CN115030891A - Test platform and test method for fuel pump of aircraft engine - Google Patents
Test platform and test method for fuel pump of aircraft engine Download PDFInfo
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- CN115030891A CN115030891A CN202210941033.0A CN202210941033A CN115030891A CN 115030891 A CN115030891 A CN 115030891A CN 202210941033 A CN202210941033 A CN 202210941033A CN 115030891 A CN115030891 A CN 115030891A
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- oil tank
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B51/00—Testing machines, pumps, or pumping installations
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
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- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a test platform and a test method for an aircraft engine fuel pump, wherein the test platform comprises: the system comprises a combined working oil tank, a temperature control system, an inert gas supply system, an explosion-proof detection and collection system, a comprehensive test system and a computer master control system: the combined working oil tank is internally provided with a test medium; the temperature control system is connected with the combined working oil tank and is used for controlling the temperature of the test medium; and the inert gas supply system is connected with the combined working oil tank and is used for injecting inert gas into the combined working oil tank to replace air in the combined working oil tank. Through the operation of the test platform for testing the fuel pump of the aircraft engine provided by the embodiment of the invention, relevant data are collected, and normal-temperature and high-temperature multipoint performance tests of the fuel pump are carried out. The comprehensive test capability is strong, the temperature test range is wide, the manufacturing cost is low, the processing and the manufacturing are easy, the maintenance is convenient, and the use is convenient and fast.
Description
Technical Field
The invention relates to the technical field of aircraft engines, in particular to a platform and a method for testing an aircraft engine fuel pump.
Background
In the field of aerospace, particularly in the field of fuel pumps of aero-engines, a large number of products need to be detected quickly, and a large number of structures and test projects need to be detected; the general detection requirements are that online real-time detection is needed, and test data needs to be obtained in real time.
With the development of science and technology, the requirement of real-time detection is more and more. For the technical field of aircraft engine fuel pumps, in order to meet the technical standard and the test requirement of the test, a set of aircraft engine fuel pump test platform which can be controlled at high precision, is low in manufacturing cost, uses various test media, is large in test temperature range, is easy to machine and manufacture and is convenient to maintain and use needs to be designed.
Disclosure of Invention
In order to solve the above problems, embodiments of the present invention provide a platform and a method for testing an aircraft engine fuel pump.
In a first aspect, an embodiment of the present invention provides an aircraft engine fuel pump test platform, which includes a combined working oil tank, a temperature control system, an inert gas supply system, an explosion-proof detection collection system, a comprehensive test system, and a computer general control system:
the combined working oil tank is internally provided with a test medium;
the temperature control system is connected with the combined working oil tank and is used for controlling the temperature of the test medium;
the inert gas supply system is connected with the combined working oil tank and is used for injecting inert gas into the combined working oil tank to replace air in the combined working oil tank;
the explosion-proof detection collecting system is connected with the combined working oil tank and is used for collecting oil gas discharged by the combined working oil tank;
the comprehensive test system is connected with the combined working oil tank and is used for detecting the thermal comprehensive performance of the fuel pump of the aircraft engine;
and the computer master control system is respectively connected with the temperature control system, the inert gas supply system, the explosion-proof detection collecting system and the comprehensive test system and is used for acquiring detection data and acquiring thermal state comprehensive performance parameters of the fuel pump of the aircraft engine.
In a second aspect, an embodiment of the invention further provides an aircraft engine fuel pump test method, and the test method is used for testing the thermal state comprehensive performance of the fuel pump by using the aircraft engine fuel pump test platform.
According to the test platform and the test method for the fuel pump of the aircraft engine, the operation of the test platform for the fuel pump of the aircraft engine is controlled, relevant data are collected, and normal-temperature and high-temperature multipoint performance tests of the fuel pump are carried out; testing the starting characteristic of the fuel pump; efficiency, flow and temperature relation tests and liquid level tests. The comprehensive test capability is strong, the temperature test range is wide, the manufacturing cost is low, the processing and the manufacturing are easy, the maintenance is convenient, and the use is convenient and fast.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural diagram illustrating an aircraft engine fuel pump test platform provided by an embodiment of the invention;
FIG. 2 is a flow chart illustrating a specific method for testing the normal/high temperature multi-point flow performance of a fuel pump in the test method for testing the fuel pump of the aircraft engine according to the embodiment of the invention;
FIG. 3 is a flow chart illustrating a specific method for testing the starting characteristic of the fuel pump in the test method for testing the fuel pump of the aircraft engine provided by the embodiment of the invention;
FIG. 4 is a flow chart illustrating a specific method for testing the relationship between fuel pump efficiency, flow and temperature in the test method for testing the fuel pump of the aircraft engine provided by the embodiment of the invention;
FIG. 5 is a flow chart illustrating a specific method for testing the liquid level of the fuel pump in the test method for testing the fuel pump of the aircraft engine provided by the embodiment of the invention.
Reference numerals are as follows:
1-a combined working oil tank;
11-a first oil inlet pipe; 12-a first drain pipe; 13-a first inlet valve; 14-a first drain valve;
2-a temperature control system;
21-a first intelligent controller; 22-first heat exchange fins; 23-heating oil tank; 24-an oil pump; 25-an electric motor; 26-a first micron filter; 27-a first pressure gauge; 28-a second pressure gauge; 29-a first one-way valve; 210-a safety overflow valve; 211-a first safety protection explosion protection device; 212-first thermometer; 213-a first level density meter; 214-a heating device; 215-second heat exchange fins; 216-an air-conditioning refrigeration unit; 217-a second oil inlet pipe; 218-a second oil drain pipe; 219-a second oil inlet valve; 220-a second oil drain valve;
3-an inert gas supply system;
31-a second intelligent controller; 32-a first inert gas source; 33-a first temperature regulator; 34-a first pressure regulator; 35-a third pressure gauge;
4-an explosion-proof detection collection system;
41-a third intelligent controller; 42-an oil gas cooler; 43-oxygen content sensor; 44-an oil collecting tank; 45-exhaust pipe; 46-a combustible gas sensor; 47-an electrically controlled valve;
5-a comprehensive test system;
51-a fourth intelligent controller; 52-testing the fuel pump; 53-combined pressure regulating valve; 54-a second micron filter; 55-a fourth pressure gauge; 56-first flow meter; 57-a second one-way valve; 58-simulated combustion oil collecting tank; 59-consumption stop valve; 510-a second flow meter; 511-a second safety protection explosion-proof device; 512-second thermometer; 513-a second liquid level densitometer; 514-a third level density meter; 515-a third thermometer; 516-a third safety protection explosion-proof device; 517-a second inert gas source; 518-a second temperature regulator; 519-a second pressure regulator; 520-a fifth pressure gauge; 521-a pressure reducing valve; 522 — a first precision pneumatic valve; 523-proportional control valve; 524 — a second precision pneumatic valve;
6-computer general control system.
Detailed Description
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Fig. 1 shows a schematic structural diagram of a test platform for fuel pumps of aircraft engines, as shown in fig. 1, the test platform comprises a combined working fuel tank 1, a temperature control system 2, an inert gas supply system 3, an explosion-proof detection collection system 4, a comprehensive test system 5 and a computer general control system 6:
the combined working oil tank 1 is internally provided with a test medium;
the temperature control system 2 is connected with the combined working oil tank 1 and is used for controlling the temperature of the test medium;
the inert gas supply system 3 is connected with the combined working oil tank 1 and is used for injecting inert gas into the combined working oil tank 1 to replace air in the combined working oil tank 1;
the explosion-proof detection collecting system 4 is connected with the combined working oil tank 1 and is used for collecting oil gas in air discharged by the combined working oil tank 1;
the comprehensive test system 5 is connected with the combined working oil tank 1 and is used for detecting the thermal comprehensive performance of the fuel pump of the aircraft engine;
and the computer master control system 6 is respectively connected with the temperature control system 2, the inert gas supply system 3, the explosion-proof detection collecting system 4 and the comprehensive test system 5 and is used for acquiring detection data and acquiring thermal state comprehensive performance parameters of the fuel pump of the aircraft engine.
In the embodiment of the invention, the fuel pump of the aircraft engine to be tested is arranged in the combined working fuel tank 1, and the temperature of the test medium in the combined working fuel tank 1 is controlled by the temperature control system 2 so as to simulate the operating environment of the fuel pump. Various data in the operation process of the fuel pump are detected through the comprehensive test system 5 and sent to the computer master control system 6, and the computer master control system 6 obtains thermal state comprehensive performance parameters of the fuel pump through calculation according to the obtained detection data.
In the test process, the computer master control system 6 controls the inert gas supply system 3 to inject inert gas into the combined working oil tank 1 to replace air in the combined working oil tank 1, so that the safety of the combined working oil tank 1 is ensured. The air exhausted from the combined working oil tank 1 enters the explosion-proof detection collecting system 4 for treatment, so that explosion or environmental pollution is avoided.
In the embodiment of the present invention, as shown in fig. 1, a combined working oil tank 1 is respectively connected to a first oil inlet pipe 11 and a first oil drain pipe 12, the first oil inlet pipe 11 is provided with a first oil inlet valve 13, and the first oil drain pipe 12 is provided with a first oil drain valve 14; the test medium arranged in the combined working oil tank 1 comprises one of gasoline, kerosene, diesel oil, engine oil or lubricating oil.
In the embodiment of the invention, the test medium in the combined working oil tank 1 can be conveniently replaced through the first oil inlet pipe 11 and the first oil discharge pipe 12. Gasoline, kerosene, diesel oil, engine oil or lubricating oil can be used as test media, the distillation range or boiling point of each oil liquid is different, and the test media with corresponding distillation ranges or boiling points can be selected according to test requirements, so that the application range of the test is greatly enlarged.
In the embodiment of the present invention, as shown in fig. 1, the temperature control system 2 includes:
the first intelligent controller 21 is connected with the computer master control system 6;
heat exchange fins including a first heat exchange fin 22 and a second heat exchange fin 215, which are disposed in the assembled working oil tank 1;
a heating oil tank 23 connected with an input end of a first heat exchange fin 22 through an oil pump 24, the oil pump 24 is connected with a motor 25, an output end of the first heat exchange fin 22 is connected to the heating oil tank 23, a first micron filter 26 is arranged between the oil pump 24 and the heating oil tank 23, a first pressure gauge 27 is further arranged between the oil pump 24 and the first micron filter 26, a second pressure gauge 28 is arranged between the oil pump 24 and the first heat exchange fin 22, the oil pump 24 and the first heat exchange fin 22 are connected to the heating oil tank 23 through a first check valve 29 and a safety overflow valve 210, the heating oil tank 23 is respectively connected with a first safety protection explosion-proof device 211, a first temperature gauge 212 and a first liquid level density meter 213, the motor 25, the first pressure gauge 27, the second pressure gauge 28, the safety overflow valve 210, the first safety protection explosion-proof device 211, the first temperature gauge 212 and the first liquid level density meter 213 are all connected with a first intelligent controller 21, the output end of the inert gas supply system 3 is connected to the heating oil tank 23, and the top of the heating oil tank 23 is connected to the explosion-proof detection and collection system 4;
a heating device 214 provided in the heating oil tank 23;
the air conditioning/cooling device 216 is connected to the second heat exchange fin 215.
In the embodiment of the present invention, the heating device 214 may adopt an electric heating pipe to heat the oil in the heating oil tank 23, the oil heated by the oil pump 24 is pumped into the first heat exchanging fin 22, and the oil is heated by the first heat exchanging fin 22 at the set temperature rising rate v t And heating the test medium in the combined working oil tank 1. After the test is finished, the air conditioner is usedThe refrigerating device 216 cooperates with the second heat exchange fin 215 to cool the test medium in the combined working oil tank 1, so as to prepare for the next test that the test medium is rapidly put into.
The safety of the heating oil tank 23 is ensured by the cooperation of the inert gas supply system 3 and the explosion-proof detection collection system 4.
In the embodiment of the present invention, as shown in fig. 1, the heating oil tank 23 is connected to a second oil inlet pipe 217 and a second oil outlet pipe 218, respectively, a second oil inlet valve 219 is disposed on the second oil inlet pipe 217, and a second oil outlet valve 220 is disposed on the second oil outlet pipe 218. The oil in the heating oil tank 23 can be conveniently replaced through the second oil inlet pipe 217 and the second oil outlet pipe 218.
In the embodiment of the present invention, as shown in fig. 1, the inert gas supply system 3 includes:
the second intelligent controller 31 is connected with the computer master control system 6;
the output end of the first inert gas source 32 is connected with the combined working oil tank 1, a first temperature regulator 33, a first pressure regulator 34 and a third pressure gauge 35 are sequentially arranged between the first inert gas source 32 and the combined working oil tank 1, and the first temperature regulator 33, the first pressure regulator 34 and the third pressure gauge 35 are respectively connected with the second intelligent controller 31.
In the embodiment of the present invention, the inert gas is outputted by the first inert gas source 32 to replace the air in the combined working oil tank 1, the output temperature of the inert gas is adjusted by the first temperature regulator 33, and the output pressure of the inert gas is adjusted by the first pressure regulator 34 to adapt to the temperature and the pressure in the combined working oil tank 1, so as to ensure the safety of the combined working oil tank 1.
In the embodiment of the present invention, as shown in fig. 1, the explosion-proof detection collection system 4 includes:
the third intelligent controller 41 is connected with the computer master control system 6;
and the input end of the oil-gas cooler 42 is communicated with the top of the combined working oil tank 1, an oxygen content sensor 43 is arranged between the oil-gas cooler 42 and the combined working oil tank 1, and the oxygen content sensor 43 and the oil-gas cooler 42 are respectively connected with the third intelligent controller 41.
And the oil collecting tank 44 is connected with the output end of the oil-gas cooler 42, the top of the oil collecting tank 44 is communicated with an exhaust pipe 45, the exhaust pipe 45 is connected with a combustible gas sensor 46 and an electric control valve 47, and the combustible gas sensor 46 and the electric control valve 47 are respectively connected with the third intelligent controller 41.
In the embodiment of the invention, the oil gas in the air discharged from the combined working oil tank 1 is cooled by the oil gas cooler 42, the oil gas is collected by the oil collecting tank 44 after being cooled, and the air from which the oil gas is removed is discharged through the exhaust pipe 45, so that the explosion or air pollution caused by the discharge of the air with the oil gas to the outside is avoided, and the safety of the test platform of the fuel pump of the aircraft engine in the embodiment of the invention is greatly improved.
In the embodiment of the present invention, as shown in fig. 1, the integrated test system 5 includes:
the fourth intelligent controller 51 is connected with the computer master control system 6;
the test fuel pump 52 is arranged in the combined working oil tank 1;
a combined pressure regulating valve 53 which is respectively connected with the output end of the test fuel pump 52 and the combined working oil tank 1, wherein a second micron filter 54, a fourth pressure gauge 55, a first flowmeter 56 and a second one-way valve 57 are sequentially arranged between the test fuel pump 52 and the combined pressure regulating valve 53, and the second micron filter 54, the fourth pressure gauge 55 and the first flowmeter 56 are respectively connected with the fourth intelligent controller 51;
the adjusting mechanism is connected with the combined pressure regulating valve 53 and used for accurately adjusting the combined pressure regulating valve 53;
the bottom of the simulated combustion oil collecting tank 58 is communicated with the combined working oil tank 1, the second check valve 57 and the combined pressure regulating valve 53 are communicated with the top of the simulated combustion oil collecting tank 58 through a consumption stop valve 59 and a second flow meter 510, the consumption stop valve 59 and the second flow meter 510 are respectively connected with the fourth intelligent controller 51, the simulated combustion oil collecting tank 58 is respectively connected with a second safety protection explosion-proof device 511, a second temperature meter 512 and a second liquid level density meter 513, the second safety protection explosion-proof device 511, the second temperature meter 512 and the second liquid level density meter 513 are respectively connected with the fourth intelligent controller 51, the output end of the inert gas supply system 3 is connected with the simulated combustion oil collecting tank 58, and the simulated combustion oil collecting tank 58 is connected with the explosion-proof detection collecting system 4.
The third liquid level densimeter 514 is arranged on the combined working oil tank 1 and is connected with the fourth intelligent controller 51;
a third thermometer 515, which is disposed on the combined working oil tank 1 and connected to the fourth intelligent controller 51;
and the third safety protection explosion-proof device 516 is arranged on the combined working oil tank 1 and is connected with the fourth intelligent controller 51.
In the embodiment of the invention, the test fuel pump 52 is used as the tested fuel pump and is arranged in the combined working oil tank 1, when the test fuel pump 52 operates, one part of the extracted test medium enters the simulated combustion oil collecting tank 58 to simulate the oil consumption of the engine, and the other part of the extracted test medium returns to the combined working oil tank 1 after passing through the combined pressure regulating valve 53. The combined pressure regulating valve 53 is accurately regulated by the regulating mechanism, so that the oil quantity entering the simulated combustion oil collecting tank 58, namely the oil quantity consumed by the operation of the aircraft engine, can be controlled.
The method comprises the following steps of (1) acquiring relevant data by controlling the operation of an aircraft engine fuel pump test platform, and performing normal-temperature and high-temperature multipoint performance tests of the fuel pump; testing the starting characteristic of the fuel pump; efficiency, flow and temperature relation tests and liquid level tests. The comprehensive test capability is strong, the temperature test range is wide, the manufacturing cost is low, the processing and the manufacturing are easy, the maintenance is convenient, and the use is convenient and fast.
In an embodiment of the present invention, as shown in fig. 1, the adjustment mechanism includes:
a second inert gas source 517;
and one end of the parallel pipeline is connected with the output end of the second inert gas source 517, the other end of the parallel pipeline is connected with the combined pressure regulating valve 53, and a second temperature regulator 518, a second pressure regulator 519 and a fifth pressure gauge 520 are sequentially arranged between the second inert gas source 517 and the parallel pipeline. The parallel pipeline is composed of a first pipeline and a second pipeline which are connected in parallel, a pressure reducing valve 521 and a first precise pneumatic valve 522 are arranged on the first pipeline, a proportional regulating valve 523 and a second precise pneumatic valve 524 are arranged on the second pipeline, and a second temperature regulator 518, a second pressure regulator 519, a fifth pressure gauge 520, a pressure reducing valve 521, the first precise pneumatic valve 522, the proportional regulating valve 523 and the second precise pneumatic valve 524 are respectively connected with the fourth intelligent controller 51. The fast and accurate regulation of the combined pressure regulating valve 53 is achieved by the inert gas output from the second inert gas source 517.
Fig. 2 is a flowchart illustrating a specific method for testing the normal/high temperature multipoint flow performance of a fuel pump in the test method for testing an aircraft engine fuel pump according to the embodiment of the present invention, and as shown in fig. 2, the specific method for testing the normal/high temperature multipoint flow performance of a fuel pump specifically includes:
step S201: install the test fuel pump that will await measuring in combination working oil tank 1, make test fuel pump inlet end submergence in experimental medium, set for:
u is the power supply voltage for testing the fuel pump;
i is the power supply current for testing the fuel pump;
p is the output pressure of the fuel pump;
q is the flow of the test fuel pump;
n is the rotating speed of the fuel pump;
v t is the rate of temperature rise of the test medium;
t is the temperature of the test medium;
T max is the upper temperature limit of the test medium;
t x is a recording time interval;
step S203: starting the test at a set temperature rise rate v t Heating the test medium in the combined working oil tank 1, and simultaneously starting the test fuel pump 52;
step S205: when the temperature T of the test medium reaches a set upper limit value T max When the test fuel pump 52 is turned off, the heating is stopped;
step S207: during the heating of the test medium, every t passes x The duration is long, 1 group of flow data Q of the test fuel pump is recorded, and n groups of data are obtained: t is n And Q n ；
Step S209: and drawing a flow Q-temperature T relation curve and a flow Q-time T relation curve so as to obtain a parameter equation of a normal/high temperature multipoint flow performance test for testing the fuel pump.
Fig. 3 shows a flowchart of a specific method for testing the starting characteristic of the fuel pump in the test method for testing the fuel pump of the aircraft engine provided by the embodiment of the invention, and as shown in fig. 3, the specific method for testing the starting characteristic of the fuel pump includes:
step S301: installing the test fuel pump 52 to be tested in the combined working fuel tank 1, immersing the oil inlet end of the test fuel pump 52 in a test medium, and setting:
u is the power supply voltage for testing the fuel pump;
i is the power supply current for testing the fuel pump;
p is the output pressure of the test fuel pump;
q is the flow of the test fuel pump;
n is the rotating speed of the fuel pump;
v t is the rate of temperature rise of the test medium;
t is the temperature of the test medium;
T max is the upper temperature limit of the test medium;
t x to record a time interval;
step S303: starting the test at a set temperature rise rate v t Heating a test medium in the combined working oil tank 1, starting a test fuel pump at the same time, exhausting air in a pipeline, filling the pipeline with the test medium, and releasing air residual pressure in the pipeline;
step S305: restarting the test fuel pump, shutting down the test fuel pump 52 when the output pressure P of the test fuel pump rises from 0 or 5kpa to 90% of the maximum output pressure;
step S307: during the process of testing the rising of the output pressure P of the fuel pump, every time t passes x And (2) recording 1 group of output pressure P data of the test fuel pump to obtain n groups of data: p n ；
Step S309: and drawing a relation curve of the output pressure P of the test fuel pump 52 and the time t, thereby obtaining a parameter equation of the test for testing the starting characteristic of the fuel pump.
Fig. 4 is a flowchart illustrating a specific method for testing the relationship between efficiency, flow rate and temperature of a fuel pump in the test method for testing an aircraft engine fuel pump according to an embodiment of the present invention, and as shown in fig. 4, the specific method for testing the relationship between efficiency, flow rate and temperature specifically includes:
step S401: presetting n sets of supply voltages U for testing the fuel pumps 52 dem As n test points, the theoretical output pressure P of the corresponding n groups of test fuel pumps 52 is obtained dem ；
Step S403: starting the test, starting the fuel pump to regulate its supply voltage to a set of U dem As a test point;
step S405: the actual supply voltage U and the actual output pressure P of the test fuel pump 52 are obtained, when all sampled values within 5s match: i U-U dem Less than or equal to 0.05V and P dem -P ≦ 5kPa, record a set of data: testing the temperature T of a medium, testing the output pressure P of the fuel pump, testing the flow Q of the fuel pump, testing the power supply voltage U of the fuel pump, testing the power supply current I of the fuel pump and testing the rotating speed N of the fuel pump;
step S407: the following results are obtained by calculation: testing the efficiency eta of the fuel pump = IUQP, and recording to finish a test point;
step S409: switching to the next test point, and obtaining related data according to the method until the recording of the n groups of test points is finished;
step S411: and drawing a relation curve of the efficiency eta and the flow Q of the test fuel pump and the temperature T of the test medium to obtain a parameter equation between the efficiency and the flow of the test fuel pump and the temperature of the test medium.
Fig. 5 is a flowchart illustrating a specific method for testing a liquid level of a fuel pump in the test method for testing an aircraft engine fuel pump according to the embodiment of the present invention, and as shown in fig. 5, the specific method for testing the liquid level of the fuel pump includes:
step S501: starting the test at a set temperature rise rate v t Heating the test medium in the combined working oil tank while turning on the test fuel pump 52;
step S503: regulating the flow into the simulated combustion oil collecting tank by the combined pressure regulating valve as the consumption flow Q Burning device ；
Step S505: monitoring the liquid level h of the combined working oil tank, and when the liquid level h descends, passing t every time x And (3) recording 1 group of data to obtain n groups of data: t is n 、Q Burning n And Q n ；
Step S507: plotting test medium temperature T-consumption flow Q Burning device -testing the relation curve of the fuel pump flow Q to obtain the test medium temperature T-consumption flow Q Burning device -testing a parametric equation between fuel pump flows Q.
According to the test method for testing the fuel pump of the aircraft engine, the operation of the test platform for testing the fuel pump of the aircraft engine is controlled, relevant data are collected, and normal-temperature and high-temperature multipoint performance tests of the fuel pump are carried out; testing the starting characteristic of the fuel pump; efficiency, flow and temperature relation tests and liquid level tests. The comprehensive test capability is strong, the temperature test range is wide, the manufacturing cost is low, the processing and the manufacturing are easy, the maintenance is convenient, and the use is convenient and fast.
The above description is only an embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of changes or substitutions within the technical scope of the present invention, and the present invention shall be covered by the claims. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. The utility model provides an aeroengine fuel pump test platform which characterized in that, includes combination work oil tank, temperature control system, inert gas supply system, explosion-proof detection collecting system, integrated test system and the total control system of computer:
the combined working oil tank is internally provided with a test medium;
the temperature control system is connected with the combined working oil tank and is used for controlling the temperature of the test medium;
the inert gas supply system is connected with the combined working oil tank and is used for injecting inert gas into the combined working oil tank to replace air in the combined working oil tank;
the explosion-proof detection collecting system is connected with the combined working oil tank and is used for collecting oil gas discharged by the combined working oil tank;
the comprehensive test system is connected with the combined working oil tank and is used for detecting the thermal comprehensive performance of the fuel pump of the aircraft engine;
and the computer master control system is respectively connected with the temperature control system, the inert gas supply system, the explosion-proof detection collecting system and the comprehensive test system and is used for acquiring detection data and acquiring thermal state comprehensive performance parameters of the fuel pump of the aircraft engine.
2. The platform of claim 1, wherein the temperature control system comprises:
the first intelligent controller is connected with the computer master control system;
the heat exchange sheet is arranged in the combined working oil tank;
the heating oil tank is connected with the input end of the heat exchange fin through an oil pump, the oil pump is connected with a motor, the output end of the heat exchange fin is connected to the heating oil tank, a first micron filter is arranged between the oil pump and the heating oil tank, the output end of the inert gas supply system is connected to the heating oil tank, and the top of the heating oil tank is connected to the explosion-proof detection and collection system;
the heating device is arranged in the heating oil tank;
and the air conditioning and refrigerating device is connected with the heat exchange sheet.
3. The platform of claim 1, wherein the inert gas supply system comprises:
the second intelligent controller is connected with the computer master control system;
the output end of the first inert gas source is connected with the combined working oil tank, a first temperature regulator, a first pressure regulator and a third pressure gauge are sequentially arranged between the first inert gas source and the combined working oil tank, and the first temperature regulator, the first pressure regulator and the third pressure gauge are respectively connected with the second intelligent controller.
4. The platform of claim 1, wherein the explosion-proof detection collection system comprises:
the third intelligent controller is connected with the computer master control system;
the input end of the oil-gas cooler is communicated with the top of the combined working oil tank, an oxygen content sensor is arranged between the oil-gas cooler and the combined working oil tank, and the oil-gas cooler and the oxygen content sensor are respectively connected with the third intelligent controller;
the oil collecting tank is connected with the output end of the oil-gas cooler, the top of the oil collecting tank is communicated with an exhaust pipe, a combustible gas sensor and an electric control valve are connected onto the exhaust pipe, and the combustible gas sensor and the electric control valve are respectively connected with the third intelligent controller.
5. The platform of claim 1, wherein the integrated test system comprises:
the fourth intelligent controller is connected with the computer master control system;
the testing fuel pump is arranged in the combined working oil tank;
the combined pressure regulating valve is respectively connected with the output end of the test fuel pump and the combined working oil tank;
the adjusting mechanism is connected with the combined pressure regulating valve and is used for accurately adjusting the combined pressure regulating valve;
the bottom of the simulated combustion oil collecting tank is communicated with the combined working oil tank, and the top of the simulated combustion oil collecting tank is communicated with the test fuel pump, the combined pressure regulating valve and the explosion-proof detection collecting system;
the third liquid level densimeter is arranged on the combined working oil tank and is connected with the fourth intelligent controller;
the third thermometer is arranged on the combined working oil tank and is connected with the fourth intelligent controller;
and the third safety protection explosion-proof device is arranged on the combined working oil tank and is connected with the fourth intelligent controller.
6. An aircraft engine fuel pump test method, which is characterized in that the test method adopts the aircraft engine fuel pump test platform of any one of claims 1 to 5 to test the thermal state comprehensive performance of a test fuel pump.
7. The method of claim 6, comprising:
installing a test fuel pump to be tested in a combined working fuel tank, and immersing an oil inlet end of the test fuel pump in a test medium;
at a set temperature rise rate v t Heating a test medium in the combined working oil tank, and starting the test fuel pump;
when the temperature T of the test medium reaches a set upper limit value T max When the test fuel pump is started, the test fuel pump is closed;
during the heating of the test medium, every t passes x And (2) recording the flow data Q of 1 group of the test fuel pumps to obtain n groups of data: t is n And Q n ；
And drawing a flow Q-temperature T relation curve and a flow Q-time T relation curve to obtain a parameter equation of a normal/high temperature multipoint flow performance test for testing the fuel pump.
8. The method of claim 6, comprising:
installing a test fuel pump to be tested in a combined working fuel tank, and immersing an oil inlet end of the test fuel pump in a test medium;
at a set temperature rise rate v t Heating a test medium in the combined working oil tank, starting the test oil fuel pump, exhausting air in a pipeline, filling the pipeline with the test medium, and releasing air residual pressure in the pipeline;
restarting the test fuel pump, shutting down the test fuel pump when the output pressure P of the test fuel pump rises from 0 or 5kpa to 90% of the maximum output pressure;
during the process of testing the output pressure P rise of the fuel pump, every time t passes x And (2) recording 1 group of output pressure P data of the test fuel pump to obtain n groups of data: p n ；
And drawing a relation curve of the output pressure P-time t of the test fuel pump to obtain a parameter equation of the test for the starting characteristic of the test fuel pump.
9. The method of claim 6, comprising:
presetting n groups of power supply voltage U for testing fuel pump dem As n test points, obtaining n groups of corresponding theoretical output pressures P of the test fuel pump dem ；
Starting the test fuel pump, and adjusting the power supply voltage of the fuel pump into a set of U dem As a test point;
acquiring the actual power supply voltage U and the actual output pressure P of the test fuel pump, and recording a group of data when all sampling values meet the set conditions within the set time: testing the temperature T of a medium, testing the output pressure P of the fuel pump, testing the flow Q of the fuel pump, testing the power supply voltage U of the fuel pump, testing the power supply current I of the fuel pump and testing the rotating speed N of the fuel pump;
calculating to obtain: testing the efficiency eta of the fuel pump = IUQP, and recording to finish a test point;
shifting to the next test point, and obtaining related data according to the method until the recording of the n groups of test points is completed;
and drawing a relation curve of the efficiency eta and the flow Q of the test fuel pump and the temperature T of the test medium to obtain a parameter equation between the efficiency and the flow of the test fuel pump and the temperature of the test medium.
10. The method of claim 6, comprising:
at a set temperature rise rate v t Heating a test medium in the combined working oil tank, and starting a test fuel pump;
the flow rate of the fuel flowing into the simulated combustion oil collecting tank is regulated through the combined pressure regulating valve and is used as the consumption flow rate Q Burning device ；
Monitoring the liquid level h of the combined working oil tank, and when the liquid level h descends, passing t every time x And (3) recording 1 group of data to obtain n groups of data: t is a unit of n 、Q Burning of And Q n ；
Plotting test medium temperature T-consumption flow Q Burning device -testing the fuel pump flow Q relation curve to obtain the test medium temperature T-consumption flow Q Burning device -testing a parametric equation between fuel pump flows Q.
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