Fuel supply system for combustion performance test of aero-engine combustion chamber and ignition test method

Abstract

The invention relates to an aero-engine combustion chamber combustion performance test oil supply system and an ignition test method.The oil supply system comprises a fuel oil supply pipeline and an oil return adjusting pipeline; an inlet of the fuel oil supply pipeline is connected with a fuel oil source. A first hand valve, a first fuel oil filter, a first temperature transmitter, a first pressure transmitter, a second hand valve, a first fuel oil booster pump, a second pressure transmitter, a third hand valve, a fourth hand valve, a second temperature transmitter, a third pressure transmitter, a second fuel oil filter, a first electromagnetic valve, a fifth hand valve, a first flowmeter and a sixth hand valve are sequentially arranged on the fuel oil supply pipeline; a second solenoid valve, a first one-way valve and a fourth pressure transmitter; an inlet and an outlet of the oil return adjusting pipeline are connected to the fuel oil supply pipeline; a seventh hand valve, a third electromagnetic valve, a fifth pressure transmitter, a first electric control valve and an eighth hand valve are sequentially arranged on the oil return adjusting pipeline.

Description

Technical Field

[0001] This application belongs to the field of combustion performance testing of aero-engine combustors, and specifically relates to a fuel supply system and ignition test method for combustion performance testing of aero-engine combustors. Background Technology

[0002] With the development of aero-engine combustor technology, combustor combustion performance testing requires the fuel supply system to be able to perform wide-range, high-precision adjustment, have high system stability, and have the ability to supply multiple fuels for testing. It should be able to meet the fuel supply and adjustment functions for combustor ignition, flameout, and other combustion performance test states.

[0003] Combustion chamber ignition tests obtain the ignition limits of the combustion chamber under different test conditions by adjusting the fuel supply to change the air-fuel ratio in the combustion chamber. The current fuel supply system does not consider the influence of combustion chamber back pressure during ignition tests. It uses a method of increasing the pressure of the fuel supply system pipeline to a certain level and then opening the fuel supply valve to inject fuel into the combustion chamber. Due to the influence of combustion chamber back pressure and nozzle throttling, this fuel supply method will cause fluctuations in the fuel injection flow rate during combustion chamber ignition, resulting in inaccurate tests. In addition, there is often a certain deviation between the actual fuel supply and the target fuel supply, making it difficult to adjust the fuel supply state during ignition and affecting test efficiency.

[0004] In view of the aforementioned technical deficiencies, this application is hereby filed. Summary of the Invention

[0005] The purpose of this application is to provide a fuel supply system and ignition test method for testing the combustion performance of an aero-engine combustor, so as to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] A fuel supply system for testing the combustion performance of an aero-engine combustion chamber includes a fuel supply line and a fuel return regulating line.

[0008] The fuel supply line has its inlet connected to the fuel source and its outlet connected to the combustion chamber fuel inlet.

[0009] The fuel supply line is sequentially equipped with the following components: first hand valve, first fuel filter, first temperature transmitter, first pressure transmitter, second hand valve, first fuel booster pump, second pressure transmitter, third hand valve, fourth hand valve, second temperature transmitter, third pressure transmitter, second fuel filter, first solenoid valve, fifth hand valve, first flow meter, sixth hand valve, second solenoid valve, first check valve, and fourth pressure transmitter.

[0010] The inlet and outlet of the return oil regulating pipeline are connected to the fuel supply pipeline. The connection point of the inlet on the fuel supply pipeline is between the sixth hand valve and the seventh solenoid valve, and the connection point of the outlet on the fuel supply pipeline is between the first hand valve and the first fuel filter.

[0011] The return oil regulating pipeline is sequentially equipped with a seventh manual valve, a third solenoid valve, a fifth pressure transmitter, a first electric regulating valve, and an eighth manual valve.

[0012] According to at least one embodiment of this application, in the above-mentioned fuel supply system for testing the combustion performance of an aero-engine combustor, the first fuel booster pump is controlled by a frequency converter and connected in parallel with a second electric regulating valve and a first safety valve.

[0013] The combination of the first solenoid valve, the fifth hand valve, the first flow meter, and the sixth hand valve is connected in parallel with the fourth solenoid valve, the fifteenth hand valve, the second flow meter, and the sixteenth hand valve;

[0014] The first electric regulating valve is connected in parallel with the third electric regulating valve.

[0015] According to at least one embodiment of this application, the above-mentioned fuel supply system for testing the combustion performance of an aero-engine combustor further includes a fuel supply redundancy pipeline and a return fuel adjustment redundancy pipeline.

[0016] The fuel supply margin pipeline inlet is connected to the fuel supply pipeline, and the outlet is connected to the combustion chamber fuel supply port. The connection node of the inlet on the fuel supply pipeline is located between the first pressure transmitter and the second hand valve.

[0017] The fuel supply margin line is sequentially equipped with the following valves: the ninth manual valve, the second fuel booster pump, the sixth pressure transmitter, the tenth manual valve, the eleventh manual valve, the third temperature transmitter, the seventh pressure transmitter, the third fuel filter, the fifth solenoid valve, the eleventh manual valve, the third flow meter, the thirteenth manual valve, the fourteenth manual valve, the sixth solenoid valve, the second check valve, and the eighth pressure transmitter.

[0018] The inlet of the return oil adjustment margin line is connected to the fuel supply margin line, and the outlet is connected to the return oil adjustment line. The connection point of the inlet on the fuel supply margin line is between the thirteenth and fourteenth hand valves, and the connection point of the outlet on the return oil adjustment line is between the first electric adjustment valve and the eighth hand valve.

[0019] The return oil adjustment margin pipeline is equipped with the seventeenth hand valve, the seventh solenoid valve, and the ninth pressure transmitter in sequence.

[0020] According to at least one embodiment of this application, in the above-mentioned fuel supply system for testing the combustion performance of an aero-engine combustor, the second fuel booster pump is controlled by a frequency converter and connected in parallel with a fourth electric regulating valve and a second safety valve.

[0021] The combination of the fifth solenoid valve, the eleventh hand valve, the third flow meter, and the thirteenth hand valve is connected in parallel with the eighth solenoid valve, the eighteenth hand valve, the fourth flow meter, and the nineteenth hand valve.

[0022] On the other hand, a method for testing the ignition of combustion performance in an aero-engine combustor is provided, implemented based on the aforementioned fuel supply system for testing combustion performance in an aero-engine combustor, characterized in that it includes:

[0023] Before combustion chamber ignition, the first solenoid valve is opened, the seventh solenoid valve is closed, and the third solenoid valve is opened, so that the fuel pressurized by the first fuel booster pump in the fuel supply line flows back to the fuel supply line through the return fuel regulating line to form a self-circulation. Then, the back pressure of the return fuel regulating line is increased by the first electric regulating valve to simulate the effect of combustion chamber back pressure on fuel supply during ignition, and the flow rate in the fuel supply line is controlled by the first fuel booster pump to achieve the target fuel supply flow rate.

[0024] Open the seventh solenoid valve and close the third solenoid valve at the same time. Through the linkage of the solenoid valves, the fuel is switched from the return fuel regulating line to the fuel supply line. Fuel is then supplied to the combustion chamber through the fuel supply line for ignition. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the fuel supply system for testing the combustion performance of an aero-engine combustion chamber, provided in an embodiment of this application.

[0026] in:

[0027] 1-First manual valve; 2-First fuel filter; 3-First temperature transmitter; 4-First pressure transmitter; 5-Second manual valve; 6-First fuel booster pump; 7-Second pressure transmitter; 8-Third manual valve; 9-Fourth manual valve; 10-Second temperature transmitter; 11-Third pressure transmitter; 12-Second fuel filter; 13-First solenoid valve; 14-Fifth manual valve; 15-First flow meter; 16-Sixth manual valve; 17-Second solenoid valve; 18-First check valve; 19-Fourth pressure transmitter; 20-Seventh manual valve; 21-Third solenoid valve; 22-Fifth pressure transmitter; 23-First electric regulating valve; 24-Second electric regulating valve; 25-First safety valve; 26-Fourth solenoid valve; 27-Third electric regulating valve; 28-Eighth manual valve; 29- 30-Second fuel booster pump; 31-Sixth pressure transmitter; 32-Tenth hand valve; 33-Eleventh hand valve; 34-Third temperature transmitter; 35-Seventh pressure transmitter; 36-Third fuel filter; 37-Fifth solenoid valve; 38-Eleventh hand valve; 39-Third flow meter; 40-Thirteenth hand valve; 41-Fourteenth hand valve; 42-Sixth solenoid valve; 43-Second check valve; 44-Eighth pressure transmitter; 45-Fifteenth hand valve; 46-Second flow meter; 47-Sixteenth hand valve; 48-Seventeenth hand valve; 49-Seventh solenoid valve; 50-Ninth pressure transmitter; 51-Fourth electric regulating valve; 52-Second safety valve; 53-Eighth solenoid valve; 54-Eighteenth hand valve; 55-Fourth flow meter; 56-Nineteenth hand valve.

[0028] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0029] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0030] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0031] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0032] A fuel supply system for testing the combustion performance of an aero-engine combustor, such as Figure 1 As shown, it includes a fuel supply line and a return line. The booster pump is used for fuel pressurization and delivery. Temperature transmitters, pressure transmitters, and flow meters are used to measure and record the temperature, pressure, and flow at the corresponding locations. The hand valve can be opened in advance or manually as needed during the test. The solenoid valve and electric regulating valve are used for switching the pipeline and real-time flow regulation.

[0033] The fuel supply line inlet is connected to the fuel source, which can be a fuel pump station or a fuel tank, and the outlet is connected to the combustion chamber fuel inlet.

[0034] The fuel supply line is sequentially equipped with the following components: first hand valve 1, first fuel filter 2, first temperature transmitter 3, first pressure transmitter 4, second hand valve 5, first fuel booster pump 6, second pressure transmitter 7, third hand valve 8, fourth hand valve 9, second temperature transmitter 10, third pressure transmitter 11, second fuel filter 12, first solenoid valve 13, fifth hand valve 14, first flow meter 15, sixth hand valve 16, second solenoid valve 17, first check valve 18, and fourth pressure transmitter 19.

[0035] The inlet and outlet of the return oil regulating pipeline are connected to the fuel supply pipeline. The inlet is connected to the fuel supply pipeline between the sixth hand valve 16 and the seventh solenoid valve 17, and the outlet is connected to the fuel supply pipeline between the first hand valve 1 and the first fuel filter 2.

[0036] The return oil regulating pipeline is sequentially equipped with a seventh hand valve 20, a third solenoid valve 21, a fifth pressure transmitter 22, a first electric regulating valve 23, and an eighth hand valve 28.

[0037] The fuel supply system for testing the combustion performance of an aero-engine combustor disclosed in the above embodiments can simulate the back pressure of the combustor using a return fuel regulating pipeline. This allows the ignition fuel supply state to be pre-adjusted in the return fuel regulating pipeline before the test. By switching the solenoid valves on the fuel supply pipeline and the return fuel regulating pipeline in a coordinated manner, the pre-adjusted fuel in the return fuel regulating pipeline is switched to the fuel supply pipeline to supply the combustor. This achieves a smooth transition of fuel from the return fuel line to the supply fuel line during the ignition process, solves the problem of fuel supply fluctuations during the ignition test, and facilitates the consistency between the actual fuel supply and the target fuel supply. The fuel supply system integrates various measurement and control components and has the functions of fuel supply and regulation for combustor ignition, flameout, and other combustion performance test states.

[0038] Based on the fuel supply system for testing the combustion performance of an aero-engine combustor disclosed in the above embodiments, an ignition test is conducted on the combustor, which can be specifically performed as follows:

[0039] Before combustion chamber ignition, the first solenoid valve 13 is opened, the seventh solenoid valve 17 is closed, and the third solenoid valve 21 is opened, so that the fuel pressurized by the first fuel booster pump 6 in the fuel supply line flows back to the fuel supply line through the return oil regulating line to form a self-circulation. Then, the back pressure of the return oil regulating line is increased by the first electric regulating valve 23 to simulate the influence of combustion chamber back pressure and test piece nozzle area on fuel supply during ignition, and the flow rate in the fuel supply line is controlled by the first fuel booster pump 6 to achieve the target fuel supply flow rate.

[0040] Open the seventh solenoid valve 17 and close the third solenoid valve 21. Through the linkage of the solenoid valves, the fuel is switched from the return fuel regulating line to the fuel supply line. The fuel is then supplied to the combustion chamber through the fuel supply line for ignition. This avoids fluctuations in the state of the combustion chamber during the ignition and fuel supply process, and achieves a smooth transition of fuel from the return fuel regulating line to the fuel supply line during the ignition process, so that the actual fuel supply is consistent with the target fuel supply.

[0041] The first fuel booster pump 6 is controlled by a frequency converter and is connected in parallel with a second electric regulating valve 24 and a first safety valve 25. The second electric regulating valve 24 can regulate the state of the fuel supplied by the first fuel booster pump 6. Part of the fuel boosted by the first fuel booster pump 6 can flow back to the front of the first fuel booster pump 6 through the second electric regulating valve 24, which can widen the operating envelope of the first fuel booster pump 6. The first safety valve 25 can protect the first fuel booster pump 6.

[0042] The combination of the first solenoid valve 13, the fifth hand valve 14, the first flow meter 15, and the sixth hand valve 16, with the fourth solenoid valve 26, the fifteenth hand valve 45, the second flow meter 46, and the sixteenth hand valve 47 connected in parallel, can broaden the flow measurement range.

[0043] The first check valve 18 is designed to prevent high-pressure air in the combustion chamber from backflowing into the fuel supply line.

[0044] The first electric regulating valve 23 is connected in parallel with the third electric regulating valve 27. The parallel electric regulating valves can generally be selected from DN4 and DN10 regulating valves for use. The return oil back pressure can be adjusted through the parallel electric regulating valves to simulate the combustion chamber back pressure, and the back pressure of the return oil regulating pipeline can be measured through the fifth pressure transmitter 22.

[0045] The fuel supply system for testing the combustion performance of an aero-engine combustor disclosed in the above embodiments further includes a fuel supply redundancy pipeline and a return fuel adjustment redundancy pipeline, which are redundancy pipelines for the fuel supply pipeline and the return fuel adjustment pipeline.

[0046] The fuel supply margin pipeline inlet is connected to the fuel supply pipeline, and the outlet is connected to the combustion chamber fuel supply port. The connection node of the inlet on the fuel supply pipeline is located between the first pressure transmitter 4 and the second hand valve 5.

[0047] The fuel supply margin pipeline is sequentially equipped with the following components: ninth hand valve 29, second fuel booster pump 30, sixth pressure transmitter 31, tenth hand valve 32, eleventh hand valve 33, third temperature transmitter 34, seventh pressure transmitter 35, third fuel filter 36, fifth solenoid valve 37, eleventh hand valve 38, third flow meter 39, thirteenth hand valve 40, fourteenth hand valve 41, sixth solenoid valve 42, second check valve 43, and eighth pressure transmitter 44.

[0048] The inlet of the return oil adjustment margin line is connected to the fuel supply margin line, and the outlet is connected to the return oil adjustment line. The connection point of the inlet on the fuel supply margin line is between the thirteenth hand valve 40 and the fourteenth hand valve 41, and the connection point of the outlet on the return oil adjustment line is between the first electric adjustment valve 23 and the eighth hand valve 28.

[0049] The return oil adjustment margin pipeline is sequentially equipped with the seventeenth hand valve 48, the seventh solenoid valve 49, and the ninth pressure transmitter 50.

[0050] The second fuel booster pump 30 is controlled by a frequency converter and is connected in parallel to the fourth electric regulating valve 51 and the second safety valve 52.

[0051] The combination of the fifth solenoid valve 37, the eleventh hand valve 38, the third flow meter 39, and the thirteenth hand valve 40 is connected in parallel with the eighth solenoid valve 53, the eighteenth hand valve 54, the fourth flow meter 55, and the nineteenth hand valve 56.

[0052] The fuel supply system for testing the combustion performance of an aero-engine combustor disclosed in the above embodiments is designed to simulate the back pressure of the combustor using a return fuel regulating pipeline. This allows the ignition fuel supply state to be pre-adjusted in the return fuel device before the test, avoiding fluctuations in the state during the combustor ignition fuel supply process. This ensures a smooth transition of fuel from the return fuel regulating pipeline to the fuel supply pipeline during the ignition process, preventing inaccuracies caused by fluctuations. Furthermore, by linking the solenoid valves of the return fuel regulating pipeline and the fuel supply pipeline, the pre-adjusted fuel in the return fuel regulating pipeline can be switched to the fuel supply pipeline, ensuring that the actual fuel supply is consistent with the target fuel supply, thus meeting the requirements for test efficiency and accuracy.

[0053] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A fuel supply system for testing the combustion performance of an aero-engine combustion chamber, characterized in that, This includes fuel supply lines and return fuel regulating lines; The fuel supply line inlet is connected to the fuel source; The fuel supply line is sequentially equipped with the following components: first hand valve (1), first fuel filter (2), first temperature transmitter (3), first pressure transmitter (4), second hand valve (5), first fuel booster pump (6), second pressure transmitter (7), third hand valve (8), fourth hand valve (9), second temperature transmitter (10), third pressure transmitter (11), second fuel filter (12), first solenoid valve (13), fifth hand valve (14), first flow meter (15), sixth hand valve (16), second solenoid valve (17), first check valve (18), and fourth pressure transmitter (19). The inlet and outlet of the return oil regulating pipeline are connected to the fuel supply pipeline. The connection point of the inlet on the fuel supply pipeline is between the sixth hand valve (16) and the seventh solenoid valve (17), and the connection point of the outlet on the fuel supply pipeline is between the first hand valve (1) and the first fuel filter (2). The return oil regulating pipeline is sequentially equipped with a seventh hand valve (20), a third solenoid valve (21), a fifth pressure transmitter (22), a first electric regulating valve (23), and an eighth hand valve (28).

2. The fuel supply system for testing the combustion performance of an aero-engine combustion chamber according to claim 1, characterized in that, The first fuel booster pump (6) is controlled by a frequency converter and connected in parallel to the second electric regulating valve (24) and the first safety valve (25). The combination of the first solenoid valve (13), the fifth hand valve (14), the first flow meter (15), and the sixth hand valve (16) is connected in parallel with the fourth solenoid valve (26), the fifteenth hand valve (45), the second flow meter (46), and the sixteenth hand valve (47). The first electric regulating valve (23) is connected in parallel with the third electric regulating valve (27).

3. The fuel supply system for testing the combustion performance of an aero-engine combustion chamber according to claim 2, characterized in that, It also includes fuel supply margin lines and return fuel adjustment margin lines; The fuel supply margin pipeline inlet is connected to the fuel supply pipeline, and the outlet is connected to the combustion chamber fuel supply port. The connection node of the inlet on the fuel supply pipeline is located between the first pressure transmitter (4) and the second hand valve (5). The fuel supply margin pipeline is sequentially equipped with the following components: the ninth manual valve (29), the second fuel booster pump (30), the sixth pressure transmitter (31), the tenth manual valve (32), the eleventh manual valve (33), the third temperature transmitter (34), the seventh pressure transmitter (35), the third fuel filter (36), the fifth solenoid valve (37), the eleventh manual valve (38), the third flow meter (39), the thirteenth manual valve (40), the fourteenth manual valve (41), the sixth solenoid valve (42), the second check valve (43), and the eighth pressure transmitter (44). The inlet of the return oil adjustment margin pipeline is connected to the fuel supply margin pipeline, and the outlet is connected to the return oil adjustment pipeline. The connection node of the inlet on the fuel supply margin pipeline is between the thirteenth hand valve (40) and the fourteenth hand valve (41), and the connection node of the outlet on the return oil adjustment pipeline is between the first electric adjustment valve (23) and the eighth hand valve (28). The return oil adjustment margin pipeline is sequentially equipped with the seventeenth hand valve (48), the seventh solenoid valve (49), and the ninth pressure transmitter (50).

4. The fuel supply system for testing the combustion performance of an aero-engine combustion chamber according to claim 3, characterized in that, The second fuel booster pump (30) is controlled by a frequency converter and connected in parallel to the fourth electric regulating valve (51) and the second safety valve (52). The combination of the fifth solenoid valve (37), the eleventh hand valve (38), the third flow meter (39), and the thirteenth hand valve (40) is connected in parallel with the eighth solenoid valve (53), the eighteenth hand valve (54), the fourth flow meter (55), and the nineteenth hand valve (56).

5. A method for ignition testing of combustion performance in an aero-engine combustor, implemented based on the fuel supply system for combustion performance testing of an aero-engine combustor as described in claim 1, characterized in that, include: Before combustion chamber ignition, the first solenoid valve (13) is opened, the seventh solenoid valve (17) is closed, and the third solenoid valve (21) is opened, so that the fuel pressurized by the first fuel booster pump (6) in the fuel supply line flows back to the fuel supply line through the return oil regulating line to form a self-circulation. Then, the back pressure of the return oil regulating line is increased by the first electric regulating valve (23) to simulate the effect of combustion chamber back pressure on fuel supply during ignition, and the flow rate in the fuel supply line is controlled by the first fuel booster pump (6) to reach the target fuel supply flow rate. Open the seventh solenoid valve (17) and close the third solenoid valve (21) at the same time. Through the linkage of the solenoid valves, the fuel is switched from the return fuel regulating line to the fuel supply line. The fuel is supplied to the combustion chamber through the fuel supply line for ignition.

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