CN115900861A - Aero-engine nozzle flow testing device and method - Google Patents
Aero-engine nozzle flow testing device and method Download PDFInfo
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- CN115900861A CN115900861A CN202310232754.9A CN202310232754A CN115900861A CN 115900861 A CN115900861 A CN 115900861A CN 202310232754 A CN202310232754 A CN 202310232754A CN 115900861 A CN115900861 A CN 115900861A
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- 239000000446 fuel Substances 0.000 claims abstract description 97
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- 239000002828 fuel tank Substances 0.000 claims description 15
- 238000012544 monitoring process Methods 0.000 claims description 12
- 238000001914 filtration Methods 0.000 claims description 10
- 238000001816 cooling Methods 0.000 claims description 8
- 238000009423 ventilation Methods 0.000 claims description 6
- 238000005086 pumping Methods 0.000 claims description 2
- 238000010998 test method Methods 0.000 claims description 2
- 239000003921 oil Substances 0.000 description 88
- 238000010586 diagram Methods 0.000 description 8
- 230000006870 function Effects 0.000 description 7
- 239000000295 fuel oil Substances 0.000 description 5
- 238000005259 measurement Methods 0.000 description 5
- 238000005299 abrasion Methods 0.000 description 4
- 238000010521 absorption reaction Methods 0.000 description 4
- 238000013522 software testing Methods 0.000 description 4
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- 238000003860 storage Methods 0.000 description 3
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- 239000010963 304 stainless steel Substances 0.000 description 2
- 229910000589 SAE 304 stainless steel Inorganic materials 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 238000004364 calculation method Methods 0.000 description 1
- 238000004590 computer program Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
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Abstract
The application provides an aeroengine nozzle flow testing device and method, including: in the testing process, oil is pumped by a pump, the oil passes through a fuel filter group and a one-way valve, a throttle valve is slowly opened, and the oil reaches a tested product after passing through a mass flowmeter and a small-range mass flowmeter; continuously adjusting the throttle valve until the product pressure gauge indicates a specified test pressure value; when the reading of the target flowmeter is stable, the programmable logic control system reads instantaneous flow data; the target flowmeter is a small-range mass flowmeter or a mass flowmeter, and the target flowmeter is switched by a pneumatic switch valve; and closing the throttle valve, and quickly reducing the pressure value indicated by the product pressure gauge to the zero point to finish the test of a single tested product and replace the next tested product. The method has the advantages that large-range flow continuous adjustable testing is effectively carried out on the nozzle of the aero-engine, and the testing efficiency is effectively improved.
Description
Technical Field
The application relates to the technical test field of fuel oil injection systems of aerospace engines, in particular to a device and a method for testing nozzle flow of an aerospace engine.
Background
The fuel nozzle is one of a plurality of important parts of an aircraft engine, the oil supply quantity change range of some excellent fuel nozzles is wide, a constant pressure valve is designed on a secondary oil way of the fuel nozzle, the valve only plays the role of the constant pressure valve, and the flow characteristic of the valve is a small flow characteristic (the fuel flow is 6-50Kg/h magnitude). Under the condition that the oil supply pressure of an oil pump is limited, in order to meet the requirement of wide oil supply quantity of an engine, a throttle valve is arranged in front of a main oil way of a fuel nozzle to replace a fuel distribution valve on a fuel regulator, the areas of a plunger and a throttle groove (hole) which play a throttling role on the valve are increased along with the increase of the pressure difference of the valve, and the flow change range is wide under the condition that the pressure drop change range of the fuel nozzle is not large. In the flow regulator, a flow regulator is called as a throttle valve, the throttle valve has a characteristic called as a flow characteristic, namely, a certain flow is generated under a certain oil pressure, a tolerance range is given to the flow to serve as a detection standard for whether the throttle valve is qualified or not, the flow characteristic of the throttle valve is a high-flow characteristic (fuel flow is 50-430Kg/h magnitude), and the two flow characteristics of the throttle valve cause that many existing test devices are difficult to detect rapidly in batches due to the large flow range and the problems of continuous measurement and the like.
The existing flow rate test equipment, as shown in figure 1, comprises a pump, an overflow valve, a buffer, a throttle valve, a mass flowmeter, a pressure gauge, a workpiece to be tested, a reversing pipe, a container, an electronic scale, a switch valve, a timer, an oil tank and the like, because the precision of mass flow rate timing in small flow rate measurement is poor, and the stability and precision of instantaneous flow rate are not reliable, the accessories such as a right container, an electronic scale, a timer and the like are adopted, more fuel oil is collected in a longer time (5-10 min), and the flow rate is calculated by using the oil liquid collected in unit time.
It can be seen that the prior art feeds back the instantaneous mass flow by using an electronic scale to weigh the fuel mass in the container. The time is longer and the precision is low.
Disclosure of Invention
In view of this, the application provides a device and a method for testing the flow of an aircraft engine nozzle, which can effectively perform continuous adjustable testing on the flow of the aircraft engine nozzle in a large range and effectively improve the testing efficiency.
The application provides an aeroengine nozzle flow testing arrangement in a first aspect, includes:
the system comprises an oil tank, a pump, a fuel filter group, an overflow valve, a check valve, a throttle valve, a small-range mass flowmeter, a product pressure gauge, a system pressure gauge, a pneumatic switch valve and a programmable logic controller system; wherein the fuel filter bank comprises at least two fuel filters; the programmable logic controller system is used for acquiring data of the small-range mass flowmeter and the mass flowmeter, and displaying instantaneous mass flow, instantaneous volume flow and medium density of the small-range mass flowmeter and the mass flowmeter on an interface;
the oil tank, the pump, the fuel filter group, the check valve, the throttle valve, the mass flowmeter, the small-range mass flowmeter and a tested product are sequentially connected in series; the tested product is connected into the oil tank; one end of the overflow valve is connected between the one-way valve and the fuel filter group, and the other end of the overflow valve is connected to the fuel tank; the system pressure gauge is connected between the throttle valve and the one-way valve; the product pressure gauge is connected between the small-range mass flowmeter and the measured product; the two ends of the small-range mass flowmeter are connected with the pneumatic switch valve in parallel;
in the test process, oil is pumped by the pump, the oil passes through the fuel filter group and the check valve, the throttle valve is opened slowly, and the oil reaches the tested product after passing through the mass flow meter and the small-range mass flow meter;
continuously adjusting the throttle valve until the product pressure gauge indicates a specified test pressure value;
when the reading of the target flowmeter is stable, the programmable logic controller system reads instantaneous flow data; the target flowmeter is the small-range mass flowmeter or the mass flowmeter, and the flowmeter is switched through the pneumatic switch valve; the instantaneous flow data comprises instantaneous mass flow, instantaneous volume flow and medium density;
and closing the throttle valve, and quickly reducing the pressure value indicated by the product pressure gauge to the zero point to finish the test of a single tested product.
Optionally, the overflow valve performs pressure relief after a value indicated by a system pressure gauge is greater than a pressure relief threshold value.
Optionally, when the oil supply flow is less than or equal to 50Kg/h, the pneumatic switch valve is closed, the bypass flow is closed, and the programmable logic controller system reads the data of the small-range mass flowmeter; when the oil supply flow is larger than 50Kg/h, the pneumatic switch valve is opened, the bypass channel is opened, and the programmable logic controller system reads the data of the mass flow meter.
Optionally, the filtering precision of at least two fuel filters included in the fuel filter group is 10 μm and 5 μm, respectively, and the fuel filter group is configured with a differential pressure alarm; the pressure difference alarm continuously monitors the state of a filter element of the fuel filter and prompts the filter element to be cleaned or replaced when the pressure difference is larger than an allowable value.
Optionally, the oil tank includes: the liquid level meter, the thermal resistor, the oil cooling pipe and the oil drain valve; the liquid level meter is used for real-time monitoring of the liquid level of the oil tank, the thermal resistor is used for monitoring the temperature of a cold medium of the oil tank, and the oil tank cover is provided with an air filter for daily oil filling and atmosphere ventilation.
A second aspect of the present application provides an aircraft engine nozzle flow testing method, which is applied to the aircraft engine nozzle flow testing apparatus according to any one of the first aspect, and the aircraft engine nozzle flow testing method includes:
pumping oil through a pump, wherein the oil passes through a fuel oil filter group and then passes through a one-way valve; wherein the fuel filter bank comprises at least two fuel filters;
slowly opening a throttle valve, wherein the oil liquid passes through a mass flow meter and a small-range mass flow meter and then reaches a tested product;
continuously adjusting the throttle valve until the product pressure gauge indicates a specified test pressure value;
when the reading of the target flowmeter is stable, the programmable logic controller system reads instantaneous flow data; the target flowmeter is the small-range mass flowmeter or the mass flowmeter, and the flowmeters can be switched through the pneumatic switch valve; the instantaneous flow data comprises instantaneous mass flow, instantaneous volume flow and medium density;
and closing the throttle valve, and quickly reducing the pressure value indicated by the product pressure gauge to the zero point to finish the test of a single tested product.
Optionally, the overflow valve performs pressure relief after a value indicated by a system pressure gauge is greater than a pressure relief threshold value.
Optionally, when the oil supply flow is less than or equal to 50Kg/h, the pneumatic switch valve is closed, the bypass flow is closed, and the programmable logic controller system reads the data of the small-range mass flowmeter; when the oil supply flow is larger than 50Kg/h, the pneumatic switch valve is opened, the bypass channel is opened, and the programmable logic controller system reads the data of the mass flow meter.
Optionally, the filtering precision of at least two fuel filters included in the fuel filter group is 10 μm and 5 μm, respectively, and the fuel filter group is configured with a differential pressure alarm; the pressure difference alarm continuously monitors the state of a filter element of the fuel filter and prompts the filter element to be cleaned or replaced when the pressure difference is larger than an allowable value.
Optionally, the oil tank includes: the device comprises a liquid level meter, a thermal resistor, an oil cooling pipe and an oil discharge valve; the liquid level meter is used for real-time monitoring of the liquid level of the oil tank, the thermal resistor is used for monitoring the temperature of a cold medium of the oil tank, and the oil tank cover is provided with an air filter for daily oil filling and atmosphere ventilation.
According to the scheme, the application provides an aeroengine nozzle flow testing device and method, and the aeroengine nozzle flow testing device comprises: the system comprises an oil tank, a pump, a fuel filter group, an overflow valve, a one-way valve, a throttle valve, a small-range mass flowmeter, a product pressure gauge, a system pressure gauge, a pneumatic switch valve and a programmable logic controller system; wherein the fuel filter bank comprises at least two fuel filters; the programmable logic controller system is used for acquiring data of the small-range mass flowmeter and the mass flowmeter, and displaying instantaneous mass flow, instantaneous volume flow and medium density of the small-range mass flowmeter and the mass flowmeter on an interface; the oil tank, the pump, the fuel filter group, the check valve, the throttle valve, the mass flowmeter, the small-range mass flowmeter and a tested product are sequentially connected in series; the tested product is connected into the oil tank; one end of the overflow valve is connected between the one-way valve and the fuel filter group, and the other end of the overflow valve is connected with the fuel tank; the system pressure gauge is connected between the throttling valve and the one-way valve; the product pressure gauge is connected between the small-range mass flowmeter and the product to be measured; the two ends of the small-range mass flowmeter are connected with the pneumatic switch valve in parallel; in the testing process, oil is pumped by the pump, the oil passes through the fuel oil filter group and the check valve, the throttle valve is opened slowly, and the oil reaches the tested product after passing through the mass flowmeter and the small-range mass flowmeter; then, continuously adjusting the throttle valve until the product pressure gauge indicates a specified test pressure value; when the reading of the target flowmeter is stable, the programmable logic controller system reads instantaneous flow data; the target flowmeter is the small-range mass flowmeter or the mass flowmeter, and the flowmeter is switched through the pneumatic switch valve; the instantaneous flow data comprises instantaneous mass flow, instantaneous volume flow and medium density; and finally, closing the throttle valve, and quickly reducing the pressure value indicated by the product pressure gauge to zero to complete the test of a single tested product and replace the next tested product. Therefore, the large-range flow continuous adjustable test is effectively carried out on the nozzle of the aero-engine, and the test efficiency is effectively improved.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, it is obvious that the drawings in the following description are only embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic diagram of a prior art flow test apparatus;
FIG. 2 is a schematic diagram of an aircraft engine nozzle flow testing device provided by an embodiment of the application;
FIG. 3 is a schematic diagram of a flow meter data interface provided by an embodiment of the present application;
FIG. 4 is a schematic diagram of a small-scale mass flow meter, a mass flow meter and a pneumatic on-off valve provided by an embodiment of the application;
fig. 5 is a specific flowchart of a method for testing the flow rate of an aircraft engine nozzle according to an embodiment of the present disclosure.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The term "include" and variations thereof as used herein are open-ended, i.e., "including but not limited to". The term "based on" is "based, at least in part, on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions for other terms will be given in the following description.
It should be noted that the terms "first", "second", and the like in the present application are only used for distinguishing different devices, modules or units, and are not used for limiting the order or interdependence relationship of the functions performed by the devices, modules or units.
It is noted that references to "a", "an", and "the" modifications in this application are intended to be illustrative rather than limiting, and that those skilled in the art will recognize that reference to "one or more" unless the context clearly dictates otherwise.
The existing flow rate test equipment, as shown in figure 1, comprises a pump, an overflow valve, a buffer, a throttle valve, a mass flowmeter, a pressure gauge, a workpiece to be tested, a reversing pipe, a container, an electronic scale, a switch valve, a timer, an oil tank and the like, because the precision of mass flow rate timing in small flow rate measurement is poor, and the stability and precision of instantaneous flow rate are not reliable, the accessories such as a right container, an electronic scale, a timer and the like are adopted, more fuel oil is collected in a longer time (5-10 min), and the flow rate is calculated by using the oil liquid collected in unit time.
The prior art feeds back the instantaneous mass flow by weighing the fuel mass in the container using an electronic scale. The time is long and the precision is low.
Moreover, for products produced in batches, the testing time of a single product is too long, the batch rapid production is restricted, and the efficiency is low.
Based on the above disadvantages in the prior art, an embodiment of the present application provides an aircraft engine nozzle flow rate testing device, as shown in fig. 2, including:
a fuel tank 10, a pump 20, a fuel filter bank 30, an overflow valve 40, a check valve 50, a throttle valve 60, a small range mass flow meter 70, a mass flow meter 80, a product pressure gauge 90, a system pressure gauge 100, a pneumatic on-off valve 110, and a programmable logic controller system 120.
Wherein the fuel filter group 30 comprises at least two fuel filters (two fuel filters are shown in fig. 2, a fuel filter 31 and a fuel filter 32); a Programmable Logic Controller (PLC) system 120 is used to collect data of the small-scale mass flow meter 70 and the mass flow meter 80, and the interface displays the instantaneous mass flow, the instantaneous volume flow and the medium density of the small-scale mass flow meter 70 (in the figure, the mass flow meter # 1 or the mass flow meter # 2) and the mass flow meter 80 (in the figure, the mass flow meter # 1 or the mass flow meter # 2), as shown in fig. 3.
Wherein, the oil tank 10, the pump 20, the fuel filter group 30, the one-way valve 50, the throttle valve 60, the mass flowmeter 80, the small-range mass flowmeter 70 and the tested product are connected in series in sequence; the tested product is connected into the oil tank 10; one end of the relief valve 40 is connected between the check valve 50 and the fuel filter group 30, and the other end is connected to the fuel tank 10; a system pressure gauge 100 is connected between the throttle valve 60 and the check valve 50; the product pressure gauge 90 is connected between the small-range mass flowmeter 70 and the product to be measured; the pneumatic switch valve 110 is connected in parallel at two ends of the small-range mass flowmeter 70, and the connection relationship of the small-range mass flowmeter 70, the mass flowmeter 80 and the pneumatic switch valve 110 is shown in fig. 4.
Optionally, in a specific implementation process of the present application, an embodiment of the fuel filter group 30 includes:
the filtration precision of at least two fuel filters included in the fuel filter group 30 is respectively 10 μm and 5 μm, and the fuel filter group 30 is provided with a differential pressure alarm; the pressure difference alarm continuously monitors the state of a filter element of the fuel filter and prompts the filter element to be cleaned or replaced when the pressure difference is larger than an allowable value.
Optionally, in a specific implementation of the present application, an embodiment of the fuel tank 10 includes:
the oil tank 10 includes: a liquid level meter, a thermal resistor, an oil cooling pipe (an oil cooling machine is provided by Party A) and an oil discharge valve. The liquid level meter is used for monitoring the liquid level of the oil tank 10 in real time, the thermal resistor is used for monitoring the temperature of a cold medium of the oil tank 10, and the air filter is arranged on the cover of the oil tank 10 and used for daily oil filling and atmosphere ventilation. The fuel tank 10 can be made of, but not limited to, 304 stainless steel plate, which is not limited herein.
The pump 20 pressurizes and conveys the fuel in the fuel supply tank 10, a Italian Samum plunger pump group can be selected and not limited to provide 1000L/H fuel flow and 0-10 MPa fuel pressure, the fuel supply capacity is larger than the test requirement, and an oil absorption filter with the filtering precision of 40 mu m is arranged in front of the pump 20 and used for reducing the abrasion of the plunger pump.
It should be noted that, in the implementation process of the present application, the relief valve 40 functions as: after the oil is pressurized by the pump 20, the oil pressure in the pipeline is monitored in the process of flowing through the overflow valve 40, and if the oil pressure in the pipeline exceeds the unloading pressure, the pressure relief opening of the overflow valve 40 is opened to release the oil into the oil tank 10, so that the pump 20 and downstream accessories are protected, and high-pressure damage is prevented.
The relief valve 40 may be set to, but not limited to, a cracking pressure of 6.9MPa, which is not limited herein.
The working process of the aircraft engine nozzle flow testing device in the application is as follows:
(1) During the test, oil is pumped by the pump 20, passes through the fuel filter group 30, passes through the check valve 50, slowly opens the throttle valve 60, and reaches the product to be tested after passing through the mass flow meter 80 and the small-range mass flow meter 70.
(2) Throttle valve 60 is continuously adjusted until product pressure gauge 90 indicates a prescribed test pressure value.
(3) The programmable logic controller system 120 reads the instantaneous flow data when the target flow meter reading is stable.
The target flowmeter is a small-range mass flowmeter 70 or a mass flowmeter 80, and the flow meters are switched by a pneumatic switch valve 110. The instantaneous flow data includes instantaneous mass flow, instantaneous volume flow, and media density.
Specifically, when the oil supply flow is less than or equal to 50Kg/h, the pneumatic switch valve 110 is closed, the bypass flow is closed, and the programmable logic controller system 120 reads the data of the small-range mass flow meter 70; when the oil supply flow is larger than 50Kg/h, the pneumatic switch valve 110 is opened, the bypass channel is opened, and the programmable logic controller system 120 reads the data of the mass flow meter 80. The range of data of the mass flow meter 80 is greater than the range of the small-range mass flow meter 70.
(4) And (4) closing the throttle valve 60, and quickly reducing the pressure value indicated by the product pressure gauge 90 to the zero point to finish the test of a single tested product.
It can be seen that the system of the present application is based on the existing equipment (see fig. 1), and components such as 'reversing pipe, container, electronic scale, switch valve, timer' and the like are removed, and a pneumatic switch valve 110 (see fig. 2) is added; it can be seen from the above test process that before the tested product is tested, the pump 20 is turned on, the pump 20 pressurizes and conveys the fuel in the fuel tank 10 (a plunger pump set of Samum Italy can be selected to provide 1000L/H fuel flow and 0-10 MPa fuel pressure), so that the fuel supply capacity is greater than the test requirement, and an oil absorption filter with the filtering precision of 40 μm is arranged in front of the pump 20 to reduce the abrasion of the plunger pump. An ideal test environment is provided for the accurate measurement of the flowmeter (the small-range mass flowmeter 70 or the mass flowmeter 80), the flowmeter accuracy is stably displayed, and the flow data accuracy and the stability of repeated tests meet the requirements after detection.
The acquisition of flowmeter data is instantaneous flow, and it is higher to show speed and efficiency of software testing, and current equipment singleton test procedure is about 10 minutes from pressure regulating, fluid collection, weighing, reading, when calculating etc. the time spent, and the operation process is numerous and diverse, and this application test singleton product time spent is about 1 minute, and this application efficiency of software testing is high.
According to the scheme, the application provides an aeroengine nozzle flow testing device, which comprises: the system comprises a fuel tank 10, a pump 20, a fuel filter group 30, an overflow valve 40, a one-way valve 50, a throttle valve 60, a small-range mass flowmeter 70, a mass flowmeter 80, a product pressure gauge 90, a system pressure gauge 100, a pneumatic switch valve 110 and a programmable logic controller system 120; wherein the fuel filter group 30 includes at least two fuel filters; the programmable logic controller system 120 is used for acquiring data of the small-scale mass flowmeter 70 and the mass flowmeter 80, and the interface displays the instantaneous mass flow, the instantaneous volume flow and the medium density of the small-scale mass flowmeter 70 and the mass flowmeter 80; wherein, the oil tank 10, the pump 20, the fuel filter group 30, the one-way valve 50, the throttle valve 60, the mass flowmeter 80, the small-range mass flowmeter 70 and the tested product are connected in series in sequence; the tested product is connected into the oil tank 10; one end of the overflow valve 40 is connected between the check valve 50 and the fuel filter group 30, and the other end is connected to the fuel tank 10; the system pressure gauge 100 is connected between the throttle valve 60 and the check valve 50; the product pressure gauge 90 is connected between the small-range mass flowmeter 70 and the product to be measured; the two ends of the small-range mass flowmeter 70 are connected with the pneumatic switch valve 110 in parallel; in the test process, oil is pumped by a pump 20, the oil passes through a fuel filter group 30, passes through a one-way valve 50, slowly opens a throttle valve 60, and reaches a tested product after passing through a mass flowmeter 80 and a small-range mass flowmeter 70; then, the throttle valve 60 is continuously adjusted until the product pressure gauge 90 indicates a prescribed test pressure value; when the target flow meter reading is stable, the programmable logic controller system 120 reads the instantaneous flow data; the target flowmeter is a small-range mass flowmeter 70 or a mass flowmeter 80, and the flowmeters are switched through a pneumatic switch valve 110; the instantaneous flow data comprises instantaneous mass flow, instantaneous volume flow and medium density; and finally, closing the throttle valve 60, and quickly reducing the pressure value indicated by the product pressure gauge 90 to zero to complete the test of a single tested product and replace the next tested product. Therefore, large-range flow continuous adjustable testing can be effectively carried out on the nozzle of the aero-engine, and the testing efficiency is effectively improved.
The aero-engine nozzle flow testing method provided by the embodiment of the application is applied to the aero-engine nozzle flow testing device according to any one of the embodiments, and as shown in fig. 5, the method includes:
s501, oil is pumped through the pump 20, passes through the fuel filter group 30 and then passes through the one-way valve 50.
Wherein the fuel filter group 30 comprises at least two fuel filters.
S502, slowly opening the throttle valve 60, and enabling the oil to reach a tested product after passing through the mass flow meter 80 and the small-range mass flow meter 70.
S503, continuing to adjust the throttle valve 60 until the product pressure gauge 90 indicates a prescribed test pressure value.
And S504, when the reading of the target flowmeter is stable, the programmable logic controller system 120 reads the instantaneous flow data.
The target flowmeter is a small-range mass flowmeter 70 or a mass flowmeter 80, and the flowmeter can be switched by a pneumatic switching valve 110. The instantaneous flow data includes instantaneous mass flow, instantaneous volume flow, and media density.
Specifically, when the oil supply flow is less than or equal to 50Kg/h, the pneumatic switch valve 110 is closed, the bypass flow is closed, and the programmable logic controller system 120 reads the data of the small-range mass flowmeter 70; when the oil supply flow is more than 50Kg/h, the pneumatic switch valve 110 is opened, the bypass channel is opened, and the programmable logic controller system 120 reads the data of the mass flow meter 80.
And S505, closing the throttle valve 60, and quickly reducing the pressure value indicated by the product pressure gauge 90 to a zero point to finish the test of a single tested product.
Optionally, in a specific implementation process of the present application, an embodiment of the fuel filter group 30 includes:
the filtration precision of at least two fuel filters included in the fuel filter group 30 is respectively 10 μm and 5 μm, and the fuel filter group 30 is provided with a differential pressure alarm; the pressure difference alarm continuously monitors the state of a filter element of the fuel filter and prompts the filter element to be cleaned or replaced when the pressure difference is larger than an allowable value.
Optionally, in a specific implementation of the present application, an embodiment of the fuel tank 10 includes:
the oil tank 10 includes: a liquid level meter, a thermal resistor, an oil cooling pipe (an oil cooling machine is provided by Party A) and an oil discharge valve. The liquid level meter is used for monitoring the liquid level of the oil tank 10 in real time, the thermal resistor is used for monitoring the temperature of a cold medium of the oil tank 10, and the air filter is arranged on the cover of the oil tank 10 and used for daily oil filling and atmosphere ventilation. The fuel tank 10 can be made of, but not limited to, 304 stainless steel plate, which is not limited herein.
The pump 20 pressurizes and conveys the fuel in the fuel supply tank 10, a Italian Samum plunger pump group can be selected and not limited to provide 1000L/H fuel flow and 0-10 MPa fuel pressure, the fuel supply capacity is larger than the test requirement, and an oil absorption filter with the filtering precision of 40 mu m is arranged in front of the pump 20 and used for reducing the abrasion of the plunger pump.
It should be noted that, in the implementation process of the present application, the relief valve 40 functions as: after the oil is pressurized by the pump 20, the oil pressure in the pipeline is monitored in the process of flowing through the overflow valve 40, and if the oil pressure in the pipeline exceeds the unloading pressure, the pressure relief opening of the overflow valve 40 is opened to release the oil into the oil tank 10, so that the pump 20 and downstream accessories are protected, and high-pressure damage is prevented.
The relief valve 40 may be set to, but not limited to, a cracking pressure of 6.9MPa, which is not limited herein.
It can be seen that the system of the present application is based on the existing equipment (see fig. 1), and components such as 'reversing pipe, container, electronic scale, switch valve, timer' and the like are removed, and a pneumatic switch valve 110 (see fig. 2) is added; it can be seen from the above test process that before the tested product is tested, the pump 20 is turned on, the pump 20 pressurizes and conveys the fuel in the fuel tank 10 (a plunger pump set of Samum Italy can be selected to provide 1000L/H fuel flow and 0-10 MPa fuel pressure), so that the fuel supply capacity is greater than the test requirement, and an oil absorption filter with the filtering precision of 40 μm is arranged in front of the pump 20 to reduce the abrasion of the plunger pump. An ideal test environment is provided for the accurate measurement of the flowmeter (the small-range mass flowmeter 70 or the mass flowmeter 80), the flowmeter accuracy is stably displayed, and the flow data accuracy and the stability of repeated tests meet the requirements after detection.
The collection of flowmeter data is instantaneous flow, and it is higher to show speed and efficiency of software testing, and current equipment singlepiece test process is about 10 minutes from pressure regulating, fluid collection, weighing, reading, time spent such as calculation, and the operation process is miscellaneous, and this application test singlepiece product time spent is about 1 minute, and this application efficiency of software testing is high.
According to the scheme, the application provides an aircraft engine nozzle flow testing method, which is applied to the aircraft engine nozzle flow testing device in the embodiment, and the aircraft engine nozzle flow testing method comprises the following steps: in the test process, oil is pumped by the pump 20, passes through the fuel filter group 30, passes through the one-way valve 50, slowly opens the throttle valve 60, and reaches a tested product after passing through the mass flowmeter 80 and the small-range mass flowmeter 70; then, the throttle valve 60 is continuously adjusted until the product pressure gauge 90 indicates a prescribed test pressure value; when the target flow meter reading is stable, the programmable logic controller system 120 reads the instantaneous flow data; the target flowmeter is a small-range mass flowmeter 70 or a mass flowmeter 80, and the flowmeters are switched through a pneumatic switch valve 110; the instantaneous flow data comprises instantaneous mass flow, instantaneous volume flow and medium density; and finally, closing the throttle valve 60, quickly reducing the pressure value indicated by the product pressure gauge 90 to the zero point, completing the test of a single tested product, and replacing the next tested product. Therefore, large-range flow continuous adjustable testing can be effectively carried out on the nozzle of the aero-engine, and the testing efficiency is effectively improved.
In the above embodiments disclosed in the present application, it should be understood that the disclosed apparatus and method may be implemented in other ways. The apparatus and method embodiments described above are illustrative only, as the flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods and computer program products according to various embodiments of the present disclosure. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
In addition, functional modules in the embodiments of the present disclosure may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part. The functions, if implemented in the form of software functional modules and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present disclosure may be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a live broadcast device, or a network device) to execute all or part of the steps of the method according to the embodiments of the present disclosure. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
Those skilled in the art can make or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. An aircraft engine nozzle flow testing device, characterized by, includes:
the system comprises an oil tank (10), a pump (20), a fuel filter group (30), an overflow valve (40), a one-way valve (50), a throttle valve (60), a small-range mass flowmeter (70), a mass flowmeter (80), a product pressure gauge (90), a system pressure gauge (100), a pneumatic switch valve (110) and a programmable logic controller system (120); wherein the fuel filter group (30) comprises at least two fuel filters; the programmable logic controller system (120) is used for collecting data of the small-scale mass flowmeter (70) and the mass flowmeter (80), and the interface displays the instantaneous mass flow, the instantaneous volume flow and the medium density of the small-scale mass flowmeter (70) and the mass flowmeter (80);
wherein the oil tank (10), the pump (20), the fuel filter group (30), the one-way valve (50), the throttle valve (60), the mass flow meter (80), the small-range mass flow meter (70) and a product to be tested are connected in series in sequence; the tested product is accessed into the oil tank (10); one end of the overflow valve (40) is connected between the check valve (50) and the fuel filter group (30), and the other end of the overflow valve is connected to the fuel tank (10); the system pressure gauge (100) is connected between the throttle valve (60) and the one-way valve (50); the product pressure gauge (90) is connected between the small-range mass flowmeter (70) and the product to be measured; the two ends of the small-range mass flowmeter (70) are connected with the pneumatic switch valve (110) in parallel;
during the test, oil is pumped by the pump (20), the oil passes through the fuel filter group (30) and the check valve (50), the throttle valve (60) is opened slowly, and the oil reaches the tested product after passing through the mass flow meter (80) and the small-range mass flow meter (70);
continuously adjusting the throttle valve (60) until the product pressure gauge (90) indicates a prescribed test pressure value;
when the reading of the target flowmeter is stable, the programmable logic controller system (120) reads instantaneous flow data; wherein the target flowmeter is the small-range mass flowmeter (70) or the mass flowmeter (80), and the flowmeter is switched through the pneumatic switch valve (110); the instantaneous flow data comprises instantaneous mass flow, instantaneous volume flow and medium density;
and closing the throttle valve (60), and quickly reducing the pressure value indicated by the product pressure gauge (90) to zero to finish the test of a single tested product.
2. The aircraft engine nozzle flow testing device of claim 1, wherein the relief valve (40) is relieved after a value indicated by a system pressure gauge (100) is greater than a relief threshold.
3. The aircraft engine nozzle flow testing device according to claim 1, characterized in that when the oil supply flow is less than or equal to 50Kg/h, the pneumatic switch valve (110) is closed, the bypass flow is closed, and the programmable logic controller system (120) reads the data of the small-scale mass flowmeter (70); when the oil supply flow is larger than 50Kg/h flow, the pneumatic switch valve (110) is opened, the bypass channel is opened, and the programmable logic controller system (120) reads the data of the mass flow meter (80).
4. The aircraft engine nozzle flow testing device according to claim 1, characterized in that the fuel filter group (30) comprises at least two fuel filters with filtering precision of 10 μm and 5 μm respectively, and the fuel filter group (30) is provided with a differential pressure alarm; the pressure difference alarm continuously monitors the state of a filter element of the fuel filter and prompts the filter element to be cleaned or replaced when the pressure difference is larger than an allowable value.
5. The aircraft engine nozzle flow testing device of claim 1, wherein the fuel tank (10) comprises: the device comprises a liquid level meter, a thermal resistor, an oil cooling pipe and an oil discharge valve; the liquid level meter is used for real-time monitoring of the liquid level of the oil tank (10), the thermal resistor is used for monitoring the temperature of a cold medium of the oil tank (10), and the oil tank (10) is covered with an air filter for daily oiling and atmosphere ventilation.
6. An aircraft engine nozzle flow testing method, which is applied to the aircraft engine nozzle flow testing device according to any one of claims 1 to 5, the aircraft engine nozzle flow testing method comprising:
pumping oil through a pump (20), wherein the oil passes through a fuel filter group (30) and then passes through a one-way valve (50); wherein the fuel filter group (30) comprises at least two fuel filters;
slowly opening a throttle valve (60), and enabling the oil liquid to reach a tested product after passing through a mass flow meter (80) and a small-range mass flow meter (70);
continuously adjusting the throttle valve (60) until a product pressure gauge (90) indicates a prescribed test pressure value;
when the reading of the target flowmeter is stable, the programmable logic controller system (120) reads instantaneous flow data; wherein the target flowmeter is the small-scale mass flowmeter (70) or the mass flowmeter (80), and the flowmeter can be switched through the pneumatic switch valve (110); the instantaneous flow data comprises instantaneous mass flow, instantaneous volume flow and medium density;
and closing the throttle valve (60), and quickly reducing the pressure value indicated by the product pressure gauge (90) to zero to finish the test of a single tested product.
7. The aircraft engine nozzle flow testing method of claim 6, wherein the relief valve (40) is depressurized after a value indicated by a system pressure gauge (100) is greater than a depressurization threshold value.
8. The aircraft engine nozzle flow testing method according to claim 6, characterized in that when the oil supply flow is less than or equal to 50Kg/h, the pneumatic switch valve (110) is closed, the bypass flow is closed, and the programmable logic controller system (120) reads the data of the small-scale mass flow meter (70); when the oil supply flow is larger than 50Kg/h flow, the pneumatic switch valve (110) is opened, the bypass channel is opened, and the programmable logic controller system (120) reads the data of the mass flow meter (80).
9. The aircraft engine nozzle flow testing method according to claim 6, characterized in that the filtration precision of at least two fuel filters comprised by the fuel filter group (30) is 10 μm and 5 μm respectively, and the fuel filter group (30) is provided with a differential pressure alarm; the pressure difference alarm continuously monitors the state of a filter element of the fuel filter and prompts the filter element to be cleaned or replaced when the pressure difference is larger than an allowable value.
10. The aircraft engine nozzle flow test method according to claim 6, characterized in that the fuel tank (10) comprises: the liquid level meter, the thermal resistor, the oil cooling pipe and the oil drain valve; the liquid level meter is used for real-time monitoring of the liquid level of the oil tank (10), the thermal resistor is used for monitoring the temperature of a cold medium of the oil tank (10), and the air filter is arranged on the cover of the oil tank (10) and used for daily oil filling and atmosphere ventilation.
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| CN202310232754.9A CN115900861A (en) | 2023-03-13 | 2023-03-13 | Aero-engine nozzle flow testing device and method |
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| CN202310232754.9A CN115900861A (en) | 2023-03-13 | 2023-03-13 | Aero-engine nozzle flow testing device and method |
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