CN108087154A - Identical three kinds of high thrusts, the three constituent element rocket thrust chamber of head construction - Google Patents
Identical three kinds of high thrusts, the three constituent element rocket thrust chamber of head construction Download PDFInfo
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- CN108087154A CN108087154A CN201810024944.0A CN201810024944A CN108087154A CN 108087154 A CN108087154 A CN 108087154A CN 201810024944 A CN201810024944 A CN 201810024944A CN 108087154 A CN108087154 A CN 108087154A
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- China
- Prior art keywords
- kerosene
- partition plate
- hydrogen
- thrust
- body portion
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
Abstract
The present invention relates to identical three kinds of high thrusts, the three constituent element rocket thrust chamber of head construction, including with liquid hydrogen and kerosene sub-sectional cooling body portion, entirely with liquid hydrogen cooling body portion, switching fuel etc..Use outside ejector filler face that burning is oxygen kerosene and external combustion burning in partition plate end face is that 19,37 and 61 of substantially equal areas of hydrogen-oxygen, the high intensity head based on thick ejector filler disk, each area's area have pedestal discharge re-generatively cooled partition plate, fuel flow path and ejector filler successively with technologies such as the switching fuel modes of two kinds of different fuels, can solve the insoluble simplified structure of existing oxygen kerosene thrust chamber reduces difficulty, repeatedly use, improve specific impulse, switch the problems such as fuel change hydrogen-oxygen.Thrust chamber is much simple in structure good with versatility, and number of components largely reduces.Reuse is expected to reach 50 times.Specific impulse can improve 20 50 seconds.Convenient for faster and better develop inexpensive engine.Suitable for engines such as the rocket assist of 200 1000 tons of thrust, level-one, core level-ones.
Description
Technical field
The present invention relates to identical three kinds of high thrusts, the three constituent element rocket thrust chambers of head construction, belong to and are promoted using three constituent elements
The Liquid Propellant Rocket Engine field of agent oxygen kerosene liquid hydrogen.
Background technology
Boosting and one-stage rocket are generally leapt high the oxygen kerosene engine higher with specific impulse with density ratio.Two level and Upper Stage
Rocket is generally with the oxyhydrogen engine than leaping high.All there are thrust cell structures for existing oxygen kerosene engine and oxyhydrogen engine
The problem of complicated.The especially technical difficulty bigger of thrust-augmented rocket thrust chamber.
Core one-stage rocket then needs previous work density ratio to leap high with middle and later periods work than the engine that integrates leapt high.
I it has been suggested that for the engine that integrates switching fuel thrust chamber (ZL201410246890.4 and
201710449991.5), it is that hydrogen peroxide liquid hydrogen is more easily switched to by hydrogen peroxide kerosene.Before last century the eighties
The Soviet Union proposed another switching fuel thrust chamber, was to cut off kerosene residue hydrogen-oxygen by tripropellant oxygen kerosene liquid hydrogen
Scheme.The switching fuel thrust cell structure of the former Soviet Union is very complicated, has no application.
Difficulty is reduced in order to solve the insoluble simplified structure of oxygen kerosene thrust chamber, repeatedly uses, improve ratio
The problems such as rushing, I passes through the three constituent element thrust chambers (201710449940.2) for having researched and proposed structure uncomplicatedization.Burning is used
Oxygen kerosene, the interior cooling of thrust chamber and partition plate cooling liquid hydrogen.But the specific impulse of this thrust chamber increase is limited, there is liquid in-out
The re-generatively cooled diaphragm structure of pipe is more complicated.My nearest invention (201711201099.1) is the discharge of double elements thrust chamber
Re-generatively cooled partition plate so that structure is very simple.As reference, the present invention is based on uses to have pedestal to discharge re-generatively cooled partition plate,
It proposes not switching two kinds of high thrusts, the three constituent element thrust chamber of fuel and a kind of three constituent element thrust chamber of high thrust of switching fuel.
In my foregoing invention there are ejector filler disk infusion slot local velocity it is bigger than normal the problem of, the present invention takes measures together
It solves.
The content of the invention
Very complicated it is difficult to develop three constituent elements that are proposed with me for the three constituent elements switching fuel thrust cell structure of the former Soviet Union
Thrust chamber has much room for improvement part, in order to develop three constituent element thrust chamber of oxygen kerosene liquid hydrogen simple in structure and applicable and corresponding
Switching fuel thrust chamber, the present invention propose three kinds of three constituent element rocket thrust chambers of high thrust.
A kind of three constituent element thrust chamber of high thrust, is made of and welded head, body portion and partition plate, head and this three parts
Connector include force-bearing base, ring flange, porous interior conical shell, outer conical shell, turbine exhaust and introduce pipe, the first load connector, the
Two load connectors, the 3rd load connector, articulation set ring, ejector filler disk, double spray orifice segmental arc plate group, single spray orifice
Segmental arc plate group, spray radial plate, interior cooling ring, overlap joint semi-ring, head kerosene enter the gentle hydrogen efferent duct of pipe.Head is with thickness
High intensity head based on ejector filler disk.Body portion is with liquid hydrogen and kerosene segmentation re-generatively cooled and the first biography without cooling ring band
Unite body portion.Partition plate be have pedestal discharge re-generatively cooled partition plate and with body portion re-generatively cooled transformation gas it is hydrogen-cooled but.From turbine exhaust
Introduce pipe entrance is that liquid oxygen and a small amount of hydrogen carry out burning and generates the oxygen rich air that temperature is no more than 800K.It is exported from gas hydrogen efferent duct
Gas hydrogen can be used as in supply system generate driving turbine gas gas generator fuel.Diameter 1.05-1.5m and thickness
Degree preferably takes the ejector filler disk of 10% diameter to be fanned by circle, 6 first lap fan sections, 12 the second circles centered on equal area partition
Shape area and 18 the 3rd circle fan sections, by concentric two row or the single intensive gas axial direction for being provided with spray oxygen rich air in Bing Ge areas
Hole, partition plate both sides gas axial hole and small gas axial hole.It, can be each area in order to mitigate the quality of disk and this some holes easy to process
Half or so is thinned in thickness at interior punching.Double spray orifice segmental arc plate group, single spray orifice segmental arc plate group and spray radial plate
Kerosene is provided with from hitting to, kerosene inclined hole and the small axial hole of kerosene, enters the body portion regeneration of pipe entrance from head kerosene for spray
Kerosene after cooling.One kerosene forms liquid gas with a gas axial hole and mutually hits spray unit or two small inclinations from hitting from hitting pair
The kerosene inclined hole of 5-30 degree and a gas axial hole composition liquid gas mutually hit spray unit, a kerosene inclined hole and a small gas axis
Spray unit is mutually hit to hole composition outer ring liquid gas.Articulation set ring is opened there are one kerosene access aperture and sets kerosene collector.It is interior
Cooling ring is circumferentially uniformly provided with gas hydrogen radial hole, small radial hole and the annulus for cooling gas hydrogen in spray.Overlap joint
It is opened on semi-ring there are one gas hydrogen delivery outlet and gas hydrogen collector is formed on the inside of it.Thus the first is formed with liquid hydrogen and kerosene point
300-600 tons of three constituent element thrust chambers of thrust in section cooling body portion.
High intensity head is load and spray with the first load connector, the second load connector and the 3rd load connector
The ejector filler disk of note and the porous interior conical shell of oxygen rich air rectification and power transmission are welded into an entirety.Porous interior conical shell, outer conical shell and
Turbine exhaust introduces pipe composition oxygen rich air input unit and power transmission arranged side by side.
The first traditional body portion as boundary at throat downstream to be divided into leading portion and back segment.Leading portion enters what pipe entered with from liquid hydrogen
Liquid hydrogen carries out re-generatively cooled, in heated inflow gas hydrogen collector after becoming gas hydrogen.Back segment enters what pipe entered with from body portion kerosene
Kerosene carries out re-generatively cooled, and flowing to head kerosene from body portion kerosene efferent duct after heated raising temperature enters pipe.The body portion is
It is selected from the traditional structures such as milling straight flute, milling spiral chute, straight bundled tube, helical bundle formula, corrugated plating soldering.
Have pedestal discharge re-generatively cooled partition plate by unsplit bedplate, the first circumferential partition plate, the second circumferential partition plate, the 3rd it is circumferential every
It is of substantially equal that plate, 6 piece of first radial direction partition plate, 12 piece of second radial direction partition plate and 18 piece of the 3rd radial direction partition plate form each area's area
37 separate plate and are welding as one.The height of each partition plate is identical preferably to take 80-100mm and as partition plate sequence number increases and increased width
Preferably take 10-20mm.Each partition plate it is single or it is double be uniformly provided with spacer width is different and elongated axial hole that diameter is different, every
On circumferential partition plate at plate right-angled intersection and the ragged edge of outer ring radial direction partition plate is provided with the elongated axial hole in small-bore.Unsplit bedplate is set
It puts the hydrogen delivery chute group to match with each baffle dimensions and lateral wall is set to be used for being welded and fixed with articulation set ring.First it is circumferential every
The approximate relation of plate inside radius R and radial direction septum plate length H is R=0.61H.And whole pedestal can not had to.
The spray face of ejector filler disk be provided with closed with double spray orifice segmental arc plate group flange sealing wide circumferential slot group, with single
The spray orifice segmental arc plate group flange sealing narrow circumferential slot group closed and the 3 narrow radial slots closed with spray radial plate flange sealing.Also
It is provided with and separates below the partition plate shut of unsplit bedplate welding of plate radial slot group below annular groove group and partition plate with 37, and with
The increase of partition plate sequence number and increase the width of slot.
The center of force-bearing base and ejector filler disk sets electric igniter pipeline, in thrust chamber ignition start electric point
The torch that firearm generates is introduced in thrust chamber.Liquid hydrogen enters the thrust indoor time preferably earlier than torch entry time 0.1-0.2 seconds,
Liquid oxygen enters the thrust indoor time and is preferably later than torch entry time 0.1-0.2 seconds, and it is preferably late that kerosene enters the thrust indoor time
In liquid oxygen entry time 0.1-0.2 seconds.
Cancel body portion kerosene and enter pipe and body portion kerosene in the traditional body portion of the first of the first three constituent element thrust chamber of high thrust
Efferent duct, and liquid hydrogen is entered the position of pipe and is moved to by throat downstream close to outside nozzle and as entirely with liquid hydrogen re-generatively cooled
With second of traditional body portion of no cooling ring band.Thus form second and pushed away entirely with the 300-600 tons in liquid hydrogen re-generatively cooled body portion
Three constituent element thrust chamber of power.
The head kerosene of second of three constituent element thrust chamber of high thrust enters one kerosene three-way pipe of welding on pipe.It is defeated in gas hydrogen
A gas hydrogen three-way pipe is welded in outlet pipe.One gas hydrogen valve is set between the gentle hydrogen three-way pipe of kerosene three-way pipe.Switch fuel
When in cutting off kerosene three-way pipe kerosene flowing after, be spaced 0.1 second to 0.3 second open gas hydrogen valve.The hydrogen that makes to bring about the desired sensation enters coal
Oil pipe line sprays into thrust chamber and oxygen rich air burning from kerosene from hitting to, kerosene inclined hole and the small axial hole of kerosene.In order not to make switching
Gas hydrogen flow velocity after fuel is excessive, and the outmost turns radial slot of ejector filler disk can use depth capacity instead and be not more than the outer of 15% disk diameter
Enclose wedged bottom radial slot.Thus the three constituent element thrust chamber of 300-600 tons thrust early period that the third switching fuel turns hydrogen-oxygen is formed.
For first, second and third kind of three constituent element thrust chamber of high thrust, there are 37 in pedestal discharge re-generatively cooled partition plate to separate plate
Increase fourth circumferential partition plate and 24 piece of the 4th radial direction partition plate and separate plate as 61.The ejector filler disk of diameter 1.5-1.9m increases by 24
A 4th circle fan section.Increase by the 4th load connector.Thus form sub-sectional cooling or cool down body portion or even switching with liquid hydrogen entirely
The three constituent element thrust chamber of 600-1000 tons thrust of fuel.
For first, second and third kind of three constituent element thrust chamber of high thrust, there are 37 in pedestal discharge re-generatively cooled partition plate to separate plate
Cancel the 3rd circumferential partition plate and 18 piece of the 3rd radial direction partition plate and separate plate as 19.The ejector filler disk of diameter 0.85-1.05m is cancelled
18 the 3rd circle fan sections.Cancel the 3rd load connector.Thus form sub-sectional cooling or cool down body portion with liquid hydrogen entirely or even cut
Change the three constituent element thrust chamber of 200-300 tons thrust of fuel.
It should be noted that when second and third kind of three constituent element thrust chamber of high thrust uses liquid hydrogen re-generatively cooled body portion entirely, in order to ensure cold
But effect needs try to increase liquid hydrogen flow.Thrust chamber can select the partition plate more than subregion, to increase divider ends oxyhydrogen combustion
Ratio.The flow of the cooling gas hydrogen out of annulus spray can also be increased.
The advantageous effect and advantage of three kinds of three constituent element rocket thrust chambers of high thrust of the present invention be：
1. using, burning is oxygen kerosene outside ejector filler face and external combustion burning in partition plate end face is the technology of hydrogen-oxygen, had both simplified and has tied
Structure, and have the subregion effect for inhibiting somatic sypermutation.Igniter fuel igniting can be cancelled and be changed to simpler electric igniter
Igniting.There is thick ejector filler disk, 2-4 load connector, the porous interior conical shell for having gas rectified action, arranged side by side on thrust chamber head
The bipyramid shell of power transmission and gas set and with the direct current ejector filler for largely reducing number of components.Cancel three cooling ring bands in body portion.
Partition plate using cancel inlet tube, outlet tube and end and it is two layer lead soldered be changed to mono-shell hole-punched have pedestal discharge re-generatively cooled every
Plate.Thrust chamber is much simple in structure good with versatility, and technical difficulty is smaller, convenient for faster and better develops inexpensive engine.
2. the cooling performance of liquid hydrogen is good, in re-generatively cooled agent and thrust chamber as body portion and partition plate, the effect of cooling agent is very
It is good.The shortcomings that effectively compensating for limited kerosene cooling performance and meeting coking so that disposable oxygen kerosene thrust chamber has
Hope the three constituent element thrust chambers for becoming to reuse up to 50 times.
3. the molecular weight very little of liquid hydrogen.The border area ratio for being used as interior cooling agent by thermogenic gas hydrogen is leapt high.As partition plate cooling agent
Outside divider ends very high specific impulse is generated with the burning of partition plate both sides oxygen rich air.According to the scale of oxyhydrogen combustion part, three
Specific impulse of the constituent element thrust chamber than oxygen kerosene thrust chamber can increase 20-50 seconds.Switch fuel become hydrogen-oxygen specific impulse increase by 100 seconds with
On.
4. hydrogen-oxygen pattern is successively turned with the switching fuel of two kinds of different fuels using fuel flow path and ejector filler, before being different from
The two-way of the Soviet Union closes fuel mode all the way.Will not ablation body portion, partition plate and ejector filler disk, the problem of kerosene will not be freezed,
Gas generator, turbine pump and system condition will not be made to have big variation.This switching fuel mode is not only simple and reliable but also is easier to
It realizes.Propellant spray hole area before and after switching fuel is constant, and the flow-rate ratio kerosene oil flow that can make spray hydrogen fuel is much smaller, but
Hydrogen-oxygen is about three times larger than the mixing ratio of oxygen kerosene and than leaping high, so thrust decline will not be too many.
5. each area's area of ejector filler disk and partition plate is of substantially equal, the area of up to 19,37 and 61.The thrust generated per area is general
No more than 16 tons, it is good to inhibit the effect of somatic sypermutation, and increases the ratio of oxyhydrogen combustion.The outer ring of ejector filler disk is radially
Slot up to 12,18 and 24 and groove width maximum can get 17mm and can set outer ring wedged bottom radial slot when needed, thus solve
The problem of ejector filler disk infusion slot local velocity is bigger than normal.
In short, the three constituent element thrust chambers of the present invention are in one the advantages of concentrating oxygen kerosene thrust chamber and hydrogen-oxygen thrust chamber
Body.More become the advanced thrust chamber that integrates particularly by switching fuel.Certainly, three constituent element thrust chambers can increase supplies all the way
System.Switching fuel can occur of short duration thrust and decline.This is not big problem.
Three kinds of high thrusts, the three constituent element thrust chamber of the present invention, steps on Mars rocket suitable for manned moon landing, repeatedly uses
The engine of rocket, economic and practical rocket and re-entry space vehicle.Two kind of three constituent element thrust chamber for not switching fuel is used for booster
And first class engine.The three constituent element thrust chamber of one kind for switching fuel is used for core first class engine.
Description of the drawings
Fig. 1 the first with the three constituent element thrust chamber schematic diagram of 300-600 tons thrust in liquid hydrogen and kerosene sub-sectional cooling body portion
Fig. 2 heads side cutaway view
/ 6th of Fig. 3 ejector fillers disk and baffle combination figure
/ 6th of Fig. 4 ejector filler disk rear views
/ 6th of Fig. 5 partition plate unsplit bedplate schematic diagrams
The third switching fuel of Fig. 6 turns the three constituent element thrust chamber head side cutaway view of 200-300 tons thrust early period of hydrogen-oxygen
The ejector filler disk of three constituent element thrust chamber of 200-300 tons of thrusts of Fig. 7 and 1/6th of baffle combination figure
The a quarter of the porous interior conical shell schematic diagram of three constituent element thrust chamber of 200-300 tons of thrusts of Fig. 8
Specific embodiment
Fig. 1 to Fig. 8 is the preferred embodiment of identical three kinds of high thrusts, the three constituent element rocket thrust chamber of head construction of the present invention.
As shown in Figures 1 to 5, a kind of three constituent element thrust chamber of high thrust, is formed and is welded by head 1, body portion 2 and partition plate 3
The connector of one, head 1 and this three parts includes force-bearing base 4, ring flange 5, porous interior conical shell 6, outer conical shell 7, turbine exhaust
Introduce pipe 8, the first load connector 9, the second load connector 9A, the 3rd load connector 9B, articulation set ring 10, ejector filler
Disk 11, double spray orifice segmental arc plate group 12, single spray orifice segmental arc plate group 12A, spray radial plate 13, interior cooling ring 14, overlap joint
Semi-ring 15, head kerosene enter 16 gentle hydrogen efferent duct 17 of pipe.Head 1 is the high intensity head based on thick ejector filler disk 11
1A.Body portion 2 is the first traditional body portion 2A with liquid hydrogen and kerosene segmentation re-generatively cooled and without cooling ring band.Partition plate 3 is that have bottom
Seat discharge re-generatively cooled partition plate 3A is simultaneously hydrogen-cooled but with the gas that 2 re-generatively cooled of body portion changes.It is from what turbine exhaust introduced the entrance of pipe 8
Liquid oxygen carries out burning with a small amount of hydrogen and generates oxygen rich air of the temperature no more than 800K.Diameter 1.05-1.5m and thickness preferably take 10% directly
The ejector filler disk 11 in footpath presses 19,12 second, the first lap fan section in circle 18,6 circle fan section centered on equal area partition
19A and 18 the 3rd circle fan section 19B.By concentric two row or the single intensive gas axial hole for being provided with spray oxygen rich air in each area
20th, partition plate both sides gas axial hole 20A and small gas axial hole 20B and the disc thickness of half herein is preferably thinned.Double spray radial
Section plate group 12, single spray orifice segmental arc plate group 12A and spray radial plate 13 are provided with kerosene and hit certainly to 21, kerosene inclined hole 22 and coal
The small axial hole 23 of oil is used for spray from the kerosene after 2 re-generatively cooled of body portion that head kerosene enters the entrance of pipe 16.One kerosene is certainly
Hit the kerosene inclined hole 22 for being hit certainly to 21 and the composition liquid of gas axial hole 20 gas and mutually hitting spray unit or two small inclination 5-30 degree
Liquid gas, which is formed, with a gas axial hole 20 mutually hits spray unit and a kerosene inclined hole 22 and a small gas axial hole 20B group
Spray unit is mutually hit into outer ring liquid gas.Articulation set ring 10 is opened there are one kerosene access aperture 24 and sets kerosene collector 25.It is interior
Cooling ring 14 is circumferentially uniformly provided with gas hydrogen radial hole 26, small radial hole 27 and the annulus for cooling gas hydrogen in spray
28.It is opened on overlap joint semi-ring 15 there are one gas hydrogen delivery outlet 29 and gas hydrogen collector 30 is formed on the inside of it.Thus the first is formed
With liquid hydrogen and the three constituent element thrust chamber of 300-600 tons thrust in kerosene sub-sectional cooling body portion.
As shown in Fig. 2, three constituent element thrust chamber of high thrust, high intensity head 1A is with the first load connector 9, the second load
Connector 9A and the 3rd load connector 9B load and the ejector filler disk 11 of spray and oxygen rich air rectification and power transmission it is porous in
Conical shell 6 is welded into an entirety.Porous interior conical shell 6, outer conical shell 7 and turbine exhaust introduce pipe 8 form oxygen rich air input unit and
Power transmission arranged side by side.
As depicted in figs. 1 and 2, three constituent element thrust chamber of high thrust, the first tradition body portion 2A at throat downstream as boundary to divide
For leading portion 31 and back segment 32.Leading portion 31 carries out re-generatively cooled with the liquid hydrogen for entering the entrance of pipe 33 from liquid hydrogen and becomes gas hydrogen heated
Gas hydrogen collector 30 is flowed into afterwards.Back segment 32 carries out re-generatively cooled with the kerosene for entering the entrance of pipe 34 from body portion kerosene and is carried heated
Head kerosene is flowed to from body portion kerosene efferent duct 35 enter pipe 16 after high-temperature.
As shown in Fig. 2, Fig. 3 and Fig. 5, three constituent element thrust chamber of high thrust has pedestal to discharge re-generatively cooled partition plate 3A by entirety
The circumferential partition plate 37A of the circumferential partition plate 37, second of pedestal 36, first, the 3rd circumferential partition plate 37B, 6 piece of first 38,12 pieces of radial direction partition plate
Second radial direction partition plate 38A and 18 piece of the 3rd radial direction partition plate 38B forms that each area's area is of substantially equal 37 to be separated plate 3A3 and weld as one
Body.The height of each partition plate is identical preferably take 80-100mm and with partition plate sequence number increases and increased width preferably takes 10-20mm.Respectively every
Plate it is single or it is double be uniformly provided with spacer width is different and elongated axial hole 39 that diameter is different.At partition plate right-angled intersection
On circumferential partition plate and the ragged edge of outer ring radial direction partition plate is provided with the elongated axial hole 39A in small-bore.Unsplit bedplate 36 set with respectively every
The hydrogen delivery chute group 40 of board size matching simultaneously sets lateral wall 41 to be used for being welded and fixed with articulation set ring 10.
As shown in Figures 2 to 5, three constituent element thrust chamber of high thrust, the spray face of ejector filler disk 11 are provided with double spray orifice
Wide circumferential slot group 42 that 12 flange sealing of segmental arc plate group closes, the narrow circumferential direction closed with single spray orifice segmental arc plate group 12A flange sealings
Slot group 42A and the 3 narrow radial slot 43 closed with 13 flange sealing of spray radial plate.Also it is provided with the integral bottom for separating plate 3A3 with 37
Radial slot group 45 and increase below 36 partition plate shut of welding of seat below annular groove group 44 and partition plate with the increase of partition plate sequence number
Add the width of slot.
As shown in Figures 2 and 3, the center of three constituent element thrust chamber of high thrust, force-bearing base 4 and ejector filler disk 11 sets electric ignition
Device pipeline 46 is used for the torch that electric igniter is generated in thrust chamber ignition start and introduces in thrust chamber.Liquid hydrogen enters thrust
The indoor time is preferably earlier than torch entry time 0.1-0.2 seconds.Liquid oxygen enters the thrust indoor time and is preferably later than torch into fashionable
Between 0.1-0.2 seconds.Kerosene enters the thrust indoor time and is preferably later than liquid oxygen entry time 0.1-0.2 seconds.
As shown in Figure 1, three constituent element thrust chamber of high thrust, the first traditional body portion 2A cancels body portion kerosene and enters pipe 34 and body
Liquid hydrogen is simultaneously entered the position of pipe 33 and is moved to by throat downstream close to outside nozzle and as using liquid entirely by portion's kerosene efferent duct 35
Hydrogen re-generatively cooled and second of traditional body portion 2B without cooling ring band.Thus second is formed entirely with the 300 of liquid hydrogen cooling body portion
- 600 tons of three constituent element thrust chambers of thrust.
As shown in Figure 2 and Figure 6, three constituent element thrust chamber of high thrust, head kerosene enter one kerosene threeway of welding on pipe 16
Pipe 47.A gas hydrogen three-way pipe 48 is welded on gas hydrogen efferent duct 17.It is set between 47 gentle hydrogen three-way pipe 48 of kerosene three-way pipe
One gas hydrogen valve 49.It is spaced 0.1 second to 0.3 second and opens after the kerosene flowing in cutting off kerosene three-way pipe 47 when switching fuel
The hydrogen that makes to bring about the desired sensation of gas hydrogen valve 49 is opened to enter kerosene pipeline and spray into 21, kerosene inclined hole 22 and the small axial hole 23 of kerosene from kerosene from hitting
Thrust chamber burns with oxygen rich air.It is straight no more than 15% disk can to use depth capacity instead for radial slot group 45 below the partition plate of ejector filler disk 11
The outer ring wedged bottom radial slot 50 in footpath.Thus three constituent element of 300-600 tons thrust early period that the third switching fuel turns hydrogen-oxygen is formed to push away
Power room.
As shown in Fig. 2, Fig. 3 and Fig. 5, three constituent element thrust chamber of high thrust has 37 in pedestal discharge re-generatively cooled partition plate 3A
Separating plate 3A3 increases fourth circumferential partition plate 37C and 24 piece of the 4th radial direction partition plate 38C and separates plate 3A4 as 61.Diameter 1.5-
The ejector filler disk 11 of 1.9m increases by 24 the 4th circle fan section 19C.Increase by the 4th load connector 9C.Thus sub-sectional cooling is formed
Or body portion is cooled down with liquid hydrogen entirely or even switch the three constituent element thrust chamber of 600-1000 tons thrust of fuel.
As shown in Fig. 2, Fig. 6, Fig. 7 and Fig. 8, three constituent element thrust chamber of high thrust has in pedestal discharge re-generatively cooled partition plate 3A
37 separate plate 3A3 cancel the 3rd partition plate 37B and 18 piece of the 3rd radial direction partition plate 38B of circumferential direction and separate plate 3A2 as 19.Diameter
The ejector filler disk 11 of 0.85-1.05m cancels 18 the 3rd circle fan section 19B.Cancel the 3rd load connector 9B.Thus form and divide
Section cooling cools down body portion with liquid hydrogen entirely or even switches the three constituent element thrust chamber of 200-300 tons thrust of fuel.
Claims (10)
1. a kind of three constituent element thrust chamber of high thrust, is made of and welded, head (1) head (1), body portion (2) and partition plate (3)
Draw with the connector of this three parts including force-bearing base (4), ring flange (5), porous interior conical shell (6), outer conical shell (7), turbine exhaust
Enter pipe (8), the first load connector (9), the second load connector (9A), the 3rd load connector (9B), articulation set ring
(10), ejector filler disk (11), double spray orifice segmental arc plate group (12), single spray orifice segmental arc plate group (12A), spray radial plate
(13), interior cooling ring (14), overlap joint semi-ring (15), head kerosene enter the gentle hydrogen efferent duct (17) of pipe (16), it is characterised in that：
The head (1) is the high intensity head (1A) based on thick ejector filler disk (11), and body portion (2) are with liquid hydrogen and kerosene point
Section re-generatively cooled and the first traditional body portion (2A) without cooling ring band, partition plate (3) is that have pedestal to discharge re-generatively cooled partition plate
(3A) and hydrogen-cooled but with the gas that body portion (2) re-generatively cooled changes, what it is from turbine exhaust introducing pipe (8) entrance is liquid oxygen and a small amount of hydrogen
It carries out burning and generates the oxygen rich air that temperature is no more than 800K, diameter 1.05-1.5m and thickness preferably take the ejector filler disk of 10% diameter
(11) by circle (18) centered on equal area partition, 6 first lap fan sections (19), 12 the second circles fan section (19A) and
18 the 3rd are enclosed fan section (19B), by concentric two row or the single intensive gas axial hole for being provided with spray oxygen rich air in each area
(20), partition plate both sides gas axial hole (20A) and small gas axial hole (20B) and the disc thickness of half herein, double spray is preferably thinned
Orifice segmental arc plate group (12), single spray orifice segmental arc plate group (12A) and spray radial plate (13) are provided with kerosene and hit certainly to (21), coal
Oily inclined hole (22) and the small axial hole of kerosene (23) are used for body portion (2) re-generatively cooled that spray enters pipe (16) entrance from head kerosene
Kerosene afterwards, kerosene form (21) and a gas axial hole (20) in liquid gas and mutually hit spray unit or two small from hitting from hitting
The kerosene inclined hole (22) of inclination angle 5-30 degree forms liquid gas with a gas axial hole (20) and mutually hits spray unit and a kerosene inclined hole
(22) spray unit is mutually hit with one small gas axial hole (20B) composition outer ring liquid gas, articulation set ring (10) opens that there are one coals
Oily access aperture (24) simultaneously sets kerosene collector (25), and interior cooling ring (14) is circumferentially uniformly provided with gas hydrogen radial hole (26), small
Radial hole (27) and the annulus (28) for the gas hydrogen of cooling in spray overlap gas hydrogen there are one being opened on semi-ring (15) and export
Hole (29) simultaneously forms gas hydrogen collector (30) on the inside of it, thus forms the first with liquid hydrogen and kerosene sub-sectional cooling body portion
300-600 tons of three constituent element thrust chambers of thrust.
2. three constituent element thrust chamber of high thrust as described in claim 1, it is characterised in that：The high intensity head (1A) is to use
First load connector (9), the second load connector (9A) and the 3rd load connector (9B) are load and the ejector filler of spray
Disk (11) and the porous interior conical shell (6) of oxygen rich air rectification and power transmission are welded into an entirety, porous interior conical shell (6), outer conical shell (7)
Pipe (8) composition oxygen rich air input unit and power transmission arranged side by side are introduced with turbine exhaust.
3. three constituent element thrust chamber of high thrust as described in claim 1, it is characterised in that：The traditional body portion (2A) of the first described
To be divided into leading portion (31) and back segment (32) as boundary at throat downstream, leading portion (31) with from liquid hydrogen enter liquid hydrogen that pipe (33) enters into
Row re-generatively cooled and it is heated become gas hydrogen after flow into gas hydrogen collector (30), back segment (32) enters pipe (34) with from body portion kerosene
The kerosene of entrance carries out re-generatively cooled and flows to head kerosene entrance from body portion kerosene efferent duct (35) after heated raising temperature
It manages (16).
4. three constituent element thrust chamber of high thrust as described in claim 1, it is characterised in that：Described has pedestal to discharge re-generatively cooled
Partition plate (3A) is by unsplit bedplate (36), the first circumferential partition plate (37), the second circumferential partition plate (37A), the 3rd circumferential partition plate (37B), 6
Block the first radial direction partition plate (38), 12 piece of second radial direction partition plate (38A) and 18 piece of the 3rd radial direction partition plate (38B) form each area's area base
This equal 37 separates plate (3A3) and is welding as one, and the height of each partition plate is identical preferably to take 80-100mm and as partition plate sequence number increases
Add and increased width preferably takes 10-20mm, each partition plate it is single or it is double be uniformly provided with spacer width is different and diameter is different
Elongated axial hole (39), on the circumferential partition plate at partition plate right-angled intersection and the ragged edge of outer ring radial direction partition plate to be provided with small-bore thin
Long axial hole (39A), unsplit bedplate (36) set the hydrogen delivery chute group (40) to match with each baffle dimensions and set lateral wall
(41) it is used for being welded and fixed with articulation set ring (10).
5. three constituent element thrust chamber of high thrust as described in claim 1, it is characterised in that：The spray of the ejector filler disk (11)
Face be provided with closed with double spray orifice segmental arc plate group (12) flange sealing wide circumferential slot group (42), with single spray orifice segmental arc plate group
The narrow circumferential slot group (42A) and the 3 narrow radial slots closed with spray radial plate (13) flange sealing that (12A) flange sealing closes
(43), annular groove group (44) and partition plate below the partition plate that unsplit bedplate (36) welding for separating plate (3A3) with 37 is shut also are provided with
Radial slot group (45) and increase the width of slot with the increase of partition plate sequence number below.
6. three constituent element thrust chamber of high thrust as described in claim 1, it is characterised in that：The force-bearing base (4) and ejector filler
The center of disk (11) sets the torch that electric igniter is used for generating electric igniter in thrust chamber ignition start with pipeline (46)
It introduces in thrust chamber, liquid hydrogen enters the thrust indoor time preferably earlier than torch entry time 0.1-0.2 seconds, and liquid oxygen enters thrust chamber
The interior time is preferably later than torch entry time 0.1-0.2 seconds, and kerosene enters the thrust indoor time and is preferably later than liquid oxygen entry time
0.1-0.2 seconds.
7. three constituent element thrust chamber of high thrust as described in claim 1, it is characterised in that：The traditional body portion (2A) of the first described
Cancel body portion kerosene to enter pipe (34) and body portion kerosene efferent duct (35) and liquid hydrogen is entered the position of pipe (33) by throat downstream
Move to becomes full liquid hydrogen re-generatively cooled and second without cooling ring band traditional body portion (2B) close to outside nozzle, thus
Second is formed entirely with the three constituent element thrust chamber of 300-600 tons thrust in liquid hydrogen cooling body portion.
8. three constituent element thrust chamber of high thrust as claimed in claim 7, it is characterised in that：The head kerosene enters pipe (16)
One kerosene three-way pipe (47) of upper welding, welds a gas hydrogen three-way pipe (48), kerosene three-way pipe on gas hydrogen efferent duct (17)
(47) a gas hydrogen valve (49) is set between gentle hydrogen three-way pipe (48), when switching fuel in cut-out kerosene three-way pipe (47)
Kerosene flowing after be spaced and opens within 0.1 second to 0.3 second gas hydrogen valve (49) hydrogen that makes to bring about the desired sensation and enter kerosene pipeline oneself hits pair from kerosene
(21), kerosene inclined hole (22) and the small axial hole of kerosene (23) spray into thrust chamber and oxygen rich air is burnt, the partition plate of ejector filler disk (11)
Radial slot group (45) can use the outer ring wedged bottom radial slot (50) that depth capacity is not more than 15% disk diameter instead below, thus form the
Three kinds of switching fuel turn the three constituent element thrust chamber of 300-600 tons thrust early period of hydrogen-oxygen.
9. the three constituent element thrust chamber of high thrust as described in claim 1 or 7, it is characterised in that：Described has pedestal discharge regeneration
37 in cooled partition (3A) separate plate (3A3) increase fourth circumferential partition plate (37C) and 24 piece of the 4th radial direction partition plate (38C) form
Plate (3A4) is separated for 61, the ejector filler disk (11) of diameter 1.5-1.9m increases by 24 the 4th circles fan section (19C), increases the 4th
Load connector (9C) thus forms sub-sectional cooling or cools down body portion with liquid hydrogen entirely or even switch the 600-1000 ton thrusts of fuel
Three constituent element thrust chambers.
10. the three constituent element thrust chamber of high thrust as described in claim 1 or 7, it is characterised in that：Described has pedestal discharge regeneration
37 in cooled partition (3A) separate that plate (3A3) cancels the 3rd circumferential partition plate (37B) and 18 piece of the 3rd radial direction partition plate (38B) forms
Plate (3A2) is separated for 19, and the ejector filler disk (11) of diameter 0.85-1.05m cancels 18 the 3rd circles fan section (19B), cancels the
Three load connectors (9B) thus form sub-sectional cooling or are pushed away entirely with the 200-300 tons that liquid hydrogen cools down body portion or even switches fuel
Three constituent element thrust chamber of power.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710449940.2A CN107084073A (en) | 2017-06-15 | 2017-06-15 | Manned moon landing steps on Mars rocket ultra-large type liquid oxygen thrust chamber |
| CN2017104499402 | 2017-06-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108087154A true CN108087154A (en) | 2018-05-29 |
Family
ID=59606823
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710449940.2A Pending CN107084073A (en) | 2017-06-15 | 2017-06-15 | Manned moon landing steps on Mars rocket ultra-large type liquid oxygen thrust chamber |
| CN201711201099.1A Active CN107956601B (en) | 2017-06-15 | 2017-11-27 | Large-diameter rocket thrust chamber with discharging regenerative cooling partition plates |
| CN201810024944.0A Pending CN108087154A (en) | 2017-06-15 | 2018-01-11 | Identical three kinds of high thrusts, the three constituent element rocket thrust chamber of head construction |
Family Applications Before (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710449940.2A Pending CN107084073A (en) | 2017-06-15 | 2017-06-15 | Manned moon landing steps on Mars rocket ultra-large type liquid oxygen thrust chamber |
| CN201711201099.1A Active CN107956601B (en) | 2017-06-15 | 2017-11-27 | Large-diameter rocket thrust chamber with discharging regenerative cooling partition plates |
Country Status (1)
| Country | Link |
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| CN (3) | CN107084073A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114592989A (en) * | 2022-05-09 | 2022-06-07 | 西安航天动力研究所 | Liquid oxygen kerosene pintle injector thrust chamber and starting method thereof |
| CN117811286A (en) * | 2024-03-01 | 2024-04-02 | 云梦山(常州)科技有限公司 | Oil-cooled motor cooling system |
| CN117811286B (en) * | 2024-03-01 | 2024-05-14 | 云梦山(常州)科技有限公司 | Oil-cooled motor cooling system |
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| CN108979900A (en) * | 2018-08-29 | 2018-12-11 | 北京航天动力研究所 | A kind of collection pendular ring in liquid rocket engine thrust chamber body portion |
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| CN109812352A (en) * | 2019-03-06 | 2019-05-28 | 中南大学 | Rocket ejector and its thermal protection structure and thermal protection method |
| CN111456866A (en) * | 2020-04-14 | 2020-07-28 | 合肥中科重明科技有限公司 | Cooling liquid film forming structure of liquid rocket engine |
| CN111963339B (en) * | 2020-08-19 | 2021-07-20 | 西安航天动力研究所 | Liquid film cooling rail attitude control engine thrust chamber |
| CN112746910A (en) * | 2020-10-29 | 2021-05-04 | 北京航天动力研究所 | Injector for inhibiting high-frequency unstable combustion |
| CN112412661A (en) * | 2020-12-01 | 2021-02-26 | 上海空间推进研究所 | Rocket engine direct-current injector combustion field partition structure |
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| CN114876671A (en) * | 2022-03-21 | 2022-08-09 | 西安航天动力研究所 | Hydrogen peroxide thrust chamber and engine |
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| CN114592989B (en) * | 2022-05-09 | 2022-08-16 | 西安航天动力研究所 | Liquid oxygen kerosene pintle injector thrust chamber and starting method thereof |
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| CN117811286B (en) * | 2024-03-01 | 2024-05-14 | 云梦山(常州)科技有限公司 | Oil-cooled motor cooling system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107956601A (en) | 2018-04-24 |
| CN107084073A (en) | 2017-08-22 |
| CN107956601B (en) | 2021-12-28 |
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