CN109282989A - A kind of supersonic speed engine testsand gas handling system - Google Patents
A kind of supersonic speed engine testsand gas handling system Download PDFInfo
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- CN109282989A CN109282989A CN201811164305.0A CN201811164305A CN109282989A CN 109282989 A CN109282989 A CN 109282989A CN 201811164305 A CN201811164305 A CN 201811164305A CN 109282989 A CN109282989 A CN 109282989A
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- 238000004088 simulation Methods 0.000 claims abstract description 78
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims abstract description 36
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 36
- 239000001301 oxygen Substances 0.000 claims abstract description 36
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 36
- 239000000446 fuel Substances 0.000 claims abstract description 35
- 239000007789 gas Substances 0.000 claims abstract description 35
- 230000001105 regulatory effect Effects 0.000 claims description 26
- 238000004891 communication Methods 0.000 claims description 5
- 238000012360 testing method Methods 0.000 abstract description 41
- 238000000034 method Methods 0.000 description 11
- 238000012546 transfer Methods 0.000 description 11
- 238000004364 calculation method Methods 0.000 description 9
- 239000012530 fluid Substances 0.000 description 8
- 238000002474 experimental method Methods 0.000 description 6
- 230000003068 static effect Effects 0.000 description 6
- 239000002699 waste material Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 3
- 239000003921 oil Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 239000010705 motor oil Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- QRSFFHRCBYCWBS-UHFFFAOYSA-N [O].[O] Chemical compound [O].[O] QRSFFHRCBYCWBS-UHFFFAOYSA-N 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000036760 body temperature Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- CNKHSLKYRMDDNQ-UHFFFAOYSA-N halofenozide Chemical compound C=1C=CC=CC=1C(=O)N(C(C)(C)C)NC(=O)C1=CC=C(Cl)C=C1 CNKHSLKYRMDDNQ-UHFFFAOYSA-N 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000001706 oxygenating effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
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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
- G01M15/02—Details or accessories of testing apparatus
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
A kind of supersonic speed engine testsand gas handling system, including supply source, temperature simulation unit, boiler-plate and supersonic nozzle；Supply source includes fuel delivery source, oxygen supply source, engine charge supply source, alcohol supply source；Temperature simulation unit includes tube body and shell, and it is first medium channel in tube body, the space between the outer wall of tube body and the inner wall of shell forms second medium channel that tube body, which is located at enclosure interior,；It is located in boiler-plate by spreadsheet engine；Supersonic nozzle includes the straight sections such as the entrance being sequentially coaxially fixedly connected, subsonic speed converging portion, initial supersonic expansion section and supersonic expansion section.Supersonic speed engine testsand gas handling system of the invention, the supersonic nozzle of Laval is set between temperature simulation unit and engine intake, when realizing supersonic speed engine and rocket engine ground test, the supersonic speed air-suction state simulation of supersonic speed engine.
Description
Technical field
The present invention relates to test measurement technical field, especially a kind of supersonic speed engine testsand gas handling system.
Background technique
Aero-engine need to do altitude simulation test on ground before being taken a flight test, when engine test, it is desirable that one group into
Gas parameter, including inlet total pressure, Induction air flow, air inlet oxygen content, inlet total temperature, engine oil oil mass are referred to as air inlet
State point, at the same reach setting value and stablize after, record its performance and parameter or examine its performance.With engine increasingly at
It is ripe, supersonic speed engine application it is increasingly extensive, on this basis, for aircraft especially unmanned plane supersonic speed engine with
And when rocket engine ground test, engine aspirating system needs to simulate the supersonic speed air-suction state of supersonic speed engine, existing hair
Motivation test bay technology there is no mature technology for the simulation of supersonic speed engine charge, when reach simultaneously for emulation mode
Stable state also without accurate theoretical determination method, causes test simulation effect poor, the test period is long, at high cost, the wasting of resources
Situation is serious.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the deficiencies of the prior art and provide a kind of supersonic speed engine testsand
Gas handling system.
The technical solution of the invention is as follows: a kind of supersonic speed engine testsand gas handling system, including supply source, temperature
Analogue unit, boiler-plate and supersonic nozzle；Supply source includes fuel delivery source, oxygen supply source, engine charge supply source,
Alcohol supply source；Temperature simulation unit includes tube body and shell, and it is first medium channel in tube body that tube body, which is located at enclosure interior,
Space between the outer wall of tube body and the inner wall of shell forms second medium channel；It is located in boiler-plate by spreadsheet engine；Supersonic
Fast jet pipe includes the straight sections such as the entrance being sequentially coaxially fixedly connected, subsonic speed converging portion, initial supersonic expansion section and supersonic speed
Expansion arc；Fuel delivery source is connected to by pipeline with by spreadsheet engine, and oxygen supply source and engine charge supply source lead to respectively
It crosses pipeline to be connected to the entrance in second medium channel, the outlet in second medium channel passes through pipeline and the entrance of supersonic nozzle etc.
The entrance of straight section is connected to, and the supersonic expansion section of supersonic nozzle is connected to by pipeline by the air inlet of spreadsheet engine, and alcohol supplies
It is connected to by pipeline with the entrance in first medium channel after igniter to source, the outlet in first medium channel and the external world are even
It is logical.
Further, during the straight sections such as entrance, subsonic speed converging portion, initial supersonic expansion section and supersonic expansion section be
Backlash swivel, the straight sections such as entrance, subsonic speed converging portion, initial supersonic expansion section are identical with the rotating shaft of supersonic expansion section；
The inner flow passage of subsonic speed converging portion is the axis surface of revolution of the circular arc continuously shunk, the inner flow passage of initial supersonic expansion section
Axis surface of revolution for the circular arc continuously expanded, the inner flow passage of supersonic expansion section are round table surface；Inside subsonic speed converging portion
Runner continuously shrinks the radius of circular arc and initial supersonic expansion intersegmental part runner identical, subsonic speed of continuously expanding the radius of circular arc
Converging portion connects the section that section is venturi with the inner flow passage of initial supersonic expansion section；The inner flow passage of supersonic expansion section
The bus of rotary table and the tail end that initial supersonic expansion intersegmental part runner continuously expands circular arc are tangent.
Further, it is connected to fuel delivery source and is provided with engine fuel supply flow rate tune on the pipeline of spreadsheet engine
It saves valve and engine fuel supplies shut-off valve.
Further, oxygen supply flow tune is provided on the pipeline of connection oxygen supply source and the entrance in second medium channel
Save valve and oxygen supply shut-off valve.
Further, engine is provided on the pipeline of connection engine charge supply source and the entrance in second medium channel
Air inlet supply pressure regulating valve.
Further, alcohol supply flow rate is provided on the pipeline of connection alcohol supply source and the entrance in first medium channel
Regulating valve and with alcohol supply shut-off valve, the outlet in first medium channel is in communication with the outside.
Further, the radius that the subsonic speed converging portion inner flow passage of jet pipe continuously shrinks circular arc is at least throat diameter
4 times.
Further, the revolution of the bus of the inner flow passage round table surface of the supersonic expansion section of jet pipe and supersonic expansion section
The angle of axis is more than or equal to 6 °, is less than or equal to 8 °.
The advantages of the present invention over the prior art are that:
1, supersonic speed engine testsand gas handling system of the invention, between temperature simulation unit and engine intake
The supersonic nozzle of Laval is set, when realizing supersonic speed engine and rocket engine ground test, supersonic speed engine
The simulation of supersonic speed air-suction state.
2, supersonic speed engine testsand gas handling system of the invention, will be by spreadsheet engine as in boiler-plate, boiler-plate
It using sealing state, is evacuated by exhaust injector, simulated engine is in the environmental pressure of different flying heights, passes through injection
Device active flow supply source provides injection air-flow for exhaust injector, and method is simple；It is realized by fuel delivery source to engine
Fuel feeding.
3, supersonic speed engine testsand gas handling system of the invention, by engine charge supply source simulated engine into
Throughput, inlet total pressure, meanwhile, it is that engine charge carries out oxygenating and by temperature simulation unit simulation by oxygen supply source
The intake air temperature of engine, realizes the real simulation of engine charge, and simulation precision is high.
4, alcohol supply source is arranged in supersonic speed engine testsand gas handling system of the invention, by igniter by alcohol
It lights and generates heat in temperature simulation unit with engine charge heat exchange, realize the adjusting of Engine Inlet Temperature.
5, supersonic speed engine testsand gas handling system of the invention realizes joint supply source by the way that various valves are arranged
Flow and pressure adjustable, and then realize multimode point simulation.
Detailed description of the invention
Fig. 1 is supersonic speed engine testsand air intake system structure schematic diagram of the invention.
Fig. 2 is the partial structurtes signal of the temperature simulation unit of supersonic speed engine testsand gas handling system of the invention
Figure.
Fig. 3 is the structural schematic diagram of the supersonic nozzle of supersonic speed engine testsand gas handling system of the invention.
Fig. 4 is the application method flow chart of supersonic speed engine testsand gas handling system of the invention.
Specific embodiment
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside", " up time
The orientation or positional relationship of the instructions such as needle ", " counterclockwise ", " axial direction ", " radial direction ", " circumferential direction " be orientation based on the figure or
Positional relationship is merely for convenience of description of the present invention and simplification of the description, rather than the device or element of indication or suggestion meaning must
There must be specific orientation, be constructed and operated in a specific orientation, therefore be not considered as limiting the invention.In addition, limit
There is the feature of " first ", " second " to can explicitly or implicitly include one or more of the features surely.Of the invention
In description, unless otherwise indicated, the meaning of " plurality " is two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection ", " abutting " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
The concrete meaning of language in the present invention.
The pressure in the present invention is identical as stagnation pressure, is stagnation pressure, and stagnation pressure is also known as stagnation pressure, refers to air velocity etc.
Pressure when closely related stagnation is to zero, is the sum of static pressure and dynamic pressure in air-flow, static pressure refers to object in static or linear uniform motion
When surface suffered by pressure, dynamic pressure, when object moves in a fluid, on the surface in the direction of positive fluid motion, fluid is complete
It is obstructed, fluid velocity herein is 0, and kinetic energy is changed into pressure energy, and pressure increases, and pressure is referred to as obstructed pressure entirely, referred to as
Total pressure or stagnation pressure, pressure, that is, static pressure of it and undisturbed place, difference, referred to as dynamic pressure.Temperature of the present invention and total temperature phase
Together, be total temperature, when total temperature refers to that a fluid is totally stationary with adiabatic process, its kinetic energy translate into it is interior can when reflect
Temperature, is the sum of dynamic temperature and static temperature, and static temperature refers to the temperature measured when thermometer and air-flow are opposing stationary.And dynamic temperature is to work as gas
Kinetic energy becomes thermal energy when stream is blocked, and increases gas temperature, raised temperature is dynamic temperature.
Supersonic speed engine testsand gas handling system of the present invention is exported in first medium feeder connection,
In first medium channel, second medium feeder connection is exported, in second medium channel, supersonic nozzle entrance, and outlet, Supersonic
Temperature sensor and pressure sensor are provided in fast jet pipe, the temperature sensor and pressure sensor should all airflow direction
Setting, stagnation pressure and total temperature for measure setup sensor section.
A kind of Supersonic engine testsand gas handling system is used for supersonic speed engine high-altitude multimode point simulation test,
It is especially adapted for use in the supersonic speed engine high-altitude multimode point simulation test of Mach 2 ship 1-5, the parameter packet of the state point
Include engine charge stagnation pressure, Induction air flow, air inlet oxygen ingredient, inlet total temperature, engine oil oil mass.
The Supersonic engine testsand gas handling system includes supply source, temperature simulation unit 200, boiler-plate 300 and super
Sonic nozzle 600.
The supply source includes fuel delivery source 110, oxygen supply source 120, engine charge supply source 130 and alcohol
Supply source 140.
The temperature simulation unit includes tube body 210 and shell 220, and the tube body 210 is located inside the shell 220,
It is first medium channel, the space shape between the outer wall of the tube body 210 and the inner wall of the shell 220 in the tube body 210
At second medium channel；When the temperature simulation unit 200 works, first medium circulates in first medium channel, and second is situated between
Matter circulates in second medium channel, and first medium temperature is higher than second medium, and the first medium and second medium pass through institute
The tube wall for stating tube body 210 realizes heat exchange.
It is located in the boiler-plate 300 by spreadsheet engine 400.
The supersonic nozzle 600 includes the straight sections 610 such as the entrance that is sequentially coaxially fixedly connected, subsonic speed converging portion 620,
Initial supersonic expansion section 640 and supersonic expansion section 650；The straight sections such as the entrance 610, subsonic speed converging portion 620 are initial super
Velocity of sound expansion arc 640 and supersonic expansion section 650 are hollow revolving body, the straight sections such as described entrance 610, subsonic speed converging portion
620, initial supersonic expansion section 640 is identical with the rotating shaft of supersonic expansion section 650；The subsonic speed converging portion 620 it is interior
Portion's runner is the axis surface of revolution of the circular arc continuously shunk, and the inner flow passage of the initial supersonic expansion section 640 is continuous expands
The axis surface of revolution for the circular arc opened, the inner flow passage of the supersonic expansion section 650 are round table surface；In subsonic speed converging portion 620
Portion's runner continuously shrinks the radius of circular arc and initial 640 inner flow passage of supersonic expansion section continuously to expand the radius of circular arc identical,
The subsonic speed converging portion 620 connects the section that section is venturi 630 with the inner flow passage of initial supersonic expansion section 640；It is super
The bus of the inner flow passage rotary table of velocity of sound expansion arc 650 and initial 640 inner flow passage of supersonic expansion section continuously expand circular arc
Tail end is tangent；The entrance in the first medium channel is connected to by pipeline with first medium source, and outlet is in communication with the outside；Described
The entrance in second medium channel is connected to second medium source, and outlet is connected to straight sections 610 such as the entrances, the supersonic nozzle work
When making, subsonic speed medium enters through nozzle entry, i.e. the straight sections entrance such as entrance, accelerates to venturi by subsonic speed converging portion and reaches
After velocity of sound, through initial supersonic expansion section initial bubble, preliminary expansion is completed when air-flow passes through current of spring area, continues to keep its expansion
Further make flow expansion to design point Mach number under conditions of angle is constant, by nozzle exit, that is, supersonic expansion section outlet spray
Out.
The fuel delivery source 110 is connected to described by spreadsheet engine 400 by pipeline, 120 He of oxygen supply source
The engine charge supply source 130 is connected to by pipeline with the entrance in second medium channel respectively, and second medium channel goes out
Mouth is connected to by the entrance of the straight sections 610 such as pipeline and the entrance of the supersonic nozzle 600, and the supersonic nozzle 600 surpasses
The outlet of velocity of sound expansion arc 650 is connected to by pipeline by the air inlet of spreadsheet engine, and the air inlet by spreadsheet engine 400 connects
Logical, to provide the engine supersonic speed charge flow rate of simulation by spreadsheet engine 400, air inlet Mach number, inlet total pressure and oxygen contain
Amount；The alcohol supply source 140 is connected to by pipeline with the entrance in first medium channel after igniter, and first medium is logical
The outlet in road is in communication with the outside, and alcohol is lighted burning and generates heat in the temperature simulation unit 200 with second by igniter
Second medium in medium channel exchanges heat to adjust the temperature of the second medium in second medium channel, thus realize engine into
Gas temperature simulation, engine charge simulation of the invention is true, and precision is high, and structure is simple.
It is connected to the fuel delivery source 110 and is provided with engine fuel supply on the pipeline of spreadsheet engine 400 with described
Flow control valve 510 is connected on the oxygen supply source 120 and the pipeline of the entrance in the second medium channel and aerobic confession is arranged
To flow control valve 530, it is connected on the engine charge supply source 130 and the pipeline of the entrance in second medium channel and is provided with
Engine charge supply pressure regulating valve 550 is connected on the pipeline of the entrance in the alcohol supply source 140 and first medium channel
Alcohol supply flow rate regulating valve 560 is provided with to realize the parameter regulation of each supply source, meets the simulation of multimode point.
Preferably, the engine testsand includes engine fuel supply shut-off valve 520,540 He of oxygen supply shut-off valve
Alcohol supplies shut-off valve 570, and engine fuel supply shut-off valve 520 setting is being connected to the fuel delivery source 110 and institute
It states by the pipeline of spreadsheet engine 400；The oxygen supply shut-off valve 540 setting be connected to the oxygen supply source 120 with it is described
On the pipeline of the entrance in second medium channel；Alcohol supply shut-off valve 570 setting be connected to the alcohol supply source 140 with
On the pipeline of the entrance in first medium channel.In the use process of engine testsand, the engine fuel supply stream is opened
The engine fuel supply shut-off valve 520 is opened before adjustable valve 510, is opened before opening the oxygen supply flow control valve 530
Oxygen supply shut-off valve 540 is opened, opens the alcohol supply shut-off valve 570 before opening the alcohol supply flow rate regulating valve 560；It closes
The engine fuel supply shut-off valve 520 is closed after closing the engine fuel supply flow rate regulating valve 510, closes the oxygen
Oxygen supply shut-off valve 540 is closed after supply flow rate regulating valve 530, closes institute after closing the alcohol supply flow rate regulating valve 560
Alcohol supply shut-off valve 570 is stated, to guarantee safety of the test bay under non-experimental state.
The application method of the supersonic speed engine testsand gas handling system, includes the following steps:
S100), engine charge stagnation pressure and oxygen content are adjusted
Engine charge supply pressure regulating valve and oxygen are adjusted according to the inlet total pressure of the first emulation mode point and oxygen content
Supply flow rate regulating valve makes the stagnation pressure and oxygen content and the of the second medium exported by the supersonic expansion section of supersonic nozzle
The inlet total pressure of one emulation mode point engine is identical with oxygen content.
S200), engine charge total temperature is adjusted
Alcohol supply flow rate regulating valve and initial igniter are adjusted according to the inlet total temperature of the first emulation mode point, lights wine
Essence makes alcohol burn, and the alcohol of burning exchanges heat in the second medium in first medium channel and second medium channel, makes by Supersonic
The total temperature of the second medium of the supersonic expansion section outlet of fast jet pipe is identical as the inlet total temperature of the first emulation mode point engine；
S210), alcohol supply flow rate regulating valve, starting are adjusted according to the highest operating condition value that temperature simulation unit can bear
Igniter, lighting alcohol makes alcohol burn, and the alcohol of burning changes in first medium channel and the second medium in second medium channel
Heat；
S220), state to the temperature simulation unit of step S310 is kept to enter steady-working state；
S230), according in the first emulation mode point, the second medium total temperature of second medium channel outlet, second medium leads to
The quality of second medium in road, the specific heat at constant pressure of second medium, inboard wall of tube body convection transfer rate, the inner wall of entire tube body
It is long-pending, the quality of first medium in first medium channel, the specific heat at constant pressure of first medium, tube wall convection transfer rate, entirely
The outer wall area of tube body and the second medium total temperature of second medium feeder connection, determine the supplying temperature of first medium；
S240), alcohol supply flow rate regulating valve is adjusted, by the first medium state in first medium channel by with temperature mould
The highest operating condition value supply that quasi-simple member can bear is adjusted to the predetermined value supply according to the first simulation test state point；
S250), keep the first medium in first medium channel according to the predetermined value of the first simulation test state point of experiment
Supply state to temperature simulation unit enters steady-working state, at this point, the supersonic expansion section by supersonic nozzle exports
Second medium total temperature it is identical as the inlet total temperature of the first emulation mode point engine.
S300), engine charge stagnation pressure is adjusted
Engine charge supply pressure regulating valve is adjusted according to the inlet total pressure of the first emulation mode point, is made by supersonic speed
The stagnation pressure of the second medium of the supersonic expansion section outlet of jet pipe is identical as the inlet total pressure of the first emulation mode point engine；
S310), engine charge supply pressure regulating valve is adjusted according to the inlet total pressure of the first emulation mode point；
S320), according in the first emulation mode point, the inlet total pressure of the first emulation mode point engine, step S250
In, first medium in first medium channel is according to the predetermined value supply state of the first simulation test state point of experiment to temperature mould
When quasi-simple member enters steady-working state, the stagnation pressure of the supersonic expansion section outlet of supersonic nozzle, the first emulation mode point hair
The charge flow rate of motivation, second medium gas constant, the inlet total temperature of the first emulation mode point engine, supersonic nozzle is interior to be situated between
The volume of matter determines that the time for entering steady operation from step S250 to supersonic nozzle, the time are Tw1, from step S250
T afterwardsw1Second, by the stagnation pressure and the first emulation mode point engine of the second medium that the supersonic expansion section of supersonic nozzle exports
Inlet total pressure it is identical；
Tw1Enter steady-working state calculation formula according to supersonic nozzle to determine；Supersonic nozzle enters steady operation shape
State calculation formula are as follows:
In formula: TwEnter the time of the operation is stable, unit s for supersonic nozzle；ptiStart for the first emulation mode point
The inlet total pressure of machine, unit Mpa are known quantity；pt1jFor in step S250, first medium in first medium channel according to
When testing predetermined value supply state to the temperature simulation unit of the first simulation test state point and entering steady-working state, supersonic speed
The stagnation pressure of the supersonic expansion section outlet of jet pipe, unit Mpa are known quantity；qmaiFor the first emulation mode point engine into
Throughput, unit kg/s are known quantity；R is second medium gas constant, and it is known quantity that unit, which is J/ (kgK),；T is
The inlet total temperature of one emulation mode point engine, unit K are known quantity；V is the volume of medium in supersonic nozzle, unit
For m3, it is known quantity.
S400), engine ignition
Engine fuel supply flow rate regulating valve is adjusted according to the fuel demand amount of engine the first emulation mode point, makes to fire
The fuel oil of oily supply source supply is identical as the fuel demand amount of engine the first emulation mode point, and engine ignition carries out first
The intake simulation of emulation mode point is tested to the state point intake simulation off-test.
S500), the simulation test of N emulation mode point
Oxygen supply flow control valve, engine charge supply pressure regulating valve, alcohol supply flow rate regulating valve are adjusted respectively
It is the stagnation pressure for the second medium for exporting the supersonic expansion section of supersonic nozzle, total with engine fuel supply flow rate regulating valve
Mild oxygen content is identical as the inlet total pressure of N emulation mode point engine, total temperature and oxygen content, the combustion of fuel delivery source supply
Oil is identical as the fuel demand of N emulation mode point engine；Wherein, N >=2；Start the examination of engine nth state point intake simulation
It tests to the state point intake simulation off-test.
S510), oxygen supply flow control valve is adjusted, the second medium for exporting the supersonic expansion section of supersonic nozzle
Oxygen content is identical as the oxygen content of N emulation mode point engine；
S520), according in N emulation mode point, the second medium total temperature of second medium channel outlet, second medium channel
The quality of interior second medium, the specific heat at constant pressure of second medium, inboard wall of tube body convection transfer rate, the inner wall area of entire tube body,
The quality of first medium in first medium channel, the specific heat at constant pressure of first medium, tube wall convection transfer rate, entire tube body
Outer wall area and second medium feeder connection second medium total temperature, determine the supplying temperature of first medium；
S530), alcohol supply flow rate regulating valve is adjusted, by the first medium state in first medium channel by the first simulation
The predetermined value supply of trystate point is adjusted to the predetermined value supply according to N simulation test state point；
S540), the first medium in first medium channel is kept to supply according to the predetermined value of experiment N simulation test state point
Enter steady-working state to state to temperature simulation unit, at this point, exported by the supersonic expansion section of supersonic nozzle
The total temperature of second medium is identical as the inlet total temperature of N emulation mode point engine；
S550), according to the inlet total pressure of N emulation mode point adjust engine charge supply pressure regulating valve, make by
The inlet total pressure phase of the stagnation pressure and N emulation mode point engine of the second medium of the supersonic expansion section outlet of supersonic nozzle
Together；
S551), engine charge supply pressure regulating valve is adjusted according to the inlet total pressure of N emulation mode point；
S552), according in N emulation mode point, the inlet total pressure of N emulation mode point engine, in step S540,
First medium in first medium channel is according to the predetermined value supply state of experiment N simulation test state point to temperature simulation list
Member enter steady-working state, supersonic nozzle supersonic expansion section outlet stagnation pressure, N emulation mode point engine into
Throughput, second medium gas constant, the inlet total temperature of N emulation mode point engine, the volume of medium in supersonic nozzle
Determine that the time for entering steady operation from step S540 to supersonic nozzle, the time are TwN, from T after step S540wNSecond,
The air inlet of the stagnation pressure and N emulation mode point engine of second medium by the supersonic expansion section outlet of supersonic nozzle is total
It presses identical；
TwNEnter steady-working state calculation formula according to supersonic nozzle to determine；Supersonic nozzle enters steady operation shape
State calculation formula are as follows:
In formula: TwNEnter the time of the operation is stable, unit s for supersonic nozzle；ptiNStart for N emulation mode point
The inlet total pressure of machine, unit Mpa are known quantity；pt1jNFor in step S540, first medium in first medium channel according to
Predetermined value supply state to the temperature simulation unit for testing N simulation test state point enters steady-working state, supersonic speed spray
The stagnation pressure of the supersonic expansion section outlet of pipe, unit Mpa are known quantity；qmaiNFor N emulation mode point engine into
Throughput, unit kg/s are known quantity；R is second medium gas constant, and it is known quantity that unit, which is J/ (kgK),；TNFor
The inlet total temperature of N emulation mode point engine, unit K are known quantity；V is the volume of medium in supersonic nozzle, unit
For m3, it is known quantity.
S560), engine fuel supply flow rate is adjusted according to the fuel demand amount of engine N emulation mode point to adjust
Valve, the fuel oil for supplying fuel delivery source is identical as the fuel demand amount of engine N emulation mode point, starts engine N
State point intake simulation is tested to the state point intake simulation off-test.
S600), step S500 is repeated until after all emulation mode experimental tests, engine misses close engine
Fuel delivery flow control valve, oxygen supply flow control valve, engine charge supply pressure regulating valve and alcohol supply flow rate tune
Save valve.
Preferably, the highest operating condition value that temperature simulation unit can bear is first Jie that temperature simulation unit can bear
Maximum pressure, maximum temperature and the maximum flow of matter；The parameter of the predetermined value of simulation test state point includes medium inlet and goes out
The pressure of mouth, the flow of medium and the temperature of medium.
Preferably, the radius that 620 inner flow passage of subsonic speed converging portion of the jet pipe 600 continuously shrinks circular arc is at least institute
4 times for stating 630 diameter of venturi, to reduce the pressure loss of medium.
Preferably, the bus of the inner flow passage round table surface of the supersonic expansion section 650 of the jet pipe 600 and the supersonic speed
The angle of the rotating shaft of expansion arc 650 is more than or equal to 6 °, is less than or equal to 8 °, to reduce pressure loss when media expansion.
Preferably, in step S320, state to the temperature simulation unit of step S310 is kept to enter steady-working state, institute
The time needed is T1；Keep the first medium in first medium channel according to the first simulation test state point of experiment in step S350
Predetermined value supply state to temperature simulation unit enter steady-working state, the required time is T2；It is kept in step S650
First medium in first medium channel is according to the predetermined value supply state of experiment N simulation test state point to temperature simulation
Unit enters steady-working state, and the required time is TN；
T1, T2And TNEnter steady-working state calculation formula according to temperature simulation unit to determine；Temperature simulation unit into
Enter steady-working state calculation formula are as follows:
In formula: TxEnter the time of steady-working state, unit s for temperature simulation unit；M is the matter of entire tube body
Amount, unit kg are known quantity；cmpFor the specific heat at constant pressure of tube body, unit J/kgK is known quantity；hhFor inboard wall of tube body pair
The coefficient of heat transfer is flowed, unit is W/ (m2It K), is known quantity；AsiFor the inner wall area of entire tube body, unit m2, it is known quantity；
mhFor the quality of the first medium in first medium channel, unit kg is known quantity；cphFor the level pressure ratio of first medium
Heat, unit J/kgK are known quantity；hcFor tube wall convection transfer rate, unit is W/ (m2It K), is known quantity；
AseFor the outer wall area of entire tube body, unit m2, it is known quantity；mcFor the matter of the second medium in second medium channel
Amount, unit kg are known quantity；cpcFor the specific heat at constant pressure of second medium, unit J/kgK is known quantity.
Preferably, step S330 is according in the first emulation mode point, the second medium total temperature of second medium channel outlet, and
The quality of second medium in second medium channel, the specific heat at constant pressure of second medium, inboard wall of tube body convection transfer rate, entire tube body
Inner wall area, the quality of first medium, the specific heat at constant pressure of first medium, tube wall heat convection system in first medium channel
Number, the outer wall area of entire tube body and the second medium total temperature of second medium feeder connection, determine the supplying temperature of first medium,
At this point, the supplying temperature of first medium is Thi1；
In step S630, according in N emulation mode point, the second medium total temperature of second medium channel outlet, second is situated between
The quality of second medium in matter channel, the specific heat at constant pressure of second medium, inboard wall of tube body convection transfer rate, the inner wall of entire tube body
Area, the quality of first medium, the specific heat at constant pressure of first medium, tube wall convection transfer rate are whole in first medium channel
The outer wall area of a tube body and the second medium total temperature of second medium feeder connection, determine the supplying temperature of first medium, at this point,
The supplying temperature of first medium is ThiN；
Thi1And ThiNDetermined according to temperature simulation unit hot-fluid input temp formula；Temperature simulation unit hot-fluid input temperature
Spend formula are as follows:
In formula:
ThixFor the supplying temperature of first medium, unit K；TcoIt is single for the second medium total temperature of second medium channel outlet
Position is K, is known quantity；mcFor the quality of second medium in second medium channel, unit kg is known quantity；cpcFor second medium
Specific heat at constant pressure, unit J/kgK, be known quantity；hhFor inboard wall of tube body convection transfer rate, unit is W/ (m2K), it is
Known quantity；AsiFor the inner wall area of entire tube body, unit m2, it is known quantity；mhFor first medium in first medium channel
Quality, unit kg are known quantity；cphFor the specific heat at constant pressure of first medium, unit J/kgK is known quantity；hcFor tube body
Outer wall convection transfer rate, unit are W/ (m2It K), is known quantity；AseFor the outer wall area of entire tube body, unit m2, it is
Known quantity；TciFor the second medium total temperature of second medium feeder connection, unit K is known quantity.
Preferably, it when carrying out engine charge simulation test, is under flying height environmental pressure by spreadsheet engine, it can be with
Pressure in boiler-plate is extracted using air-extractor, it is preferable that air-extractor is vacuum tank or injector.
For supersonic speed engine testsand gas handling system of the invention, in addition to the advantageous effects mentioned before,
Application method has following advantageous effects:
1, using first adjusting inlet total pressure and oxygen content, then inlet total temperature is adjusted, then after accurate adjustment inlet total pressure, oil-feeding points
The mode of fire, adjustment speed is fast, when saving the adjusting of the simulation of test bay engine charge and the simulation of flying height environmental pressure
Between, experimentation cost is reduced, energy waste is avoided.
2, by a large amount of test data and creativeness to curve-fitting data, it is determined that supersonic nozzle medium fills
Expire and enter steady-working state calculation formula, can accurately determine that supersonic nozzle enters the time of steady-working state, greatly
Width shortens test period, reduces experimentation cost, avoids energy waste.
3, in the use process of temperature simulation unit, it is creative on startup, can first be held using temperature simulation unit
The highest operating condition value received inputs thermal current to heat exchanger, so that the inner tube of temperature simulation unit is operated at full capacity, with most fast speed
It warms up, it is fast that tube body temperature promotes speed, uniformity of temperature profile, then is adjusted to test predetermined value by full load condition, into steady
Determine the working condition time and substantially shortens.
4, in the use process of temperature simulation unit, pass through the quasi- to data and curves of a large amount of test data and creativeness
It closes, it is determined that the temperature simulation unit of high accuracy enters steady-working state calculation formula, being capable of accurate temperature simulation
Unit enters the time of steady-working state, substantially shortens test period, reduces experimentation cost, avoids energy waste.
5, in the use process of temperature simulation unit, pass through the quasi- to data and curves of a large amount of test data and creativeness
It closes, it is determined that the temperature simulation unit hot-fluid of high accuracy inputs calculation formula, the temperature simulation unit heat that can accurately determine
Input temp is flowed, substantially shortens test period, reduces experimentation cost, avoid energy waste.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " illustrative examples ",
The description of " example ", " specific example " or " some examples " etc. means specific features described in conjunction with this embodiment or example, knot
Structure, material or feature are included at least one embodiment or example of the invention.In the present specification, to above-mentioned term
Schematic representation may not refer to the same embodiment or example.Moreover, specific features, structure, material or the spy of description
Point can be combined in any suitable manner in any one or more of the embodiments or examples.
Although an embodiment of the present invention has been shown and described, it will be understood by those skilled in the art that: not
A variety of change, modification, replacement and modification can be carried out to these embodiments in the case where being detached from the principle of the present invention and objective, this
The range of invention is defined by the claims and their equivalents.
Claims (8)
1. a kind of supersonic speed engine testsand gas handling system, which is characterized in that including supply source, temperature simulation unit, simulation
Cabin and supersonic nozzle；
Supply source includes fuel delivery source, oxygen supply source, engine charge supply source, alcohol supply source；
Temperature simulation unit includes tube body and shell, and tube body is located at enclosure interior, is first medium channel in tube body, tube body it is outer
Space between wall and the inner wall of shell forms second medium channel；
It is located in boiler-plate by spreadsheet engine；
Supersonic nozzle includes the straight sections such as the entrance being sequentially coaxially fixedly connected, subsonic speed converging portion, initial supersonic expansion section
With supersonic expansion section；
Fuel delivery source is connected to by pipeline with by spreadsheet engine, and oxygen supply source and engine charge supply source pass through pipe respectively
Road is connected to the entrance in second medium channel, and the outlet in second medium channel passes through the straight sections such as the entrance of pipeline and supersonic nozzle
Entrance connection, the supersonic expansion section of supersonic nozzle is connected to by pipeline by the air inlet of spreadsheet engine, alcohol supply source
It is connected to by pipeline with the entrance in first medium channel after igniter, the outlet in first medium channel is in communication with the outside.
2. supersonic speed engine testsand gas handling system according to claim 1, it is characterised in that: the straight sections such as entrance, it is sub-
Velocity of sound converging portion, initial supersonic expansion section and supersonic expansion section are hollow revolving body, the straight sections such as entrance, subsonic speed convergence
Section, initial supersonic expansion section are identical with the rotating shaft of supersonic expansion section；The inner flow passage of subsonic speed converging portion is continuous receives
The axis surface of revolution of the circular arc of contracting, the inner flow passage of initial supersonic expansion section are the axis surface of revolution for the circular arc continuously expanded,
The inner flow passage of supersonic expansion section is round table surface；Subsonic speed converging portion inner flow passage continuously shrinks the radius of circular arc and initially surpasses
The radius that velocity of sound expansion arc inner flow passage continuously expands circular arc is identical, the inside of subsonic speed converging portion and initial supersonic expansion section
Runner connects the section that section is venturi；In the bus of the inner flow passage rotary table of supersonic expansion section and initial supersonic expansion section
The tail end that portion's runner continuously expands circular arc is tangent.
3. supersonic speed engine testsand gas handling system according to claim 1, it is characterised in that: connection fuel delivery source
Be provided on the pipeline by spreadsheet engine engine fuel supply flow rate regulating valve and engine fuel supply shut-off valve.
4. supersonic speed engine testsand gas handling system according to claim 1, it is characterised in that: connection oxygen supply source
Oxygen supply flow control valve and oxygen supply shut-off valve are provided with on the pipeline of the entrance in second medium channel.
5. supersonic speed engine testsand gas handling system according to claim 1, it is characterised in that: connection engine charge
Engine charge supply pressure regulating valve is provided on the pipeline of supply source and the entrance in second medium channel.
6. supersonic speed engine testsand gas handling system according to claim 1, it is characterised in that: connection alcohol supply source
Be provided on the pipeline of the entrance in first medium channel alcohol supply flow rate regulating valve and with alcohol supply shut-off valve, first be situated between
The outlet in matter channel is in communication with the outside.
7. supersonic speed engine testsand gas handling system according to claim 1, it is characterised in that: the subsonic speed of jet pipe is received
It holds back intersegmental part runner and continuously shrinks the radius of circular arc and be at least 4 times of throat diameter.
8. supersonic speed engine testsand gas handling system according to claim 1, it is characterised in that: the supersonic speed of jet pipe is swollen
The angle of the rotating shaft of the bus and supersonic expansion section of swollen section of inner flow passage round table surface is more than or equal to 6 °, is less than or equal to 8 °.
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