Aero-engine afterburner temperature sensing part calibration test device

Abstract

The invention provides an aero-engine afterburner temperature sensing part calibration test device, and relates to the field of aviation tests, the aero-engine afterburner temperature sensing part calibration test device comprises a device lower mounting seat and a device upper mounting seat, the lower mounting seat is fixed on the outer wall of a gas channel in a sealed manner, and the upper mounting seat is fixed on the lower mounting seat in a sealed manner to form a sealed cavity; a sensing part mounting seat and a temperature sensing part, the sensing part mounting seat is arranged in the sealed cavity and is fixedly connected with the pipe wall of the gas channel, the temperature sensing part is fixedly mounted on the sensing part mounting seat, and a sensing part mounting hole in the sensing part mounting seat is arranged to be a U-shaped groove, so that radial adjustment of the temperature sensing part is realized through the U-shaped groove; the top of the upper mounting base is provided with a cooling gas connector, so that cooling gas is introduced into the sealing cavity through the cooling gas connector, and air cooling is carried out on the galvanic couple lead part of the temperature sensing part. According to the invention, the height of the temperature sensing part can be adjusted in the radial direction, and the sealing performance is good.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation testing, and in particular to a calibration test device for a temperature sensing part of an afterburner combustion chamber of an aviation engine. Background Art

[0002] The afterburner is a key component of an aircraft engine. Its outlet is characterized by high temperatures and high flow rates. Currently, afterburner outlet temperature measurement is mostly performed using a fixed temperature sensor. This fixed installation approach has the disadvantage that the afterburner outlet temperature sensor is exposed to high-temperature gases for extended periods, subjecting it to erosion and potentially causing temperature failure or a decrease in measurement accuracy. Therefore, regular calibration testing of the temperature sensor is necessary to ensure accuracy.

[0003] Based on the above test requirements, a large amount of literature was consulted. Most domestic and foreign calibration tests for the temperature sensing part are conducted under atmospheric pressure. However, most aircraft engine afterburner outlet pressure tests are conducted under pressure. Therefore, the existing calibration test conditions differ significantly from the actual operating conditions. To meet the actual test requirements of the afterburner outlet temperature sensing part, it is urgent to design a calibration device that can withstand high temperatures and high pressures. In addition, due to the influence of the flow and heat transfer of the water jacket cooling water, it is difficult to achieve uniform temperature across the entire measurement section within the straight pipe section. Even under different test conditions, the temperature difference between the combustion core area and the boundary area can reach as high as 100°C. Therefore, the uniform temperature measurement area that can meet the calibration test requirements is small. Based on this, when there is a stable heat source at the front end of the temperature sensing part's intake, the radial height of the temperature sensing part needs to be adjusted so that the temperature measurement point of the sensing part enters the core temperature measurement area. Summary of the Invention

[0004] In view of this, an embodiment of the present application provides a calibration test device for the temperature sensing part of the afterburner of an aircraft engine, which solves the problems that the calibration test of the temperature sensing part of the afterburner outlet cannot meet the high temperature and high pressure test conditions and the fixed measuring point cannot adjust the radial position. At the same time, it realizes that this device can be accurately adjusted in radial height within the stable heat source area.

[0005] The present application provides the following technical solution: a calibration test device for a temperature sensing part of an aircraft engine afterburner, comprising:

[0006] A lower mounting seat and an upper mounting seat, wherein the lower mounting seat is sealingly fixed to the outer wall of the gas passage at the afterburner outlet, and the upper mounting seat is sealingly fixed to the lower mounting seat, so that a sealed cavity is formed by the lower mounting seat and the upper mounting seat.

[0007] A sensing part mounting seat and a temperature sensing part, wherein the sensing part mounting seat is disposed in the sealed cavity and fixedly connected to the pipe wall of the gas channel, and the temperature sensing part is fixedly mounted on the sensing part mounting seat; wherein the sensing part mounting hole on the sensing part mounting seat is configured as a U-shaped groove, so that the temperature sensing part can be radially adjusted through the U-shaped groove;

[0008] A cooling air joint is provided on the top of the mounting seat of the device, so that cooling air is introduced into the sealed cavity through the cooling air joint to cool the thermocouple lead wire portion of the temperature sensing portion.

[0009] According to one embodiment of the present application, the temperature sensing part includes an upper section of an electric couple lead section and a lower section of a measuring point fixed section, a first water-cooled sealed cavity is arranged inside the measuring point fixed section, a sensing part cooling water joint is arranged on the side wall of the mounting seat on the device, a cooling water pipe is connected to the sensing part cooling water joint, and the cooling water pipe is connected to the first water-cooled sealed cavity to water-cool the measuring point part of the temperature sensing part.

[0010] According to one embodiment of the present application, the cooling water joint of the sensing part also includes a water-cooled sealing seat, which is filled with high-temperature asbestos rope and is compressed and sealed by a pre-tightening ring, a pre-tightening block and a ball head pressure cap on the top.

[0011] According to one embodiment of the present application, the temperature sensing part is in close contact with the inner wall of the sealed cavity, and a second water-cooled sealed cavity is provided on the outer wall of the sealed cavity at a position corresponding to the temperature sensing part. Cooling water is introduced into the second water-cooled sealed cavity through a cooling water joint to perform water cooling around the temperature sensing part.

[0012] According to one embodiment of the present application, it further includes a thermocouple lead sealing seat, which is fixedly arranged on the top of the mounting seat on the device, and the thermocouple lead of the temperature sensing part is led out from the thermocouple lead sealing seat.

[0013] According to one embodiment of the present application, the thermocouple lead sealing seat is filled with high-temperature asbestos rope and is compressed and sealed using a pre-tightening ring, a pre-tightening block and a ball head pressure cap on the top.

[0014] According to one embodiment of the present application, the pipe wall of the gas channel includes an inner wall and an outer wall of a water jacket, a water cooling channel for passing cooling water is provided between the inner wall and the outer wall of the water jacket, and a guide rib is provided in the water cooling channel.

[0015] According to one embodiment of the present application, the lower mounting seat of the device is welded and fixed to the outer wall of the gas channel, the upper mounting seat of the device is fixedly connected to the lower mounting seat of the device by screws, and an air-cooling cavity sealing plate is provided on the fixed mounting surface, and the air-cooling cavity sealing plate is in contact with the outer wall of the temperature sensing part to isolate and seal the air-cooling cavity.

[0016] According to one embodiment of the present application, a mounting hole is provided on the mounting seat of the device, and a static pressure test connector is fixedly provided on the mounting hole so as to introduce a static pressure measurement point for detecting the pressure in the sealing cavity through the static pressure test connector.

[0017] According to one embodiment of the present application, the groove height of the U-shaped groove is 20 mm.

[0018] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least the following: the embodiments of the present invention are aimed at the calibration requirements of the existing afterburner outlet temperature sensing part in a high-temperature and high-pressure test environment, and at the same time, the radially adjustable height of the temperature sensing part is achieved, while having good sealing performance. In addition, an air-cooled cavity sealing plate is used to isolate the high-temperature and high-pressure gas, while the air-cooled cavity is cooled by normal-temperature cooling air, effectively protecting the thermocouple leads of the sensing part. Two inner and outer water-cooled cavities are used to cool and protect the measuring points of the sensing part. A static pressure test connector is installed on the mounting seat of the sealing device to monitor the pressure in the air-cooled sealing cavity in real time to ensure the successful implementation of the test. The present invention provides high-temperature and high-pressure calibration test conditions for the temperature sensing part of the afterburner outlet of an aircraft engine, solving the problem that the fixed mounting seat of the temperature sensing part cannot achieve radial height adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0020] Figure 1 A longitudinal cross-sectional structural diagram of a calibration test device for a temperature sensing portion of an aircraft engine afterburner chamber according to an embodiment of the present invention;

[0021] Figure 2 This is a transverse cross-sectional structural diagram of a calibration test device for a temperature sensing portion of an aircraft engine afterburner chamber according to an embodiment of the present invention;

[0022] Among them, 1-inner wall of water jacket; 2-outer wall of water jacket; 3-lower mounting seat of device; 4-sensing part mounting seat; 5-M6 hexagon screw; 6-first flat washer; 7-first spring washer; 8-first nut; 9-sensing part mounting gasket; 10-static pressure test joint; 11-upper mounting seat of device; 12-cooling air joint; 13-ball head pressure cap; 14-preload block; 15-thermocouple sealing seat joint; 16-high-temperature asbestos rope; 17-preload ring; 18-cooling water joint; 19-water cooling chamber cover; 20-temperature sensing part; 21-M5 hexagon screw; 22-second flat washer; 23-second spring washer; 24-second nut; 25-cooling water pipe; 26-sensing part cooling water joint; 27-sensing part thermocouple lead; 28-air cooling chamber sealing plate. DETAILED DESCRIPTION

[0023] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0024] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0025] like Figure 1-Figure 2 As shown, an embodiment of the present invention provides a calibration test device for a temperature sensing part of an aircraft engine afterburner. The radially adjustable temperature sensing part sealing device includes a water jacket inner wall 1, a water jacket outer wall 2, a device lower mounting seat 3, a sensing part mounting seat 4, a static pressure test joint 10, a device upper mounting seat 11, a cooling water joint 18, a temperature sensing part 20, and an air cooling chamber sealing plate 28, wherein:

[0026] The front end of the lower mounting seat 3 is welded to the outer wall 2 and inner wall 1 of the water jacket, while the rear end of the lower mounting seat 3 is welded to the outer wall 2 and the sensing portion mounting seat 4, respectively. The sensing portion mounting seat 4 is welded to the inner wall 1 of the water jacket. The upper mounting seat 11 is connected to the lower mounting seat 3 by a bolt assembly (M6 hexagonal screw 5, first flat washer 6, first spring washer 7, first nut 8). The sealing surface connecting the upper mounting seat 11 and the lower mounting seat 3 is provided with an air-cooling chamber sealing plate 28. The sensing portion mounting seat 4 is disposed within the sealed cavity formed by the lower mounting seat 3 and the upper mounting seat 11 and is fixedly connected to the pipe wall of the gas channel. The temperature sensing portion 20 is fixedly mounted on the sensing portion mounting seat 4. The sensing portion mounting hole on the sensing portion mounting seat 4 is configured as a U-shaped groove, so that the temperature sensing portion 20 can be radially adjusted through the U-shaped groove.

[0027] A cooling air connector 12 is provided on the top of the mounting seat 11 of the device, so that cooling air can be introduced into the sealed cavity through the cooling air connector 12 to cool the thermocouple lead portion of the temperature sensing portion 20 .

[0028] During specific implementation, the mounting seat 11 on the device is provided with mounting holes, a static pressure test joint 10 is welded to the hole near the rear end, two symmetrical cooling air joints 12 and a thermocouple sealing seat joint 15 are welded to the hole near the upper end, two symmetrical cooling water joints 18 are welded to the hole near the front end, and two symmetrical sensing part cooling water joints 26 are welded to the holes near the left and right ends; the temperature sensing part 20 is connected to the sensing part mounting seat 4 by a bolt group (M5 hexagonal screw 21, second flat washer 22, second spring washer 23, second nut 24), and a sensing part mounting gasket 9 is provided on the connecting surface between the temperature sensing part 20 and the sensing part mounting seat 4; the sensing part thermocouple lead 27 and the cooling water pipe 25 pass through the inner holes of the thermocouple sealing seat joint 15 and the sensing part cooling water joint 26 respectively, and are pressed and sealed with a high-temperature asbestos rope 16, a pre-tightening ring 17, a pre-tightening block 14, and a ball head pressure cap 13.

[0029] In specific implementation, the temperature sensing part 20 includes an upper section of the electric couple lead section and a lower section of the measuring point fixed section. A first water-cooled sealed cavity is arranged inside the measuring point fixed section. A sensing part cooling water joint 26 is arranged on the side wall of the mounting seat 11 on the device. A cooling water pipe 25 is connected to the sensing part cooling water joint 26. The cooling water pipe 25 is connected to the first water-cooled sealed cavity to water-cool the measuring point part of the temperature sensing part.

[0030] In specific implementation, the temperature sensing portion 20 is in close contact with the inner wall of the sealed cavity. A second water-cooled sealed cavity is provided on the outer wall of the sealed cavity at a position corresponding to the temperature sensing portion 20. Cooling water is introduced into the second water-cooled sealed cavity through a cooling water connector 18 to cool the area surrounding the temperature sensing portion. Specifically, the second water-cooled sealed cavity is formed by bending the edge of the device upper mounting seat 11 upward, and the water-cooled cavity cover plate 19 is welded and fixed to the device upper mounting seat 11 to form the second water-cooled sealed cavity.

[0031] In specific implementation, an annular water cooling structure is adopted between the inner wall 1 and the outer wall 2 of the water jacket, and the cooling water flows for heat exchange to cool the lower mounting seat 3 of the cooling device and the sensing part mounting seat 4.

[0032] In practice, selecting sensing element mounting gaskets 9 of varying thicknesses adjusts the gap between the front end of the temperature sensing element 20 and the mounting base 11 along the X-direction. Along the Y-direction, the air-cooling chamber sealing plate 28 contacts the left and right ends of the temperature sensing element 20. Adjusting the relative position of the temperature sensing element 20 and the mounting holes of the sensing element mounting base 4 along the Z-direction allows for radial adjustment of the temperature sensing element.

[0033] In specific implementation, both the thermocouple sealing base connector 15 and the sensing part cooling water connector 26 utilize a ball-cap structure. High-temperature asbestos rope 16 provides filling and insulation, while the preload block 14, preload ring 17, and ball-cap 13 provide fastening. The water-cooling cavity in the area where the mounting base 11 contacts the high-temperature gas is cooled by cooling water. This cooling water in the cooling cavity utilizes a one-in, one-out flow for heat exchange, and the connector utilizes a ball-cap connector. The air-cooling cavity in the mounting base 11 utilizes ambient temperature gas for cooling, and the cooling gas connector 12 utilizes a ball-cap connector.

[0034] By setting up this calibration device, the embodiment of the present invention installs the temperature sensing part as a whole inside the device, and uses cooling air and cooling water to cool the thermocouple leads of the sensing part and the device respectively, ensuring that the calibration test conditions meet actual use requirements while extending the use time of the temperature sensing part.

[0035] Furthermore, to address the issue of the calibration test equipment's small high-temperature uniform heat source, only a small portion of the temperature sensing unit's measuring points fall within the uniform heat source's range when installed in the same position. This requires radial adjustment of the temperature sensing unit within the sealing device to ensure that all measuring points on the temperature sensing unit complete the calibration test. In this embodiment of the present invention, the screw holes in the temperature sensing unit's mounting base are positioned as "U"-shaped slots with a height of 20 mm, enabling radial adjustment of the temperature sensing unit's measuring points within the uniform heat source's range.

[0036] The assembly process of a temperature sensing part calibration test device for an aircraft engine afterburner combustion chamber according to an embodiment of the present invention is as follows: first, weld the sensing part mounting seat to the water jacket, and weld the lower mounting seat of the device to the inner and outer walls of the water jacket and the sensing part mounting seat, respectively; then, install the sensing part mounting gasket between the temperature sensing part and the sensing part mounting seat, and connect them with bolts; next, pass the sensing part cooling water pipe and the sensing part thermocouple lead through the sensing part cooling water joint and the thermocouple sealing seat joint, respectively; then, install the upper mounting seat of the device on the lower mounting seat of the device, adjust the gap between the air cooling chamber sealing plate and the temperature sensing part, and connect them with bolts; finally, tighten the sensing part cooling water joint and the thermocouple sealing seat joint to the corresponding pressure caps, respectively. The assembly of a temperature sensing part calibration test device for an aircraft engine afterburner combustion chamber is complete.

[0037] The cooling measures of this embodiment of the present invention are as follows: The lower mounting seat of the device is welded to the water jacket shell. The lower end surface of the front end of the device is machined into an arc-shaped structure with a step radius identical to that of the inner cylinder of the water jacket. The lower end surface of the rear end of the device is machined into an arc-shaped structure with a step radius identical to that of the outer cylinder of the water jacket. After welding, it is flush with the inner wall of the water jacket, maximizing the uniformity of the flow field within the water jacket. Simultaneously, the cooling water in the water jacket cools the lower mounting seat of the device through heat exchange. The water-cooling chamber cover is welded to the upper mounting seat of the device. Through convection heat transfer with the cooling water, the contact area between the upper mounting seat and the high-temperature gas meets test requirements. The sensing portion mounting seat is internally slotted and welded to the inner and outer walls of the water jacket. The lower end surface is machined into an arc-shaped structure with a step radius identical to that of the inner cylinder of the water jacket, and the upper end surface has a step radius identical to that of the outer cylinder of the water jacket. This ensures that the cooling water in the water jacket enters the groove of the sensing portion mounting seat, maximizing heat exchange and cooling of the sensing portion mounting seat. The cooling air inlet is located just above the sensing part mounting seat, and the cooling air blows directly onto the sensing part mounting seat to achieve a further cooling effect. The above welding is all done using argon arc welding.

[0038] The sealing measures of the present invention are as follows: an air cooling cavity sealing plate is arranged between the lower mounting seat and the upper mounting seat of the device, such as Figure 2 As shown, the air-cooled chamber sealing plate adheres closely to the temperature sensing element along the Y direction, providing a seal and preventing crosstalk between the two different gases within the water jacket and the device. (High-temperature gas from the water jacket can enter the sealing device, potentially seriously affecting the temperature sensing element's test accuracy and even causing burns in the temperature sensing element's leads. Similarly, if cooling gas from the sealing device enters the inner wall of the water jacket, mixing with the high-temperature gas will affect the measurement results.) Different thicknesses of the sensing element's mounting gaskets are selected along the X direction to adjust the gap between the front end of the temperature sensing element and the sealing device. Simultaneously, the test equipment uses the static pressure test connector on the device's mounting base to introduce a static pressure measurement point, monitoring the static pressure of the cooling gas within the sealed chamber in real time. The thermocouple leads pass through the thermocouple sealing base connector and are sequentially inserted into a preload ring, high-temperature asbestos rope, and preload block, which are then compressed and sealed with a pressure cap. The cooling water pipe is sealed in the same manner.

[0039] like Figure 2 As shown, a U-shaped groove is provided at the screw hole location of the sensing unit mounting base. The sensing unit mounting base and the sensing unit are connected by screws to solve the problem of adjusting the radial height of the temperature sensing unit. The U-shaped groove is 20mm high. After completing a single test, the connecting screws are removed, the radial height of the sensing unit is adjusted, and the connecting screws are re-tightened to complete the subsequent test content.

[0040] This embodiment of the present invention addresses the calibration requirements of existing afterburner outlet temperature sensors in high-temperature, high-pressure test environments. While achieving radially adjustable height for the temperature sensor, it also provides excellent sealing performance. Furthermore, an air-cooled chamber sealing plate isolates the high-temperature, high-pressure gas, while ambient-temperature cooling air cools the air-cooled chamber, effectively protecting the thermocouple leads in the sensor. Two internal and external water-cooled chambers provide cooling protection for the sensor's measuring points. A static pressure test connector is installed on the sealing device's mounting base, enabling real-time monitoring of pressure within the air-cooled sealed chamber to ensure successful testing.

[0041] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A temperature sensing unit calibration test device for an aircraft engine afterburner, characterized in that: include: A lower mounting seat and an upper mounting seat, wherein the lower mounting seat is sealingly fixed to the outer wall of the gas passage at the afterburner outlet, and the upper mounting seat is sealingly fixed to the lower mounting seat, so that a sealed cavity is formed by the lower mounting seat and the upper mounting seat. A sensing part mounting seat and a temperature sensing part, wherein the sensing part mounting seat is disposed in the sealed cavity and fixedly connected to the pipe wall of the gas channel, and the temperature sensing part is fixedly mounted on the sensing part mounting seat; wherein the sensing part mounting hole on the sensing part mounting seat is configured as a U-shaped groove, so that the temperature sensing part can be radially adjusted through the U-shaped groove; A cooling air joint is provided on the top of the mounting seat of the device, so that cooling air is introduced into the sealed cavity through the cooling air joint to air-cool the thermocouple lead wire portion of the temperature sensing portion.

2. The aircraft engine afterburner temperature sensor calibration test device according to claim 1, characterized in that: The temperature sensing part includes an upper section of the electric couple lead section and a lower section of the measuring point fixing section. A first water-cooled sealed cavity is arranged inside the measuring point fixing section. A sensing part cooling water joint is arranged on the side wall of the mounting seat on the device. A cooling water pipe is connected to the sensing part cooling water joint. The cooling water pipe is connected to the first water-cooled sealed cavity to water-cool the measuring point part of the temperature sensing part.

3. The aircraft engine afterburner temperature sensor calibration test device according to claim 2, characterized in that: The sensing part cooling water joint also includes a water-cooled sealing seat, which is filled with high-temperature asbestos rope and is compressed and sealed by a pre-tightening ring, a pre-tightening block and a ball head pressure cap on the top.

4. The aircraft engine afterburner temperature sensor calibration test device according to claim 1, characterized in that: The temperature sensing part is in close contact with the inner wall of the sealed cavity, and a second water-cooled sealed cavity is provided on the outer wall of the sealed cavity at a position corresponding to the temperature sensing part. Cooling water is introduced into the second water-cooled sealed cavity through a cooling water joint to water-cool the area around the temperature sensing part.

5. The aircraft engine afterburner temperature sensor calibration test device according to claim 1, characterized in that: It also includes a thermocouple lead sealing seat, which is fixedly arranged on the top of the mounting seat on the device, and the thermocouple lead of the temperature sensing part is led out from the thermocouple lead sealing seat.

6. The aircraft engine afterburner temperature sensor calibration test device according to claim 5, characterized in that: The thermocouple lead sealing seat is filled with high-temperature asbestos rope and is sealed by a pre-tightening ring, a pre-tightening block and a ball head pressure cap on the top.

7. The aircraft engine afterburner temperature sensor calibration test device according to claim 1, characterized in that: The pipe wall of the gas channel includes a water jacket inner wall and a water jacket outer wall. A water cooling channel for passing cooling water is provided between the water jacket inner wall and the water jacket outer wall. Guide ribs are provided in the water cooling channel.

8. The aircraft engine afterburner temperature sensor calibration test device according to claim 1, characterized in that: The lower mounting seat of the device is welded and fixed to the outer wall of the gas channel, the upper mounting seat of the device is fixedly connected to the lower mounting seat of the device by screws, and an air-cooling cavity sealing plate is provided on the fixed mounting surface, and the air-cooling cavity sealing plate contacts the outer wall of the temperature sensing part to isolate and seal the air-cooling cavity.

9. The aircraft engine afterburner temperature sensor calibration test device according to claim 1, characterized in that: A mounting hole is provided on the mounting seat of the device, and a static pressure test joint is fixedly provided on the mounting hole so as to introduce a static pressure measuring point for detecting the pressure in the sealing cavity through the static pressure test joint.

10. The aircraft engine afterburner temperature sensor calibration test device according to claim 1, characterized in that: The U-shaped groove has a groove height of 20 mm.

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