out of the lead hole and introduced into a measurement point, and a temperature sensor is arranged at the end of the temperature measurement lead away from the measurement chip.

[0007] Preferably, the temperature measurement lead has four groups, and two temperature measurement leads are introduced into the labyrinth ring, one is introduced into the side wall surface of the bearing inner ring, and the other is introduced into the inner surface of the bearing inner ring.

[0008] Preferably, the temperature measurement lead has four groups, and two temperature measurement leads are introduced into the labyrinth ring to form a first measurement point and a second measurement point; one is introduced into the side wall surface of the bearing inner ring to form a third measurement point; and one is introduced into the inner surface of the bearing inner ring to form a fourth measurement point.

[0009] Preferably, the shell comprises an upper shell and a lower shell, the outer wall surfaces of the upper shell and the lower shell are both arc surfaces coaxially arranged with the labyrinth ring, a closed inner cavity is arranged between the upper shell and the lower shell, the temperature measurement chip is arranged in the inner cavity, and the upper shell, the lower shell and the labyrinth ring are provided with lead holes for leading out the temperature measurement lead.

[0010] Preferably, the inner wall surface of the labyrinth ring is provided with a cylindrical inner hole arranged along the radial direction of the main shaft, the upper shell is provided with a cylindrical mounting seat arranged along the radial direction of the main shaft, and the mounting seat is inserted into the inner hole.

[0011] Preferably, a clamping ring is arranged coaxially in the inner hole, and an annular clamping groove is arranged on the mounting seat and can be clamped with the clamping ring.

[0012] Preferably, the two side wall surfaces of the upper shell and the lower shell are both provided with bosses abutting against the inner wall of the containing cavity, and the inner wall surface of the lower shell is provided with a limiting groove matched with the high-pressure turbine shaft.

[0013] Preferably, the containing cavity is a ring groove with a size of 18.6mmX10mm.

[0014] The bearing cavity temperature measurement lead structure of the application can work normally at a suitable temperature by setting the temperature measurement chip in the accommodating cavity on the inner ring surface of the labyrinth ring, and can draw out the temperature measurement lead connected with the temperature measurement chip through the lead hole, the temperature measurement lead is connected with the temperature sensor and placed at the measurement point to be measured, the temperature sensor collects the signal at the measurement point and transmits it to the temperature measurement chip for processing and storage through the temperature measurement lead, and after the measurement is completed, the temperature measurement chip is removed to export the data, which is convenient and stable for measurement, and the battery is arranged on the temperature measurement chip to ensure the stable power supply of the temperature measurement chip. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical solutions provided by the application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the application.

[0016] Figure 1 It is a schematic diagram of the overall structure of the application.

[0017] Figure 2 It is a schematic diagram of the cross-sectional structure of the application.

[0018] Figure 3 It is a schematic diagram of the structure of the measuring chip highlighted by the shell of the application.

[0019] Figure 4 It is a schematic diagram of the overall structure of the shell of the application.

[0020] 1, high pressure turbine shaft; 2, low pressure turbine shaft; 3, cylindrical roller bearing; 4, labyrinth ring; 5, accommodating cavity; 6, measuring chip; 7, lead hole; 8, temperature measurement lead; 9, first measurement point; 10, second measurement point; 11, third measurement point; 12, fourth measurement point; 13, upper shell; 14, lower shell; 15, mounting seat; 16, annular clamping groove; 17, boss; 18, limiting groove. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the application clearer, the technical solutions in the embodiments of the application will be described in more detail below in combination with the drawings in the embodiments of the application.

[0022] A bearing cavity temperature measurement lead structure, as Figure 1 , Figure 2As shown, including high pressure turbine shaft 1, low pressure turbine shaft 2, cylindrical roller bearing 3, grid ring 4. The bearing inner ring of the cylindrical roller bearing 3 is connected with the high pressure turbine shaft 1, and the bearing outer ring is connected with the low pressure turbine shaft 2; the grid ring 4 is arranged between the high pressure turbine shaft 1 and the low pressure turbine shaft 2 and abuts against the high pressure turbine shaft 1, and plays a closing role between the high pressure turbine shaft 1 and the low pressure turbine shaft 2; the grid ring 4 is arranged at the inlet of the core machine, and one side of the grid ring 4 abuts against the bearing inner ring of the cylindrical roller bearing 3.

[0023] Through the analysis of the structure, it can be known that, since the grid ring 4 is close to the cylindrical roller bearing 3, and the grid ring 4 and the high pressure turbine shaft 1 can form a relatively closed structure, and the grid ring 4 can rotate synchronously with the high pressure turbine shaft 1, close to the outside of the core machine, therefore, the temperature measuring structure arranged in the grid ring 4 can effectively meet the temperature measuring demand.

[0024] Specifically, the inner ring surface of the grid ring 4 is provided with a containing cavity 5, the containing cavity 5 is provided with a shell connected with the grid ring 4, and the shell is provided with a measuring chip 6; the grid ring 4 is provided with a lead hole 7, the measuring chip 6 is provided with a temperature measuring lead 8, the temperature measuring lead 8 is led out from the lead hole 7 and led into a measuring point, and a temperature sensor is arranged at the end of the temperature measuring lead 8 away from the measuring chip 6, and the temperature sensor is arranged on the measuring point; the measuring chip is provided with a battery.

[0025] When measuring, the temperature of the measuring point is detected by the temperature sensor, the detected signal is transmitted to the measuring chip 6 inside the grid ring 4 through the temperature measuring lead 8, and the measuring chip 6 rotates synchronously with the high pressure turbine shaft 1 under the limiting of the shell, so that the signal of the temperature measuring lead 8 can be stably received and processed and stored, and after the measurement is completed, the measuring chip is disassembled, the temperature data is read through special software, and since the temperature in the grid ring 4 is low, the measuring chip can work stably and accurately measure the temperature of the measuring point. The temperature change of the inner ring of the roller bearing between the rotating shafts under different rotating speeds is measured in the harsh environment of the narrow space of the engine, oil and gas mixing, high temperature and high centrifugal force. It provides valuable data support for optimizing the bearing structure design and improving the bearing reliability.

[0026] Preferably, the temperature measuring lead 8 has four groups, and two temperature measuring leads 8 are led into the grid ring 4 to form a first measuring point 9 and a second measuring point 10; one is led into the side wall surface of the bearing inner ring to form a third measuring point 11; and one is led into the inner surface of the bearing inner ring to form a fourth measuring point 12. By arranging four temperature measuring leads 8, the temperatures of the grid ring 4, the inner surface and the side wall surface of the bearing inner ring of the cylindrical roller bearing 3 can be accurately measured. At the same time, since the second measuring point 10, the third measuring point 11 and the fourth measuring point 12 cannot be directly measured by the lead, the joint can be processed near the contact surface between the grid ring 4 and the bearing inner ring.

[0027] As Figure 3 , Figure 4 shown, preferably, a ring groove of 18.6mmX10mm is formed at the accommodating cavity 5, the shell comprises an upper shell 13 connected with the gill ring 4 and a lower shell 14 connected with the high-pressure turbine shaft 1, the outer wall surface of the upper shell 13 and the lower shell 14 is a circular arc surface coaxially arranged with the gill ring 4, a closed inner cavity is arranged between the upper shell 13 and the lower shell 14, the temperature measuring chip is arranged in the inner cavity, the upper shell 13, the lower shell 14 and the gill ring 4 are provided with lead hole 7 for leading out the temperature measuring lead 8, the lead hole 7 on the gill ring 4 is arranged at the corner corresponding to the lower shell 14.

[0028] The temperature measuring chip is clamped between the upper shell 13 and the lower shell 14 to realize stable fixation of the temperature measuring chip, the length of the upper shell 13 and the lower shell 14 is 18mm to facilitate installation, the lead hole 7 is arranged to stably lead out the temperature measuring lead 8 and play a certain guiding and fixing role for the temperature measuring lead 8.

[0029] Preferably, a cylindrical inner hole is arranged on the inner wall surface of the gill ring 4 along the radial direction of the main shaft, a cylindrical mounting seat 15 is arranged on the upper shell 13 along the radial direction of the main shaft, and the mounting seat 15 is inserted into the inner hole. Through the cooperation of the mounting seat 15 and the inner hole, the upper shell 13 and the gill ring 4 are stably fixed.

[0030] Preferably, a clamping ring is arranged coaxially in the inner hole, an annular clamping groove 16 capable of clamping the clamping ring is arranged on the mounting seat 15, and the gill ring 4 and the upper shell 13 are further fixed through the arrangement of the clamping ring and the annular clamping groove 16.

[0031] Preferably, a boss 17 abutting against the inner wall of the accommodating cavity 5 is arranged on the two side wall surfaces of the upper shell 13 and the lower shell 14, and a limiting groove 18 cooperating with the high-pressure turbine shaft 1 is arranged on the inner wall surface of the lower shell 14. Because the temperature of the gill ring 4 is relatively high, the arrangement of the boss 17 can avoid the side surface of the upper shell 13 and the lower shell 14 from contacting the side surface of the gill ring 4, preventing the temperature measuring chip in the shell from being burned out due to too high temperature, and the arrangement of the limiting groove 18 can stably position and clamp the lower shell 14 and the high-pressure turbine shaft 1.

[0032] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any changes or replacements within the technical range disclosed by the present application can be easily thought by those skilled in the art, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A bearing cavity temperature sensing lead structure, comprising a high-pressure turbine shaft (1), a low-pressure turbine shaft (2), a cylindrical roller bearing (3) disposed between the high-pressure turbine shaft (1) and the low-pressure turbine shaft (2), and a toothed ring (4) disposed between the high-pressure turbine shaft (1) and the low-pressure turbine shaft (2), characterized in that: The inner ring surface of the toothed ring (4) is provided with a receiving cavity (5), and the receiving cavity (5) is provided with a housing connected to the toothed ring (4). The housing is provided with a measuring chip (6). The toothed ring (4) is provided with a lead hole (7), and the measuring chip (6) has a temperature measuring lead (8). The temperature measuring lead (8) is led out from the lead hole (7) and introduced into the measuring point. The end of the temperature measuring lead (8) away from the measuring chip (6) has a temperature sensor. The temperature sensor is installed at the measuring point. The measuring chip (6) is provided with a battery. There are four sets of temperature measuring leads (8), and two temperature measuring leads (8) are introduced into the toothed ring (4) to form the first measuring point (9) and the second measuring point (10); one is introduced into the inner ring side wall of the bearing to form the third measuring point (11); and one is introduced into the inner surface of the inner ring of the bearing to form the fourth measuring point (12). The second measuring point (10) is located on the side of the first measuring point (9) close to the cylindrical roller bearing (3). The second measuring point (10), the third measuring point (11) and the fourth measuring point (12) are respectively subjected to jointing treatment.

2. The bearing cavity temperature sensing lead structure as described in claim 1, characterized in that: The housing includes an upper housing (13) and a lower housing (14). The outer walls of the upper housing (13) and the lower housing (14) are both arc surfaces coaxially arranged with the toothed ring (4). A closed inner cavity is opened between the upper housing (13) and the lower housing (14). The measuring chip (6) is located in the inner cavity. The upper housing (13), the lower housing (14), and the toothed ring (4) are provided with lead holes (7) for the temperature measuring lead wire (8) to be led out.

3. The bearing cavity temperature sensing lead structure as described in claim 2, characterized in that: The inner wall of the toothed ring (4) is provided with a cylindrical inner hole arranged radially along the main axis, and the upper housing (13) is provided with a cylindrical mounting seat (15) arranged radially along the main axis, and the mounting seat (15) is inserted into the inner hole.

4. The bearing cavity temperature sensing lead structure as described in claim 3, characterized in that: The inner hole is provided with a coaxial retaining ring, and the mounting base (15) is provided with an annular groove (16) that can engage with the retaining ring.

5. The bearing cavity temperature sensing lead structure as described in claim 2, characterized in that: The upper housing (13) and the lower housing (14) are provided with protrusions (17) on both sides of the side wall that abut against the inner wall of the receiving cavity (5), and the lower housing (14) is provided with a limiting groove (18) that cooperates with the high-pressure turbine shaft (1).

6. The bearing cavity temperature sensing lead structure as described in claim 1, characterized in that: The receiving cavity (5) is an annular groove of 18.6mm x 10mm.

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