CN-122016324-A - Oil supply system for combustion performance test of aero-engine combustion chamber and ignition test method

CN122016324ACN 122016324 ACN122016324 ACN 122016324ACN-122016324-A

Abstract

The application relates to an oil supply system for a combustion performance test of an aeroengine combustion chamber and an ignition test method, wherein the oil supply system comprises a fuel supply pipeline and an oil return adjusting pipeline, an inlet of the fuel supply pipeline is connected with a fuel source, an outlet of the fuel supply pipeline is connected with a fuel supply port of the combustion chamber, a first hand valve, a first fuel filter, a first temperature transmitter, a first pressure transmitter, a second hand valve, a first fuel 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 filter, a first electromagnetic valve, a fifth hand valve, a first flowmeter, a sixth hand valve, a second electromagnetic valve, a first one-way valve and a fourth pressure transmitter are sequentially arranged on the fuel supply pipeline, an inlet and an outlet of the oil return adjusting pipeline are connected to the fuel supply pipeline, and a seventh hand valve, a third electromagnetic valve, a fifth pressure transmitter, a first electric adjusting valve and an eighth hand valve are sequentially arranged on the oil return pipeline.

Inventors

GAO HONGDA
WANG XINYAO
ZHANG YUGUANG
WU PENGLONG
XIAO YAO
ZHAO YU
WU ZHENDONG
FENG XIAO
ZHANG JIFENG
XU XINGLIANG

Assignees

中国航发沈阳发动机研究所

Dates

Publication Date: 20260512
Application Date: 20260210

Claims (5)

1. The fuel supply system for the combustion performance test of the aero-engine combustion chamber is characterized by comprising a fuel supply pipeline and an oil return regulating pipeline; the inlet of the fuel oil supply pipeline is connected with a fuel source; The fuel oil supply pipeline is sequentially provided with a first hand valve (1), a first fuel oil filter (2), a first temperature transmitter (3), a first pressure transmitter (4), a second hand valve (5), a first fuel oil booster pump (6), a second pressure transmitter (7), a third hand valve (8), a fourth hand valve (9), a second temperature transmitter (10), a third pressure transmitter (11), a second fuel oil filter (12), a first electromagnetic valve (13), a fifth hand valve (14), a first flowmeter (15), a sixth hand valve (16), a second electromagnetic valve (17), a first one-way valve (18) and a fourth pressure transmitter (19); The inlet and the outlet of the oil return regulating pipeline are connected to the fuel oil supply pipeline, wherein the connecting node of the inlet on the fuel oil supply pipeline is positioned between the sixth hand valve (16) and the seventh electromagnetic valve (17), and the connecting node of the outlet on the fuel oil supply pipeline is positioned between the first hand valve (1) and the first fuel filter (2); The oil return regulating pipeline is sequentially provided with a seventh hand valve (20), a third electromagnetic 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 the combustion performance test of the aero-engine combustion chamber according to claim 1, wherein the first fuel booster pump (6) controls the working state through a frequency converter and is connected in parallel with a second electric regulating valve (24) and with a first safety valve (25); A combination of a first electromagnetic valve (13), a fifth hand valve (14), a first flowmeter (15) and a sixth hand valve (16), and a fourth electromagnetic valve (26), a fifteenth hand valve (45), a second flowmeter (46) and a sixteenth hand valve (47) are connected in parallel; the first electric regulating valve (23) is connected in parallel with a third electric regulating valve (27).
3. The fuel supply system for the combustion performance test of the combustion chamber of the aero-engine according to claim 2, further comprising a fuel supply redundancy pipeline and a fuel return adjustment redundancy pipeline; The inlet of the fuel oil supply redundancy pipeline is connected with the fuel oil supply pipeline, the outlet of the fuel oil supply redundancy pipeline is connected with the fuel oil supply port of the combustion chamber, wherein the connection node of the inlet on the fuel oil supply pipeline is positioned between the first pressure transmitter (4) and the second hand valve (5); A ninth hand valve (29), a second fuel booster pump (30), a sixth pressure transmitter (31), a tenth hand valve (32), an eleventh hand valve (30), a third temperature transmitter (34), a seventh pressure transmitter (35), a third fuel filter (36), a fifth electromagnetic valve (37), a twelfth hand valve (38), a third flowmeter (39), a thirteenth hand valve (40), a fourteenth hand valve (41), a sixth electromagnetic valve (42), a second one-way valve (43) and an eighth pressure transmitter (44) are sequentially arranged on the fuel oil supply redundancy pipeline; the inlet of the oil return adjusting redundancy pipeline is connected to the oil supply redundancy pipeline, the outlet of the oil return adjusting redundancy pipeline is connected to the oil return adjusting pipeline, wherein the connecting node of the inlet on the oil supply redundancy pipeline is positioned between a thirteenth hand valve (40) and a fourteenth hand valve (41), and the connecting node of the outlet on the oil return adjusting pipeline is positioned between a first electric adjusting valve (23) and an eighth hand valve (28); A seventeenth hand valve (48), a seventh electromagnetic valve (49) and a ninth pressure transmitter (50) are sequentially arranged on the oil return adjustment redundancy pipeline.
4. An aircraft engine combustion chamber combustion performance test oil supply system according to claim 3, characterized in that the second fuel booster pump (30) controls the working state through a frequency converter and is connected in parallel with a fourth electric regulating valve (51) and with a second safety valve (52); a combination of a fifth electromagnetic valve (37), a twelfth hand valve (38), a third flowmeter (39) and a thirteenth hand valve (40) is connected in parallel with an eighth electromagnetic valve (53), an eighteenth hand valve (54), a fourth flowmeter (55) and a nineteenth hand valve (56).
5. An aircraft engine combustion chamber combustion performance test ignition test method implemented based on the aircraft engine combustion chamber combustion performance test oil supply system according to claim 1, comprising: Before the combustion chamber ignites, the first electromagnetic valve (13) is opened, the seventh electromagnetic valve (17) is closed, the third electromagnetic valve (21) is opened, so that the fuel oil which is pressurized in the fuel oil supply pipeline by the first fuel oil booster pump (6) flows back to the fuel oil supply pipeline through the fuel oil return adjusting pipeline to form self-circulation, the back pressure of the fuel oil return adjusting pipeline is further controlled and improved through the first electric adjusting valve (23), the influence of the back pressure of the combustion chamber on the fuel oil supply in the ignition process is simulated, and the flow in the fuel oil supply pipeline is controlled through the first fuel oil booster pump (6) to reach the target fuel oil flow; and the seventh electromagnetic valve (17) is opened, the third electromagnetic valve (21) is closed, the switching of fuel oil from the oil return adjusting pipeline to the fuel oil supply pipeline is realized through the linkage of the electromagnetic valves, and the fuel oil is supplied to the combustion chamber through the fuel oil supply pipeline to perform ignition.

Description

Oil supply system for combustion performance test of aero-engine combustion chamber and ignition test method Technical Field The application belongs to the field of combustion performance tests of aero-engine combustion chambers, and particularly relates to an oil supply system and an ignition test method for the combustion performance test of an aero-engine combustion chamber. Background With the development of the technology of the aeroengine combustion chamber, the combustion performance test of the combustion chamber requires the oil supply system to be capable of performing wide-range high-precision adjustment, has high system stability and multiple fuel test supply capacities, and can meet the fuel supply and adjustment functions of the combustion chamber for ignition, flameout and other combustion performance test state adjustment. The ignition limit of the combustion chamber under different test states is obtained by changing the oil-gas ratio in the combustion chamber through adjusting the oil supply quantity, the influence of the back pressure of the combustion chamber in the ignition test is not considered in the current oil supply system, the oil supply is carried out by adopting a mode of opening the oil supply valve to spray fuel into the combustion chamber after increasing the pipeline of the oil supply system to a certain pressure, and due to the influence of the back pressure of the combustion chamber and the throttling of a nozzle orifice, the oil supply mode can cause fluctuation of the fuel spraying flow during the ignition of the combustion chamber to cause inaccurate test, and on the other hand, the actual oil supply quantity and the target oil supply quantity often have certain deviation, so that the oil supply state in the ignition process is difficult to adjust to influence the test efficiency. The present application has been made in view of the above-described technical drawbacks. Disclosure of Invention The application aims to provide an oil supply system for combustion performance test of an aeroengine combustion chamber and an ignition test method, which overcome or alleviate at least one technical defect of the prior art. The technical scheme of the application is as follows: An oil supply system for a combustion performance test of an aero-engine combustion chamber comprises a fuel oil supply pipeline and an oil return adjusting pipeline; the inlet of the fuel oil supply pipeline is connected with a fuel source, the outlet is connected with an oil supply port of the combustion chamber; The fuel oil supply pipeline is sequentially provided with 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, a sixth hand valve, a second electromagnetic valve, a first one-way valve and a fourth pressure transmitter; The inlet and the outlet of the oil return regulating pipeline are connected to the fuel oil supply pipeline, wherein the connecting node of the inlet on the fuel oil supply pipeline is positioned between the sixth hand valve and the seventh electromagnetic valve, and the connecting node of the outlet on the fuel oil supply pipeline is positioned between the first hand valve and the first fuel filter; the seventh hand valve, the third electromagnetic valve, the fifth pressure transmitter, the first electric regulating valve and the eighth hand valve are sequentially arranged on the oil return regulating pipeline. According to at least one embodiment of the application, in the fuel supply system for the combustion performance test of the combustion chamber of the aero-engine, the first fuel booster pump controls the working state through the frequency converter, and is connected with the second electric regulating valve in parallel and the first safety valve in parallel; a fourth electromagnetic valve, a fifteenth hand valve, a second flowmeter and a sixteenth hand valve are connected in parallel with the combination of the first electromagnetic valve, the fifth hand valve, the first flowmeter and the sixth hand valve; the first electric regulating valve is connected in parallel with the third electric regulating valve. According to at least one embodiment of the application, the fuel supply system for the combustion performance test of the combustion chamber of the aero-engine further comprises a fuel supply redundancy pipeline and a fuel return adjustment redundancy pipeline; The inlet of the fuel oil supply redundancy pipeline is connected with the fuel oil supply pipeline, the outlet of the fuel oil supply redundancy pipeline is connected with the fuel oil supply port of the combustion chamber, and the connection node of the inlet on the fuel