CN104634578A - Total environment high-altitude test system and total environment high-altitude test method for aviation turbocharged internal combustion engine - Google Patents
Total environment high-altitude test system and total environment high-altitude test method for aviation turbocharged internal combustion engine Download PDFInfo
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Abstract
The invention relates to a total environment high-altitude test system and a total environment high-altitude test method for an aviation turbocharged internal combustion engine and belongs to the technical field of simulation tests. According to the test system and the test method, a measured power system is arranged in a sealing cabin body; low-temperature gas is produced by using a low-temperature gas supply system, is transmitted to the inside of a test chamber through a gas path and is used for creating a low-temperature environment adapting to the altitude in the chamber; the gas in the test chamber is forced to be exhausted by adopting an ejection system for simulating a high-altitude low-pressure environment, so that the test environment is simulated to more approach to a real high-altitude working environment of an engine, and a high-efficiency and reliable simulation test means is provided for verifying high-altitude performances of the aviation turbocharged internal combustion engine.
Description
Technical field
The present invention relates to modelling technique field, be specifically related to a kind of aviation turbocharging internal-combustion engines loopful border altitude test system and test method.
Background technology
At present, turbocharging internal-combustion engines high-altitude simulation testing system for carrying out the every upper air performance checking of engine all adopts direct-connect test system, can not engine high-altitude that is virtually reality like reality running environment, therefore cannot verify engine aloft work performance comprehensively.
Therefore, how to design a kind of high-altitude loopful border performance simulation test system and test method of aviation turbocharging internal-combustion engines, to verify serviceability under the true environment of engine high-altitude, become technical matters urgently to be resolved hurrily.
Summary of the invention
(1) technical matters that will solve
The technical problem to be solved in the present invention is: how to design a kind of high-altitude loopful border performance simulation test system of aviation turbocharging internal-combustion engines and corresponding test method, to verify serviceability under the true environment of engine high-altitude.
(2) technical scheme
In order to solve the problems of the technologies described above, the invention provides a kind of aviation turbocharging internal-combustion engines loopful border altitude test system, comprising low temperature air supply system, ejection system, cooling system, experimental cabin, tested power system and TT&C system;
Described low temperature air supply system, for building the low temperature test run environment under simulated environment height;
Described ejection system is used for the air in experimental cabin to discharge, thus realizes upper low experimental enviroment;
Described TT&C system controls for the running status of carrying out tested power system and experimental cabin;
Described cooling system comprises cooling gas circuit and cooling water channel, described cooling gas circuit is for the non-high-temperature resistant parts under the cryogenic gas cooling down high-temperature environment that utilizes low temperature air feed system and produce, described cooling water channel is used for water-filled radiator supply chilled water, described water-filled radiator is used for test engine Performance Characteristics at different conditions, also for ensureing that engine health is normally run.
Preferably, described low temperature air supply system comprises low temperature air feed system, gas circuit and solenoid valve; Described low temperature air feed system is for the manufacture of cryogenic gas, and the cryogenic gas that described gas circuit is used for low temperature feedway to produce imports experimental cabin, and described solenoid valve is for controlling the cryogenic gas flow flowing into experimental cabin.
Preferably, described ejection system comprises injector and source of the gas gas circuit; Described injector is used for air in experimental cabin to discharge in order to build upper low experimental enviroment, and described source of the gas gas circuit connects injector and experimental cabin.
Preferably, described experimental cabin comprises sealing cabin, air inlet pipeline, engine mounting base and gas exhaust piping; Described sealing cabin is shaped seals structure, for placing tested power system, described air inlet pipeline is the cooling pipelines entering sealing cabin, and described engine mounting base is for supporting tested power system, and described gas exhaust piping is used for engine being run the waste gas produced and discharges experimental cabin; Measurand comprises tested power system, dynamometer machine and relevant topworks.
Preferably, cold constant temperature system and water cooling heat exchanger during described water-filled radiator comprises, in described, cold constant temperature system is used for the Performance Characteristics of test engine at various inlet temperature; Described water cooling heat exchanger is for use in testing for the situation of change of engine performance under different lubricating oil, coolant temperature.
Preferably, described TT&C system comprises engine control system, altitude simulation control system, temperature simulation control system, engine operating parameter monitoring system, experimental cabin running state monitoring system;
Described engine control system is used for the engine behavior manipulation associated components according to presetting;
Described altitude simulation control system is used for the environmental pressure of simulation test cabin under certain altitude;
Described temperature simulation control system is used for the environment temperature of simulation test cabin under certain altitude;
Described engine operating parameter monitoring system is used for monitoring engine operational factor;
Described experimental cabin operational factor monitoring system is used for monitoring test cabin operational factor.
Preferably, described engine operating parameter monitoring system comprises signals collecting case and display module, and described signals collecting case is used for gathering engine operating parameter, and described display module is used for carrying out display translation to engine operating parameter.
Preferably, described pilot system also comprises fuel feed system, for being other module energy supply of pilot system, comprises fuel tank and fuel pump.
Present invention also offers a kind of method utilizing said system to carry out loopful border altitude test, comprise the following steps:
S1, according to engine design state, manufacture and design engine mounting base, to support tested power system, guarantee that tested power system is on the axial line of experimental cabin;
S2, according to aircraft flight state, calculation engine run time outside wind speed variation range, according to result of calculation determination experimental cabin air inlet pipeline diameter, and select corresponding solenoid valve for controlling air mass flow;
S3, on engine body, install radome fairing additional, body running environment in simulated flight process, and the air inlet branch line on experimental cabin air inlet pipeline is directly connected radome fairing;
In S4, employing, cold constant temperature system replaces charge air cooler, with the Performance Characteristics of test engine at various inlet temperature; Water cooling heat exchanger is adopted to replace air-cooled lubricating oil, cooling water radiator, in order to the situation of change of test engine engine performance under different lubricating oil, coolant temperature; Described water cooling heat exchanger comprises water-cooled oil heat exchanger, cooling by water liquid heat interchanger;
S5, by water-cooled oil heat exchanger, cooling by water liquid heat interchanger, in cold thermostat, fuel tank, signals collecting case etc. be arranged in experimental cabin outside;
S6, according to test demand, on the engine mounting arrangements engine operating parameter sensor, by signals collecting case, the display module of the signal input engine operating parameter monitoring system that engine operating parameter sensor is gathered;
S7, according to the operating characteristic of the sensor of participating in the experiment of experimental cabin and installation site, install cooling gas circuit additional at the sensor of participating in the experiment being in hyperthermia radiation district;
S8, complete signal wiring after, check the duty of TT&C system, guarantee its normal operation; After confirming that each system works is normal, close test hatchcover, test preliminary work terminates;
S9, carry out engine warming up and performance test in surface air state, open ejection system and cooling system, run under making it be in low flow rate condition;
S10, complete state of ground content of the test after, open low temperature air feed system, after temperature is reduced to preset value in experimental cabin, improve ejection system duty, according to flying speed requirement, regulate experimental cabin induction air flow ratio, realize the full environmental simulation under certain altitude;
S11, when simulated environment height is constant, according to preset requirement, the cooling water flow of cold constant temperature system, water-cooled oil heat exchanger, cooling by water liquid heat interchanger in adjustment, realizes the serviceability certification test of engine under same height above sea level, different operating state;
S12, complete this height performance test after, by first regulating experimental cabin analog temperature, the order of rear adjustment simulation test height carries out the engine performance test under each sea level elevation.
(3) beneficial effect
Tested power system is placed in sealing cabin by the present invention, utilizes low temperature air supply system to manufacture cryogenic gas, and is delivered in experimental cabin by gas circuit, in order to build the low temperature environment adapted with sea level elevation in cabin; Ejection system is adopted to force the gas in experimental cabin to be discharged, carry out upper low environmental simulation, make experimental enviroment in analog more close to the true aloft work environment of engine, for the checking of aviation turbocharging internal-combustion engines high-level performance provides a kind of efficient, reliable simulation test means.
Accompanying drawing explanation
Fig. 1 is one-piece construction schematic diagram of the present invention;
Fig. 2 is the concrete syndeton schematic diagram between part-structure of the present invention.
Embodiment
For making object of the present invention, content and advantage clearly, below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.
The main thought of a kind of aviation turbocharging internal-combustion engines loopful border provided by the invention altitude test system is: be placed in sealing cabin by tested power system, low temperature air supply system is utilized to manufacture cryogenic gas, and be delivered in experimental cabin by gas circuit, in order to build the low temperature environment adapted with sea level elevation in cabin; Ejection system is adopted to force the gas in experimental cabin to be discharged, and then upper low environmental simulation, make experimental enviroment in analog more close to the true aloft work environment of engine, for the checking of aviation turbocharging internal-combustion engines high-level performance provides a kind of efficient, reliable simulation test means.
As shown in Figure 1 and Figure 2, aviation turbocharging internal-combustion engines loopful border of the present invention altitude test system comprises low temperature air supply system, ejection system, cooling system, experimental cabin, tested power system and TT&C system;
Described low temperature air supply system, for building the low temperature test run environment under simulated environment height;
Described ejection system is used for the air in experimental cabin to discharge, thus realizes upper low experimental enviroment;
Described TT&C system controls for the running status of carrying out tested power system and experimental cabin;
Described cooling system comprises cooling gas circuit and cooling water channel, described cooling gas circuit is for the non-high-temperature resistant parts under the cryogenic gas cooling down high-temperature environment that utilizes low temperature air feed system and produce, described cooling water channel is used for water-filled radiator supply chilled water, described water-filled radiator is used for test engine Performance Characteristics at different conditions, and ensures that engine health is normally run.
Described low temperature air supply system comprises low temperature air feed system, gas circuit and solenoid valve; Described low temperature air feed system is for the manufacture of cryogenic gas, and the cryogenic gas that described gas circuit is used for low temperature feedway to produce imports experimental cabin, and described solenoid valve is for controlling the cryogenic gas flow flowing into experimental cabin.
Described ejection system comprises injector and source of the gas gas circuit; Described injector is used for air in experimental cabin to discharge in order to build upper low experimental enviroment, and described source of the gas gas circuit connects injector and experimental cabin;
Described experimental cabin comprises sealing cabin, air inlet pipeline, engine mounting base and gas exhaust piping; Described sealing cabin is shaped seals structure, for placing tested power system, described air inlet pipeline is the cooling pipelines entering sealing cabin, and described engine mounting base is for supporting tested power system, and described gas exhaust piping is used for engine being run the waste gas produced and discharges experimental cabin; Measurand comprises tested power system, dynamometer machine and relevant topworks.
Cold constant temperature system and water cooling heat exchanger during described water-filled radiator comprises, by the temperature mode of being down within usable range of water-cooled oil heat exchanger, cooling by water liquid heat interchanger, water-filled radiator is by ensureing that engine health is normally run, in described, cold constant temperature system is used for the Performance Characteristics of test engine at various inlet temperature; Described water cooling heat exchanger is for use in testing for the situation of change of engine performance under different lubricating oil, coolant temperature.
Described TT&C system comprises engine control system, altitude simulation control system, temperature simulation control system, engine operating parameter monitoring system, experimental cabin running state monitoring system;
Described engine control system is used for the engine behavior manipulation associated components according to presetting, and described associated components comprises the moment of torsion of engine throttle and dynamometer machine;
Described altitude simulation control system is used for the environmental pressure of simulation test cabin under certain altitude;
Described temperature simulation control system is used for the environment temperature of simulation test cabin under certain altitude;
Described engine operating parameter monitoring system is used for monitoring engine operational factor, comprises rotating speed and power;
Described experimental cabin operational factor monitoring system is used for monitoring test cabin operational factor, comprises environmental pressure and environment temperature.
Described engine operating parameter monitoring system comprises signals collecting case and display module, and described signals collecting case is used for gathering engine operating parameter, and described display module is used for carrying out display translation to engine operating parameter.
Described pilot system also comprises fuel feed system, for being other module energy supply of pilot system, comprises fuel tank and fuel pump.
Correspondingly, present invention also offers a kind of method utilizing said system to carry out altitude test, comprise the following steps:
S1, according to engine design state, manufacture and design engine mounting base, to support tested power system, comprise engine, low temperature resistant dynamometer machine, relevant execution unit (such as throttle actuator etc.), guarantee that tested power system is on the axial line of experimental cabin;
S2, according to aircraft flight state, calculation engine run time outside wind speed variation range, according to result of calculation determination experimental cabin air inlet pipeline diameter, and select corresponding solenoid valve for controlling air mass flow;
S3, on engine body, install radome fairing additional, body running environment in simulated flight process, and the air inlet branch line on experimental cabin air inlet pipeline is directly connected radome fairing;
In S4, employing, cold constant temperature system replaces charge air cooler, to examine the Performance Characteristics of engine at various inlet temperature; Water cooling heat exchanger is adopted to replace air-cooled lubricating oil, cooling water radiator, in order to examine the situation of change of engine engine performance under different lubricating oil, coolant temperature; In adopting in the present invention, cold constant temperature system and water cooling heat exchanger, be water cooling plant, and relative to air cooling equipment, be easy to realize, cost is low, is convenient to install. and water cooling heat exchanger comprises water-cooled oil heat exchanger, cooling by water liquid heat interchanger;
S5, by water-cooled oil heat exchanger, cooling by water liquid heat interchanger, in cold thermostat, fuel tank, signals collecting case etc. be arranged in experimental cabin outside.Fuel tank should away from pilot system other parts, to meet fire protection requirement;
S6, according to test demand, on the engine mounting arrangements engine operating parameter sensor, by the modular converter in signals collecting case, the display module of the signal input engine operating parameter monitoring system that engine operating parameter sensor is gathered;
S7, according to the operating characteristic of the sensor of participating in the experiment of experimental cabin and installation site, install cooling gas circuit additional at the sensor of participating in the experiment being in hyperthermia radiation district;
S8, complete signal wiring after, check the duty of engine control system, engine operating parameter monitoring system, testing table running state monitoring system etc. in TT&C system, guarantee its normal operation; After confirming that each system works is normal, close test hatchcover, test preliminary work terminates;
S9, first carry out engine warming up and performance test in surface air state, open ejection system, cooling system, run under making it be in low flow rate condition;
S10, complete state of ground content of the test after, open low temperature air feed system, temperature in experimental cabin to be reduced in charter after required value, improve ejection system duty, according to flying speed requirement, regulate experimental cabin induction air flow ratio, realize the full environmental simulation under certain altitude;
S11, when simulated environment height is constant, according to requirement in test mission book, in adjustment, the cooling water flow of cold constant temperature system, water-cooled oil heat exchanger, cooling by water liquid heat interchanger etc., realizes the serviceability certification test of engine under same height above sea level, different operating state;
S12, complete this height performance test after, by first regulating experimental cabin analog temperature, the order of rear adjustment simulation test height carries out the engine performance test under each sea level elevation.Test shows, first regulate experimental cabin analog temperature, the order of rear adjustment simulation test height can reach the object of quick adjustment.
Said method is utilized to carry out the test findings of aviation turbocharging internal-combustion engines loopful border altitude test as shown in table 1 below.
Table 1
As can be seen from the above table, pilot system of the present invention can complete aeroturbine boosting internal combustion engine altitude simulation test.The service condition of the engine low-pressure low-temperature in test under simulating high altitude environment.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and distortion, these improve and distortion also should be considered as protection scope of the present invention.
Claims (9)
1. an aviation turbocharging internal-combustion engines loopful border altitude test system, is characterized in that, comprise low temperature air supply system, ejection system, cooling system, experimental cabin, tested power system and TT&C system;
Described low temperature air supply system, for building the low temperature test run environment under simulated environment height;
Described ejection system is used for the air in experimental cabin to discharge, thus realizes upper low experimental enviroment;
Described TT&C system controls for the running status of carrying out tested power system and experimental cabin;
Described cooling system comprises cooling gas circuit and cooling water channel, described cooling gas circuit is for the non-high-temperature resistant parts under the cryogenic gas cooling down high-temperature environment that utilizes low temperature air feed system and produce, described cooling water channel is used for water-filled radiator supply chilled water, described water-filled radiator is used for test engine Performance Characteristics at different conditions, also for ensureing that engine health is normally run.
2. the system as claimed in claim 1, is characterized in that, described low temperature air supply system comprises low temperature air feed system, gas circuit and solenoid valve; Described low temperature air feed system is for the manufacture of cryogenic gas, and the cryogenic gas that described gas circuit is used for low temperature feedway to produce imports experimental cabin, and described solenoid valve is for controlling the cryogenic gas flow flowing into experimental cabin.
3. the system as claimed in claim 1, is characterized in that, described ejection system comprises injector and source of the gas gas circuit; Described injector is used for air in experimental cabin to discharge in order to build upper low experimental enviroment, and described source of the gas gas circuit connects injector and experimental cabin.
4. system as claimed in claim 2, it is characterized in that, described experimental cabin comprises sealing cabin, air inlet pipeline, engine mounting base and gas exhaust piping; Described sealing cabin is shaped seals structure, for placing tested power system, described air inlet pipeline is the cooling pipelines entering sealing cabin, and described engine mounting base is for supporting tested power system, and described gas exhaust piping is used for engine being run the waste gas produced and discharges experimental cabin; Measurand comprises tested power system, dynamometer machine and relevant topworks.
5. system as claimed in claim 4, is characterized in that, cold constant temperature system and water cooling heat exchanger during described water-filled radiator comprises, and in described, cold constant temperature system is used for the Performance Characteristics of test engine at various inlet temperature; Described water cooling heat exchanger is for use in testing for the situation of change of engine performance under different lubricating oil, coolant temperature.
6. system as claimed in claim 5, it is characterized in that, described TT&C system comprises engine control system, altitude simulation control system, temperature simulation control system, engine operating parameter monitoring system, experimental cabin running state monitoring system;
Described engine control system is used for the engine behavior manipulation associated components according to presetting;
Described altitude simulation control system is used for the environmental pressure of simulation test cabin under certain altitude;
Described temperature simulation control system is used for the environment temperature of simulation test cabin under certain altitude;
Described engine operating parameter monitoring system is used for monitoring engine operational factor;
Described experimental cabin operational factor monitoring system is used for monitoring test cabin operational factor.
7. system as claimed in claim 6, it is characterized in that, described engine operating parameter monitoring system comprises signals collecting case and display module, and described signals collecting case is used for gathering engine operating parameter, and described display module is used for carrying out display translation to engine operating parameter.
8. system as claimed in claim 7, it is characterized in that, described pilot system also comprises fuel feed system, for being other module energy supply of pilot system, comprises fuel tank and fuel pump.
9. utilize the system described in claim 8 to carry out a method for loopful border altitude test, it is characterized in that, comprise the following steps:
S1, according to engine design state, manufacture and design engine mounting base, to support tested power system, guarantee that tested power system is on the axial line of experimental cabin;
S2, according to aircraft flight state, calculation engine run time outside wind speed variation range, according to result of calculation determination experimental cabin air inlet pipeline diameter, and select corresponding solenoid valve for controlling air mass flow;
S3, on engine body, install radome fairing additional, body running environment in simulated flight process, and the air inlet branch line on experimental cabin air inlet pipeline is directly connected radome fairing;
In S4, employing, cold constant temperature system replaces charge air cooler, with the Performance Characteristics of test engine at various inlet temperature; Water cooling heat exchanger is adopted to replace air-cooled lubricating oil, cooling water radiator, in order to the situation of change of test engine engine performance under different lubricating oil, coolant temperature; Described water cooling heat exchanger comprises water-cooled oil heat exchanger, cooling by water liquid heat interchanger;
S5, by water-cooled oil heat exchanger, cooling by water liquid heat interchanger, in cold thermostat, fuel tank, signals collecting case etc. be arranged in experimental cabin outside;
S6, according to test demand, on the engine mounting arrangements engine operating parameter sensor, by signals collecting case, the display module of the signal input engine operating parameter monitoring system that engine operating parameter sensor is gathered;
S7, according to the operating characteristic of the sensor of participating in the experiment of experimental cabin and installation site, install cooling gas circuit additional at the sensor of participating in the experiment being in hyperthermia radiation district;
S8, complete signal wiring after, check the duty of TT&C system, guarantee its normal operation; After confirming that each system works is normal, close test hatchcover, test preliminary work terminates;
S9, carry out engine warming up and performance test in surface air state, open ejection system and cooling system, run under making it be in low flow rate condition;
S10, complete state of ground content of the test after, open low temperature air feed system, after temperature is reduced to preset value in experimental cabin, improve ejection system duty, according to flying speed requirement, regulate experimental cabin induction air flow ratio, realize the full environmental simulation under certain altitude;
S11, when simulated environment height is constant, according to preset requirement, the cooling water flow of cold constant temperature system, water-cooled oil heat exchanger, cooling by water liquid heat interchanger in adjustment, realizes the serviceability certification test of engine under same height above sea level, different operating state;
S12, complete this height performance test after, by first regulating experimental cabin analog temperature, the order of rear adjustment simulation test height carries out the engine performance test under each sea level elevation.
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