CN106988930A - The gas generator and experimental rig of powder gases experiment are swallowed suitable for engine - Google Patents
The gas generator and experimental rig of powder gases experiment are swallowed suitable for engine Download PDFInfo
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- CN106988930A CN106988930A CN201710409335.2A CN201710409335A CN106988930A CN 106988930 A CN106988930 A CN 106988930A CN 201710409335 A CN201710409335 A CN 201710409335A CN 106988930 A CN106988930 A CN 106988930A
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- gas generator
- combustion chamber
- engine
- igniter
- type ball
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The present invention provides a kind of gas generator and experimental rig that powder gases experiment is swallowed suitable for engine, and gas generator includes：Igniter, is arranged on one end of the gas generator；Combustion chamber, the fuel chamber is mounted therein with many powder columns, and many powder columns are contacted with the igniter；Collection chamber, is arranged at the outside of the combustion chamber and coats the combustion chamber；And jet pipe, the other end of the gas generator is arranged on, and connect with the collection chamber.The gas generator and experimental rig controllability of the present invention is strong, work safety, stably, can accurately the weapon such as simulated rocket bullet, guided missile jet pipe spray high-temperature gas environment, it can meet when aircraft and engine are shaped, the engine to be carried out swallows powder gases experiment or suction weapon exhaust system test, fills up the domestic vacancy in the special test field.
Description
Technical field
It is more particularly to a kind of to swallow powder gases experiment suitable for engine the present invention relates to Engine Block Test device field
Gas generator.
Background technology
In operation, the high-temperature tail gas produced by weapons such as aircraft its own transmission guided missile, rocket projectiles is easily sent out by aircraft
Motivation is sucked, and Engine Inlet Temperature is significantly jumped, and is caused engine charge distortion, penalty, is caused power loss,
Engine stabilizer operating envelope is reduced, or even engine stall, surge, flame-out, flame-out in flight can be caused, is not only bungled the chance of winning a battle,
It may can also cause aviation accident.Therefore, when engine or aircraft are shaped, engine must be carried out and swallow powder gases experiment.
Engine swallows powder gases experiment, also known as sucks aircraft weapon exhaust system test, and its principle is：In ground experiment
Platform, engine sucks the high-temperature flue gas discharged by a kind of special experimental rig of the weapons such as simulated rocket bullet, guided missile, winged to simulate
The high-temperature tail gas that machine sucks the weapons such as its own transmission guided missile, rocket projectile and produced, to determine that the suction of engine acceptable is military
The device exhaust work limit and influence of the powder gases to engine performance is swallowed, and examine the working condition of control system.But
Current experimental rig can not carry out flow control to the high-temperature tail gas that simulation is produced, in test with certain danger.
The content of the invention
It is an object of the invention to for the deficiencies in the prior art there is provided a kind of flow gamut is adjustable, temperature,
Pressure controllable, is easy to operation, it is easy to control, safe and reliable fuel gas generator device.
The purpose of the present invention can be achieved through the following technical solutions：
On the one hand, the present invention provides a kind of gas generator that powder gases experiment is swallowed suitable for engine, including：
Igniter, is arranged on one end of the gas generator；
Combustion chamber, the fuel chamber is mounted therein with many powder columns, and many powder columns are contacted with the igniter；
Collection chamber, is arranged at the outside of the combustion chamber and coats the combustion chamber；And
Jet pipe, is arranged on the other end of the gas generator, and connect with the collection chamber.
In an embodiment of the gas generator of the present invention, the igniter includes：Harness, electrical connection
Device, medicine box, ignition charge, celluloid and connecting bolt component.
In another embodiment of the gas generator of the present invention, the harness and the medicine box pass through described
Electric connector is connected, and the ignition charge and the celluloid are located in the medicine box, and the connecting bolt component is located at described
The periphery of medicine box.
In another embodiment of the gas generator of the present invention, the arrangement mode of many powder columns is interior real row
Row.
In another embodiment of the gas generator of the present invention, a grate is provided with the combustion chamber, with solid
The fixed many powder columns.
In another embodiment of the gas generator of the present invention, the combustion chamber is relative with the igniter
One end has multiple first perforates.
In another embodiment of the gas generator of the present invention, in addition to smoke elimination room, the smoke elimination room is arranged on
Between the combustion chamber and the collection chamber, and coat the combustion chamber.
In another embodiment of the gas generator of the present invention, one end of the smoke elimination room has multiple second to open
Hole, the other end has multiple 3rd perforates.
On the other hand, the present invention also provides a kind of experimental rig that powder gases experiment is swallowed suitable for engine, including
Foregoing gas generator, blast pipe and multiple V-type ball valves, the blast pipe have an entrance and a multiple outlets, the entrance and
The jet pipe is connected, and the V-type ball valve is arranged on the multiple outlet to control the capacity of the multiple outlet respectively.
In an embodiment of the experimental rig of the present invention, experimental rig also includes a control system, to control
State unlatching and the aperture of the multiple V-type ball valve of ignition system.
Design principle of the fuel gas generator device of the present invention according to solid propellant rocket, increases collection chamber, the row of improvement
Gas system, and set up V-type ball valve in exhaust outlet, controllability is strong, work safety, stably, can the accurate force such as simulated rocket bullet, guided missile
Device jet pipe sprays the environment of high-temperature gas, can meet in aircraft and engine sizing, the engine to be carried out swallows gunpowder
Gas test or suction weapon exhaust system test, fill up the domestic vacancy in the special test field.
Brief description of the drawings
Fig. 1 is the structural representation of the experimental rig of one embodiment of the present invention；
Fig. 2 be Fig. 1 shown in experimental rig in gas generator structural representation；
Fig. 3 be Fig. 2 shown in gas generator in igniter structural representation；
Fig. 4 be Fig. 2 shown in gas generator in powder column structural representation；
Fig. 5 be Fig. 2 shown in gas generator in powder column arrangement and grate structural representation and its Section A-A figure；
Fig. 6 be Fig. 2 shown in gas generator in combustion chamber structural representation；
Fig. 7 be Fig. 2 shown in gas generator in smoke elimination room structural representation.
Wherein, description of reference numerals is as follows：
1：V-type ball valve
2：Gas generator
3：V-type ball valve
4：Control system
21：Igniter
22：Gas generator bottom plate
23：Powder column
24：Grate
25：Thermal insulation layer
26：Combustion chamber
27：Smoke elimination room
28：Collection chamber
29：Jet pipe
211：Harness
212：Electric connector
213：Medicine box
214：Celluloid
215：Ignition charge
216：Connecting bolt component
Embodiment
Technical scheme is described further below according to specific embodiment.Protection scope of the present invention is not limited
In following examples, these examples are enumerated merely for exemplary purpose without limiting the present invention in any way.
The experimental rig of the present invention is to swallow powder gases test specification according to engine, passes through inspection information, side
The effort of the multiple directions such as case demonstration, numerical computations, verification experimental verification, what final design went out meets the special dress of experiment of test requirements document
Put.
Fig. 1 is the structural representation of the experimental rig of one embodiment of the present invention, as shown in Figure 1, it is adaptable to engine
Swallowing the experimental rig of powder gases experiment includes gas generator 2, blast pipe, V-type ball valve 1, V-type ball valve 3 and control system
4。
Fig. 2 be Fig. 1 shown in experimental rig in gas generator structural representation, as shown in Fig. 2 gas generator 2
Including igniter 21, gas generator bottom plate 22, combustion chamber 26, smoke elimination room 27, collection chamber 28 and jet pipe 29.
Igniter 21 is arranged on one end of gas generator 2, and is fixed on gas generator bottom plate 22.Fig. 3 is Fig. 2
The structural representation of igniter in shown gas generator, as shown in figure 3, igniter 21 includes harness 211, electricity
Connector 212, medicine box 213, celluloid 214, ignition charge 215 and connecting bolt component 216, harness 211 and medicine box 213
Connected by electric connector 212, ignition charge 215 and celluloid 214 are located in medicine box 213, and connecting bolt component 216 is located at medicine
The periphery of box 213.Electric connector 212 is used to harness 211 importing medicine box 213, the one end of harness 211 connection control electricity
In ignition charge 215 in cable, other end embedment medicine box 213, celluloid (inflammable) 214 is coated on the surface of ignition charge 215, rises
Combustion-supporting effect.Playing ignition principle is：Firing command is sent by control system 4, harness 211 is received and carried out a little after signal
Fire, ignition charge 215 and celluloid 214 are ignited rapidly, and the celluloid 214 caught fire covers whole ignition charge 215, makes igniting
The rapid burning comprehensively of medicine 215, produces a large amount of high-temperature high-pressure fuel gas into combustion chamber 26, ignite rapidly powder column within the most short time
23, complete gas generator 2 and light a fire.The structure of igniter 21 is identical with the ignition system of solid propellant rocket with principle.
Combustion chamber 26 is the core chamber of gas generator 2, it typically is cylindrical shape, is also secured at gas generator bottom plate
On 22.Many powder columns 23 are installed, igniter 21 is communicated with combustion chamber 26 in combustion chamber 26, many powder columns 23 and igniter
21 contacts.
Powder column 23 used is cast powder charge in the experimental rig of the present invention, as shown in Figure 4 by structure.In combustion chamber 26
Powder column is combined by n roots, outside diameter d, internal diameter d0Powder column composition, arrangement mode is interior real arrangement, and powder column is divided into three layers, and centre separates
Come, combustion system is interior external combustion, wherein parameter n, d, d0Computational methods reference《Design of Solid Propellant Rocket Engine》(Wang Yuanyou
Deng work).
As shown in fig. 6, being the high-temperature high-pressure fuel gas stabilization for making reaction generation, safe and reliable outflow, in combustion chamber 26
Afterbody (one end relative with igniter 21) opens up n1Individual a diameter of d1Equally distributed first perforates of mm so that combustion gas is therefrom
Smoothly outflow.First perforate can be opened on the side wall of combustion chamber 26, can be also opened on the end wall of combustion chamber 26.
The design principle of the housing of combustion chamber 26 is identical with solid propellant rocket, and the thickness of shell of combustion chamber 26 is designed as
Tmm, because of the requirement of combustion face burning, need to reserve l in the wall of outermost layer powder column 23 Yu combustion chamber 261Mm distance.
For fixed powder column 23, one grate 24 can be set at the middle part of combustion chamber 26, as shown in figure 5, grate 24 also has
There are multiple perforates and corresponding with many powder columns 23, for supporting, fix powder column, it is to avoid powder column directly contacts generation abrasion.
Smoke elimination room 27 is arranged between combustion chamber 26 and collection chamber 28, and substantially coats combustion chamber 26, is also secured at combustion
On gas generator bottom plate 22.The major function of smoke elimination room 27 is the cigarette for eliminating the gas that double base propellant burning is produced.
As shown in fig. 7, n is respectively opened in the rear and front end in smoke elimination room 27, same selection2Individual a diameter of d2Mm equally distributed
Two perforates and the 3rd perforate, are easy to the combustion gas discharge by smoke elimination room 27.Design principle is identical with combustion chamber 26, and its housing is thick
Degree is designed as tmm.
n、d、d0For powder column parameter, calculated according to parameters such as burning section, burning velocity, burning time, gaseous-pressures
Draw；n1、d1, t be combustion-chamber parameter, with the relating to parameters such as gaseous-pressure, flow, flow velocity；n2、d2It is smoke elimination room parameter, equally
With the relating to parameters such as gaseous-pressure, flow, flow velocity.Above parameter calculates complicated, specific method and process《Solid propellant rocket
Design》It is described in detail in (work such as Wang Yuanyou).
Collection chamber 28 is arranged at the outside of combustion chamber 26 and smoke elimination room 27 and coated, and its major function is to collect biradical
The high-temperature gas that propellant combustion is produced, its housing is the housing of gas generator 2, therefore collection chamber 28 is also referred to as combustion gas hair
The exocoel of raw device 2.
Jet pipe 29 is arranged on the other end of gas generator 2, and is connected with collection chamber 28, with outside conveying high-temperature gas.
Collection chamber 28 is except in addition to the position that jet pipe 29 is connected, essentially sealing state.
Blast pipe is located at the exit of gas generator, and with an entrance and multiple outlets, entrance is connected simultaneously with jet pipe 29
And size matches with jet pipe 29, V-type ball valve is respectively arranged to control the capacity of multiple outlets on multiple outlets, and it is led
Want the exhaust that function is the weapons such as simulated missile, rocket projectile, and the control extraction flow of gamut.
As shown in figure 1, blast pipe has two outlets (outlet 1 and outlet 2), V-type ball valve 1 and V-type ball valve 3 are each controlled
Laid with engine intake by central coaxial line and certain distance one outlet, the outlet of V-type ball valve 1；V-type ball valve 3 exports remote
Engine intake leads to elsewhere, and control line of the control system 4 respectively with V-type ball valve 1, gas generator 2, V-type ball valve 3 is connected
Connect.
The aperture of V-type ball valve 1 and V-type ball valve 3 can be adjusted by control system 4, specific regulative mode is as follows：
1) closing V-type ball valve 1, standard-sized sheet V-type ball valve 3, the flow for now exporting 1 is 0, and the flow of outlet 2 is to design most
Big value Qmax。
(2) keep the full-gear of V-type ball valve 3 constant, the aperture of regulation V-type ball valve 1 is used as one using every x% apertures
State, finally to the standard-sized sheet of V-type ball valve 1.The flow of this process middle outlet 1 is stepped up as 0.5Q from 0max, the flow of outlet 2 is then
By QmaxProgressively it is changed into 0.5Qmax。
(3) aperture of valve is further adjusted, this process keeps the full-gear of V-type ball valve 1 constant, the state of V-type ball valve 3
Full-shut position is then gradually become by standard-sized sheet.The flow of this procedure exit 1 is from 0.5QmaxContinue to be increased to maximum Qmax；And export 2
Flow is then by 0.5QmaxGradually it is kept to 0.
By regulation and control above, experimental rig of the invention realizes flow from 0 to QmaxControl.
Control system 4 is by signal-transmitting cable, system software and control interface composition, and major control igniting device 21 is opened
Open, the aperture of V-type ball valve 1,3.
When being tested, control system 4 sends " igniting " and instructed to gas generator 2, and gas generator 2 is lighted a fire, opened
Begin to burn, the combustion gas of generation is discharged by V-type ball valve 1 and V-type ball valve 3；Simultaneously according to test requirements document control system 4 by fixed
The aperture of program regulation V-type ball valve 1 and V-type ball valve, is controlled to the gas flow, temperature, pressure produced by gas generator 2
System.
The experimental rig of the present invention passes through numerical simulation, and successfully passes verification experimental verification, and controllability is strong, work safety,
It is stable, fault-free in experiment, and have no adverse effect, as a result prove feasible.
Numerical result is consistent with result of the test, specific as follows：
1) when the aperture of V-type ball valve 1 and V-type ball valve 3 is constant, its flow, temperature, speed, pressure distribution are basicly stable.
2) with the increase of the aperture of V-type ball valve 1, the aperture of V-type ball valve 3 is constant, and the mass flow approximately linear of outlet 1 increases
Plus, the mass flow approximately linear of outlet 2 is reduced.
3) with the increase of the aperture of V-type ball valve 1, the aperture of V-type ball valve 3 is constant, and outlet 1 pressure increase, 2 pressure of outlet subtract
It is small.Because outlet 1 aperture increase, receives and expands by acutely becoming gentle, expansion ratio is less and less, then the pressure of outlet 1
Just gradually increase；And for outlet 2, because the reduction of mass flow, pressure is gradually lowered.
4) with the increase of the aperture of V-type ball valve 1, the aperture of V-type ball valve 3 is constant, temperature rise, outlet 2 temperature rise.This
It is due to that expansion ratio reduces, the reason for muzzle velocity is reduced；The reason for 2 temperature are raised is exported, it is same.
5) with the increase of 1 aperture of outlet, the aperture of V-type ball valve 3 is constant, outlet 1 speed reduction, and 2 speed of outlet are gradually
Reduction.
6) experimental rig of the invention can provide pressure, mass flow, temperature and speed stable examination during operation
Test and use combustion gas.
In summary, the design principle of fuel gas generator device of the invention according to solid propellant rocket, increases gas collection
Room, improves gas extraction system, and sets up V-type ball valve in exhaust outlet, and controllability is strong, work safety, stably, can accurate simulated rocket
The weapon such as bullet, guided missile jet pipe sprays the environment of high-temperature gas, can meet in aircraft and engine sizing, what is carried out starts
Machine swallows powder gases experiment or suction weapon exhaust system test, fills up the domestic vacancy in the special test field.
Those skilled in the art should be noted that embodiment described in the invention is only exemplary, can be
Various other replacements, changes and improvements are made in the scope of the present invention.Thus, the invention is not restricted to above-mentioned embodiment, and only
It is defined by the claims.
Claims (10)
1. a kind of gas generator that powder gases experiment is swallowed suitable for engine, including：
Igniter, is arranged on one end of the gas generator；
Combustion chamber, the fuel chamber is mounted therein with many powder columns, and many powder columns are contacted with the igniter；
Collection chamber, is arranged at the outside of the combustion chamber and coats the combustion chamber；And
Jet pipe, is arranged on the other end of the gas generator, and connect with the collection chamber.
2. gas generator as claimed in claim 1, wherein the igniter includes：Harness, electric connector, medicine
Box, ignition charge, celluloid and connecting bolt component.
3. gas generator as claimed in claim 2, wherein the harness and the medicine box pass through the electric connector
Connection, the ignition charge and the celluloid are located in the medicine box, and the connecting bolt component is located at the week of the medicine box
Edge.
4. gas generator as claimed in claim 1, wherein the arrangement mode of many powder columns is interior real arrangement.
5. gas generator as claimed in claim 1 a, wherein grate is provided with the combustion chamber, with fixed described many
Powder column.
6. gas generator as claimed in claim 1, wherein combustion chamber one end relative with the igniter has
Multiple first perforates.
7. gas generator as claimed in claim 6, in addition to smoke elimination room, the smoke elimination room are arranged on the combustion chamber and institute
State between collection chamber, and coat the combustion chamber.
8. gas generator as claimed in claim 7, wherein one end of the smoke elimination room has multiple second perforates, the other end
With multiple 3rd perforates.
9. a kind of experimental rig that powder gases experiment is swallowed suitable for engine, including such as any one of claim 1 to 8 institute
Gas generator, blast pipe and the multiple V-type ball valves stated, the blast pipe have an entrance and a multiple outlets, the entrance and
The jet pipe is connected, and the V-type ball valve is arranged on the multiple outlet to control the capacity of the multiple outlet respectively.
10. experimental rig as claimed in claim 9, in addition to a control system, with control the ignition system unlatching and
The aperture of the multiple V-type ball valve.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710409335.2A CN106988930B (en) | 2017-06-02 | 2017-06-02 | The gas generator and experimental rig of powder gases experiment are swallowed suitable for engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710409335.2A CN106988930B (en) | 2017-06-02 | 2017-06-02 | The gas generator and experimental rig of powder gases experiment are swallowed suitable for engine |
Publications (2)
| Publication Number | Publication Date |
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| CN106988930A true CN106988930A (en) | 2017-07-28 |
| CN106988930B CN106988930B (en) | 2018-08-17 |
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ID=59421988
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710409335.2A Active CN106988930B (en) | 2017-06-02 | 2017-06-02 | The gas generator and experimental rig of powder gases experiment are swallowed suitable for engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108827638A (en) * | 2018-04-19 | 2018-11-16 | 中国航发湖南动力机械研究所 | Aeroengine combustor buring room component water ingestion test device and method |
| CN109884267A (en) * | 2019-01-29 | 2019-06-14 | 北京理工大学 | The experimental provision and method measured for propellant multi-angle burn rate under overload condition |
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| JP2004211603A (en) * | 2002-12-27 | 2004-07-29 | Mitsubishi Heavy Ind Ltd | Testing method and device for structure for passing supersonic working fluid |
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| US4733751A (en) * | 1985-12-27 | 1988-03-29 | General Dynamics, Pomona Division | Rocket exhaust disrupter |
| JP2004211603A (en) * | 2002-12-27 | 2004-07-29 | Mitsubishi Heavy Ind Ltd | Testing method and device for structure for passing supersonic working fluid |
| CN102174914A (en) * | 2011-03-10 | 2011-09-07 | 西北工业大学 | Test device for studying distribution of plume condensed-phase particles of spray pipe |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108827638A (en) * | 2018-04-19 | 2018-11-16 | 中国航发湖南动力机械研究所 | Aeroengine combustor buring room component water ingestion test device and method |
| CN108827638B (en) * | 2018-04-19 | 2020-06-23 | 中国航发湖南动力机械研究所 | Aeroengine combustor part water swallowing test device and method |
| CN109884267A (en) * | 2019-01-29 | 2019-06-14 | 北京理工大学 | The experimental provision and method measured for propellant multi-angle burn rate under overload condition |
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| Publication number | Publication date |
|---|---|
| CN106988930B (en) | 2018-08-17 |
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