CN104634578B - Aviation turbocharging internal-combustion engines full ambient engine altitude test system and test method - Google Patents
Aviation turbocharging internal-combustion engines full ambient engine altitude test system and test method Download PDFInfo
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Abstract
The present invention relates to a kind of aviation turbocharging internal-combustion engines full ambient engine altitude test system and test method, belong to modelling technique field.The present invention is placed in tested dynamical system in sealing cabin, manufactures cryogenic gas using low temperature air supply system, and is delivered in experimental cabin by gas circuit, to build the low temperature environment being adapted with height above sea level in cabin；Force to discharge the gas in experimental cabin using ejection system, carry out upper low environmental simulation, be more nearly the true aloft work environment of electromotor with making experimental enviroment simulation, a kind of efficient, reliable simulation test means are provided for the checking of aviation turbocharging internal-combustion engines high-level performance.
Description
Technical field
The present invention relates to modelling technique field, and in particular to a kind of aviation turbocharging internal-combustion engines full ambient engine high-altitude
Pilot system and test method.
Background technology
It is presently used for carrying out the turbocharging internal-combustion engines altitude simulation test system of electromotor items upper air performance checking
System adopts direct-connect test system, it is impossible to simulate real electromotor high-altitude running environment, thus cannot comprehensive verification start
Machine aloft work performance.
Therefore, high-altitude full ambient engine performance simulation test system and the examination of a kind of aviation turbocharging internal-combustion engines how to be designed
Proved recipe method, to verify service behaviour under the true environment of electromotor high-altitude, becomes technical problem urgently to be resolved hurrily.
The content of the invention
(1) technical problem to be solved
The technical problem to be solved in the present invention is：How a kind of high-altitude full ambient engine of aviation turbocharging internal-combustion engines is designed
Performance simulation test system and corresponding test method, to verify service behaviour under the true environment of electromotor high-altitude.
(2) technical scheme
In order to solve above-mentioned technical problem, the invention provides a kind of aviation is tried with turbocharging internal-combustion engines full ambient engine high-altitude
Check system, including low temperature air supply system, ejection system, cooling system, experimental cabin, tested dynamical system and TT＆C system；
The low temperature air supply system, for building the low temperature test run environment under simulated environment height；
The ejection system for by experimental cabin air discharge, so as to realize upper low experimental enviroment；
The TT＆C system is used for the running status control for carrying out tested dynamical system and experimental cabin；
The cooling system includes cooling down gas circuit and cooling water channel, and the cooling gas circuit is used for using low temperature air feed system
Non-high-temperature resistant part under the cryogenic gas cooling down high-temperature environment of generation, the cooling water channel are cold for supplying to water-filled radiator
But water, the water-filled radiator are used for test engine Performance Characteristics at different conditions, are additionally operable to ensure engine health
It is normal to run.
Preferably, the low temperature air supply system includes low temperature air feed system, gas circuit and electromagnetic valve；The low temperature gas supply
Device is used to manufacture cryogenic gas, and the gas circuit imports experimental cabin for the cryogenic gas for producing low temperature feedway, described
Electromagnetic valve is used for the cryogenic gas flow for controlling to flow into experimental cabin.
Preferably, the ejection system includes injector and source of the gas gas circuit；The injector is for by air in experimental cabin
Discharge to build upper low experimental enviroment, the source of the gas gas circuit connection injector and experimental cabin.
Preferably, the experimental cabin includes sealing cabin, air inlet pipeline, electromotor installation pedestal and gas exhaust piping；It is described
Sealing cabin is shaped seals structure, and for placing tested dynamical system, the air inlet pipeline is the cold air into sealing cabin
Pipeline, the electromotor installation pedestal are used to support tested dynamical system, the gas exhaust piping to produce for electromotor is run
Waste gas discharge experimental cabin；Measurand includes tested dynamical system, dynamometer machine and related actuator.
Preferably, the water-filled radiator cold constant temperature system and water cooling heat exchanger in including, it is described in cold constant temperature system use
Performance Characteristics in test engine at a temperature of various inlet；The water cooling heat exchanger is used for test in different lubricating oil, cooling
The situation of change of engine performance under liquid temp.
Preferably, the TT＆C system includes electromotor control system, altitude simulation control system, temperature simulation control system
System, engine operating parameter monitoring system, experimental cabin running state monitoring system；
The electromotor control system is for according to default engine behavior manipulation associated components；
The altitude simulation control system is used for ambient pressure of the simulation test cabin under certain altitude；
The temperature simulation control system is used for ambient temperature of the simulation test cabin under certain altitude；
The engine operating parameter monitoring system is used to monitor engine operating parameter；
The experimental cabin operational factor monitoring system is used for monitoring test cabin operational factor.
Preferably, the engine operating parameter monitoring system includes signals collecting case and display module, and the signal is adopted
, for being acquired to engine operating parameter, the display module is defeated for display is carried out to engine operating parameter for header
Go out.
Preferably, the pilot system also includes fuel feed system, for for other module energy supplies of pilot system, including
Fuel tank and fuel pump.
Present invention also offers a kind of method that utilization said system carries out full ambient engine altitude test, comprises the following steps：
S1, according to electromotor design point, manufacture and design electromotor installation pedestal, to support tested dynamical system, it is ensured that
Tested dynamical system is on the axial line of experimental cabin；
S2, according to aircraft flight state, calculate outside wind speed excursion when electromotor runs, according to result of calculation
Determine experimental cabin air inlet pipeline diameter, and be used to control air mass flow from corresponding electromagnetic valve；
S3, install trouserss on engine body additional, body running environment during simulated flight, and by experimental cabin air inlet
Air inlet branch line on pipeline is directly connected to trouserss；
In S4, employing, cold constant temperature system replaces charge air cooler, the Performance Characteristics with test engine at a temperature of various inlet；
Air-cooled lubricating oil, cooling water radiator are replaced using water cooling heat exchanger, to test engine under different lubricating oil, coolant temperature
The situation of change of engine performance；The water cooling heat exchanger includes water-cooled oil heat exchanger, cooling by water liquid heat exchanger；
S5, by water-cooled oil heat exchanger, cooling by water liquid heat exchanger, in cold thermostat, fuel tank, signals collecting case etc.
It is arranged in outside experimental cabin；
S6, according to test demand, mounting arrangements engine operating parameter sensor on the engine, by signals collecting
Case, by the display module of the signal input engine operating parameter monitoring system of engine operating parameter sensor acquisition；
S7, according to the operating characteristic and installation site of the sensor of participating in the experiment of experimental cabin, in participating in the experiment in hyperthermia radiation area
Sensor installs cooling gas circuit additional；
S8, complete hardware connection after, check TT＆C system working condition, it is ensured that its normal operation；Confirm each system work
After making normally, test hatchcover is closed, test preparation terminates；
S9, electromotor warming up and performance test are carried out in surface air state, open ejection system and cooling system so as to
Run under low flow rate condition；
S10, complete state of ground content of the test after, open low temperature air feed system, temperature in experimental cabin is reduced to pre-
If after value, improving ejection system working condition, required according to flight speed, adjust experimental cabin induction air flow ratio, realize certain altitude
Under full ambient engine simulation；
S11, in the case where simulated environment is highly constant, according to preset requirement, cold constant temperature system, water-cooled lubricating oil in regulation
The cooling water flow of heat exchanger, cooling by water liquid heat exchanger, realizes work of the electromotor under same height above sea level, different working condition
Guaranteed performance test；
S12, complete the height performance test after, by first adjust experimental cabin analog temperature, afterwards adjust simulation test height
Order carry out the engine performance test under each height above sea level.
(3) beneficial effect
The present invention is placed in tested dynamical system in sealing cabin, manufactures cryogenic gas using low temperature air supply system, and leads to
Cross gas circuit to be delivered in experimental cabin, to build the low temperature environment being adapted with height above sea level in cabin；Forced using ejection system
Gas in experimental cabin is discharged, upper low environmental simulation is carried out, electromotor is more nearly with making experimental enviroment simulation true
Aloft work environment, provides a kind of efficient, reliable simulation test for the checking of aviation turbocharging internal-combustion engines high-level performance
Means.
Description of the drawings
Fig. 1 is the overall structure diagram of the present invention；
Fig. 2 is the concrete attachment structure schematic diagram between the part-structure of the present invention.
Specific embodiment
To make the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to the present invention's
Specific embodiment is described in further detail.
The main thought of a kind of aviation turbocharging internal-combustion engines full ambient engine altitude test system that the present invention is provided is：Will
Tested dynamical system is placed in sealing cabin, is manufactured cryogenic gas using low temperature air supply system, and is delivered to test by gas circuit
In cabin, to build the low temperature environment being adapted with height above sea level in cabin；Forced the gas in experimental cabin using ejection system
Discharge, and then upper low environmental simulation, it is more nearly the true aloft work environment of electromotor with making experimental enviroment simulation, is boat
Empty turbocharging internal-combustion engines high-level performance checking is there is provided a kind of efficient, reliable simulation test means.
As shown in Figure 1 and Figure 2, aviation turbocharging internal-combustion engines full ambient engine altitude test system of the invention includes low temperature
Air supply system, ejection system, cooling system, experimental cabin, tested dynamical system and TT＆C system；
The low temperature air supply system, for building the low temperature test run environment under simulated environment height；
The ejection system for by experimental cabin air discharge, so as to realize upper low experimental enviroment；
The TT＆C system is used for the running status control for carrying out tested dynamical system and experimental cabin；
The cooling system includes cooling down gas circuit and cooling water channel, and the cooling gas circuit is used for using low temperature air feed system
Non-high-temperature resistant part under the cryogenic gas cooling down high-temperature environment of generation, the cooling water channel are cold for supplying to water-filled radiator
But water, the water-filled radiator are used for test engine Performance Characteristics at different conditions, and just ensure engine health
Often run.
The low temperature air supply system includes low temperature air feed system, gas circuit and electromagnetic valve；The low temperature air feed system is used
In manufacture cryogenic gas, the gas circuit imports experimental cabin, the electromagnetic valve for the cryogenic gas for producing low temperature feedway
For controlling to flow into the cryogenic gas flow of experimental cabin.
The ejection system includes injector and source of the gas gas circuit；The injector for by experimental cabin air discharge to
Build upper low experimental enviroment, the source of the gas gas circuit connection injector and experimental cabin；
The experimental cabin includes sealing cabin, air inlet pipeline, electromotor installation pedestal and gas exhaust piping；The sealing cabin
For shaped seals structure, for placing tested dynamical system, the air inlet pipeline is the cooling pipelines into sealing cabin, described
Electromotor installation pedestal is used to support tested dynamical system, the gas exhaust piping to discharge for electromotor to be run the waste gas for producing
Experimental cabin；Measurand includes tested dynamical system, dynamometer machine and related actuator.
The water-filled radiator cold constant temperature system and water cooling heat exchanger in including, water-filled radiator is by water-cooled lubricating oil is changed
The mode that hot device, the temperature of cooling by water liquid heat exchanger are down within use range ensures that engine health is normally run, described
In cold constant temperature system be used for Performance Characteristics of the test engine at a temperature of various inlet；The water cooling heat exchanger is used for test and exists
The situation of change of engine performance under different lubricating oil, coolant temperature.
The TT＆C system includes electromotor control system, altitude simulation control system, temperature simulation control system, starts
Machine operational factor monitoring system, experimental cabin running state monitoring system；
The electromotor control system is for according to default engine behavior manipulation associated components, the dependent part
Part includes the moment of torsion of engine throttle and dynamometer machine；
The altitude simulation control system is used for ambient pressure of the simulation test cabin under certain altitude；
The temperature simulation control system is used for ambient temperature of the simulation test cabin under certain altitude；
The engine operating parameter monitoring system is used to monitor engine operating parameter, including rotating speed and power；
The experimental cabin operational factor monitoring system is used for monitoring test cabin operational factor, including ambient pressure and environment temperature
Degree.
The engine operating parameter monitoring system includes signals collecting case and display module, and the signals collecting case is used for
Engine operating parameter is acquired, the display module is for carrying out display output to engine operating parameter.
The pilot system also includes fuel feed system, for for other module energy supplies of pilot system, including fuel tank
And fuel pump.
Correspondingly, present invention also offers a kind of utilization said system method for carrying out altitude test, comprises the following steps：
S1, according to electromotor design point, manufacture and design electromotor installation pedestal, to support tested dynamical system, including
Electromotor, low temperature resistant dynamometer machine, related execution unit (such as throttle actuator etc.), it is ensured that tested dynamical system is in experimental cabin
On axial line；
S2, according to aircraft flight state, calculate outside wind speed excursion when electromotor runs, according to result of calculation
Determine experimental cabin air inlet pipeline diameter, and be used to control air mass flow from corresponding electromagnetic valve；
S3, install trouserss on engine body additional, body running environment during simulated flight, and by experimental cabin air inlet
Air inlet branch line on pipeline is directly connected to trouserss；
In S4, employing, cold constant temperature system replaces charge air cooler, to examine Performance Characteristics of the electromotor at a temperature of various inlet；
Air-cooled lubricating oil, cooling water radiator are replaced using water cooling heat exchanger, to examine electromotor under different lubricating oil, coolant temperature
The situation of change of engine performance；Cold constant temperature system and water cooling heat exchanger in adopting in the present invention, are water cooling plant, relatively
For air cooling equipment, it is easy to accomplish, low cost is easily installed. and water cooling heat exchanger includes water-cooled oil heat exchanger, cooling by water
Liquid heat exchanger；
S5, by water-cooled oil heat exchanger, cooling by water liquid heat exchanger, in cold thermostat, fuel tank, signals collecting case etc.
It is arranged in outside experimental cabin.Fuel tank should be away from pilot system other parts, to meet fire protection requirement；
S6, according to test demand, mounting arrangements engine operating parameter sensor on the engine, by signals collecting case
In modular converter, by the display of the signal input engine operating parameter monitoring system of engine operating parameter sensor acquisition
Module；
S7, according to the operating characteristic and installation site of the sensor of participating in the experiment of experimental cabin, in participating in the experiment in hyperthermia radiation area
Sensor installs cooling gas circuit additional；
S8, complete hardware connection after, check TT＆C system in electromotor control system, engine operating parameter monitoring system
The working condition of system, testing stand running state monitoring system etc., it is ensured that its normal operation；After confirming that each system is working properly, close
Test hatchcover is closed, test preparation terminates；
S9, electromotor warming up and performance test are carried out in surface air state first, open ejection system, cooling system,
It is at running under low flow rate condition；
S10, complete state of ground content of the test after, open low temperature air feed system, by temperature in experimental cabin be reduced to appoint
In business book after required value, ejection system working condition is improved, required according to flight speed, adjust experimental cabin induction air flow ratio, realized
Full ambient engine simulation under certain altitude；
S11, in the case where simulated environment is highly constant, require according in test mission book, cold constant temperature system in regulation,
The cooling water flow of water-cooled oil heat exchanger, cooling by water liquid heat exchanger etc., realizes electromotor in same height above sea level, different operating shape
Service behaviour certification test under state；
S12, complete the height performance test after, by first adjust experimental cabin analog temperature, afterwards adjust simulation test height
Order carry out the engine performance test under each height above sea level.Test shows, first adjusts experimental cabin analog temperature, adjust mould afterwards
The order for intending test height can reach the purpose of quick regulation.
The result of the test such as table 1 below institute of aviation turbocharging internal-combustion engines full ambient engine altitude test is carried out using said method
Show.
Table 1
As can be seen from the above table, pilot system of the invention can complete aeroturbine boosting internal combustion engine altitude simulation test.
The in test service condition of the electromotor low-pressure low-temperature under simulating high altitude environment.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, on the premise of without departing from the technology of the present invention principle, some improvement and deformation can also be made, these improve and deform
Also should be regarded as protection scope of the present invention.
Claims (1)
1. a kind of method that utilization aviation carries out full ambient engine altitude test with turbocharging internal-combustion engines full ambient engine altitude test system,
Characterized in that, comprising the following steps：
S1, according to electromotor design point, manufacture and design electromotor installation pedestal, to support tested dynamical system, it is ensured that tested
Dynamical system is on the axial line of experimental cabin；
S2, according to aircraft flight state, calculate outside wind speed excursion when electromotor runs, according to result of calculation determination
Experimental cabin air inlet pipeline diameter, and be used to control air mass flow from corresponding electromagnetic valve；
S3, install trouserss on engine body additional, body running environment during simulated flight, and by experimental cabin air inlet pipeline
On air inlet branch line be directly connected to trouserss；
In S4, employing, cold constant temperature system replaces charge air cooler, the Performance Characteristics with test engine at a temperature of various inlet；Using
Water cooling heat exchanger replaces air-cooled lubricating oil, cooling water radiator, starts under different lubricating oil, coolant temperature to test engine
The situation of change of machine performance；The water cooling heat exchanger includes water-cooled oil heat exchanger, cooling by water liquid heat exchanger；
S5, by water-cooled oil heat exchanger, cooling by water liquid heat exchanger, in cold thermostat, fuel tank, signals collecting case be arranged in
Outside experimental cabin；
S6, according to test demand, mounting arrangements engine operating parameter sensor on the engine, by signals collecting case, will
The display module of the signal input engine operating parameter monitoring system of engine operating parameter sensor acquisition；
S7, according to the operating characteristic and installation site of the sensor of participating in the experiment of experimental cabin, in the sensing of participating in the experiment in hyperthermia radiation area
Device installs cooling gas circuit additional；
S8, complete hardware connection after, check TT＆C system working condition, it is ensured that its normal operation；Confirm that each system just works
Chang Hou, closes test hatchcover, and test preparation terminates；
S9, electromotor warming up and performance test are carried out in surface air state, open ejection system and cooling system so as to be in
Run under low flow rate condition；
S10, complete state of ground content of the test after, open low temperature air feed system, temperature in experimental cabin is reduced to into preset value
Afterwards, ejection system working condition is improved, is required according to flight speed, adjusted experimental cabin induction air flow ratio, realize under certain altitude
Full ambient engine is simulated；
S11, in the case where simulated environment is highly constant, according to preset requirement, cold constant temperature system in regulation, the heat exchange of water-cooled lubricating oil
The cooling water flow of device, cooling by water liquid heat exchanger, realizes service behaviour of the electromotor under same height above sea level, different working condition
Certification test；
S12, complete the height performance test after, by first adjust experimental cabin analog temperature, afterwards adjust simulation test height it is suitable
Sequence carries out the engine performance test under each height above sea level；
The aviation turbocharging internal-combustion engines full ambient engine altitude test system includes low temperature air supply system, ejection system, cooling
System, experimental cabin, tested dynamical system and TT＆C system；
The low temperature air supply system, for building the low temperature test run environment under simulated environment height；
The ejection system for by experimental cabin air discharge, so as to realize upper low experimental enviroment；
The TT＆C system is used for the running status control for carrying out tested dynamical system and experimental cabin；
The cooling system includes cooling down gas circuit and cooling water channel, and the cooling gas circuit is used to produce using low temperature air feed system
Cryogenic gas cooling down high-temperature environment under non-high-temperature resistant part, the cooling water channel for water-filled radiator supply cool down
Water, the water-filled radiator are used for the Performance Characteristics for test engine at different conditions and provide test condition, are additionally operable to protect
Card engine health is normally run；
The low temperature air supply system includes low temperature air feed system, gas circuit and electromagnetic valve；The low temperature air feed system is used to make
Cryogenic gas is made, the gas circuit imports experimental cabin for the cryogenic gas for producing low temperature feedway, and the electromagnetic valve is used for
Control flows into the cryogenic gas flow of experimental cabin；
The ejection system includes injector and source of the gas gas circuit；The injector for by experimental cabin air discharge to build
Upper low experimental enviroment, the source of the gas gas circuit connection injector and experimental cabin；
The experimental cabin includes sealing cabin, air inlet pipeline, electromotor installation pedestal and gas exhaust piping；The sealing cabin is cylinder
Shape sealing structure, for placing tested dynamical system, the air inlet pipeline is the cooling pipelines into sealing cabin, described to start
Machine installation pedestal is used to support tested dynamical system, the gas exhaust piping to discharge test for electromotor to be run the waste gas for producing
Cabin；Measurand includes tested dynamical system, dynamometer machine and related actuator；
The water-filled radiator cold constant temperature system and water cooling heat exchanger in including, it is described in cold constant temperature system for for test start
Performance Characteristics of the machine at a temperature of various inlet provides test condition；The water cooling heat exchanger be used for for test different lubricating oil,
Under coolant temperature, the situation of change of engine performance provides test condition；
The TT＆C system includes electromotor control system, altitude simulation control system, temperature simulation control system, electromotor fortune
Line parameter monitoring system, experimental cabin running state monitoring system；
The electromotor control system is for according to default engine behavior manipulation associated components；
The altitude simulation control system is used for ambient pressure of the simulation test cabin under certain altitude；
The temperature simulation control system is used for ambient temperature of the simulation test cabin under certain altitude；
The engine operating parameter monitoring system is used to monitor engine operating parameter；
The experimental cabin operational factor monitoring system is used for monitoring test cabin operational factor；
The engine operating parameter monitoring system includes signals collecting case and display module, and the signals collecting case is for sending out
Motivation operational factor is acquired, and the display module is for carrying out display output to engine operating parameter；
The pilot system also includes fuel feed system, for for other module energy supplies of pilot system, including fuel tank and combustion
Oil pump.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101231215A (en) * | 2008-02-28 | 2008-07-30 | 北京航空航天大学 | Device and method for testing upper air performance of aircraft engine fuel oil system |
| CN102023096A (en) * | 2010-11-15 | 2011-04-20 | 北京航空航天大学 | Internal-flow high-altitude simulation test device and test method of aviation piston engine |
| CN203101056U (en) * | 2012-12-27 | 2013-07-31 | 东南大学 | Device for testing low-temperature low-air-pressure starting and operating characteristics of engine |
| CN103364197A (en) * | 2012-03-30 | 2013-10-23 | 广西玉柴机器股份有限公司 | An engine low-pressure simulation testing platform |
-
2015
- 2015-03-09 CN CN201510102304.3A patent/CN104634578B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101231215A (en) * | 2008-02-28 | 2008-07-30 | 北京航空航天大学 | Device and method for testing upper air performance of aircraft engine fuel oil system |
| CN102023096A (en) * | 2010-11-15 | 2011-04-20 | 北京航空航天大学 | Internal-flow high-altitude simulation test device and test method of aviation piston engine |
| CN103364197A (en) * | 2012-03-30 | 2013-10-23 | 广西玉柴机器股份有限公司 | An engine low-pressure simulation testing platform |
| CN203101056U (en) * | 2012-12-27 | 2013-07-31 | 东南大学 | Device for testing low-temperature low-air-pressure starting and operating characteristics of engine |
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