Aero-engine thrust augmentation spray rod flow performance test system

Abstract

A flow performance test system for an aero-engine thrust augmentation spray boom belongs to the technical field of aero-engine part manufacturing and comprises an oil tank module, a cooling module, an oil supply module, a measurement module, a pneumatic control module and an electrical cabinet. The cooling module is connected with the oil tank module; the oil supply module is arranged between an oil inlet of the stress application spray rod and the oil tank module; the measuring module is arranged between a nozzle of the stress application spray rod and the oil tank module; the pneumatic control module is connected with the measuring module; and all electric components in the oil tank module, the cooling module, the oil supply module, the measurement module and the pneumatic control module are electrically connected with the electrical cabinet. According to the aero-engine thrust augmentation spray rod flow performance test system, multiple nozzles on multiple thrust augmentation spray rods can be tested synchronously, the test efficiency and the test precision are greatly improved, and the batch test requirement of the thrust augmentation spray rods can be effectively met.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of manufacturing parts of an aero-engine, and particularly relates to an aero-engine afterburner nozzle flow performance testing system. BACKGROUND

[0002] The afterburner nozzle is an important component of an aero-engine, and the flow performance of a manufactured afterburner nozzle needs to be tested before being installed on an aero-engine. Only when the flow range and flow coefficient deviation of the afterburner nozzle meet the design requirements can the afterburner nozzle be assembled on the aero-engine as a qualified component.

[0003] Currently, when the flow performance of afterburner nozzles of various types of aero-engines is tested, the multiple nozzles on a single afterburner nozzle are tested one by one, which is low in testing efficiency and accuracy and has been difficult to meet the needs of batch testing of afterburner nozzles. SUMMARY

[0004] In view of the problems in the prior art, the present application provides an aero-engine afterburner nozzle flow performance testing system, which can simultaneously test multiple nozzles on multiple afterburner nozzles, greatly improving the testing efficiency and accuracy and effectively meeting the needs of batch testing of afterburner nozzles.

[0005] To achieve the above-mentioned purpose, the present application adopts the following technical solution: an aero-engine afterburner nozzle flow performance testing system, comprising an oil tank module, a cooling module, an oil supply module, a measurement module, a pneumatic control module and an electrical cabinet; the cooling module is connected with the oil tank module; the oil supply module is arranged between the oil inlet of the afterburner nozzle and the oil tank module; the measurement module is arranged between the nozzle of the afterburner nozzle and the oil tank module; the pneumatic control module is connected with the measurement module; all electric components in the oil tank module, the cooling module, the oil supply module, the measurement module and the pneumatic control module are electrically connected with the electrical cabinet.

[0006] The oil tank module comprises a main oil tank, a column type liquid level indicator, a first temperature sensor, an explosion-proof tuning fork densimeter, a floating ball liquid level switch and an air breathing filter; the column type liquid level indicator is arranged outside the main oil tank; the first temperature sensor, the explosion-proof tuning fork densimeter and the floating ball liquid level switch are arranged inside the main oil tank; the air breathing filter is arranged on the top of the main oil tank; a first ball valve is arranged at the oil outlet of the main oil tank; the first temperature sensor, the explosion-proof tuning fork densimeter and the floating ball liquid level switch are electrically connected with the electrical cabinet.

[0007] The cooling module comprises a stainless steel vortex magnetic pump, a plate heat exchanger, an air-cooled water chiller, a first low-pressure pipeline precision filter and a second low-pressure pipeline precision filter; the oil suction port of the stainless steel vortex magnetic pump is connected with the main oil tank in communication, a second ball valve is arranged on the pipeline between the oil suction port of the stainless steel vortex magnetic pump and the main oil tank; the oil discharge port of the stainless steel vortex magnetic pump is connected with the oil inlet of the plate heat exchanger in communication, the oil outlet of the plate heat exchanger is connected with the main oil tank in turn through the first low-pressure pipeline precision filter and the second low-pressure pipeline precision filter, a needle valve is connected externally on the pipeline between the oil outlet of the plate heat exchanger and the oil inlet of the first low-pressure pipeline precision filter; the water inlet of the plate heat exchanger is connected with the water outlet of the air-cooled water chiller in communication, a third ball valve is arranged on the pipeline between the water inlet of the plate heat exchanger and the water outlet of the air-cooled water chiller; the water outlet of the plate heat exchanger is connected with the water inlet of the air-cooled water chiller in communication, a fourth ball valve is arranged on the pipeline between the water outlet of the plate heat exchanger and the water inlet of the air-cooled water chiller; the stainless steel vortex magnetic pump is electrically connected with the electrical cabinet.

[0008] The oil supply module comprises a fuel pump, an oil suction filter, a direct-acting overflow valve, a gas-controlled proportional overflow valve, an accumulator, a first pressure pipeline filter, a second pressure pipeline filter, a mass flow meter, an oil supply throttle valve, a second temperature sensor and an anti-overflow oil receiving disc; the oil suction port of the fuel pump is connected with the main oil tank in communication through the oil suction filter, a fifth ball valve is arranged on the pipeline between the oil suction port of the fuel pump and the oil suction filter; the oil discharge port of the fuel pump is divided into three paths, the first path is connected with the main oil tank through the direct-acting overflow valve, the second path is connected with the main oil tank in turn through the accumulator and the gas-controlled proportional overflow valve, and the third path is connected with the oil inlet of the force augmenting spray rod in turn through the first pressure pipeline filter, the second pressure pipeline filter, the mass flow meter, the oil supply throttle valve and the second temperature sensor; the force augmenting spray rod is horizontally arranged and the multiple nozzles thereon are downward, the anti-overflow oil receiving disc is located below the multiple nozzles of the force augmenting spray rod, and the oil discharge port of the anti-overflow oil receiving disc is connected with the main oil tank through a pipeline; the fuel pump, the gas-controlled proportional overflow valve, the mass flow meter and the second temperature sensor are electrically connected with the electrical cabinet.

[0009] A pressure gauge is connected externally on the pipeline between the accumulator and the first pressure pipeline filter, a sixth ball valve is arranged between the pressure gauge and the pipeline; a seventh ball valve is arranged on the pipeline between the second pressure pipeline filter and the mass flow meter; a first gas-controlled reversing valve is connected externally between the oil inlet of the force augmenting spray rod and the oil discharge port of the anti-overflow oil receiving disc, a first pressure transmitter is arranged at the oil inlet of the first gas-controlled reversing valve, and a second pressure transmitter is arranged at the oil outlet of the first gas-controlled reversing valve; the pressure gauge, the first pressure transmitter and the second pressure transmitter are electrically connected with the electrical cabinet.

[0010] The measurement module comprises a plurality of measurement units arranged in a straight line, the number of the measurement units being the same as the number of the nozzles on the afterburner spray bar; the measurement unit comprises an oil receiving pipe, a measuring cylinder, a third pressure transmitter and a second air control reversing valve, the upper pipe opening of the oil receiving pipe is located directly below the nozzle of the afterburner spray bar, the oil receiving pipe is sealed through the anti-overflow oil receiving disc and is inserted downward into the measuring cylinder, the oil discharge port at the bottom of the measuring cylinder is connected in communication with the main oil tank through the second air control reversing valve; the third pressure transmitter is arranged at the oil discharge port at the bottom of the measuring cylinder; the third pressure transmitter is electrically connected with the electrical cabinet.

[0011] The air control module comprises an air pump, an air combination element, a residual pressure release valve, a pressure switch, an electromagnetic switch valve, a first electromagnetic reversing valve, an air cylinder, a linkage rod, a butterfly valve, an electrical proportional valve, a second electromagnetic reversing valve, a third electromagnetic reversing valve, a pressure reducing valve and a sound-attenuating exhaust throttle valve; the air suction port of the air pump is in communication with the atmosphere, the air discharge port of the air pump is in communication with the air control interfaces of the second air control reversing valves in all the measurement units in sequence through the residual pressure release valve, the pressure switch and the electromagnetic switch valve; the pressure switch is arranged on the pipeline between the residual pressure release valve and the electromagnetic switch valve; an eighth ball valve is arranged on the pipeline between the air discharge port of the air pump and the air combination element; the number of the butterfly valves is the same as the number of the measurement units, and one butterfly valve is arranged on the oil receiving pipe in each measurement unit; the linkage rod is connected in series with the control ends of the butterfly valves in all the measurement units; the piston rod of the air cylinder is in transmission connection with the linkage rod; four external pipelines are arranged on the pipeline between the residual pressure release valve and the electromagnetic switch valve, the first external pipeline is in communication with the atmosphere, the pressure reducing valve and the sound-attenuating exhaust throttle valve are arranged on the first external pipeline in sequence; the second external pipeline is in communication with the air control interface of the air control proportional overflow valve, the electrical proportional valve and the first electromagnetic reversing valve are arranged on the second external pipeline in sequence; the third external pipeline is in communication with the air control interface of the first air control reversing valve, the second electromagnetic reversing valve is arranged on the third external pipeline; the fourth external pipeline is in communication with the air control interface of the air cylinder, and the third electromagnetic reversing valve is arranged on the fourth external pipeline; the air pump, the residual pressure release valve, the pressure switch, the electromagnetic switch valve, the first electromagnetic reversing valve, the electrical proportional valve, the second electromagnetic reversing valve and the third electromagnetic reversing valve are electrically connected with the electrical cabinet.

[0012] The beneficial effects of the present application are as follows: The afterburner spray bar flow performance test system for an aero-engine can simultaneously test a plurality of nozzles on a plurality of afterburner spray bars, greatly improves the test efficiency and test accuracy, and can effectively meet the batch test needs of the afterburner spray bar. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 It is a schematic diagram of the afterburner spray bar flow performance test system for an aero-engine. In the figure, 1 - force spraying rod, 2 - main oil tank, 3 - column type liquid level indicator, 4 - first temperature sensor, 5 - explosion-proof tuning fork densimeter, 6 - float ball liquid level switch, 7 - air breathing filter, 8 - first ball valve, 9 - stainless steel vortex magnetic pump, 10 - plate heat exchanger, 11 - air-cooled water chiller, 12 - first low-pressure pipeline precision filter, 13 - second low-pressure pipeline precision filter, 14 - second ball valve, 15 - needle valve, 16 - third ball valve, 17 - fourth ball valve, 18 - fuel pump, 19 - oil suction filter, 20 - direct-acting overflow valve, 21 - air control proportional overflow valve, 22 - pressure accumulator, 23 - first pressure pipeline filter, 24 - second pressure pipeline filter, 25 - mass flow meter, 26 - oil supply throttle valve, 27 - second temperature sensor, 28 - anti-overflow oil receiving tray, 29 - fifth ball valve, 30 - sixth ball valve, 31 - seventh ball valve, 32 - first air control reversing valve, 33 - first pressure transmitter, 34 - second pressure transmitter, 35 - oil receiving pipe, 36 - measuring cylinder, 37 - third pressure transmitter, 38 - second air control reversing valve, 39 - air pump, 40 - air combination element, 41 - residual pressure release valve, 42 - pressure switch, 43 - electromagnetic on-off valve, 44 - first electromagnetic reversing valve, 45 - air cylinder, 46 - linkage rod, 47 - butterfly valve, 48 - electric proportional valve, 49 - second electromagnetic reversing valve, 50 - third electromagnetic reversing valve, 51 - pressure reducing valve, 52 - sound-attenuating exhaust throttle valve, 53 - eighth ball valve, 54 - pressure gauge. DETAILED DESCRIPTION

[0014] The application will be further described in detail below with reference to the accompanying drawings and specific examples.

[0015] As Figure 1 shown, an afterburner flow performance test system of an aero-engine includes an oil tank module, a cooling module, an oil supply module, a measurement module, an air control module and an electrical cabinet; the cooling module is connected with the oil tank module; the oil supply module is arranged between the oil inlet of the afterburner 1 and the oil tank module; the measurement module is arranged between the nozzle of the afterburner 1 and the oil tank module; the air control module is connected with the measurement module; all electric components in the oil tank module, the cooling module, the oil supply module, the measurement module and the air control module are electrically connected with the electrical cabinet.

[0016] The oil tank module comprises a main oil tank 2, a column type liquid level indicator 3, a first temperature sensor 4, an explosion-proof tuning fork densimeter 5, a float ball liquid level switch 6 and an air breathing filter 7; the column type liquid level indicator 3 is arranged outside the main oil tank 2; the first temperature sensor 4, the explosion-proof tuning fork densimeter 5 and the float ball liquid level switch 6 are all arranged inside the main oil tank 2; the air breathing filter 7 is arranged at the top of the main oil tank 2; a first ball valve 8 is arranged at the oil outlet of the main oil tank 2; the first temperature sensor 4, the explosion-proof tuning fork densimeter 5 and the float ball liquid level switch 6 are all electrically connected with the electrical cabinet.

[0017] The cooling module comprises a stainless steel vortex magnetic pump 9, a plate heat exchanger 10, an air-cooled water chiller 11, a first low-pressure pipeline precision filter 12 and a second low-pressure pipeline precision filter 13; the oil suction port of the stainless steel vortex magnetic pump 9 is communicated with the main oil tank 2, and a second ball valve 14 is arranged on the pipeline between the oil suction port of the stainless steel vortex magnetic pump 9 and the main oil tank 2; the oil discharge port of the stainless steel vortex magnetic pump 9 is communicated with the oil inlet of the plate heat exchanger 10, the oil outlet of the plate heat exchanger 10 is sequentially communicated with the main oil tank 2 through the first low-pressure pipeline precision filter 12 and the second low-pressure pipeline precision filter 13, and a needle valve 15 is connected outside the pipeline between the oil outlet of the plate heat exchanger 10 and the oil inlet of the first low-pressure pipeline precision filter 12; the water inlet of the plate heat exchanger 10 is communicated with the water outlet of the air-cooled water chiller 11, and a third ball valve 16 is arranged on the pipeline between the water inlet of the plate heat exchanger 10 and the water outlet of the air-cooled water chiller 11; the water outlet of the plate heat exchanger 10 is communicated with the water inlet of the air-cooled water chiller 11, and a fourth ball valve 17 is arranged on the pipeline between the water outlet of the plate heat exchanger 10 and the water inlet of the air-cooled water chiller 11; the stainless steel vortex magnetic pump 9 is electrically connected with the electrical cabinet.

[0018] The oil supply module comprises a fuel pump 18, an oil suction filter 19, a direct-acting overflow valve 20, a gas-controlled proportional overflow valve 21, an accumulator 22, a first pressure pipeline filter 23, a second pressure pipeline filter 24, a mass flow meter 25, an oil supply throttle valve 26, a second temperature sensor 27, and an anti-overflow oil receiving tray 28; the oil suction port of the fuel pump 18 is connected with the main oil tank 2 through the oil suction filter 19, and a fifth ball valve 29 is arranged on the pipeline between the oil suction port of the fuel pump 18 and the oil suction filter 19; the oil discharge port of the fuel pump 18 is divided into three paths, the first path is connected with the main oil tank 2 through the direct-acting overflow valve 20, the second path is connected with the main oil tank 2 in sequence through the accumulator 22 and the gas-controlled proportional overflow valve 21, and the third path is connected with the oil inlet of the force amplification spray rod 1 in sequence through the first pressure pipeline filter 23, the second pressure pipeline filter 24, the mass flow meter 25, the oil supply throttle valve 26, and the second temperature sensor 27; the force amplification spray rod 1 is horizontally arranged, and the multiple nozzles thereon are downward, the anti-overflow oil receiving tray 28 is located below the multiple nozzles of the force amplification spray rod 1, and the oil discharge port of the anti-overflow oil receiving tray 28 is connected with the main oil tank 2 through a pipeline; the fuel pump 18, the gas-controlled proportional overflow valve 21, the mass flow meter 25, and the second temperature sensor 27 are electrically connected with the electrical cabinet.

[0019] A pressure gauge 54 is externally connected to the pipeline between the accumulator 22 and the first pressure pipeline filter 23, and a sixth ball valve 30 is arranged between the pressure gauge 54 and the pipeline; a seventh ball valve 31 is arranged on the pipeline between the second pressure pipeline filter 24 and the mass flow meter 25; a first gas-controlled reversing valve 32 is externally connected between the oil inlet of the force amplification spray rod 1 and the oil discharge port of the anti-overflow oil receiving tray 28, a first pressure transmitter 33 is arranged at the oil inlet of the first gas-controlled reversing valve 32, and a second pressure transmitter 34 is arranged at the oil outlet of the first gas-controlled reversing valve 32; the pressure gauge 54, the first pressure transmitter 33, and the second pressure transmitter 34 are electrically connected with the electrical cabinet.

[0020] The measurement module comprises a plurality of measurement units arranged in a straight line, and the number of the measurement units is the same as the number of the nozzles on the force amplification spray rod 1; each measurement unit comprises an oil receiving pipe 35, a measuring cylinder 36, a third pressure transmitter 37, and a second gas-controlled reversing valve 38; the upper pipe port of the oil receiving pipe 35 is located directly below the nozzle of the force amplification spray rod 1, the oil receiving pipe 35 is sealed through the anti-overflow oil receiving tray 28 and is inserted into the measuring cylinder 36 downward, and the oil discharge port at the bottom of the measuring cylinder 36 is connected with the main oil tank 2 through the second gas-controlled reversing valve 38; the third pressure transmitter 37 is arranged at the oil discharge port at the bottom of the measuring cylinder 36; the third pressure transmitter 37 is electrically connected with the electrical cabinet.

[0021] The air control module comprises an air pump 39, an air combination element 40, a residual pressure release valve 41, a pressure switch 42, an electromagnetic switch valve 43, a first electromagnetic reversing valve 44, an air cylinder 45, a linkage rod 46, butterfly valves 47, an electric proportional valve 48, a second electromagnetic reversing valve 49, a third electromagnetic reversing valve 50, a pressure reducing valve 51 and a sound-attenuating exhaust throttle valve 52; the air suction port of the air pump 39 is in communication with the atmosphere, the air exhaust port of the air pump 39 is in communication with the air control interface of the second air control reversing valve 38 in all the measuring units in sequence through the residual pressure release valve 41, the pressure switch 42 and the electromagnetic switch valve 43; the eighth ball valve 53 is arranged on the pipeline between the air exhaust port of the air pump 39 and the air combination element 40; the number of the butterfly valves 47 is the same as that of the measuring units, and one butterfly valve 47 is arranged on the oil receiving pipe 35 in each measuring unit; the linkage rod 46 is connected in series with the control ends of the butterfly valves 47 in all the measuring units; the piston rod of the air cylinder 45 is in transmission connection with the linkage rod 46; four external pipelines are arranged on the pipeline between the residual pressure release valve 41 and the electromagnetic switch valve 43, the first external pipeline is in communication with the atmosphere, the pressure reducing valve 51 and the sound-attenuating exhaust throttle valve 52 are arranged on the first external pipeline in sequence; the second external pipeline is in communication with the air control interface of the air control proportional overflow valve 21, the electric proportional valve 48 and the first electromagnetic reversing valve 44 are arranged on the second external pipeline in sequence; the third external pipeline is in communication with the air control interface of the first air control reversing valve 32, the second electromagnetic reversing valve 49 is arranged on the third external pipeline; the fourth external pipeline is in communication with the air control interface of the air cylinder 45, the third electromagnetic reversing valve 50 is arranged on the fourth external pipeline; the air pump 39, the residual pressure release valve 41, the pressure switch 42, the electromagnetic switch valve 43, the first electromagnetic reversing valve 44, the electric proportional valve 48, the second electromagnetic reversing valve 49 and the third electromagnetic reversing valve 50 are electrically connected with the electric cabinet.

[0022] The following describes the one-time use process of the application in combination with the drawings: In the embodiment, the number of single tests of the force-adding spray rod 1 is two, and the number of nozzles on each force-adding spray rod 1 is eight, that is, sixteen nozzles on two force-adding spray rods 1 are simultaneously tested at one time.

[0023] First, the clamping and fixing of the afterburner 1 is completed, the oil inlet of the afterburner 1 is connected to the oil supply module, and the sixteen nozzles are accurately aligned with the sixteen oil receiving pipes 35 below. During the debugging stage, if the aviation kerosene sprayed by the nozzles exists incomplete oil collection such as splashing, dripping and the like, the clamping position of the afterburner 1 needs to be adjusted again until the aviation kerosene sprayed by the sixteen nozzles can be completely collected into the corresponding oil receiving pipes 35. Finally, the aviation kerosene splashed and dripped in the anti-overflow oil receiving disc 28 and the aviation kerosene collected during the debugging stage flowing into the measuring cylinder 36 are uniformly discharged back to the main oil tank 2, preparing for formal testing.

[0024] Before formal testing, the column type liquid level indicator 3 and the first temperature sensor 4 can feed back the liquid level data and temperature data of the aviation kerosene in the main oil tank 2 to the display control panel of the electrical cabinet in real time. Subsequently, the second ball valve 14, the third ball valve 16 and the fourth ball valve 17 in the cooling module are adjusted to the open state, and the stainless steel vortex magnetic pump 9 and the air-cooled water cooler 11 are started. Under the pumping force of the stainless steel vortex magnetic pump 9, the aviation kerosene in the main oil tank 2 passes through the stainless steel vortex magnetic pump 9, the plate heat exchanger 10, the first low-pressure pipeline precision filter 12 and the second low-pressure pipeline precision filter 13 in turn and returns to the main oil tank 2. The aviation kerosene realizes heat exchange with the cold water output by the air-cooled water cooler 11 at the plate heat exchanger 10, so that the aviation kerosene in the main oil tank 2 realizes circulating cooling and keeps the oil temperature relatively constant. The double filtration of the first low-pressure pipeline precision filter 12 and the second low-pressure pipeline precision filter 13 ensures that the oil is always clean, providing protection for subsequent flow testing.

[0025] When starting the test, the oil supply module, the measuring module and the air control module are started synchronously and perform the set program as the working state. The fifth ball valve 29, the sixth ball valve 30, the seventh ball valve 31 and the eighth ball valve 53 are all adjusted to the open state.

[0026] For the oil supply module, with the start of the fuel pump 18, the aviation kerosene in the main oil tank 2 passes through the oil suction filter 19, the fuel pump 18, the first pressure pipeline filter 23, the second pressure pipeline filter 24, the mass flow meter 25 and the oil supply throttle valve 26 into the afterburner 1 under the pumping force. The mass flow meter 25 and the second temperature sensor 27 can feed back the mass flow data and temperature data in the oil supply state to the display control panel of the electrical cabinet in real time.

[0027] For the air control module, with the start of the air pump 39, first the third electromagnetic reversing valve 50 is powered on, and the compressed gas enters the rodless cavity of the air cylinder 45 through the air combination element 40, the residual pressure release valve 41 and the third electromagnetic reversing valve 50 in turn, drives the piston rod of the air cylinder 45 to extend, and then drives the linkage rod 46 to move, until the sixteen butterfly valves 47 are driven by the linkage rod 46 to synchronously switch from the closed state to the open state, so that the sixteen oil connection pipes 35 are all turned on.

[0028] In the state that the sixteen oil connection pipes 35 are all turned on, the sixteen nozzles on the force spraying rod 1 synchronously spray oil, and the sprayed aviation kerosene enters the sixteen measuring cylinders 36 below through the oil connection pipes 35 for collection. When the set oil spraying time ends, first the third electromagnetic reversing valve 50 is reversed, and the compressed gas enters the rod cavity of the air cylinder 45 through the third electromagnetic reversing valve 50, and then drives the linkage rod 46 to move, until the sixteen butterfly valves 47 are driven by the linkage rod 46 to synchronously switch from the open state to the closed state, and the sixteen oil connection pipes 35 are all adjusted to the cut-off state, and the collection of aviation kerosene in the sixteen measuring cylinders 36 ends.

[0029] After the collection of aviation kerosene in the sixteen measuring cylinders 36 ends, the second electromagnetic reversing valve 49 is powered on, the compressed gas passes through the air control interface of the second electromagnetic reversing valve 49 and the first air control reversing valve 32 to make the first air control reversing valve 32 reverse, and the aviation kerosene no longer enters the force spraying rod 1, but directly returns to the main oil tank 2 through the open first air control reversing valve 32. At this time, the test system enters the standby state.

[0030] In addition, after the collection of aviation kerosene in the sixteen measuring cylinders 36 ends, the volume of aviation kerosene in each measuring cylinder 36 will be synchronously converted into a pressure electric signal of the third pressure transmitter 37, which will be fed back to the air control proportional overflow valve 21 electric cabinet in real time, and finally through real-time data conversion and reflected on the display control panel of the electric cabinet, the flow data, and the flow range, flow coefficient deviation and other indicators are also reflected on the display control panel of the electric cabinet, the test results are automatically saved and recorded, and the whole test process is automated.

[0031] When different oil supply conditions need to be simulated, first, the electromagnetic switch valve 43 is powered on, the compressed gas passes through the electromagnetic switch valve 43 and the gas control interface of all sixteen second gas control reversing valves 38 to be conducted, so that the first gas control reversing valve 32 realizes reversing, the aviation kerosene in the sixteen measuring cylinders 36 will be directly returned to the main oil tank 2 through the first gas control reversing valve 32, after the aviation kerosene in the sixteen measuring cylinders 36 is completely discharged, the first electromagnetic reversing valve 44 is powered on, the compressed gas passes through the first electromagnetic reversing valve 44 and the electric proportional valve 48 and the gas control interface of the gas control proportional overflow valve 21 to be conducted, to adjust the overflow of the gas control proportional overflow valve 21, so as to change the flow parameter of the aviation kerosene entering the afterburner 1, so as to realize the change of the oil supply condition.

[0032] The scheme in the embodiment is not used to limit the protection scope of the present application, and equivalent implementation or changes made without departing from the present application are included in the protection scope of the present application.

Claims

1. A test system for the flow performance of an aero-engine afterburner boom, characterized in that: It includes an oil tank module, a cooling module, an oil supply module, a measurement module, a pneumatic control module, and an electrical cabinet; the cooling module is connected to the oil tank module; the oil supply module is located between the oil inlet of the booster spray bar and the oil tank module; the measurement module is located between the nozzle of the booster spray bar and the oil tank module; the pneumatic control module is connected to the measurement module; all electrical components in the oil tank module, cooling module, oil supply module, measurement module, and pneumatic control module are electrically connected to the electrical cabinet.

2. The aero-engine afterburner boom flow performance testing system according to claim 1, characterized in that: The oil tank module includes a main oil tank, a column-type liquid level indicator, a first temperature sensor, an explosion-proof tuning fork density meter, a float level switch, and an air breathing filter; the column-type liquid level indicator is located outside the main oil tank; the first temperature sensor, the explosion-proof tuning fork density meter, and the float level switch are all located inside the main oil tank; the air breathing filter is located on the top of the main oil tank; a first ball valve is installed at the oil drain port of the main oil tank; the first temperature sensor, the explosion-proof tuning fork density meter, and the float level switch are all electrically connected to the electrical cabinet.

3. The aero-engine afterburner boom flow performance testing system according to claim 2, characterized in that: The cooling module includes a stainless steel vortex magnetic pump, a plate heat exchanger, an air-cooled chiller, a first low-pressure pipeline precision filter, and a second low-pressure pipeline precision filter. The oil suction port of the stainless steel vortex magnetic pump is connected to the main oil tank, and a second ball valve is installed on the pipeline between the oil suction port of the stainless steel vortex magnetic pump and the main oil tank. The oil discharge port of the stainless steel vortex magnetic pump is connected to the oil inlet of the plate heat exchanger, and the oil outlet of the plate heat exchanger is connected to the main oil tank sequentially through the first and second low-pressure pipeline precision filters. A needle valve is externally connected to the pipeline between the oil outlet of the plate heat exchanger and the oil inlet of the first low-pressure pipeline precision filter; the water inlet of the plate heat exchanger is connected to the water outlet of the air-cooled chiller, and a third ball valve is installed on the pipeline between the water inlet of the plate heat exchanger and the water outlet of the air-cooled chiller; the water outlet of the plate heat exchanger is connected to the water inlet of the air-cooled chiller, and a fourth ball valve is installed on the pipeline between the water outlet of the plate heat exchanger and the water inlet of the air-cooled chiller; the stainless steel vortex magnetic pump is electrically connected to the electrical cabinet.

4. The aero-engine afterburner boom flow performance testing system according to claim 3, characterized in that: The fuel supply module includes a fuel pump, a fuel suction filter, a direct-acting overflow valve, a pneumatically controlled proportional overflow valve, an accumulator, a first pressure pipeline filter, a second pressure pipeline filter, a mass flow meter, a fuel supply throttle valve, a second temperature sensor, and an anti-overflow drip tray. The fuel pump's suction port is connected to the main fuel tank via the fuel suction filter, and a fifth ball valve is installed on the pipeline between the fuel pump's suction port and the fuel suction filter. The fuel pump's discharge port has three outputs: the first output is connected to the main fuel tank via the direct-acting overflow valve, the second output is connected to the accumulator in sequence... The compressor and pneumatic proportional relief valve are connected to the main fuel tank. The third path is connected to the fuel inlet of the booster injector via the first pressure pipeline filter, the second pressure pipeline filter, the mass flow meter, the fuel supply throttle valve, and the second temperature sensor. The booster injector is horizontally positioned with its multiple nozzles pointing downwards. The anti-overflow drip tray is located below the multiple nozzles of the booster injector, and the drain port of the anti-overflow drip tray is connected to the main fuel tank via a pipeline. The fuel pump, the pneumatic proportional relief valve, the mass flow meter, and the second temperature sensor are all electrically connected to the electrical cabinet.

5. The aero-engine afterburner boom flow performance testing system according to claim 4, characterized in that: A pressure gauge is externally connected to the pipeline between the accumulator and the first pressure pipeline filter, and a sixth ball valve is installed between the pressure gauge and the pipeline; a seventh ball valve is installed on the pipeline between the second pressure pipeline filter and the mass flow meter; a first pneumatic directional valve is externally connected between the oil inlet of the booster spray bar and the oil outlet of the anti-overflow receiving pan, a first pressure transmitter is installed at the oil inlet of the first pneumatic directional valve, and a second pressure transmitter is installed at the oil outlet of the first pneumatic directional valve; the pressure gauge, the first pressure transmitter, and the second pressure transmitter are all electrically connected to the electrical cabinet.

6. The aero-engine afterburner boom flow performance testing system according to claim 5, characterized in that: The measurement module includes several measurement units arranged in a straight line, the number of which is the same as the number of nozzles on the booster spray bar. Each measurement unit includes an oil inlet pipe, a measuring cylinder, a third pressure transmitter, and a second pneumatically controlled directional valve. The upper inlet of the oil inlet pipe is located directly below the nozzles of the booster spray bar. The oil inlet pipe passes through an anti-overflow oil receiving pan and is inserted downwards into the measuring cylinder. The oil outlet at the bottom of the measuring cylinder is connected to the main oil tank via the second pneumatically controlled directional valve. The third pressure transmitter is located at the oil outlet at the bottom of the measuring cylinder. The third pressure transmitter is electrically connected to the electrical cabinet.

7. The aero-engine afterburner boom flow performance testing system according to claim 6, characterized in that: The pneumatic control module includes an air pump, an air assembly, a residual pressure relief valve, a pressure switch, a solenoid valve, a first solenoid directional valve, a cylinder, a linkage rod, a butterfly valve, an electro-proportional valve, a second solenoid directional valve, a third solenoid directional valve, a pressure reducing valve, and a silencer-type exhaust throttle valve. The air pump's intake port is open to the atmosphere, and its exhaust port is connected sequentially to the air control interface of the second pneumatic directional valve in all measurement units via the air assembly, the residual pressure relief valve, and the solenoid valve. The pressure switch is located on the pipeline between the residual pressure relief valve and the solenoid valve. An eighth ball valve is installed on the pipeline between the air pump's exhaust port and the air assembly. The number of butterfly valves is several, the same as the number of measurement units, and one butterfly valve is installed on the oil inlet pipe in each measurement unit. The linkage rod is connected in series with the control terminals of the butterfly valves in all measurement units. The cylinder... The piston rod is connected to the linkage rod via a transmission. Four external pipelines are installed on the pipeline between the residual pressure relief valve and the solenoid switch valve. The first external pipeline is open to the atmosphere, and the pressure reducing valve and the silencer-type exhaust throttle valve are sequentially installed on the first external pipeline. The second external pipeline is connected to the pneumatic control interface of the pneumatic proportional relief valve, and the electro-proportional valve and the first solenoid directional valve are sequentially installed on the second external pipeline. The third external pipeline is connected to the pneumatic control interface of the first pneumatic directional valve, and the second solenoid directional valve is installed on the third external pipeline. The fourth external pipeline is connected to the pneumatic control interface of the cylinder, and the third solenoid directional valve is installed on the fourth external pipeline. The air pump, residual pressure relief valve, pressure switch, solenoid switch valve, first solenoid directional valve, electro-proportional valve, second solenoid directional valve, and third solenoid directional valve are all electrically connected to the electrical cabinet.

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