CN102817745A - Low-cost and simple unit round-to-square plug nozzle test device - Google Patents
Low-cost and simple unit round-to-square plug nozzle test device Download PDFInfo
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- CN102817745A CN102817745A CN201210291246XA CN201210291246A CN102817745A CN 102817745 A CN102817745 A CN 102817745A CN 201210291246X A CN201210291246X A CN 201210291246XA CN 201210291246 A CN201210291246 A CN 201210291246A CN 102817745 A CN102817745 A CN 102817745A
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Abstract
The invention discloses a low-cost and simple unit round-to-square plug nozzle test device, which comprises an igniter assembly, an injector assembly, a thrust chamber assembly, a plug cone assembly, a thrust measuring support table frame assembly and an ejection exhaust tube, wherein the injector assembly is provided with a hydrogen cavity and an oxygen cavity, a hydrogen and oxygen gas direct flow spray nozzle with the single hydrogen and oxygen injection function is arranged in the hydrogen cavity, the igniter assembly formed by three layers of sleeves is arranged inside the injector assembly, the injector assembly is connected with the thrust chamber assembly with a round-to-square inner nozzle, the plug cone assembly and the thrust chamber assembly are connected, are supported by the thrust measuring support table frame assembly and can forwards and backwards slide on the support table frame assembly, a platform with an installing thrust frame is also arranged on the support table frame assembly, and the back part of the plug cone is positioned in the ejection exhaust tube. The low-cost and simple unit round-to-square plug nozzle test device has the advantages that the structure is simple, the measurement precision is high, the cost is low, in addition, the application range is wide, the study content is rich, and the repeated use for many times can be realized.
Description
Technical field
The present invention relates to Aero-Space engine test technical field, specifically, is circle commentaries on classics side, a kind of unit with low cost, simple in structure plug nozzle testing apparatus.
Background technique
Improving nozzle efficiency, alleviate jet pipe weight, is the main target of rocket motor design.Because the Aero-Space vehicle will experience different flying heights in flight course; Tradition bell jet pipe only could obtain best performance at design height; Be higher or lower than design height and all can cause certain performance loss, promptly owe expansion-loss or overexpansion loss.Pneumatic plug nozzle is because the open fluidal texture in its outside; Making that combustion gas is one-sided communicates with external pressure; Influenced by the environment back-pressure and regulate swelling state automatically, combustion gas is on whole flying height fully or near the state of complete expansion, the height performance of jet pipe has automatic compensation characteristic.Research both at home and abroad shows that near the performance of plug nozzle design point is close with desirable bell jet pipe, and low-altitude performance obviously is superior to the bell jet pipe, and nozzle efficiency can improve 20%～30% at most; Area plug nozzle length when identical is short more than the bell jet pipe, and weight can alleviate.The application prospect of plug nozzle is extremely extensive, and its altimetric compensation characteristic makes it to be particularly useful for the aloft work environment of the big or large size ratio of requirement exit area ratio excursion.The reusable vehicle that is the basis with the plug nozzle motor is expected to be used for many important space industries as a general space means of transportation, like manned space flight, the transportation of space station goods and materials, interspace transportation, moonfall transportation, satellite lift-launch etc.
The development process of plug nozzle motor need experience a large amount of research in advance and the experimental research of subsystem; Grasp the key factor that influences the plug nozzle performance through theory analysis, numerical simulation and verification experimental verification; Afterwards that multinomial decomposition technique is comprehensive, carry out repeatedly the experiment of system-wide ground and high-altitude flight demonstration and verification.The work difficulty of experimental research experimental duties big, that expend height, test setup time length, testpieces completion are limited at present, and particularly to the test of motor hot-fluid, the testpieces access times are limited.
Summary of the invention
In order to address the above problem, the present invention proposes a kind of with low cost, simple in structure, both can adopt air to carry out cold-flow test, can adopt light a fire circle commentaries on classics side, the unit plug nozzle testing apparatus of hot-fluid test of gas hydrogen oxygen propellant agent again.
Circle commentaries on classics side, a kind of low cost simple unit plug nozzle testing apparatus comprises ignitor assembly, ejector filler assembly, thrust chamber assembly, plug awl assembly and support, thrust measurement support stand assembly and injection exhaust pipe.
Described ejector filler assembly comprises that spray tube, ejector filler lid, ejector filler upper base and ejector filler go to the bottom gas oxygen pipe joint and gas hydrogen pipe joint.Wherein, spray tube upper end fixedly taper ejector filler is covered, and spray tube inside is fixed with the ejector filler upper base and ejector filler is gone to the bottom along axial direction; Form the oxygen chamber of ejector filler thus between ejector filler lid and ejector filler upper base, form the hydrogen chamber of ejector filler between ejector filler upper base and ejector filler are gone to the bottom; The fixing gas oxygen pipe joint that is communicated with of ejector filler lid outside symmetry; The external stability of spray tube is communicated with gas hydrogen pipe joint.In ejector filler hydrogen chamber, be provided with the oxyhydrogen gas gas smooth-bore tip that constitutes by the gentle hydrogen smooth-bore tip of gas oxygen smooth-bore tip; Wherein, gas oxygen smooth-bore tip is used for the gas oxygen in the spray oxygen chamber, and the upper end is weldingly fixed on the ejector filler upper base; The lower end suspends, and end face and the ejector filler bottom surface of going to the bottom flushes; Gas hydrogen smooth-bore tip is used for the gas hydrogen in the spray hydrogen chamber; Two ends are fixedly mounted on respectively on ejector filler upper base and ejector filler go to the bottom; Make between gas hydrogen smooth-bore tip outer side wall and gas oxygen smooth-bore tip madial wall to have the gap, and have through hole along the circumferential tangent line of gas hydrogen smooth-bore tip.The center of going to the bottom at described ejector filler lid, ejector filler upper base and ejector filler all has igniter fixed hole A.
Described ignitor assembly comprises by managing in locking cap, the igniter in pipe in the igniter, pipe and igniter outer tube constitute in the igniter three layers of sleeve structure and the igniter manages locking cap.Wherein, the pipe locking cap is fixedly mounted on ejector filler and covers on the end face in the igniter, and the pipe locking cap is fixedly mounted on pipe locking cap upper end in the igniter in the igniter, manages on the locking cap firearm fixed hole B battle in the igniter in pipe locking cap and the igniter.Pipe with the mounting type of igniter outer tube is in the interior pipe of said igniter, the igniter:
The igniter outer tube penetrates ejector filler lid, ejector filler upper base and the ejector filler igniter fixed hole A on going to the bottom, and igniter outer tube lower end and the ejector filler igniter fixed hole A on going to the bottom circumferentially is connected, and the igniter fixed hole A that upper end and ejector filler cover circumferentially is connected.Pipe is positioned at igniter outer tube inside in the igniter, has certain interval between pipe and igniter outer tube in the igniter, forms gas oxygen transfer passage; The pipe lower end surface flushes with igniter outer tube lower end surface in the igniter, and the igniter fixed hole B in upper end and the igniter on the pipe locking cap circumferentially is connected; And have cavity between pipe in pipe locking cap madial wall and the igniter in the igniter, form the hydrogen chamber of igniter, the hydrogen chamber is communicated with gas hydrogen conveyance conduit; Have the hydrogen supply hole on the pipe locking cap in the igniter; It is inner that pipe is arranged in the igniter pipe in the igniter, has certain interval between pipe in pipe and the igniter in the igniter; The pipe lower end surface flushes with igniter outer tube lower end surface in the igniter; The upper end circumferentially is connected with the interior igniter fixed hole B that manages on the locking cap of igniter; Realize the location between interior pipe of igniter and igniter outer tube thus; And have cavity between pipe in pipe locking cap madial wall and the igniter in the igniter, form the oxygen chamber of igniter, the oxygen chamber is communicated with gas oxygen transfer passage; Have the oxygen supply hole on the pipe locking cap in the igniter;
Described thrust chamber assembly comprises burning zone and nozzle section; Burning zone is measured joint by combustion outer case, firing chamber liner and combustion chamber pressure and is constituted.Wherein, combustion outer case is a tubular, and the combustion outer case internal fixation is provided with the firing chamber liner that is all tubular; Corresponding position has the joint mounting hole on firing chamber liner and combustion outer case; Combustion chamber pressure is measured joint and the joint mounting hole is connected, and with firing chamber liner internal communication; Nozzle section is made up of circle commentaries on classics side's inner nozzle and inner nozzle overcoat.Wherein, the inner nozzle overcoat is a tubular; Circle commentaries on classics side inner nozzle is a tubular structure, is fixedly mounted on the inside of inner nozzle overcoat.Inner nozzle inside, circle commentaries on classics side begins to have contraction chamber and expansion cavity successively by the upper end; The entry end port internal diameter of contraction chamber equates with firing chamber liner internal diameter; The outlet end of contraction chamber and the entry end of expansion cavity join, and the entry end of expansion cavity to outlet end changes square structure for the circle that is formed to the square-section by round section transitions.
Spray tube lower end is connected in above-mentioned combustion outer case upper end and the ejector filler assembly, and the outer set upper side of combustion outer case lower end and inner nozzle is connected.
Described plug awl assembly comprises plug awl, plug cone flank plate, base plate, plug awl pillar and thrust frame link.Wherein, described plug awl upper end is connected with inner nozzle overcoat lower end, plug awl both sides fixing plug cone flank plate; The lower end of said plug awl is fixedly mounted on the base plate, and plug awl top is fixed through plug awl pillar and base plate.
Described thrust measurement support stand assembly comprises that four support posts, dunnage, bearing shaft, base for supporting, thrust frame mountion plate and door shape frame constitute.Wherein, two support posts constitute one group, are installed in the both sides of support plate upper surface through the bolt symmetry, between every group of support post vertically horizontal axis be connected to two bearing shaft.Above above-mentioned floor level is arranged between two groups of support posts and between the bearing shaft of below; Through the top between two groups of support posts and the bearing shaft of below base plate is carried out in vertical direction spacingly, and realize base plates spacing on left and right directions through two groups of support posts.Above-mentioned dunnage is fixedly mounted on the base for supporting upper surface; Said base for supporting front end is fixedly connected with the thrust frame mountion plate, is welded with door shape frame at thrust frame mountion plate upper surface.
It is inner that said plug awl bottom is arranged on the injection exhaust pipe, is connected with vacuum system through the injection exhaust pipe.
The invention has the advantages that:
1, circle commentaries on classics side, unit of the present invention plug nozzle testing apparatus; The air that both can adopt applied widely carries out cold-flow test; Can adopt the light a fire hot-fluid test of gas hydrogen oxygen propellant agent again; And research contents is abundant, is connected with vacuum system through passive ejection structure, can study the plug nozzle performance of unit circle commentaries on classics side's plug nozzle under different flying heights;
2, circle commentaries on classics side inner nozzle is independently processed design in circle commentaries on classics side, the unit of the present invention plug nozzle testing apparatus, can prevent effectively that the hot-fluid in the circle commentaries on classics side inner nozzle from causing ablation to jet pipe, can be repeatedly used, and dismounting and change is convenient;
3, circle commentaries on classics side, unit of the present invention plug nozzle testing apparatus; Adopt and ablate and the heat sink passive type of cooling; There is not the initiatively complicated cooling system of cooling, and reusable, continuous lower with cost; And adopt the support and the thrust measurement stand of autonomous Design to carry out the measurement of motor power, measuring accuracy is high, simple in structure, with low cost.
Description of drawings
Fig. 1 is the present invention's circle commentaries on classics side plug nozzle testing apparatus overall structure schematic representation;
Fig. 2 cuts open schematic representation for the present invention's circle commentaries on classics side plug nozzle testing apparatus overall structure;
Fig. 3 is ignitor assembly and ejector filler modular construction schematic representation in the present invention's circle commentaries on classics side plug nozzle testing apparatus;
Fig. 4 is thrust chamber modular construction schematic representation in the present invention's circle commentaries on classics side plug nozzle testing apparatus;
Fig. 5 is thrust chamber modular construction sectional view in the present invention's circle commentaries on classics side plug nozzle testing apparatus;
Fig. 6 is plug awl modular construction schematic representation in the present invention's circle commentaries on classics side plug nozzle testing apparatus;
Fig. 7 is thrust measurement support stand modular construction schematic representation in the present invention's circle commentaries on classics side plug nozzle testing apparatus.
Among the figure:
1-ignitor assembly 2-ejector filler assembly 3-thrust chamber assembly 4-plug awl assembly
5-thrust measurement support platform 6-injection exhaust pipe 201-spray tube 202-ejector filler lid frame component
The 203-ejector filler upper base 204-ejector filler 205-gas oxygen pipeline of going to the bottom connects 206-gas hydrogen pipeline and connects
The head
207-oxyhydrogen gas gas direct current 207a-gas oxygen direct current 207b-gas hydrogen direct current spray 208-through hole nozzle nozzle mouth
209-hole 210-igniter is fixedly managed in the interior pipe of the 101-igniter 102-igniter
Hole A
Managing the 106-igniter in the pipe 105-igniter in the 103-igniter outer tube 104-igniter fixes
Locking cap locking cap hole B
301b-firing chamber liner 301c-combustion chamber pressure outside the 301-burning zone 301a-firing chamber
Cover is measured joint
Spray 303-contraction chamber in the outer 302b-circle of the 302-nozzle section 302a-inner nozzle commentaries on classics side
Sleeve pipe
304-expansion cavity 401-plug awl 402-plug cone flank plate 403-base plate
404-plug awl pillar 405-thrust frame connects 406-subsonic speed backflow 501-support post
The part district
502-dunnage 503-bearing shaft 503a-transverse axis 503b-bearing
504-base for supporting 505-thrust frame is installed the 506-door shape frame
Platform
Embodiment
Below in conjunction with accompanying drawing the present invention is described further.
Circle commentaries on classics side, a kind of low cost simple of the present invention unit plug nozzle testing apparatus; The present invention is circle commentaries on classics side, an a kind of low cost simple unit plug nozzle testing apparatus; As depicted in figs. 1 and 2, described testing apparatus mainly comprises ignitor assembly 1, ejector filler assembly 2, thrust chamber assembly 3, plug awl assembly 4, thrust measurement support stand assembly 5 and injection exhaust pipe 6.
Described ejector filler assembly 2 comprises that spray tube 201, ejector filler lid 202, ejector filler upper base 203 and ejector filler go to the bottom 204, and gas oxygen pipe joint 205 and gas hydrogen pipe joint 206 are as shown in Figure 3.Wherein, spray tube 201 upper ends welding taper ejector filler lid 202, spray tube 201 inside have ejector filler upper base 203 and ejector filler to go to the bottom 204 along the axial direction coaxial welding; The go to the bottom hydrogen chamber of 204 formation ejector fillers of the oxygen chamber of ejector filler lid 202 and 203 formation ejector fillers of ejector filler upper base thus, ejector filler upper base 203 and ejector filler.Ejector filler covers 202 outsides along circumferentially evenly welding fixing 3 ~ 5 gas oxygen pipe joints 205, and gas oxygen pipe joint 205 is communicated with the oxygen chamber of ejector filler, is used in the oxygen chamber of ejector filler, supplying with oxygen.Spray tube 201 is outside, and gas hydrogen pipe joint 206 is communicated with the hydrogen chamber of ejector filler along circumferential even fixing 3 ~ 5 gas hydrogen pipe joints 206 of welding, is used for hydrogen supply in the hydrogen chamber of ejector filler.Along circumferentially evenly arranging inside and outside two circle coaxial-type oxyhydrogen gas gas smooth-bore tips 207, wherein inner ring is arranged 6 ~ 8 gas gas smooth-bore tips 207 in ejector filler hydrogen chamber, and 8 ~ 10 gas gas smooth-bore tips 207 are arranged in the outer ring.Described coaxial-type oxyhydrogen gas gas smooth-bore tip 207 is made up of the gentle hydrogen smooth-bore tip of gas oxygen smooth-bore tip 207a 207b, the coaxial gas oxygen smooth-bore tip outside that is socketed in of gas hydrogen smooth-bore tip; Wherein, gas oxygen smooth-bore tip 207a is used for the gas oxygen in the spray oxygen chamber, and the upper end is weldingly fixed on the ejector filler upper base 203, and the lower end suspends, and end face and ejector filler 204 bottom surfaces of going to the bottom flush; Gas hydrogen smooth-bore tip 207b is used for the gas hydrogen in the spray hydrogen chamber; Two ends are fixedly mounted on ejector filler upper base 203 and ejector filler respectively and go to the bottom on 204; Make between gas hydrogen smooth-bore tip 207b outer side wall and gas oxygen smooth-bore tip 207a madial wall and have the gap; And have through hole 208 along the circumferential tangent line of gas hydrogen smooth-bore tip 207b; Gas hydrogen in the hydrogen chamber can get into the back by through hole 208 and located carry out spray by the slit between gas hydrogen smooth-bore tip 207b and gas oxygen smooth-bore tip 207a thus, and hydrogen and oxygen can effectively be isolated in the spray process.More even in order to mix between the gas hydrogen that makes spray and gas oxygen, in the ejector filler perforate 209 on 204 of going to the bottom, be positioned at ejector filler and go to the bottom between 204 outward edges and nozzle thus, be used for spray gas hydrogen, form nearly wall cryosphere and prevent that high-temperature fuel gas from refluxing.All have igniter fixed hole A210 in go to the bottom 204 center of described ejector filler lid 202, ejector filler upper base 203 and ejector filler, be used for installing ignitor assembly 1.Described spray tube 201 lower ends have flange arrangement, are used for connecting thrust chamber assembly 3.
Described ignitor assembly 1 comprise by manage 101 in the igniter, pipe locking cap 105 in pipe locking cap 104, the igniter in pipe 102 and igniter outer tube 103 constitute in the igniter three layers of sleeve structure and the igniter, as shown in Figure 3; Wherein, Pipe locking cap 105 is fixedly mounted on ejector filler and covers on 202 upper-end surfaces in the igniter; Pipe locking cap 104 is fixedly mounted on pipe locking cap 105 upper ends in the igniter in the igniter; Have the igniter fixed hole B106 coaxial on the pipe locking cap 104 in pipe locking cap 105 and the igniter in the igniter, be used for fixing in interior pipe 101 of igniter and the igniter and manage 102 with igniter fixed hole A210.In the said igniter in pipe 101, the igniter mounting type of pipe 102 and igniter outer tube 103 be:
Igniter outer tube 103 penetrates ejector filler lid 202, ejector filler upper base 203 and the ejector filler igniter fixed hole A210 on 204 that goes to the bottom; And the igniter fixed hole A210 that igniter outer tube 103 lower ends and ejector filler are gone to the bottom on 204 circumferentially is connected; The upper end circumferentially is connected with the igniter fixed hole A210 that ejector filler covers on 202; Igniter fixed hole A210 and igniter outer tube 103 on the ejector filler upper base 203 is connected the connection of reinforcement point firearm outer tube 103 simultaneously.Pipe 102 is positioned at igniter outer tube 103 inside in the igniter, and there are certain interval in pipe 102 and 103 of igniter outer tubes in the igniter, forms gas oxygen transfer passage; Pipe 102 lower end surfaces flush with igniter outer tube 103 lower end surfaces in the igniter, and the igniter fixed hole B106 that manages in upper end and the igniter on the locking cap 105 circumferentially is connected, and realize managing in the igniter 102 and the location of 103 of igniter outer tubes thus; And manage 102 in pipe locking cap 105 madial walls and the igniter in the igniter and have cavity, form the hydrogen chamber of igniter, the hydrogen chamber is communicated with gas hydrogen conveyance conduit; Have the hydrogen supply hole on the pipe locking cap 105 in the igniter, be used for hydrogen supply in the hydrogen chamber of igniter.Pipe 101 is arranged in igniter pipe 102 inside in the igniter, and there is certain interval in 102 of pipes in interior pipe 101 of igniter and the igniter, form gas oxygen transfer passage; Pipe 101 lower end surfaces flush with igniter outer tube 103 lower end surfaces in the igniter, and the igniter fixed hole B106 in upper end and the igniter on the pipe locking cap 104 circumferentially is connected, and realize the location of 103 of interior pipe 101 of igniter and igniter outer tubes thus; And manage 101 in pipe locking cap 104 madial walls and the igniter in the igniter and have cavity, form the oxygen chamber of igniter, the oxygen chamber is communicated with gas oxygen transfer passage; Have the oxygen supply hole on the pipe locking cap 104 in the igniter, be used in the oxygen chamber of igniter, supplying with oxygen.Pipe 6 be the detonation wave transfer conduit in the above-mentioned igniter, and to thrust chamber top, the gas in igniter hydrogen chamber and the oxygen chamber can be under the effect of detonation wave be put to fight through gas hydrogen transfer passage and the realization of gas oxygen transfer passage and is used for keeping lighting-off torch with detonation wave propagation.Above-mentioned ignitor assembly 1 is environment under low pressure in the successful three first layers pipeline of igniting; After lighting a fire successfully; Damage igniter structure for preventing that high-temperature fuel gas from refluxing; Hydrogen supply in the pipe 101 in igniter, pipe 102 remains unchanged with igniter outer tube 103 interior supply working medium in the igniter, makes ignition module play nozzle.
Described thrust chamber assembly 3 like Fig. 4, shown in Figure 5, comprises burning zone 301 and nozzle section 302.Burning zone 301 is measured joint 301c by combustion outer case 301a, firing chamber liner 301b and combustion chamber pressure and is constituted; Wherein, combustion outer case 301a is a tubular, and two ends have flange arrangement, and combustion outer case 301a set inside has the firing chamber liner 301b that is all tubular, and firing chamber liner 301b adopts tungsten to ooze copper (Wu-Cu) materials processing, is used for ablation protection; Adopt west of a river glue to be connected between firing chamber liner 301b outer side wall and combustion outer case 301a madial wall, can further improve the TPP of ejector filler structure.Corresponding position has the joint mounting hole on firing chamber liner 301b and combustion outer case 301; Combustion chamber pressure is measured joint 301c and is connected with the joint mounting hole, and with firing chamber liner 301b internal communication, be used for pressure among the installation code pressure transducer measurement firing chamber liner 301b.Nozzle section 302 is made up of circle commentaries on classics side inner nozzle 302a and inner nozzle overcoat 302b.Wherein, inner nozzle overcoat 302a is a tubular, and the upper end has flange arrangement.Circle commentaries on classics side inner nozzle 302b is fixedly mounted on the inside of inner nozzle overcoat 302a, and realizes axial seal through viton seal ring between inner nozzle overcoat 302a.Circle commentaries on classics side inner nozzle 302b is all tubular structure, and inside begins to have successively contraction chamber 304 and expansion cavity 305 by the upper end; Wherein, contraction chamber 303 is an axisymmetric cavity, and the entry end port internal diameter of contraction chamber 303 equates with firing chamber liner 301b internal diameter; The entry end of the outlet end of contraction chamber 303 and expansion cavity 304 joins, and the entry end of expansion cavity 304 to outlet end, is formed circle and changes square structure to the square-section by round section transitions, adopts the long-pending transformation approach design of equal length uniform section.Above-mentioned circle commentaries on classics side inner nozzle 302a is a field-replaceable unit, adopts two kinds of materials to process, and when adopting the 1Cr18Ni9Ti material, can be used for blowing of cold flow air and low temperature combustion gas blowing experiment; When adopting the Wu-Cu material, can be used for high-temperature fuel gas blowing experiment, and can guarantee more than 3400K, not ablate.
Described plug awl assembly 4 comprises plug awl 401, plug cone flank plate 402, base plate 403, plug awl pillar 404 and thrust frame link 405, and is as shown in Figure 6; Wherein, described plug awl 401 adopts parabola and cubic curve method of approximation to carry out the profile design; Plug awl 401 upper ends adopt screw to be connected with inner nozzle overcoat 302a lower end; Plug awl 401 bottom surfaces are designed to outside arc form; With plug awl 401 wall smooth transition, be used for reducing the volume in plug awl subsonic speed recirculating zone, 401 bottom 406 (zone between bottom surface and horizontal plane).Said plug cone flank plate 402 is through being provided with the stud realization and filling in being connected of awl 401 both sides in plug awl 401 inner transverse through holes.The bottom of said plug awl 401 is installed on the base plate 403 through bolt, and plug awl 401 tops are fixing with base plate 403 through plug awl pillar 404.On the plug awl pillar thrust frame link is installed.
Described thrust measurement support stand assembly 5; Be used for supporting and the fixing jet pipe testing apparatus and the experiment with measuring jet pipe thrust frame that constitute of each part mentioned above; As shown in Figure 7, comprise that four support posts 501, dunnage 502, bearing shaft 503, base for supporting 504, thrust frame mountion plate 505 constitute with door shape frame 506.Wherein, two support posts 501 constitute one group, are installed in the both sides of dunnage 502 upper surfaces through the bolt symmetry, and every group of 501 of support post vertically is horizontally installed with two bearing shaft 503.Said bearing shaft 503 is made up of transverse axis 503a and bearing 503b, and wherein, transverse axis 503a two ends are connected with every group of two support posts 501 respectively, and a bearing 503b is respectively installed in the both sides of transverse axis 503a, and bearing 503b can rotate on transverse axis 503a.Above-mentioned base plate 403 is horizontally placed between the bearing shaft 503 of 501 tops of two groups of support posts and below; Carry out spacing through the bearing 503b in the bearing shaft 503 of 501 tops of two groups of support posts and below in vertical direction to base plate 403 thus; And realize base plates 403 spacing on left and right directions through two groups of support posts 501, and base plate 403 can move at the effect lower edge of bearing 503b fore-and-aft direction.Above-mentioned dunnage 502 is fixedly mounted on base for supporting 504 upper surfaces, and many mounting points of bolt hole being convenient to adjustable support column 501 are set on dunnage 502.Said base for supporting 504 front ends are fixedly connected with thrust frame mountion plate 505, are welded with door shape frame 506 at thrust frame mountion plate 505 upper surfaces, are used for locating thrust frame 505.Said thrust frame is vertically mounted on the plug awl pillar 404 through thrust frame link 405, and fixing through steel wire and door shape frame 506.
Bore 401 bottoms at said plug and be provided with the injection exhaust pipe; As shown in Figure 1; Make plug awl 401 bottoms be positioned at injection exhaust pipe 6 inside; Be connected with vacuum system through injection exhaust pipe 6, can in injection exhaust pipe 6, form different back pressure environment thus, be used for studying the performance of circle commentaries on classics side's plug nozzle under different flying heights.
Claims (10)
1. circle commentaries on classics side, low cost simple unit plug nozzle testing apparatus is characterized in that: comprise ignitor assembly, ejector filler assembly, thrust chamber assembly, plug awl assembly and support, thrust measurement support stand assembly and injection exhaust pipe.
Described ejector filler assembly comprises that spray tube, ejector filler lid, ejector filler upper base and ejector filler go to the bottom gas oxygen pipe joint and gas hydrogen pipe joint; Wherein, spray tube upper end fixedly taper ejector filler is covered, and spray tube inside is fixed with the ejector filler upper base and ejector filler is gone to the bottom along axial direction; Form the oxygen chamber of ejector filler thus between ejector filler lid and ejector filler upper base, form the hydrogen chamber of ejector filler between ejector filler upper base and ejector filler are gone to the bottom; The fixing gas oxygen pipe joint that is communicated with of ejector filler lid outside symmetry; The external stability of spray tube is communicated with gas hydrogen pipe joint; In ejector filler hydrogen chamber, be provided with the oxyhydrogen gas gas smooth-bore tip that constitutes by the gentle hydrogen smooth-bore tip of gas oxygen smooth-bore tip; Wherein, gas oxygen smooth-bore tip is used for the gas oxygen in the spray oxygen chamber, and the upper end is weldingly fixed on the ejector filler upper base; The lower end suspends, and end face and the ejector filler bottom surface of going to the bottom flushes; Gas hydrogen smooth-bore tip is used for the gas hydrogen in the spray hydrogen chamber; Two ends are fixedly mounted on respectively on ejector filler upper base and ejector filler go to the bottom; Make between gas hydrogen smooth-bore tip outer side wall and gas oxygen smooth-bore tip madial wall to have the gap, and have through hole along the circumferential tangent line of gas hydrogen smooth-bore tip; The center of going to the bottom at described ejector filler lid, ejector filler upper base and ejector filler all has igniter fixed hole A;
Described ignitor assembly comprises by managing in locking cap, the igniter in pipe in the igniter, pipe and igniter outer tube constitute in the igniter three layers of sleeve structure and the igniter manages locking cap; Wherein, the pipe locking cap is fixedly mounted on ejector filler and covers on the end face in the igniter, and the pipe locking cap is fixedly mounted on pipe locking cap upper end in the igniter in the igniter, manages on the locking cap firearm fixed hole B battle in the igniter in pipe locking cap and the igniter; Pipe with the mounting type of igniter outer tube is in the interior pipe of said igniter, the igniter:
The igniter outer tube penetrates ejector filler lid, ejector filler upper base and the ejector filler igniter fixed hole A on going to the bottom, and igniter outer tube lower end and the ejector filler igniter fixed hole A on going to the bottom circumferentially is connected, and the igniter fixed hole A that upper end and ejector filler cover circumferentially is connected; Pipe is positioned at igniter outer tube inside in the igniter, has certain interval between pipe and igniter outer tube in the igniter, forms gas oxygen transfer passage; The pipe lower end surface flushes with igniter outer tube lower end surface in the igniter, and the igniter fixed hole B in upper end and the igniter on the pipe locking cap circumferentially is connected; And have cavity between pipe in pipe locking cap madial wall and the igniter in the igniter, form the hydrogen chamber of igniter, the hydrogen chamber is communicated with gas hydrogen conveyance conduit; Have the hydrogen supply hole on the pipe locking cap in the igniter; It is inner that pipe is arranged in the igniter pipe in the igniter, has certain interval between pipe in pipe and the igniter in the igniter; The pipe lower end surface flushes with igniter outer tube lower end surface in the igniter; The upper end circumferentially is connected with the interior igniter fixed hole B that manages on the locking cap of igniter; Realize the location between interior pipe of igniter and igniter outer tube thus; And have cavity between pipe in pipe locking cap madial wall and the igniter in the igniter, form the oxygen chamber of igniter, the oxygen chamber is communicated with gas oxygen transfer passage; Have the oxygen supply hole on the pipe locking cap in the igniter;
Described thrust chamber assembly comprises burning zone and nozzle section; Burning zone is measured joint by combustion outer case, firing chamber liner and combustion chamber pressure and is constituted; Wherein, combustion outer case is a tubular, and the combustion outer case internal fixation is provided with the firing chamber liner that is all tubular; Corresponding position has the joint mounting hole on firing chamber liner and combustion outer case; Combustion chamber pressure is measured joint and the joint mounting hole is connected, and with firing chamber liner internal communication; Nozzle section is made up of circle commentaries on classics side's inner nozzle and inner nozzle overcoat; Wherein, the inner nozzle overcoat is a tubular; Circle commentaries on classics side inner nozzle is a tubular structure, is fixedly mounted on the inside of inner nozzle overcoat; Inner nozzle inside, circle commentaries on classics side begins to have contraction chamber and expansion cavity successively by the upper end; The entry end port internal diameter of contraction chamber equates with firing chamber liner internal diameter; The outlet end of contraction chamber and the entry end of expansion cavity join, and the entry end of expansion cavity to outlet end changes square structure for the circle that is formed to the square-section by round section transitions;
Spray tube lower end is connected in above-mentioned combustion outer case upper end and the ejector filler assembly, and the outer set upper side of combustion outer case lower end and inner nozzle is connected;
Described plug awl assembly comprises plug awl, plug cone flank plate, base plate, plug awl pillar and thrust frame link; Wherein, described plug awl upper end is connected with inner nozzle overcoat lower end, plug awl both sides fixing plug cone flank plate; The lower end of said plug awl is fixedly mounted on the base plate, and plug awl top is fixed through plug awl pillar and base plate;
Described thrust measurement support stand assembly comprises that four support posts, dunnage, bearing shaft, base for supporting, thrust frame mountion plate and door shape frame constitute; Wherein, two support posts constitute one group, are installed in the both sides of support plate upper surface through the bolt symmetry, between every group of support post vertically horizontal axis be connected to two bearing shaft; Above above-mentioned floor level is arranged between two groups of support posts and between the bearing shaft of below; Through the top between two groups of support posts and the bearing shaft of below base plate is carried out in vertical direction spacingly, and realize base plates spacing on left and right directions through two groups of support posts; Above-mentioned dunnage is fixedly mounted on the base for supporting upper surface; Said base for supporting front end is fixedly connected with the thrust frame mountion plate, is welded with door shape frame at thrust frame mountion plate upper surface;
It is inner that said plug awl bottom is arranged on the injection exhaust pipe, is connected with vacuum system through the injection exhaust pipe.
2. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus, it is characterized in that: said gas oxygen pipe joint and gas hydrogen pipe joint are 3 ~ 5, evenly are provided with.
3. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus is characterized in that: said gas gas smooth-bore tip is circumferentially evenly arranged inside and outside two circles in ejector filler hydrogen chamber; Wherein inner ring is arranged 6 ~ 8, and the outer ring is arranged 8 ~ 10.
4. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus, it is characterized in that: said ejector filler has the hole on going to the bottom.
5. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus is characterized in that: said firing chamber liner adopts tungsten to ooze copper product processing.
6. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus is characterized in that: adopt west of a river glue to be connected between said firing chamber liner outer side wall and combustion outer case madial wall.
7. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus is characterized in that: the outer inner room of circle commentaries on classics side's inner nozzle and inner nozzle is realized axial seal through viton seal ring; Pass through the radial seal of ejector filler red copper pad between combustion outer case upper end and spray tube lower end; Combustion outer case lower end and inner nozzle pass through the radial seal of thrust chamber red copper pad between outer set upper side.
8. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus is characterized in that: said circle commentaries on classics side inner nozzle adopts the 1Cr18Ni9Ti material to carry out blowing of cold flow air and low temperature combustion gas blowing experiment; Adopt the Wu-Cu material to carry out high-temperature fuel gas blowing experiment.
9. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus; It is characterized in that: the bottom surface of said plug awl is designed to outside arc form; With plug awl wall smooth transition, be used for reducing the volume in zone between plug awl bottom surface and horizontal plane.
10. circle commentaries on classics side, a kind of according to claim 1 low cost simple unit plug nozzle testing apparatus; It is characterized in that: said bearing shaft is made up of transverse axis and bearing; Wherein, The transverse axis two ends are connected with every group of two support posts respectively, and a bearing is respectively installed in the both sides of transverse axis, and bearing is between every group of two support posts.
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| CN201210291246.XA CN102817745B (en) | 2012-08-16 | 2012-08-16 | Low-cost and simple unit round-to-square plug nozzle test device |
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| CN201210291246.XA CN102817745B (en) | 2012-08-16 | 2012-08-16 | Low-cost and simple unit round-to-square plug nozzle test device |
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| CN102817745A true CN102817745A (en) | 2012-12-12 |
| CN102817745B CN102817745B (en) | 2014-06-18 |
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| CN201210291246.XA Expired - Fee Related CN102817745B (en) | 2012-08-16 | 2012-08-16 | Low-cost and simple unit round-to-square plug nozzle test device |
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| CN103470400A (en) * | 2013-07-24 | 2013-12-25 | 南京航空航天大学 | Design method of exhaust nozzle with controllable inlet and outlet shapes for air-breathing hypersonic flight vehicle |
| CN103592132A (en) * | 2013-10-31 | 2014-02-19 | 哈尔滨汽轮机厂有限责任公司 | Pressurization visual combustion test device of combustor of gas turbine |
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| CN106321282A (en) * | 2016-08-18 | 2017-01-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Convergent-divergent nozzle with stealth function |
| CN109128715A (en) * | 2018-10-15 | 2019-01-04 | 北京动力机械研究所 | The preparation method of water cooling jet pipe measurement segment structure under big gas flow use condition |
| CN109269811A (en) * | 2018-10-15 | 2019-01-25 | 北京动力机械研究所 | Water cooling jet pipe under big gas flow use condition measures segment structure |
| CN110242440A (en) * | 2019-07-23 | 2019-09-17 | 西安航天动力研究所 | A kind of high pressure staged combustion cycle engine Multifunctional split-type thrust chamber protective device |
| CN110242440B (en) * | 2019-07-23 | 2020-08-18 | 西安航天动力研究所 | Multifunctional split type thrust chamber protection device for high-pressure afterburning engine |
| CN115683229A (en) * | 2022-11-16 | 2023-02-03 | 南京尚景智造科技有限公司 | Measuring device and measuring method for solid rocket combustion chamber |
| CN115683229B (en) * | 2022-11-16 | 2024-02-20 | 南京尚景智造科技有限公司 | Solid rocket combustion chamber measuring device and measuring method |
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| CN102817745B (en) | 2014-06-18 |
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