CN107956601A - One group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate - Google Patents
One group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate Download PDFInfo
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- CN107956601A CN107956601A CN201711201099.1A CN201711201099A CN107956601A CN 107956601 A CN107956601 A CN 107956601A CN 201711201099 A CN201711201099 A CN 201711201099A CN 107956601 A CN107956601 A CN 107956601A
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- Prior art keywords
- partition plate
- axial hole
- liquid
- hydrogen
- thrust chamber
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- 238000005192 partition Methods 0.000 title claims abstract description 165
- 239000007788 liquid Substances 0.000 claims abstract description 120
- 239000007789 gas Substances 0.000 claims abstract description 115
- 239000001257 hydrogen Substances 0.000 claims abstract description 85
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 85
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 82
- 239000001301 oxygen Substances 0.000 claims abstract description 75
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 75
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 claims abstract description 64
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 53
- 239000003350 kerosene Substances 0.000 claims abstract description 32
- 238000001816 cooling Methods 0.000 claims abstract description 22
- 238000000034 method Methods 0.000 claims abstract description 7
- 239000007921 spray Substances 0.000 claims description 90
- 239000002826 coolant Substances 0.000 claims description 42
- 239000000446 fuel Substances 0.000 claims description 41
- 239000000945 filler Substances 0.000 claims description 39
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 18
- 239000003795 chemical substances by application Substances 0.000 claims description 15
- 238000002485 combustion reaction Methods 0.000 claims description 14
- 239000000203 mixture Substances 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 7
- 230000002269 spontaneous effect Effects 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000005068 transpiration Effects 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 229910001882 dioxygen Inorganic materials 0.000 claims description 2
- 150000002431 hydrogen Chemical class 0.000 claims 3
- 230000008929 regeneration Effects 0.000 claims 2
- 238000011069 regeneration method Methods 0.000 claims 2
- 230000005611 electricity Effects 0.000 claims 1
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 abstract description 3
- 230000001464 adherent effect Effects 0.000 abstract description 2
- 230000000392 somatic effect Effects 0.000 abstract description 2
- 230000007812 deficiency Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000000354 decomposition reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000338 in vitro Methods 0.000 description 2
- 239000007791 liquid phase Substances 0.000 description 2
- 150000002978 peroxides Chemical class 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 239000012071 phase Substances 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Classifications
-
- 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
- F02K9/60—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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Separation By Low-Temperature Treatments (AREA)
Abstract
The present invention relates to one group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate.Have that oxygen kerosene is large-scale super-huge or huge, hydrogen-oxygen is large-scale or it is super-huge, hydrogen peroxide is large-scale super-huge or huge, large-scale or ten kinds super-huge etc. with the hydrogen-oxygen of hydrogen rich gas.Provide and uniformly open elongated axial hole and with or without 13 (10) areas, 29 (22) areas and 45 (34) areas discharge re-generatively cooled partition plate of termination, can effectively suppress somatic sypermutation.Give the interior cooling improved procedure of annulus, make liquid film or air film evenly with it is adherent.Having increases the reinforced bipyramid shell head of third and fourth load connector.Gas jets axial hole and nozzle for liquid form Orifice Injector with small straight hole.Thrust chamber is simple in structure and versatility is good, and number of components is largely reduced.Technical difficulty is smaller, can shorten the lead time and reduce cost.Hydrogen peroxide and hydrogen-oxygen thrust chamber can reuse 25 200 times and 2 25 times respectively.Mars rocket engine etc. is stepped on suitable for manned moon landing.
Description
Technical field
The present invention relates to one group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate, belong to oxygen kerosene, hydrogen-oxygen
With peroxide rocket technical field.
Background technology
The ultra-large type and large rocket thrust chamber (201710449940.2,201710449991.5 and PCT/ that I proposes
CN2017/000482), although having many good qualities and being worth selecting, there is also some shortcomings.Mainly using has disengaging liquid pipe
Re-generatively cooled partition plate, structure are more complicated.It is both advantageous and disadvantageous that partition plate cooling agent is used as cooling film liquid in thrust chamber.Profit is to improve thrust chamber
Interior cooling performance etc..Disadvantage is the composition tripropellant thrust chamber having, and increases the complexity of engine supply system, and makes fortune
Carry rocket increase storage tank and supply line.In addition, thrust chamber is not provided with electric ignition device, it is impossible to meets hydrogen-oxygen and peroxide very well
Change the quick requirement of hydrogen thrust chamber ignition start.High intensity head is only inadequate with 1 or 2 load connector, particularly with
Huge rocket thrust chamber more dislikes few.The gas that pipe introducing is introduced from turbine exhaust only limits oxygen rich air, does not meet oxyhydrogen engine whirlpool
The gas-powered present situation of wheel hydrogen-rich.
In view of the above problems, I finds the method for eliminating deficiency by further investigation.Mainly with discharge re-generatively cooled
Partition plate, also has some other technical measures.The cooling agent of this partition plate is not used as cooling film liquid in thrust chamber, but is discharged into and pushes away
Burning is participated in power room.Partition plate disengaging liquid pipe can thus be cancelled.Thus more simple and practical ultra-large type and large rocket are formed
Thrust chamber, and huge rocket thrust chamber.
The content of the invention
The manned moon landing proposed for me steps on Mars ultra-large type and large rocket thrust chamber there are above-mentioned deficiency, in order to
Deficiency is eliminated so as to develop more simple and practical large-scale, ultra-large type and huge rocket thrust chamber, the present invention provides one group with row
Put the major diameter rocket thrust chamber of re-generatively cooled partition plate.
A kind of major diameter basic model thrust chamber, 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, spray segmental arc plate group, spray radial plate, head body
Connect attachment strap, igniter fuel collector and igniter fuel and enter pipe.Head is the 3rd load connector of increase spray and stress
Ejector filler disk and the more firm reinforced bipyramid shell enlarged head being connected of the porous interior conical shell of gas rectification and power transmission.Body portion is to use
Kerosene is as re-generatively cooled agent and interior cooling agent and only with the first traditional body portion of second and third road cooling ring band.Partition plate is
29th area or 22nd area discharge re-generatively cooled partition plate.What it is from turbine exhaust introducing pipe entrance is that whole liquid oxygen burn with a small amount of kerosene
Produce the oxygen rich air that temperature is no more than 800K.It is a interior that thickness preferably takes the ejector filler disk of 90-140mm to be divided into central circular area, 4 (3)
By concentric two row or single intensive spray is provided with fan section, a outer fan section Bing Ge areas in a fan section in 8 (6) and 16 (12)
Gas axial hole, partition plate both sides gas axial hole and the outer ring gas axial hole of oxygen rich air.Spray segmental arc plate group and spray radial plate are double
Or the single liquid that is provided with is from the kerosene hit after being used for spray body portion re-generatively cooled to, small axial hole and liquid outer ring inclined hole.One
Liquid forms liquid gas with a gas axial hole and mutually hits spray unit from hitting from hitting pair.One or two liquid outer ring inclined hole and one
The liquid gas that outer ring gas axial hole composition mutually hits angle 0-30 degree mutually hits spray unit.Articulation set ring is circumferentially uniformly provided with igniting combustion
Expect inclined hole, cooling agent sprocket hole and annulus.Thrust chamber diameter D=0.9-1.4m.Thus form with discharge re-generatively cooled every
The ultra-large type oxygen kerosene thrust chamber of plate.
29th area of major diameter basic model thrust chamber or 22nd area discharge re-generatively cooled partition plate be by circumferential partition plate, outer circumferential direction every
Plate, 4 (3) blocks radially inside partition plate, 8 (6) block radial direction partition plates and 16 (12) block outer radial partition plates composition and it is welded.Partition plate
For suppress somatic sypermutation and reduce single order is tangential, single order radially, the acoustic vibration such as second order is tangential.Each composition portion of partition plate
Point be uniformly provided with elongated axial hole be used for the kerosene as partition plate cooling agent to be discharged into thrust chamber and with partition plate both sides gas axis
Mixed combustion is carried out to the oxygen rich air of hole spray.This liquid phase subregion ejector filler, contribute to enhancing partition plate effectiveness in vibration suppression and
Reduce single order longitudinal direction acoustic vibration.What a outer radial partition plate ragged edge in 16 (12) was opened is the elongated axial hole of minor diameter.Partition plate is high
Degree preferably takes 80-100mm.Each part of partition plate and two corresponding annulars in radial slot group and annular groove group that ejector filler disk is opened
Groove matching merging is welded and fixed.
The annulus of major diameter basic model thrust chamber is opened between the gap inner wall of articulation set ring and gap outer wall.Seam
Gap outer wall is circumferentially uniformly provided with small radial hole.The a small amount of re-generatively cooled agent introduced from small radial hole enters corner behind annulus
90 degree of sprays, become cooling improved procedure in similar cooling ring band but different thrust chamber.
Major diameter basic model thrust chamber is reduced, and head is a outer fan section of cancellation 16 (12) and the 3rd load connector
The diminution head formed.Use outer ring gas axial hole and corresponding liquid outer ring inclined hole instead in the outer ring in a fan section in 8 (6).Partition plate is
Cancel 13rd area or the 10th area discharge re-generatively cooled partition plate that outer circumferential partition plate and 16 (12) block outer radial partition plates form.Radial direction partition plate
What ragged edge was opened is the elongated axial hole of minor diameter.Ejector filler disc thickness is preferably changed to 60-90mm and thrust chamber diameter D=0.6-
0.9m.Thus large-scale oxygen kerosene thrust chamber i.e. the first derivative type thrust chamber with discharge re-generatively cooled partition plate is formed.
The first derivative type thrust chamber and major diameter basic model thrust chamber carry out same local change and refuelling.Spray
Note segmental arc plate group cancels the liquid opened from hitting pair and liquid outer ring inclined hole changes out the gas hydrogen axial hole and outer ring gas hydrogen of dense arrangement
Axial hole.Body portion is to use second as re-generatively cooled agent and without cooling ring band traditional body portion of liquid hydrogen instead, and liquid hydrogen by
Heat deflection is from annulus, small axial hole, gas hydrogen axial hole, outer ring gas hydrogen axial hole, elongated axial hole and small straight after gas hydrogen
The elongated axial hole spray in footpath.The oxygen rich air that pipe entrance is introduced from turbine exhaust is changed to whole liquid oxygen and a small amount of gas hydrogen or liquid hydrogen progress
Burning produces the oxygen rich air that temperature is no more than 800K.Cancel igniter fuel collector, igniter fuel enters pipe and igniter fuel is oblique
Hole and the center of changing into force-bearing base and ejector filler disk sets electric igniter pipeline.Oxygen rich air and the corresponding partition plate of gas hydrogen burning are high
Degree preferably uses 60-80mm.Respectively constitute large-scale hydrogen-oxygen thrust chamber i.e. second of derivative type thrust chamber with discharge re-generatively cooled partition plate
With ultra-large type hydrogen-oxygen thrust chamber i.e. the third derivative type thrust chamber with discharge re-generatively cooled partition plate.
The first derivative type thrust chamber and major diameter basic model thrust chamber carry out same change and refuelling.Outer ring gas
The small axial hole in liquid outer ring is added on the outside of axial hole.Articulation set ring is cancelled igniter fuel inclined hole and cooling agent sprocket hole and is become
Increase the articulation set ring A for the liquid radial hole that is uniformly distributed along the circumference.Articulation set ring A outside increase liquid collector and liquid into
Enter pipe.From liquid enter pipe enter and from liquid from hit to, it is small axial hole, liquid outer ring inclined hole, the small axial hole in liquid outer ring, thin
Long axial hole and the elongated axial hole spray of minor diameter are kerosene or NHMF fuel or liquid hydrogen with hydrogen peroxide spontaneous combustion.Head body connects
Connect attachment strap and be changed to circumferentially uniformly be provided with the head body of cooling agent delivery outlet and be connected with hole attachment strap, add cooling agent output collection on it
Clutch and cooling agent efferent duct.Body portion is to use technical grade 70%-84.9% hydrogen peroxide instead for re-generatively cooled agent and without cooling ring
The third traditional body portion of band, and most of re-generatively cooled agent and sub-fraction are exported from annulus from cooling agent efferent duct
Spray.The oxygen rich air that pipe entrance is introduced from turbine exhaust is changed to complete or incomplete decomposing technical grade 70%-84.9% peroxidating
Hydrogen produces the oxygen rich air of temperature 600-800K.Cancel igniter fuel collector and igniter fuel enters pipe and changes into force-bearing base and spray
The center for noting device disk sets electric igniter pipeline.Respectively constitute the large-scale hydrogen peroxide thrust chamber with discharge re-generatively cooled partition plate
That is the 4th kind of derivative type thrust chamber and ultra-large type hydrogen peroxide thrust chamber i.e. the 5th kind derivative type with discharge re-generatively cooled partition plate
Thrust chamber.
4th kind of derivative type thrust chamber and the 5th kind of same refuelling of derivative type thrust chamber.Use second of tradition instead in body portion
Body portion, and liquid hydrogen it is heated be changed into gas hydrogen after largely sprayed from the output of cooling agent efferent duct and sub-fraction from annulus
Note.From liquid enter pipe enter and from liquid from hit to, it is small axial hole, the small axial hole in liquid outer ring, liquid outer ring inclined hole, elongated
Axial hole and the elongated axial hole spray of minor diameter are most of liquid oxygen.From turbine exhaust introduce pipe enter and from gas axial hole,
Partition plate both sides gas axial hole and outer ring gas axial hole spray are that gas hydrogen is burnt and mixed generation temperature with fraction liquid oxygen
Hydrogen rich gas no more than 800K.Respectively constitute large-scale hydrogen-oxygen thrust chamber i.e. the 6th kind with discharge re-generatively cooled partition plate and hydrogen rich gas
Derivative type thrust chamber and ultra-large type hydrogen-oxygen thrust chamber i.e. the 7th kind derivative type thrust with discharge re-generatively cooled partition plate and hydrogen rich gas
Room.
Major diameter basic model thrust chamber and the 5th kind of derivative type thrust chamber are equally amplified.Head is that increase by 16 (12) is a
The enlarged head that 4th circle fan section and the 4th load connector form.The outer ring gas axial hole and phase in a outer fan section in 16 (12)
The liquid outer ring inclined hole answered changes the outer ring for being arranged on a 4th circle fan section in 16 (12).Partition plate is the circumferential partition plate and 16 of increase the 3rd
(12) block the 4th encloses 45th area or the 34th area discharge re-generatively cooled partition plate that radial direction partition plate forms.A outer radial partition plate outermost in 16 (12)
While the elongated axial hole of the minor diameter opened changes the ragged edge for being arranged on 16 (12) blocks the 4th circle radial direction partition plate.Ejector filler disc thickness preferably takes
140-170mm, thrust chamber diameter D=1.4-1.7m.Respectively constitute the huge oxygen kerosene thrust with discharge re-generatively cooled partition plate
Room i.e. the 8th kind derivative type thrust chamber and huge hydrogen peroxide thrust chamber i.e. the 9th kind derivative type with discharge re-generatively cooled partition plate
Thrust chamber.
According to this amplification method, megathrust room can also use 61 (46) areas or 77 (58) to separate plate, and accordingly increase
Five, the six load connectors and ejector filler disk is thickened to 170-230mm, the thrust chamber for diameter D=1.7-2.3m.
It should be pointed out that 13 (10) areas, 29 (22) areas and the discharge of 45 (34) areas re-generatively cooled partition plate kerosene and hydrogen peroxide
The NHMF of spontaneous combustion is when liquid fuel is as partition plate cooling agent, and the aperture of elongated axial hole is insufficient to small, can make liquid phase subregion
The mixed combustion of ejector filler is incomplete, and thrust chamber efficiency of combustion and specific impulse decline.It is small that this uniformly can be provided with spray by setting
The termination in hole solves.It is corresponding circumferential in each part welding of partition plate exemplified by discharging re-generatively cooled partition plate by 29 (22) areas
Clapboard end, outer circumferential clapboard end, a radially inside clapboard end in 4 (3), a radial direction clapboard end in 8 (6) and 16 (12) are a outer
Side radial direction clapboard end.Uniformly it is covered with aperture on each termination made by porous transpiration material or high-temperature heat-resistance material to be less than
The spray aperture of 0.5mm.The partition plate cooling agent of spray micropore jet is fully mixed with the oxygen rich air of partition plate both sides gas axial hole spray
Combination burning.The spray aperture arrangement density of 16 (12) block outer radial clapboard end ragged edges is small.
The present invention one group totally ten kinds with discharge re-generatively cooled partition plate major diameter rocket thrust chamber beneficial effect and advantage
It is：
Elongated axial hole is uniformly opened 1. providing and with or without the discharge re-generatively cooled partition plate of termination, suppresses the unstable combustion of high frequency
The effect of burning is good.Cancel inlet tube, outlet tube and base, and mono-shell hole-punched is changed to two layer lead soldered, it is much simple in structure and add
Work is convenient.13 (10) separate large-scale thrust chamber of the plate suitable for 100-200 tons of thrust.29 (22) separate plate and are suitable for 200-500
The ultra-large type thrust chamber of ton thrust.45 (34) separate the megathrust room that plate is then suitable for 500-800 tons of thrust.
2. thrust chamber head be by the ejector filler disk of thickness 60-170mm, two to four load connectors, porous interior conical shell,
The reinforced bipyramid shell head of the parts such as outer conical shell composition, intensity height and reliable operation.Ejector filler is to include axial hole, hit certainly pair
With the single flow of inclined hole, beneficial to vibration damping, protection panels and efficiency of combustion is improved.With the three of existing oxygen kerosene and hydrogen-oxygen thrust chamber
Layer bottom or four layers of bottom head construction and coaxial tube nozzle are very different.Structure is simpler, especially cancels thousands of
Nozzle greatly reduces number of components.
3. thrust cell structure versatility is good.One group totally ten kinds of oxygen kerosenes, hydrogen-oxygen and hydrogen peroxide thrust chamber head knot
Structure is similar.Same partition plate is that subregion is how many and the difference of height.Without three constituent element thrust chambers, simplify structure and use
It is convenient.Hydrogen-oxygen thrust chamber both useful oxygen rich air, also useful hydrogen rich gas, it can match from different supply systems and turbine pump
Close.
4. provide the interior cooling improved procedure of annulus, make in thrust chamber cooling liquid film or air film evenly with it is adherent.
The requirement started always according to hydrogen-oxygen and hydrogen peroxide thrust chamber rapid-ignition, electric igniter pipeline is set in thrust chamber center,
Igniter of powering, which sprays, starts torch use.
5. hydrogen peroxide thrust chamber is used as oxidant and re-generatively cooled agent using the hydrogen peroxide of technical grade 70% to 84.9%
It is safe, cooling performance is good, easy to use, and density ratio is leapt high, and price is relatively low.The thousands of degree of ignition temperature are reduced to 1958-
2430 DEG C, it is 600-800K to control actual decomposition temperature by complete or endless decomposition, 20-40 DEG C of re-generatively cooled temperature rise so that
Thrust chamber operating condition is greatly improved, economic and practical and reuse and lay technical foundation 25-200 times for engine.
6. the technical difficulty of one group of ten kinds of major diameter thrust chamber is smaller, development progress can be accelerated, shorten the lead time and
Reduce cost.
The major diameter rocket thrust chamber of discharge re-generatively cooled partition plate of one group of the present invention, Mars is stepped on suitable for manned moon landing
Rocket, the engine for repeatedly using rocket, economic and practical rocket and re-entry space vehicle.Oxygen kerosene thrust chamber therein is used
In disposable booster and first class engine.The core firsts and seconds that hydrogen-oxygen thrust chamber is used for access times 1-25 time is sent out
Motivation.Hydrogen peroxide thrust chamber is used for each stage motor of access times 1-200 times.
Brief description of the drawings
The ultra-large type oxygen kerosene thrust chamber schematic diagram of Fig. 1 discharge re-generatively cooled partition plates
Fig. 2 heads and a quarter of partition plate side cutaway view
The a quarter of Fig. 3 ejector fillers disk and baffle combination figure
The connection figure of Fig. 4 partition plates etc. and ejector filler disk
The connection profile of Fig. 4-1 circumferential direction partition plates and ejector filler disk
The connection profile of Fig. 4-2 radial directions partition plate and ejector filler disk
Fig. 4-3 sprays radial plate and the connection profile of ejector filler disk
The a quarter of Fig. 5 large-scale the hydrogen-oxygen thrust chamber ejector filler disk and baffle combination figure of discharge re-generatively cooled partition plate
Fig. 6 with discharge re-generatively cooled partition plate large-scale hydrogen peroxide thrust chamber head and partition plate side cutaway view four/
One
The a quarter of Fig. 7 ejector filler disks corresponding with Fig. 6 and baffle combination figure
45th areas of Fig. 8 megathrusts Shi and 34 separate plate schematic diagram
29th areas of Fig. 9 or the clapboard end connection figure and spray aperture arrangement figure of 22nd area discharge re-generatively cooled partition plate
The connection profile of Fig. 9-1 circumferential direction clapboard ends and circumferential partition plate
The connection profile of Fig. 9-2 radial directions clapboard end and radial direction partition plate
The spray aperture arrangement figure of Fig. 9-3 circumferential direction clapboard ends
The spray aperture arrangement figure of Fig. 9-4 outer radial clapboard ends
Embodiment
Fig. 1 to Fig. 9 is the preferred embodiment of one group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate of the present invention.
As shown in Figure 1, Figure 2 and Figure 3, a kind of major diameter basic model thrust chamber is formed and welded by head 1, body portion 2 and partition plate 3
Connect one.The connector of head 1 and this three parts includes force-bearing base 4, ring flange 5, porous interior conical shell 6, outer conical shell 7, turbine row
Gas introduces pipe 8, the first load connector 9, the second load connector 9A, the 3rd load connector 9B, articulation set ring 10, spray
Device disk 11, spray segmental arc plate group 12, spray radial plate 13, head body connection attachment strap 14, igniter fuel collector 15 and igniter fuel
Into pipe 16.Head 1 is the 3rd load connector 9B of increase the ejector filler disk 11 of spray and stress and gas rectification and power transmission
The more firm connected reinforced bipyramid shell enlarged head 1A of porous interior conical shell 6.Body portion 2 is to be used as re-generatively cooled agent and interior by the use of kerosene
Cooling agent and only with the first tradition body portion 2A of second cooling ring band 17A and the 3rd cooling ring with 17B.Partition plate 3 is
29th area or 22nd area discharge re-generatively cooled partition plate 3A.What it is from the turbine exhaust introducing entrance of pipe 8 is that whole liquid oxygen are carried out with a small amount of kerosene
Burning produces the oxygen rich air that temperature is no more than 800K.Thickness preferably takes the ejector filler disk 11 of 90-140mm to divide for central circular area 18,4
(3) a interior fan section 19A, in a outer fan section 19B Bing Ge areas of a fan section 19 and 16 (12) in 8 (6) by concentric two row or
The single intensive gas axial hole 20 for being provided with spray oxygen rich air, partition plate both sides gas axial hole 20A and outer ring gas axial hole 20B.Spray
Segmental arc plate group 12 and spray radial plate 13 is double or the single liquid that is provided with is from hitting to 21, small axial hole 22 and liquid outer ring inclined hole 23
For the kerosene after 2 re-generatively cooled of spray body portion.One liquid is mutual from hitting to 21 and the composition liquid gas of gas axial hole 20 from hitting
Hit spray unit and one or two liquid outer ring inclined hole 23 and an outer ring gas axial hole 20B composition mutually hits the liquid of angle 0-30 degree
Gas mutually hits spray unit.Articulation set ring 10 is circumferentially uniformly provided with igniter fuel inclined hole 24, cooling agent sprocket hole 25 and annular
Gap 26.Thrust chamber diameter D=0.9-1.4m.Thus the ultra-large type oxygen kerosene thrust with discharge re-generatively cooled partition plate is formed
Room.
As shown in Figure 2, Figure 3 and Figure 4, major diameter basic model thrust chamber, 29th area or 22nd area discharge re-generatively cooled partition plate 3A are
By circumferential partition plate 27, outer circumferential partition plate 27A, 4 (3) blocks radially inside outside partition plate 28A, 8 (6) block radial direction partition plates 28 and 16 (12) blocks
Radial direction partition plate 28B compositions in side are simultaneously welded.Each part of partition plate is uniformly provided with elongated axial hole 29 and is used as partition plate for handle
The kerosene of cooling agent is discharged into thrust chamber and carries out mixed combustion with the oxygen rich airs of partition plate both sides gas axial hole 20A sprays, and 16
(12) that a outer radial partition plate 28B ragged edges are opened is the elongated axial hole 29A of minor diameter, and divider height preferably takes 80-100mm, every
Each part of plate is engaged with two corresponding annular grooves in radial slot group 30 and annular groove group (31) that ejector filler disk 11 is opened
And it is welded and fixed.
As shown in Figures 2 and 3, major diameter basic model thrust chamber, annulus 26 are opened in the gap of articulation set ring 10
Between wall 32 and gap outer wall 33.Gap outer wall 33 is circumferentially uniformly provided with small radial hole 34.Lack from what small radial hole 34 introduced
Re-generatively cooled agent is measured into 90 degree of sprays of corner behind annulus 26 and as the improved procedure of cooling in thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 6 and Fig. 7, major diameter basic model thrust chamber, head 1 is a outer fan section of cancellation 16 (12)
The diminution head 1B that 19B and the 3rd load connector 9B are formed.Use outer ring gas axial hole 20B instead in the outer ring in a fan section 19 in 8 (6)
And corresponding liquid outer ring inclined hole 23.Partition plate 3 is to cancel outer circumferential direction partition plate 27A and 16 (12) block outer radial partition plate 28B to form
13rd area or 10th area discharge re-generatively cooled partition plate 3B.That 28 ragged edge of radial direction partition plate is opened is the elongated axial hole 29A of minor diameter.Spray
The thickness of device disk 11 is preferably changed to 60-90mm and thrust chamber diameter D=0.6-0.9m.Thus form with discharge re-generatively cooled partition plate
Large-scale oxygen kerosene thrust chamber i.e. the first derivative type thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 5 and Fig. 6, the first derivative type thrust chamber, spray segmental arc plate group 12 cancels the liquid opened
From hitting the gas hydrogen axial hole 35 and outer ring gas hydrogen axial hole 35A that 21 and liquid outer ring inclined hole 23 changed out with dense arrangement.Body portion 2 is
Use second tradition body portion 2B and liquid hydrogen of the liquid hydrogen as re-generatively cooled agent and without cooling ring band instead and be changed into gas hydrogen heated
Afterwards from annulus 26, small axial hole 22, gas hydrogen axial hole 35, outer ring gas hydrogen axial hole 35A, elongated axial hole 29 and minor diameter
Elongated axial hole 29A sprays.From turbine exhaust introduce the oxygen rich air that pipe 8 enters be changed to whole liquid oxygen and a small amount of gas hydrogen or liquid hydrogen into
Row burning produces the oxygen rich air that temperature is no more than 800K.Cancel igniter fuel collector 15, igniter fuel enters pipe 16 and igniting
Fuel inclined hole 24 and the center of changing into force-bearing base 4 and ejector filler disk 11 sets electric igniter pipeline 36.Oxygen rich air is fired with gas hydrogen
The correspondence divider height of burning preferably uses 60-80mm.Thus the large-scale hydrogen-oxygen thrust chamber i.e. second with discharge re-generatively cooled partition plate is formed
Kind derivative type thrust chamber.
As shown in Fig. 2, Fig. 3 and Fig. 5, major diameter basic model thrust chamber, spray segmental arc plate group 12 changes out the gas of dense arrangement
Hydrogen axial hole 35 and outer ring gas hydrogen axial hole 35A.Body portion 2 is to use second of tradition body portion 2B instead and liquid hydrogen is changed into heated
From annulus 26, small axial hole 22, gas hydrogen axial hole 35, outer ring gas hydrogen axial hole 35A, elongated axial hole 29 and small after gas hydrogen
The elongated axial hole 29A sprays of diameter.What it is from the turbine exhaust introducing entrance of pipe 8 is that liquid oxygen gas hydrogen or liquid hydrogen burning produce temperature and do not surpass
Cross the oxygen rich air of 800K.Cancel igniter fuel collector 15, igniter fuel enters pipe 16 and igniter fuel inclined hole 24 and changes into and hold
The center of power seat 4 and ejector filler disk 11 sets electric igniter pipeline 36.Oxygen rich air and the corresponding divider height of gas hydrogen burning are suitable
Use 60-80mm.Thus a kind of ultra-large type hydrogen-oxygen thrust chamber i.e. the third derivative type thrust with discharge re-generatively cooled partition plate is formed
Room.
As shown in Fig. 2, Fig. 3, Fig. 6 and Fig. 7, the first derivative type thrust chamber, adds liquid on the outside of the gas axial hole 20B of outer ring
Small axial hole 22A is enclosed in vitro.Articulation set ring 10, which cancels igniter fuel inclined hole 24 and cooling agent sprocket hole 25, becomes increase along circle
The articulation set ring A 10A of Zhou Junbu liquid radial hole 37.The outside increase liquid collector 38 and liquid of articulation set ring A 10A
Body enters pipe 39.Enter pipe 39 from liquid to hit to 21, small axial hole 22, liquid outer ring inclined hole 23, liquid certainly into and from liquid
The small axial hole 22A in outer ring, elongated axial hole 29 and the elongated axial hole 29A sprays of minor diameter be kerosene or with hydrogen peroxide spontaneous combustion
NHMF fuel or liquid hydrogen.The head body that head body connection attachment strap 14 is changed to circumferentially uniformly be provided with cooling agent delivery outlet 40 is connected with hole
Attachment strap 14A simultaneously adds cooling agent output set device 41 and cooling agent efferent duct 42 on it.Body portion 2 is to use technical grade 70%- instead
84.9% hydrogen peroxide is for re-generatively cooled agent and the third tradition body portion 3C without cooling ring band and from cooling agent efferent duct 42
Most of re-generatively cooled agent and sub-fraction are exported from 26 spray of annulus.The oxygen rich air of the entrance of pipe 8 is introduced from turbine exhaust
It is changed to the oxygen rich air that complete or incomplete decomposing technical grade 70%-84.9% hydrogen peroxide produces temperature 600-800K.Cancel point
The center that fiery fuel collector 15 and igniter fuel enter pipe 16 and change into force-bearing base 4 and ejector filler disk 11 sets electric igniter to use
Pipeline 36.Thus large-scale hydrogen peroxide thrust chamber i.e. the 4th kind derivative type thrust chamber with discharge re-generatively cooled partition plate is formed.
As shown in Fig. 2, Fig. 3, Fig. 6 and Fig. 7, major diameter basic model thrust chamber, adds liquid on the outside of the gas axial hole 20B of outer ring
Small axial hole 22A is enclosed in vitro.Use articulation set ring A 10A instead and increase liquid collector 38 and liquid on the outside of it into pipe
39.Enter pipe 39 from liquid to hit to 21, small axial hole 22, liquid outer ring inclined hole 23, the small axis in liquid outer ring certainly into and from liquid
It is kerosene to hole 22A, elongated axial hole 29 and the elongated axial hole 29A sprays of minor diameter or is fired with the NHMF of hydrogen peroxide spontaneous combustion
Material or liquid hydrogen.A body is used instead to be connected with hole attachment strap 14A and add cooling agent output set device 41 and cooling agent efferent duct on it
42.Use the third tradition body portion 2C instead and the most of from cooling agent of 70% one 84.9% hydrogen peroxide of technical grade in body portion 2
Efferent duct 42 exports and sub-fraction is from 26 spray of annulus.The oxygen rich air that the entrance of pipe 8 is introduced from turbine exhaust is changed to completely
Or incomplete decomposing technical grade 70%-84.9% hydrogen peroxide produces the oxygen rich air of temperature 600-800K.Cancel igniter fuel collection
The center that clutch 15 and igniter fuel enter pipe 16 and change into force-bearing base 4 and ejector filler disk 11 sets electric igniter pipeline 36,
Thus ultra-large type hydrogen peroxide thrust chamber i.e. the 5th kind derivative type thrust chamber with discharge re-generatively cooled partition plate is formed.
As shown in Figure 6 and Figure 7, the 4th kind of derivative type thrust chamber, body portion 2 uses second of tradition body portion 2B instead and liquid hydrogen exists
It is heated to be changed into after gas hydrogen largely from the output of cooling agent efferent duct 42 and sub-fraction from 26 spray of annulus.From liquid into
Enter pipe 39 to enter and from liquid from hitting to 21, small axial hole 22, the small axial hole 22A in liquid outer ring, liquid outer ring inclined hole 23, elongated
Axial hole 29 and the elongated axial hole 29A sprays of minor diameter are most of liquid oxygen.Pipe 8 is introduced from turbine exhaust to enter and from gas axis
To hole 20, partition plate both sides gas axial hole 20A and outer ring gas axial hole 20B sprays be gas hydrogen and fraction liquid oxygen burnt and
Mixing produces the hydrogen rich gas that temperature is no more than 800K.Thus a kind of discharge re-generatively cooled partition plate and the large-scale hydrogen of hydrogen rich gas are formed
Oxygen thrust chamber i.e. the 6th kind derivative type thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 6 and Fig. 7, the 5th kind of derivative type thrust chamber, body portion 2 uses second of traditional body portion 2B instead simultaneously
And liquid hydrogen is changed into after gas hydrogen largely from the output of cooling agent efferent duct 42 and sub-fraction from 26 spray of annulus heated.
Enter from liquid into pipe 39 and oblique to 21, small axial hole 22, the small axial hole 22A in liquid outer ring, liquid outer ring from liquid from hitting
Hole 23, elongated axial hole 29 and the elongated axial hole 29A sprays of minor diameter are most of liquid oxygen.From turbine exhaust introduce pipe 8 into
Enter and from gas axial hole 20, partition plate both sides gas axial hole 20A and outer ring gas axial hole 20B sprays be gas hydrogen and fraction liquid oxygen
Burnt and mixed and produce the hydrogen rich gas that temperature is no more than 800K.Thus a kind of discharge re-generatively cooled partition plate and hydrogen-rich are formed
Ultra-large type hydrogen-oxygen thrust chamber i.e. the 7th kind derivative type thrust chamber of gas.
As shown in Fig. 2, Fig. 3 and Fig. 8, major diameter basic model thrust chamber, head 1 is a 4th circle fan section of increase by 16 (12)
The enlarged head 1C that 19C and the 4th load connector 9C are formed.The outer ring gas axial hole 20B of a outer fan section 19B in 16 (12) and
Corresponding liquid outer ring inclined hole 23 changes the outer ring for being arranged on a 4th circle fan section 19C in 16 (12).Partition plate 3 is that increase the 3rd is circumferential
45th area or 34th area discharge re-generatively cooled partition plate 3C that partition plate 27B and 16 (12) blocks the 4th circle radial direction partition plate 28C are formed.16 (12) are a
The elongated axial hole 29A of minor diameter that outer radial partition plate 28B ragged edges are opened, which changes, is arranged on 16 (12) blocks the 4th circle radial direction partition plate 28C
Ragged edge.11 thickness of ejector filler disk preferably takes 140-170mm and thrust chamber diameter D=1.4-1.7m.Thus form with discharge again
Huge oxygen kerosene thrust chamber i.e. the 8th kind derivative type thrust chamber of raw cooled partition.
As shown in Fig. 2, Fig. 3, Fig. 6, Fig. 7 and Fig. 8, the 5th kind of derivative type thrust chamber, head 1 is increase by 16 (12) a 4th
The outer ring gas of the enlarged head 1C that circle fan section 19C and the 4th load connector 9C is formed, a outer fan section 19B in 16 (12) are axial
Hole 20B and corresponding liquid outer ring inclined hole 23 change the outer ring for being arranged on a 4th circle fan section 19C in 16 (12).Partition plate 3 is increase
45th area or 34th area discharge re-generatively cooled partition plate 3C that 3rd circumferential direction partition plate 27B and 16 (12) blocks the 4th circle radial direction partition plate 28C are formed.
The elongated axial hole 29A of minor diameter that a outer radial partition plate 28B ragged edges in 16 (12) are opened, which changes, is arranged on 16 (12) blocks the 4th circle footpath
To the ragged edge of partition plate 28C.11 thickness of ejector filler disk preferably takes 140-170mm and thrust chamber diameter D=1.4-1.7m.Thus form
With huge hydrogen peroxide thrust chamber i.e. the 9th kind derivative type thrust chamber of discharge re-generatively cooled partition plate.
As shown in Fig. 2, Fig. 3, Fig. 4, Fig. 8 and Fig. 9, re-generatively cooled is discharged in major diameter basic model thrust chamber, 29th area or 22nd area
The corresponding circumferential clapboard end 43 of each part welding of partition plate 3A, outer circumferential clapboard end 43A, a radially inside partition plate in 4 (3)
Termination 44A, 8 (6) a outer radial clapboard end 44B of a radial direction clapboard end 44 and 16 (12).By porous transpiration material or height
It is little to be uniformly covered with spray aperture 45 of the aperture less than 0.5mm such as double perforate and pitch-row on each termination that warm heat proof material makes
0-20 degree, partition plate cooling agent and the gas axial hole 20A sprays of partition plate both sides of 45 spray of spray aperture are tilted in 4mm and to both sides
Oxygen rich air is sufficiently mixed burning, and 45 layout density of spray aperture of 16 (12) block outer radial clapboard end 44B ragged edges is small such as
Axially open single hole.
Claims (13)
1. a kind of major diameter basic model thrust chamber, 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), spray segmental arc plate group (12), spray radial plate (13), head body connection attachment strap (14), igniter fuel collection
Clutch (15) and igniter fuel enter pipe (16), it is characterised in that：The head (1) is the 3rd load connector (9B) of increase
The ejector filler disk (11) of spray and stress and more firm reinforced pair to be connected of the porous interior conical shell (6) of gas rectification and power transmission
Conical shell enlarged head (1A), body portion (2) are by the use of kerosene as re-generatively cooled agent and interior cooling agent and only use second cooling ring band
The first of (17A) and the 3rd cooling ring band (17B) tradition body portion (2A), partition plate (3) are that 29th area or the discharge of 22nd area are raw and cold again
But partition plate (3A), from turbine exhaust introduce that pipe (8) enters to be whole liquid oxygen carry out burning generation temperature with a small amount of kerosene does not surpass
The oxygen rich air of 800K is crossed, thickness preferably takes the ejector filler disk (11) of 90-140mm to be divided into central circular area (18), a interior sector in 4 (3)
Concentric two row or single close is pressed in area (19A), a fan section in 8 (6) (19) and 16 (12) in a outer fan section (19B) Bing Ge areas
Collection is provided with the gas axial hole (20), partition plate both sides gas axial hole (20A) and outer ring gas axial hole (20B) of spray oxygen rich air, spray
Segmental arc plate group (12) and spray radial plate (13) is double or the single liquid that is provided with is from hitting outside to (21), small axial hole (22) and liquid
The kerosene that inclined hole (23) is used for after spray body portion (2) re-generatively cooled is enclosed, a liquid is hit to (21) and a gas axial hole certainly
(20) composition liquid gas is hit certainly mutually hits spray unit and one or two liquid outer ring inclined hole (23) and an outer ring gas axial hole
The liquid gas that (20B) composition mutually hits angle 0-30 degree mutually hits spray unit, and articulation set ring (10) is circumferentially uniformly provided with igniter fuel
Inclined hole (24), cooling agent sprocket hole (25) and annulus (26), thrust chamber diameter D=0.9-1.4m, thus composition discharge
The ultra-large type oxygen kerosene thrust chamber of re-generatively cooled partition plate.
2. major diameter basic model thrust chamber as claimed in claim 1, it is characterised in that：29th area or the discharge regeneration of 22nd area
Cooled partition (3A) is by circumferential partition plate (27), outer circumferential partition plate (27A), 4 (3) blocks radially inside partition plate (28A), 8 (6) block footpaths
Formed to partition plate (28) and 16 (12) block outer radial partition plates (28B) and welded, each part of partition plate is uniformly provided with carefully
Long axial hole (29) be used for the kerosene as partition plate cooling agent is discharged into thrust chamber and with partition plate both sides gas axial hole (20A)
The oxygen rich air of spray carries out mixed combustion, and what a outer radial partition plate (28B) ragged edge in 16 (12) was opened is the elongated axial direction of minor diameter
Hole (29A), divider height preferably take 80-100mm, the radial slot group (30) and ring that each part of partition plate is opened with ejector filler disk (11)
Two corresponding annular groove matching merging in shape groove group (31) are welded and fixed.
3. major diameter basic model thrust chamber as claimed in claim 1, it is characterised in that：Described annulus (26) company of being opened in
Connect between the gap inner wall (32) of ring assembly (10) and gap outer wall (33), gap outer wall (33) is circumferentially uniformly provided with small radial direction
Hole (34), a small amount of re-generatively cooled agent introduced from small radial hole (34) enters annulus (26), and 90 degree of sprays of corner form afterwards
For in thrust chamber
The improved procedure of cooling.
4. major diameter basic model thrust chamber as claimed in claim 1, it is characterised in that：The head (1) is cancellation 16
(12) the diminution head (1B) that a outer fan section (19B) and the 3rd load connector (9B) form, a fan section in 8 (6) (19)
Outer ring uses outer ring gas axial hole (20B) and corresponding liquid outer ring inclined hole (23) instead, and partition plate (3) is to cancel outer circumferential partition plate
13rd area or 10th area discharge re-generatively cooled partition plate (3B) that (27A) and 16 (12) block outer radial partition plates (28B) form, radial direction partition plate
(28) what ragged edge was opened is the elongated axial hole of minor diameter (29A), and the thickness of ejector filler disk (11) is preferably changed to 60-90mm and thrust chamber
Diameter D=0.6-0.9m, thus forms large-scale oxygen kerosene thrust chamber i.e. the first derivative type with discharge re-generatively cooled partition plate
Thrust chamber.
5. the first derivative type thrust chamber as claimed in claim 4, it is characterised in that：The spray segmental arc plate group (12) takes
The liquid to disappear out hits the gas hydrogen axial hole (35) and outer ring gas hydrogen that (21) and liquid outer ring inclined hole (23) are changed out with dense arrangement certainly
Axial hole (35A), body portion (2) are to use second traditional body portion (2B) of the liquid hydrogen as re-generatively cooled agent and without cooling ring band instead simultaneously
And liquid hydrogen is changed into after gas hydrogen from annulus (26), small axial hole (22), gas hydrogen axial hole (35), outer ring gas hydrogen axis heated
To hole (35A), elongated axial hole (29) and the elongated axial hole of minor diameter (29A) spray, introduce what pipe (8) entered from turbine exhaust
Oxygen rich air is changed to whole liquid oxygen and carries out oxygen rich air of the burning generation temperature no more than 800K with a small amount of gas hydrogen or liquid hydrogen, cancels igniting
Fuel collector (15), igniter fuel enter pipe (16) and igniter fuel inclined hole (24) and change into force-bearing base (4) and ejector filler disk
(11) center sets electric igniter preferably to use 60-80mm with the corresponding divider height of gas hydrogen burning with pipeline (36), oxygen rich air, by
This forms a kind of large-scale hydrogen-oxygen thrust chamber i.e. second of derivative type thrust chamber with discharge re-generatively cooled partition plate.
6. major diameter basic model thrust chamber as claimed in claim 1, it is characterised in that：The spray segmental arc plate group (12) changes
The gas hydrogen axial hole (35) and outer ring gas hydrogen axial hole (35A) of dense arrangement are opened, body portion (2) are to use second of traditional body portion instead
(2B) and liquid hydrogen are changed into after gas hydrogen from annulus (26), small axial hole (22), gas hydrogen axial hole (35), outer ring heated
Gas hydrogen axial hole (35A), elongated axial hole (29) and the elongated axial hole of minor diameter (29A) spray, pipe (8) is introduced from turbine exhaust
What is entered is that liquid oxygen gas hydrogen or liquid hydrogen burn and produce the oxygen rich air that temperature is no more than 800K, cancellation igniter fuel collector (15),
The center that igniter fuel enters pipe (16) and igniter fuel inclined hole (24) and changes into force-bearing base (4) and ejector filler disk (11) sets electricity
Igniter preferably uses 60-80mm with pipeline (36), oxygen rich air with the corresponding divider height of gas hydrogen burning, thus forms one kind discharge
The ultra-large type hydrogen-oxygen thrust chamber of re-generatively cooled partition plate i.e. the third derivative type thrust chamber.
7. the first derivative type thrust chamber as claimed in claim 4, it is characterised in that：The outer ring gas axial hole (20B)
Outside add the small axial hole in liquid outer ring (22A), articulation set ring (10) cancels igniter fuel inclined hole (24) and cooling agent is defeated
The articulation set ring A (10A) for sending hole (25) to be uniformly distributed along the circumference liquid radial hole (37) as increase, articulation set ring A's (10A)
Outside increase liquid collector (38) and liquid enter pipe (39), and entering pipe (39) from liquid enters and hit pair certainly from liquid
(21), small axial hole (22), liquid outer ring inclined hole (23), the small axial hole in liquid outer ring (22A), elongated axial hole (29) and small straight
Footpath elongated axial hole (29A) spray is kerosene or NHMF fuel or liquid hydrogen with hydrogen peroxide spontaneous combustion, and head body connects attachment strap
(14) the head body for being changed to circumferentially uniformly be provided with cooling agent delivery outlet (40) is connected with hole attachment strap (14A) and adds cooling on it
Agent output set device (41) and cooling agent efferent duct (42), body portion (2) are to use technical grade 70%-84.9% hydrogen peroxide instead as again
Raw cooling agent and the third traditional body portion (3C) without cooling ring band and export most of regeneration from cooling agent efferent duct (42)
Cooling agent and sub-fraction from annulus (26) spray, from turbine exhaust introduce the oxygen rich air that pipe (8) enters be changed to completely or
Incomplete decomposing technical grade 70%-84.9% hydrogen peroxide produces the oxygen rich air of temperature 600-800K, cancels igniter fuel set
The center that device (15) and igniter fuel enter pipe (16) and change into force-bearing base (4) and ejector filler disk (11) sets electric igniter to manage
Road (36), thus forms large-scale hydrogen peroxide thrust chamber i.e. the 4th kind derivative type thrust chamber with discharge re-generatively cooled partition plate.
8. major diameter basic model thrust chamber as claimed in claim 1, it is characterised in that：The outer ring gas axial hole (20B)
Outside add the small axial hole in liquid outer ring (22A), use instead articulation set ring A (10A) and on the outside of it increase liquid collector
(38) and liquid is into pipe (39), enters pipe (39) from liquid and is hit certainly to (21), small axial hole (22), liquid into and from liquid
Outer ring inclined hole (23), the small axial hole in liquid outer ring (22A), elongated axial hole (29) and the elongated axial hole of minor diameter (29A) spray
Be kerosene or NHMF fuel or liquid hydrogen with hydrogen peroxide spontaneous combustion, use a body instead and be connected with hole attachment strap (14A) and increase on it
If cooling agent output set device (41) and cooling agent efferent duct (42), body portion (2) use the third traditional body portion (2C) and handle instead
Technical grade 70%-84.9% hydrogen peroxide it is most of from cooling agent efferent duct (42) output and sub-fraction from annulus
(26) spray, the oxygen rich air that pipe (8) entrance is introduced from turbine exhaust are changed to complete or incomplete decomposing technical grade 70%-84.9%
Hydrogen peroxide produces the oxygen rich air of temperature 600-800K, cancel igniter fuel collector (15) and igniter fuel enter manage (16) and
The center for changing into force-bearing base (4) and ejector filler disk (11) sets electric igniter pipeline (36), thus forms raw and cold again with discharge
But ultra-large type hydrogen peroxide thrust chamber i.e. the 5th kind derivative type thrust chamber of partition plate.
9. the 4th kind of derivative type thrust chamber as claimed in claim 7, it is characterised in that：The body portion (2) uses instead second
Traditional body portion (2B) and liquid hydrogen are changed into after gas hydrogen largely from cooling agent efferent duct (42) output and sub-fraction heated
From annulus (26) spray, enter pipe (39) from liquid and hit certainly outside to (21), small axial hole (22), liquid into and from liquid
Enclose small axial hole (22A), liquid outer ring inclined hole (23), elongated axial hole (29) and the elongated axial hole of minor diameter (29A) spray
Most of liquid oxygen, from turbine exhaust introduce pipe (8) enter and from gas axial hole (20), partition plate both sides gas axial hole (20A) and
Outer ring gas axial hole (20B) spray be gas hydrogen burnt with fraction liquid oxygen and mix produce temperature be no more than 800K richness
Hydrogen, thus forms a kind of large-scale hydrogen-oxygen thrust chamber i.e. the 6th kind derivative type with discharge re-generatively cooled partition plate and hydrogen rich gas and pushes away
Power room.
10. the 5th kind of derivative type thrust chamber as claimed in claim 8, it is characterised in that：The body portion (2) uses instead second
Traditional body portion (2B) and liquid hydrogen are changed into after gas hydrogen largely from cooling agent efferent duct (42) output and sub-fraction heated
From annulus (26) spray, enter pipe (39) from liquid and hit certainly outside to (21), small axial hole (22), liquid into and from liquid
Enclose small axial hole (22A), liquid outer ring inclined hole (23), elongated axial hole (29) and the elongated axial hole of minor diameter (29A) spray
Most of liquid oxygen, from turbine exhaust introduce pipe (8) enter and from gas axial hole (20), partition plate both sides gas axial hole (20A) and
Outer ring gas axial hole (20B) spray be gas hydrogen burnt with fraction liquid oxygen and mix produce temperature be no more than 800K richness
Hydrogen, thus forms a kind of discharge re-generatively cooled partition plate and ultra-large type hydrogen-oxygen thrust chamber i.e. the 7th kind derivative type of hydrogen rich gas
Thrust chamber.
11. major diameter basic model thrust chamber as claimed in claim 1, it is characterised in that：The head (1) is increase by 16
(12) enlarged head (1C) that a 4th circle fan section (19C) and the 4th load connector (9C) form, a outer sector in 16 (12)
The outer ring gas axial hole (20B) in area (19B) and corresponding liquid outer ring inclined hole (23), which change, is arranged on a 4th circle sector in 16 (12)
The outer ring in area (19C), partition plate (3) are that the circumferential partition plate (27B) of increase the 3rd and 16 (12) blocks the 4th circle radial direction partition plate (28C) form
45th area or 34th area discharge re-generatively cooled partition plate (3C), the minor diameter that a outer radial partition plate (28B) ragged edge in 16 (12) is opened is thin
Long axial hole (29A) changes the ragged edge for being arranged on 16 (12) blocks the 4th circle radial direction partition plate (28C), and ejector filler disk (11) thickness preferably takes
140-170mm and thrust chamber diameter D=1.4-1.7m, thus forms the huge oxygen kerosene thrust with discharge re-generatively cooled partition plate
Room i.e. the 8th kind derivative type thrust chamber.
12. the 5th kind of derivative type thrust chamber as claimed in claim 8, it is characterised in that：The head (1) is increase by 16
(12) enlarged head (1C) that a 4th circle fan section (19C) and the 4th load connector (9C) form, a outer sector in 16 (12)
The outer ring gas axial hole (20B) in area (19B) and corresponding liquid outer ring inclined hole (23), which change, is arranged on a 4th circle sector in 16 (12)
The outer ring in area (19C), partition plate (3) are that the circumferential partition plate (27B) of increase the 3rd and 16 (12) blocks the 4th circle radial direction partition plate (28C) form
45th area or 34th area discharge re-generatively cooled partition plate (3C), the minor diameter that a outer radial partition plate (28B) ragged edge in 16 (12) is opened is thin
Long axial hole (29A) changes the ragged edge for being arranged on 16 (12) blocks the 4th circle radial direction partition plate (28C), and ejector filler disk (11) thickness preferably takes
140-170mm and thrust chamber diameter D=1.4-1.7m, thus forms the huge hydrogen peroxide thrust with discharge re-generatively cooled partition plate
Room i.e. the 9th kind derivative type thrust chamber.
13. major diameter basic model thrust chamber as claimed in claim 2, it is characterised in that：29th area or the discharge of 22nd area are again
Circumferential clapboard end (43), outer circumferential clapboard end (43A), 4 (3) are a accordingly for raw each part welding of cooled partition (3A)
Radially inside clapboard end (44A), a outer radial clapboard end (44B) of a radial direction clapboard end (44) in 8 (6) and 16 (12),
Uniformly it is covered with the spray aperture (45) that aperture is less than 0.5mm on each termination made by porous transpiration material or high-temperature heat-resistance material
Tilt 0-20 degree such as double perforate and pitch-row no more than 4mm and to both sides, the partition plate cooling agent of spray aperture (45) spray with every
The oxygen rich air of plate both sides gas axial hole (20A) spray is sufficiently mixed burning, 16 (12) block outer radial clapboard end (44B) outermosts
Spray aperture (45) layout density on side is small to open single hole as axial.
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| 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 |
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| 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 |
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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 |
| CN111963339A (en) * | 2020-08-19 | 2020-11-20 | 西安航天动力研究所 | Liquid film cooling rail attitude control engine thrust chamber |
| 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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| 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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| CN114658565B (en) * | 2022-03-02 | 2024-02-09 | 北京星际荣耀科技有限责任公司 | Propelling device, engine and aircraft |
| CN114876671A (en) * | 2022-03-21 | 2022-08-09 | 西安航天动力研究所 | Hydrogen peroxide thrust chamber and engine |
| 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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| 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 |
| CN111963339A (en) * | 2020-08-19 | 2020-11-20 | 西安航天动力研究所 | Liquid film cooling rail attitude control engine thrust chamber |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108087154A (en) | 2018-05-29 |
| CN107956601B (en) | 2021-12-28 |
| CN107084073A (en) | 2017-08-22 |
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