Fuel oil icing prevention system for ignition test of aero-engine combustion chamber

Abstract

The invention discloses a fuel oil icing prevention system for an ignition test of an aero-engine combustion chamber, and belongs to the technical field of ground tests of aero-engine combustion chambers. The system comprises an oil depot, a temporary anti-freezing oil storage assembly and a test piece, the temporary anti-freezing oil storage assembly is connected with the oil depot through a pipe set, the test piece is connected with the temporary anti-freezing oil storage assembly through an oil conveying pipe, and the oil conveying pipe is sequentially provided with a flow detection assembly, a flow oil pressure regulation and control assembly, a valve D, an oil pressure detection assembly and a temperature detection assembly. And the flow detection assembly is arranged close to the temporary anti-freezing oil storage assembly. The system temporarily stores fuel oil through the temporary anti-freezing oil storage assembly, the purpose of preventing the fuel oil from freezing is achieved by adding an anti-icing agent into the temporary anti-freezing oil storage assembly, and the system is simple in structure, low in manufacturing cost, capable of solving the problem of fuel oil freezing in the low-temperature environment, easy to operate and high in practicability. And the ignition test of the aero-engine combustion chamber can be smoothly carried out.

Description

TECHNICAL FIELD

[0001] The present application relates to a kind of for aero-engine combustion chamber ignition test anti-fuel icing system, belong to aero-engine combustion chamber ground test technical field. BACKGROUND

[0002] Aero-engine combustion chamber ground test is very necessary for the design of engine, for measuring the performance of product. Among them, aero-engine ignition test is an important part of aero-engine ground test, can simulate the ignition situation of engine under various conditions, to find potential problems in advance to promote engine design improvement. In aero-engine ignition test, simulate the ignition situation of engine in plateau low pressure and high altitude low temperature low pressure and other harsh environments, it is beneficial to improve the ignition performance of engine in extreme harsh environment.

[0003] In the test bench, the commonly used method for simulating aero-engine low-temperature ignition is to reduce the inlet temperature of test piece for ignition. But in the test, it is found that under low temperature condition, fuel is easy to freeze and cause nozzle blockage, which in turn leads to fuel flow reduction and ignition failure. Based on this, the following two technical measures are currently mainly used to improve the ignition success rate of aero-engine under low temperature environment: the first technical measure is to design a fuel warming system to heat the fuel to prevent fuel icing during ignition test, but this fuel warming system is complex in structure and high in cost. The second technical measure is to connect high-pressure nitrogen into the manifold for purging when the nozzle is blocked, to empty the fuel in the manifold and the icing material at the fuel nozzle, and then supply oil for ignition. If the ignition is unsuccessful, the above operation needs to be repeated constantly, which is tedious. In addition, due to the complex structure of the manifold and the nozzle, the fuel inside cannot be completely purged, and there will still be a small amount of fuel left. These fuels continue to freeze, resulting in a still large decrease in fuel FN value, so the actual effect is not ideal. SUMMARY

[0004] To solve the above technical problems, the present application provides an anti-fuel icing system for aero-engine combustion chamber ignition test.

[0005] The present application is realized by the following technical solutions:

[0006] An anti-fuel icing system for aero-engine combustion chamber ignition test, comprising an oil tank, a temporary anti-freezing oil storage assembly and a test piece, the temporary anti-freezing oil storage assembly is connected with the oil tank through a pipe group, the test piece is connected with the temporary anti-freezing oil storage assembly through an oil delivery pipe, the oil delivery pipe is sequentially provided with a flow detection assembly, a flow oil pressure control assembly, a valve D, an oil pressure detection assembly and a temperature detection assembly, and the flow detection assembly is arranged close to the temporary anti-freezing oil storage assembly.

[0007] The temporary anti-freezing oil storage assembly comprises a support and an oil tank arranged on the support.

[0008] The support is fixed on the ground by expansion screws, and a staircase is arranged on one side of the support.

[0009] The volume of the oil tank is not less than 700L, a breathing valve is arranged on the top of the oil tank, a stirring device is arranged on the top of the oil tank and partially extends into the oil tank, an anti-icing agent filling port is arranged on the top of the oil tank, and a sealing cover is arranged on the top of the oil tank at the anti-icing agent filling port, and a magnetic flap liquid level meter is arranged on the oil tank.

[0010] The pipe group comprises an inlet and outlet oil pipe, one end of the inlet and outlet oil pipe is connected with the bottom of the oil tank, the other end of the inlet and outlet oil pipe is connected with the oil depot through three oil delivery pipes, a valve A is arranged on the inlet and outlet oil pipe near the three oil delivery pipes, and a valve B is arranged on the three oil delivery pipes near the inlet and outlet oil pipe.

[0011] One end of the oil delivery pipe away from the test piece is connected with the inlet and outlet oil pipe, and the connection point of the oil delivery pipe and the inlet and outlet oil pipe is the same as the connection point of the inlet and outlet oil pipe and the three oil delivery pipes, and a valve C is arranged on the oil delivery pipe near the three oil delivery pipes.

[0012] The flow detection assembly is a mass flow meter.

[0013] The fuel pump, the gas film regulating valve A and the gas film regulating valve B are connected in series, the fuel pump is arranged between the gas film regulating valve B and the flow detection assembly, and the gas film regulating valve A is connected in parallel with the fuel pump.

[0014] A quick-response electromagnetic valve is arranged between the valve D and the oil pressure detection assembly on the oil delivery pipe.

[0015] The oil pressure detection assembly is a pressure sensor.

[0016] The temperature detection assembly is a temperature sensor.

[0017] The system temporarily stores fuel through the temporary anti-freezing oil storage assembly, and prevents the fuel from freezing by adding anti-icing agent into the temporary anti-freezing oil storage assembly, the system has simple structure and low manufacturing cost, can solve the problem of fuel freezing in low-temperature environment, has simple operation, and ensures that the aviation engine combustion chamber ignition test can be carried out smoothly, which has important significance for the low-temperature ignition test of the aviation engine. BRIEF DESCRIPTION OF DRAWINGS

[0018] Fig. 1 It is a structural schematic diagram of the present application.

[0019] Fig. 2The assembly structure diagram of the temporary anti-freezing oil storage component, pipe group and oil conveying pipe of the application;

[0020] Fig. 3 The front view structure diagram of the oil tank of the application;

[0021] Fig. 4 The left view structure diagram of the oil tank of the application.

[0022] In the figure: 1-oil depot, 2-pipe group, 20-inlet and outlet oil pipe, 21-oil conveying pipe, 22-valve A, 23-valve B, 3-temporary anti-freezing oil storage component, 30-bracket, 31-oil tank, 32-expansion screw, 33-stairway, 34-breather valve, 35-stirring device, 36-anti-icing agent filling port, 37-magnetic flap liquid level meter, 38-steel angle, 4-oil conveying pipe, 40-valve C, 5-flow detection component, 6-flow and oil pressure regulation component, 60-fuel pump, 61-air film regulating valve A, 62-air film regulating valve B, 7-valve D, 8-fast response electromagnetic valve, 9-oil pressure detection component, 10-temperature detection component, 11-test piece. DETAILED DESCRIPTION

[0023] The technical solutions of the application are further described below, but the scope of protection is not limited to the description.

[0024] As Figs. 1 to 4 shown in the figure, the anti-fuel icing system for the ignition test of the combustion chamber of an aero-engine provided by the application comprises an oil depot 1, a temporary anti-freezing oil storage component 3 and a test piece 11, the temporary anti-freezing oil storage component 3 is connected with the oil depot 1 through a pipe group 2, the test piece 11 is connected with the temporary anti-freezing oil storage component 3 through an oil conveying pipe 4, the oil conveying pipe 4 is sequentially provided with a flow detection component 5, a flow and oil pressure regulation component 6, a valve D 7, an oil pressure detection component 9 and a temperature detection component 10, and the flow detection component 5 is arranged close to the temporary anti-freezing oil storage component 3. Before the ignition test of the combustion chamber of an aero-engine is performed, part of the fuel in the oil depot 1 is injected into the temporary anti-freezing oil storage component 3, and then an anti-icing agent is added into the temporary anti-freezing oil storage component 3 to prevent the fuel from icing, the fuel output by the temporary anti-freezing oil storage component 3 is subjected to flow detection through the flow detection component 5, flow and oil pressure regulation through the flow and oil pressure regulation component 6, oil pressure detection through the oil pressure detection component 9 and temperature detection through the temperature detection component 10, and then is conveyed to the test piece 11 for ignition test. The system provided by the application temporarily stores fuel through the temporary anti-freezing oil storage component 3, and achieves the purpose of preventing the fuel from icing by adding an anti-icing agent into the temporary anti-freezing oil storage component 3, the system has simple structure and low manufacturing cost, can solve the problem of fuel icing in a low-temperature environment, and has simple operation, thereby ensuring that the ignition test of the combustion chamber of an aero-engine can be smoothly performed, and having important significance for the low-temperature ignition test of an aero-engine.

[0025] The temporary anti-freezing oil storage assembly 3 comprises a support 30 and an oil tank 31 arranged on the support 30. The oil tank 31 is elevated by the support 30, so that the fuel in the oil tank 31 has a corresponding pre-pump oil pressure.

[0026] The support 30 is fixed on the ground by expansion screws 32, and one side of the support 30 is provided with a staircase 33.

[0027] The volume of the oil tank 31 is not less than 700L. The top of the oil tank 31 is provided with a breather valve 34, a stirring device 35 arranged on the top of the oil tank 31 and partially extending into the oil tank 31, an anti-icing agent filling port 36 formed on the top of the oil tank 31, and a sealing cover arranged on the top of the oil tank 31 at the anti-icing agent filling port 36. A magnetic flap liquid level meter 37 is arranged on the oil tank 31. The volume of the oil tank 31 is not less than 700L, which can meet the oil demand of the ignition test of the aero-engine. The stirring device 35 comprises a stirring motor and a stirring shaft. The stirring motor is arranged on the top of the oil tank 31, and the stirring shaft is arranged in the oil tank 31. A plurality of stirring blades are arranged on the stirring shaft, and the upper end of the stirring shaft is connected with the output shaft of the stirring motor. The stirring shaft and the stirring blades are driven to rotate by the stirring motor, so as to stir the fuel and the anti-icing agent in the oil tank 31. Angle steels 38 are welded on the outer wall of the oil tank 31 in the circumferential direction for reinforcement.

[0028] The pipe group 2 comprises an inlet and outlet oil pipe 20. One end of the inlet and outlet oil pipe 20 is connected with the bottom of the oil tank 31, and the other end is connected with the oil depot 1 through three oil delivery pipes 21. A valve A 22 is arranged on the inlet and outlet oil pipe 20 near the three oil delivery pipes 21. Valves B 23 are respectively arranged on the three oil delivery pipes 21 near the inlet and outlet oil pipe 20.

[0029] The end of the oil delivery pipe 4 away from the test piece 11 is connected with the inlet and outlet oil pipe 20. The connection point of the oil delivery pipe 4 and the inlet and outlet oil pipe 20 is the same as the connection point of the inlet and outlet oil pipe 20 and the three oil delivery pipes 21. A valve C 40 is arranged on the oil delivery pipe 4 near the three oil delivery pipes 21.

[0030] The flow detection assembly 5 is a mass flow meter. The fuel flow is detected by the mass flow meter.

[0031] The flow oil pressure regulation assembly 6 comprises a fuel pump 60, a gas film regulating valve A 61 and a gas film regulating valve B 62. The gas film regulating valve B 62 is connected in series with the fuel pump 60, and the fuel pump 60 is located between the gas film regulating valve B 62 and the flow detection assembly 5. The gas film regulating valve A 61 is connected in parallel with the fuel pump 60.

[0032] The quick-response electromagnetic valve 8 is arranged between the valve D 7 and the oil pressure detection assembly 9 on the oil delivery pipe 4.

[0033] The oil pressure detection component 9 is a pressure sensor.

[0034] The temperature detection component 10 is a temperature sensor.

[0035] The working principle or use method of the anti-fuel icing system for the ignition test of the aircraft engine combustion chamber is as follows:

[0036] The valve C40 is closed, the valve A22 is opened, and the valve B23 on one of the three oil pipes 21 is opened, the oil depot 1 injects the fuel of the required mark (such as No. 3 fuel or No. 5 fuel) into the oil tank 31, and then the valve B23 and the valve A22 are closed.

[0037] After the operator climbs to the top of the support 30 through the ladder 33, opens the anti-icing agent filling port 36, and adds an appropriate amount of anti-icing agent to the oil tank 31, the anti-icing agent filling port 36 is closed. Next, the stirring device 35 is started to fully mix and uniformly mix the fuel and the anti-icing agent.

[0038] After the mixed fuel flows through the oil pipe 4, the fuel flow is detected by the mass flow meter, the fuel pressure and flow are increased by the fuel pump 60, the fuel flow is adjusted to the final required flow by the gas film regulating valve A60 and the gas film regulating valve B62, and finally the valve D7 and the quick response electromagnetic valve 8 are opened to supply the fuel to the test piece 11 for ignition, and the fuel pressure before the test piece 11 is detected by the pressure sensor, and the fuel temperature before the test piece 11 is detected by the temperature sensor. In addition, the FN value of the fuel is recorded, and whether the ignition nozzle of the fuel is blocked is judged.

[0039] After the operator climbs to the top of the support 30 through the ladder 33, opens the anti-icing agent filling port 36, and adds an appropriate amount of anti-icing agent to the oil tank 31, the anti-icing agent filling port 36 is closed. Next, the stirring device 35 is started to fully mix and uniformly mix the fuel and the anti-icing agent.

Claims

1. A fuel icing prevention system for ignition tests in aircraft engine combustion chambers, characterized in that: It includes an oil depot (1), a temporary antifreeze oil storage assembly (3) and a test piece (11). The temporary antifreeze oil storage assembly (3) is connected to the oil depot (1) through a pipe group (2). The test piece (11) is connected to the temporary antifreeze oil storage assembly (3) through an oil delivery pipe (4). The oil delivery pipe (4) is sequentially equipped with a flow detection assembly (5), a flow and oil pressure control assembly (6), a valve D (7), an oil pressure detection assembly (9) and a temperature detection assembly (10), and the flow detection assembly (5) is arranged close to the temporary antifreeze oil storage assembly (3).

2. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 1, characterized in that: The temporary antifreeze oil storage assembly (3) includes a bracket (30) and an oil tank (31) mounted on the bracket (30).

3. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 2, characterized in that: The bracket (30) is fixed to the ground by expansion screws (32), and a ladder (33) is provided on one side of the bracket (30).

4. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 2, characterized in that: The volume of the oil tank (31) is not less than 700L. The top of the oil tank (31) is equipped with a breather valve (34). The top of the oil tank (31) is equipped with a stirring device (35), and the stirring device (35) extends into the oil tank (31). The top of the oil tank (31) is provided with an anti-icing agent filling port (36), and the top of the oil tank (31) is provided with a sealing cap at the anti-icing agent filling port (36). The oil tank (31) is equipped with a magnetic float level gauge (37).

5. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 2, characterized in that: The pipe assembly (2) includes an inlet and outlet oil pipe (20). One end of the inlet and outlet oil pipe (20) is connected to the bottom of the oil tank (31), and the other end is connected to the oil depot (1) through three oil delivery pipes (21). A valve A (22) is installed on the inlet and outlet oil pipe (20) near the three oil delivery pipes (21), and a valve B (23) is installed on the three oil delivery pipes (21) near the inlet and outlet oil pipe (20). The end of the oil supply pipe (4) away from the test piece (11) is connected to the inlet and outlet oil pipe (20), and the connection point between the oil supply pipe (4) and the inlet and outlet oil pipe (20) is the same as the connection point between the inlet and outlet oil pipe (20) and the three oil delivery pipes (21). A valve C (40) is installed on the oil supply pipe (4) near the three oil delivery pipes (21).

6. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 1, characterized in that: The flow detection component (5) is a mass flow meter.

7. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 1, characterized in that: The flow and oil pressure control assembly (6) includes a fuel pump (60), a film regulating valve A (61) and a film regulating valve B (62). The film regulating valve B (62) is connected in series with the fuel pump (60), and the fuel pump (60) is located between the film regulating valve B (62) and the flow detection assembly (5). The film regulating valve A (61) is connected in parallel with the fuel pump (60).

8. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 1, characterized in that: A fast-response solenoid valve (8) is provided on the oil pipeline (4) between valve D (7) and oil pressure detection assembly (9).

9. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 1, characterized in that: The oil pressure detection component (9) is a pressure sensor.

10. The fuel icing prevention system for ignition testing of an aero-engine combustion chamber as described in claim 1, characterized in that: The temperature detection component (10) is a temperature sensor.

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