A high-temperature supersonic multi-point total temperature probe for testing temperature of exhaust jet of a tail nozzle

Abstract

The application discloses a high-temperature supersonic multi-point total temperature probe for testing the jet exhaust temperature of a tail nozzle, which comprises: a total temperature probe capable of reducing the testing error of a thermocouple electrode sensor on the jet exhaust temperature of the tail nozzle. The length-diameter ratio of the stagnation cover is 5, and the area ratio of the inlet and outlet is 2.53. In the supersonic environment with a Mach number ranging from 3 to 5, the thermal resistance of the stagnation cover is increased, the heat conduction error is reduced, the temperature of the inner wall surface of the head of the stagnation cover is increased, the radiation error of the thermocouple electrode sensor in the stagnation cover is reduced, the deviation of the thermocouple electrode sensor on the testing of the jet exhaust temperature of the tail nozzle is also reduced, and the testing error of the thermocouple electrode sensor on the jet exhaust temperature of the tail nozzle is reduced after the stagnation cover is designed.

Description

Technical Field

[0001] This invention relates to a high-temperature supersonic multi-point total temperature probe for testing the exhaust jet temperature of a tailpipe, belonging to the field of aero-engine temperature testing technology. Background Technology

[0002] The engine's exhaust nozzle expands and accelerates the high-temperature, high-pressure combustion gases, generating thrust for the engine. Testing the temperature parameters of the exhaust plume at the nozzle exit is used to assess whether the nozzle meets design requirements in supersonic environments within the Mach 3-5 range.

[0003] When the thermocouple electrode sensor on the total temperature probe obtains the jet exhaust temperature of the tail nozzle for testing, the stagnation shield needs to be designed to reduce the test error of the thermocouple electrode sensor on the jet exhaust temperature of the tail nozzle because the thermocouple electrode sensor is located in the stagnation shield. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a high-temperature supersonic multi-point total temperature probe for testing the jet exhaust temperature of a tailpipe.

[0005] The present invention is achieved through the following technical solutions.

[0006] This invention provides a high-temperature supersonic multi-point total temperature probe for measuring the jet exhaust temperature of a tailpipe, comprising: A total temperature probe that can reduce the error in measuring the jet exhaust temperature of the tailpipe by thermocouple electrode sensors.

[0007] The total temperature probe includes a support rod; A stagnation shield is fixed on the airflow-facing surface of the support rod. There are multiple stagnation shields distributed at intervals, and thermocouple electrode sensors are installed inside each of the multiple stagnation shields. The length distance from the root to the end of the stagnation cover, which is fixedly connected to the support rod, is L. The outer diameter of the stagnation cover is ΦA, and the length-to-diameter ratio of the stagnation cover is 5. The stagnation cover is provided with an air inlet hole with a diameter of ΦB and an exhaust hole with a diameter of ΦC. There are two exhaust holes, and the ratio of the air inlet to the exhaust area is 2.53.

[0008] The support rod has a water inlet chamber A and a water inlet chamber B inside. Water inlet nozzles are fixedly installed on the support rod corresponding to the top of water inlet chamber A and water inlet chamber B. There are two water inlet nozzles distributed front and back.

[0009] The support rod has holes on the front and rear sides at the top to fix and connect two water inlet nozzles. The two water inlet nozzles connect to water inlet chamber A and water inlet chamber B respectively. There is a wiring cavity inside the support rod between water inlet chamber A and water inlet chamber B.

[0010] The wiring cavity contains cables, with the top end of the cables passing through the top of the support rod and connected to an electrical connector. The bottom end of the cables is connected to a thermocouple electrode sensor for testing the temperature of the jet exhaust from the tailpipe.

[0011] The thermocouple electrode sensor and the hysteresis cover are insulated and fixed together by an alumina ceramic tube.

[0012] The bottom of the support rod is fixedly connected to a drain rod, and the top of the drain rod is fixedly connected to a drain spout for discharging water; it also includes a mounting base that provides an installation foundation, and the support rod and drain spout are fixedly installed on the mounting base; so that the drain spout, mounting base, support rod, and drain rod support each other.

[0013] The airflow-facing surface of the support rod is coated with a hafnium oxide coating; the head of the airflow-facing surface of the support rod is a 60° cone.

[0014] The beneficial effects of this invention are as follows: due to the length-to-diameter ratio of the stagnation shield being 5 and the inlet-to-outlet area ratio being 2.53, in a supersonic environment with a Mach number of 3-5, the thermal resistance of the stagnation shield increases, the thermal conductivity error decreases, and the temperature of the inner wall surface of the stagnation shield head increases. This reduces the radiation error of the thermocouple electrode sensor inside the stagnation shield, and the deviation of the thermocouple electrode sensor in measuring the jet exhaust temperature of the tail nozzle also decreases. After designing the stagnation shield in this way, the measurement error of the thermocouple electrode sensor in measuring the jet exhaust temperature of the tail nozzle is reduced. Attached Figure Description

[0015] Figure 1 This is a front view schematic diagram of the present invention; Figure 2 This is a front cross-sectional view of the mounting of the stagnation cover, thermocouple electrode sensor, and ceramic tube of the present invention; Figure 3 This is a schematic front cross-sectional view of the stabilizing cover of the present invention; Figure 4 This is a schematic front cross-sectional view of the support rod of the present invention; In the diagram: 1-Water inlet nozzle; 2-Mounting base; 3-Support rod; 31-Water inlet chamber A; 32-Water inlet chamber B; 33-Wiring chamber; 4-Stagnation cover; 41-Air inlet; 42-Exhaust port; 5-Water outlet rod; 6-Water outlet nozzle; 7-Thermocouple electrode sensor; 71-Cable; 72-Ceramic tube. Detailed Implementation

[0016] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0017] like Figures 1 to 4 As shown.

[0018] This application discloses a high-temperature supersonic multi-point total temperature probe for measuring the jet exhaust temperature of a tailpipe, comprising: The support rod 3 has an internal water inlet chamber A31 and a water inlet chamber B32. Water inlet nozzles 1 are fixedly installed on the support rod 3 corresponding to the top of water inlet chambers A31 and B32. Two water inlet nozzles 1 are distributed front and rear. Holes are opened on the front and rear sides of the top of the support rod 3 to fix and connect the two water inlet nozzles 1. The two water inlet nozzles 1 connect to water inlet chambers A31 and B32 respectively. A wiring cavity 33 is located inside the support rod 3 between water inlet chambers A31 and B32. A cable 71 is arranged inside the wiring cavity 33. The top end of the cable 71 passes through the top of the support rod 3 and connects to an electrical connector. The bottom end of the cable 71 is connected to a thermocouple electrode sensor 7 for measuring the temperature of the exhaust jet from the tailpipe.

[0019] The bottom of the support rod 3 is fixedly connected to a drainage outlet rod 5, and the top of the drainage outlet rod 5 is fixedly connected to a water outlet nozzle 6 for water discharge. It also includes a mounting base 2 providing an installation foundation, on which the support rod 3 and the water outlet nozzle 6 are fixedly mounted. This allows the water outlet nozzle 6, mounting base 2, support rod 3, and drainage rod 5 to support each other, enhancing their ability to withstand supersonic airflow speeds. Cooling water enters through the water inlet 1 and flows into the water inlet chambers A31 and B32, then flows through the drainage rod 5 and the water outlet nozzle 6 before being discharged, thus cooling the support rod 3.

[0020] A stagnation cover 4 is fixed on the airflow-facing surface of the support rod 3. Multiple stagnation covers 4 are spaced apart, and each stagnation cover 4 contains a thermocouple electrode sensor 7 to achieve multi-point temperature measurement. The thermocouple electrode sensor 7 is insulated from the stagnation cover 4 by an alumina ceramic tube 72. The alumina ceramic tube 72 is heat-resistant up to 1800℃, ensuring an insulation resistance ≥0.1MΩ at high temperatures.

[0021] The length distance from the root to the end of the stagnation shield 4, which is fixedly connected to the support rod 3, is L. The outer diameter of the stagnation shield 4 is ΦA, and the length-to-diameter ratio (L / ΦA) of the stagnation shield 4 is 5. The stagnation shield 4 is provided with an air inlet 41 with a diameter of ΦB and an exhaust port 42 with a diameter of ΦC. There are two exhaust ports 42, and the ratio of the air inlet and exhaust area (ΦB / 2*ΦC) is 2.53. Due to the length-to-diameter ratio of the stagnation shield 4 being 5 and the air inlet and exhaust area ratio being 2.53, in a supersonic environment with a Mach number of 3-5, the thermal resistance of the stagnation shield 4 increases, the thermal conductivity error decreases, and the temperature of the inner wall surface of the head of the stagnation shield 4 increases. This reduces the radiation error of the thermocouple electrode sensor 7 inside the stagnation shield 4, and the deviation of the thermocouple electrode sensor 7 in measuring the exhaust jet temperature of the tail nozzle also decreases. After designing the stagnation shield in this way, the measurement error of the thermocouple electrode sensor 7 in measuring the exhaust jet temperature of the tail nozzle is reduced.

[0022] The airflow-facing surface of the support rod 3 is coated with a hafnium oxide coating; the head of the airflow-facing surface of the support rod 3 is a 60° conical shape. The material of the support rod 3 is high-temperature alloy GH3128.

Claims

1. A high-temperature supersonic multi-point total temperature probe for measuring the exhaust jet temperature of a tailpipe, characterized in that, include: The total temperature probe can reduce the error of the thermocouple electrode sensor (7) in measuring the jet exhaust temperature of the tail nozzle.

2. The high-temperature supersonic multi-point total temperature probe for testing the exhaust jet temperature of the tail nozzle as described in claim 1, characterized in that: The total temperature probe includes a support rod (3); The support rod (3) has a stagnation cover (4) fixed on the airflow surface. There are multiple stagnation covers (4) spaced apart, and each of the multiple stagnation covers (4) is equipped with a thermocouple electrode sensor (7). The length distance from the root of the stagnation cover (4) to the end of the stagnation cover (4) is L, the outer diameter of the stagnation cover (4) is ΦA, and the length-to-diameter ratio of the stagnation cover (4) is 5. The stagnation cover (4) is provided with an air inlet (41) with a diameter of ΦB and an exhaust hole (42) with a diameter of ΦC. There are two exhaust holes (42), and the ratio of the air inlet to the exhaust area is 2.

53.

3. The high-temperature supersonic multi-point total temperature probe for testing the exhaust jet temperature of the tail nozzle as described in claim 2, characterized in that: The support rod (3) has a water inlet chamber A (31) and a water inlet chamber B (32) inside. Water inlet nozzles (1) are fixedly installed on the support rod (3) corresponding to the top of the water inlet chamber A (31) and the water inlet chamber B (32). There are two water inlet nozzles (1) distributed in front and behind.

4. The high-temperature supersonic multi-point total temperature probe for testing the exhaust jet temperature of the tail nozzle as described in claim 3, characterized in that: The support rod (3) has holes on the front and rear sides of its top to fix and connect two water inlet nozzles (1). The two water inlet nozzles (1) are connected to the water inlet chamber A (31) and the water inlet chamber B (32). The support rod (3) between the water inlet chamber A (31) and the water inlet chamber B (32) has a wiring cavity (33).

5. The high-temperature supersonic multi-point total temperature probe for testing the exhaust jet temperature of the tail nozzle as described in claim 4, characterized in that: The wiring cavity (33) contains a cable (71), the top end of which passes through the top of the support rod (3) and is connected to an electrical connector. The bottom end of the cable (71) is connected to a thermocouple electrode sensor (7) for testing the temperature of the jet exhaust flow from the tail nozzle.

6. The high-temperature supersonic multi-point total temperature probe for testing the jet exhaust temperature of the tail nozzle as described in claim 2, characterized in that: The thermocouple electrode sensor (7) and the stagnation cover (4) are insulated and fixed together by an alumina ceramic tube (72).

7. The high-temperature supersonic multi-point total temperature probe for testing the jet exhaust temperature of the tail nozzle as described in claim 2, characterized in that: The bottom of the support rod (3) is fixedly connected to a drain rod (5), and the top of the drain rod (5) is fixedly connected to a drain spout (6) for discharging water; it also includes a mounting base (2) that provides an installation foundation, and the support rod (3) and the drain spout (6) are fixedly installed on the mounting base (2); so that the drain spout (6), the mounting base (2), the support rod (3), and the drain rod (5) support each other.

8. The high-temperature supersonic multi-point total temperature probe for testing the jet exhaust temperature of the tail nozzle as described in claim 2 or 7, characterized in that: The support rod (3) is coated with hafnium oxide on the airflow-facing surface; the head of the airflow-facing surface of the support rod (3) is a 60° cone.

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