CN108953002A - With the rocket series thrust chamber on single flow head and cooling discharge partition - Google Patents
With the rocket series thrust chamber on single flow head and cooling discharge partition Download PDFInfo
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- CN108953002A CN108953002A CN201810597642.2A CN201810597642A CN108953002A CN 108953002 A CN108953002 A CN 108953002A CN 201810597642 A CN201810597642 A CN 201810597642A CN 108953002 A CN108953002 A CN 108953002A
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- partition
- head
- thrust chamber
- axial hole
- spray
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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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
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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
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The present invention relates to the rocket series thrust chambers with single flow head and cooling discharge partition.There are oxygen kerosene or methane, liquid oxygen liquid hydrogen, intermediate concentration hydrogen peroxide kerosene or the Non-toxics bipropellant rocket thrust chamber such as liquid hydrogen or NHMF fuel.Thrust range: it is 30-150 tons medium-sized, it is 150-400 tons large-scale, 400-800 tons of ultra-large type.Thrust cell structure versatility is good and relatively simple.Single flow head strength is high and rigidity is big, and number of components greatly reduces, and has the turbine exhaust input unit of bipyramid shell.Cooling discharge partition structure is simpler, and reliable operation can effectively inhibit somatic sypermutation.Technology inheritance with traditional body portion is good.The interior cooling improved procedure of annular gap is provided, cooling effect is more preferable.Basic model of the invention and eight kinds of derivative type rocket thrust chambers are suitable for single machine unfailing performance and are increased to 0.9999 and reuse number up to 10-200 rocket engine.
Description
Technical field
The present invention relates to the rocket series thrust chambers with single flow head and cooling discharge partition, belong to oxygen kerosene, liquid
The rocket engines technical fields such as oxygen methane, liquid oxygen liquid hydrogen, hydrogen peroxide.
Background technique
The developing direction of rocket engine is to improve reliability by a relatively large margin by simplifying the technical measures such as structure, according to fire
Arrow launch mission needs constantly to increase thrust, needs to be changed into repeatedly from disposable according to rocket launching cost is substantially reduced
It reuses.For this purpose, proposing " one group of major diameter rocket thrust chamber with discharge re-generatively cooled partition " (patent of invention Shen in person
It please 201711201099.1).This group of rocket thrust chamber has structure compared with simple, versatility is good, number of components is few, head strength is high
With rigidity it is big, can effectively inhibit the advantages that somatic sypermutation.But there is also thrust chamber diameters to get 1.7 meters of excessive, propulsions
Agent not methane containing liquid oxygen, partition Division area not etc., partition have that end part, hydrogen-oxygen thrust chamber oxygen rich air is not practical, has
The disadvantages of collector is extra.Thrust chamber diameter is now scheduled on 0.3-1.5 meters, increases liquid oxygen methane propellant, with homalographic subregion
Partition, cancels clapboard end part, and hydrogen-oxygen thrust chamber only uses hydrogen rich gas, has and do not set outer collector at interior collector.Again with this
Apply for patent of invention.
Summary of the invention
For the above-mentioned patent applied before me, there are six disadvantages, in order to overcome these disadvantages to provide more preferably more
Medium-sized, the large-scale and ultra-large type rocket thrust chamber of practical more propellants, the present invention are provided with single flow head and cooling discharge
The rocket series thrust chamber of partition.
A kind of basic model rocket thrust chamber is made of and welded head, body portion and partition.Head and this three parts
Connector includes force-bearing base, ring flange, porous interior conical shell, outer conical shell, turbine exhaust introducing pipe, the first load connector, second
Load connector, third load connector, articulation set ring, ejector filler disk, spray segmental arc board group, spray radial plate, head body connect
It connects attachment strap, igniter fuel collector and igniter fuel and enters pipe.Head be thick each load connector of ejector filler disk with it is more
The high-intensitive head that conical shell is integrally connected in hole.Introduce pipe entrance from turbine exhaust is whole liquid oxygen and a small amount of kerosene or methane
It carries out burning and generates the oxygen rich air that temperature is no more than 800K.Porous interior conical shell, outer conical shell and turbine exhaust introduce pipe and form turbine
It is vented input unit.Body portion is that cylindrical section internal diameter is 1.05-1.5m and with kerosene or methane re-generatively cooled and has coolant entrance
Traditional body portion of pipe.Partition is to flow through the cooling discharge partition put side by side from inside with kerosene or methane.Thickness preferably takes 10% straight
The ejector filler disk of diameter is center circle, 6 first lap fan sections, 12 second circle fan sections and 18 the by equal area partition
Three circle fan sections.By concentric two row and single intensively gas axial hole, partition both sides gas axial hole and outer ring gas are provided in each area
Axial hole is used to spray turbine exhaust.Spray segmental arc board group and the double and single fluid that is provided with of spray radial plate are from hitting to, fluid
Small axial hole and outer ring fluid inclined hole are used to spray kerosene or methane.One from hit the fluid of angle 0-30 degree from hit to one
Gas axial hole composition hits certainly and mutually hits spray unit, and an outer ring fluid inclined hole and an outer ring gas axial hole composition mutually hit angle 0-30
Degree mutually hits spray unit.Articulation set ring is circumferentially uniformly provided with igniter fuel inclined hole, coolant sprocket hole and annular gap.
Thus the ultra-large type oxygen kerosene or methane thrust chamber with single flow head and cooling discharge partition are constituted.
For basic model rocket thrust chamber, cooling discharge partition is circumferential by the first circumferential partition, the second circumferential partition, third
Partition, 6 pieces of first lap radial direction partitions, the radial partition of 12 piece of second circle and 18 pieces of third circle radial direction partition compositions are simultaneously welded.
The numerical relation of the inside radius R of first circumferential partition and each radial septum plate length H are R=0.61H, with this separator lined at etc.
37th area of area.Each partition it is single or it is double uniformly be provided with elongated delivery blind hole and it is double be provided with end spray inclined hole, be used to handle
It flows through in the kerosene or methane spray to thrust chamber of partition and carries out mixing combustion with the oxygen rich air of partition both sides gas axial hole spray
It burns.What third circle radial direction partition ragged edge was opened is two minor diameter end spray inclined holes.End spray inclined hole and minor diameter end
The inclination angle of spray inclined hole is all 5-20 degree.The height of each partition is equal and preferably takes 80-100mm.Each partition is together with spray segmental arc
Board group and spray radial plate and the corresponding slot matching merging fillet welding in the radial slot group and annular groove group that ejector filler disk is opened enter
Groove angle weldering or flange soldering connection are fixed.
For basic model rocket thrust chamber, annular gap is opened between the gap inner wall of articulation set ring and gap outer wall.
Gap outer wall is circumferentially uniformly provided with small radial hole.The kerosene or methane flowed into from small radial hole enters corner nine behind annular gap
Ten degree of sprays and become improved procedure cooling in thrust chamber.
For basic model rocket thrust chamber, head is made of cancelling 18 third circle fan sections and third load connector
Reduce head.The partition both sides gas axial hole of 12 second circle fan section outer rings is changed to outer ring gas axial hole and increase accordingly outer ring
Fluid inclined hole.Body portion is that cylindrical section internal diameter is contracted to 0.65-1.05m and traditional body portion with kerosene or methane re-generatively cooled.Every
Plate is the cooling discharge partition of 19 area's fuel of homalographic made of cancelling third circumferential direction partition and 18 pieces of third circle radial direction partitions.Second
What the radial partition ragged edge of circle was opened is two minor diameter end spray inclined holes.Thus composition single flow head and cooling discharge every
The large-scale oxygen kerosene or methane thrust chamber of plate i.e. the first derivative type thrust chamber.
For basic model rocket thrust chamber, head is to cancel 18 third circle fan sections, 12 the second circle fan sections, third
Head is reduced again made of load connector and the second load connector.The partition both sides gas axis of 6 first lap fan sections outer ring
Outer ring gas axial hole is changed to hole and increase accordingly outer ring fluid inclined hole.Body portion be cylindrical section internal diameter be contracted to 0.3-0.65m and
With traditional body portion of kerosene or methane re-generatively cooled.Partition is to cancel third circumferential direction partition, the second circumferential partition, 18 pieces of third circles
The cooling discharge partition of 7 area's fuel of homalographic made of radial partition and the radial partition of 12 piece of second circle.First lap radial direction partition is most
What outside was opened is two minor diameter end spray inclined holes.Thus the medium-sized liquid oxygen with single flow head and cooling discharge partition is constituted
Kerosene or methane thrust chamber i.e. second of derivative type thrust chamber.
For basic model rocket thrust chamber, the turbine exhaust on head introduces the oxygen rich air that pipe enters and is changed to a small amount of liquid oxygen and gas
Hydrogen or liquid hydrogen burning generate the hydrogen rich gas that temperature is no more than 800K.The outer ring gas axial hole of ejector filler disk is cancelled and corresponding
Outer ring fluid inclined hole is changed to the small axial hole of outer ring fluid.Articulation set ring is changed to cancel the articulation set ring A of coolant sprocket hole
And increase a liquid oxygen on the outside and enter pipe, so that fluid is from hitting to, the small axial hole of fluid and the small axial hole spray of outer ring fluid
Note is liquid oxygen.Head body connection attachment strap is changed to porose head body connection attachment strap and adds coolant efferent duct on it.Body portion is
Cylindrical section internal diameter is 1.05-1.5m and with traditional body portion of liquid hydrogen re-generatively cooled and makes endothermic transition at the major part of low temperature gas hydrogen
It is sprayed from the output of coolant efferent duct and sub-fraction from annular gap.Partition is cold with 37th area of homalographic of the cooling spray of liquid oxygen
But discharge partition, and two minor diameter end spray inclined holes that third circle radial direction partition ragged edge is opened are changed to an outer ring fluid
Small axial hole.It is electric to cancel the center setting that igniter fuel collector and igniter fuel enter pipe and change into force-bearing base and ejector filler disk
Igniter pipeline.Thus the ultra-large type liquid oxygen liquid hydrogen thrust chamber of composition single flow head and cooling discharge partition i.e. the third spread out
Raw type thrust chamber.
For basic model rocket thrust chamber, head is made of cancelling 18 third circle fan sections and third load connector
Reduce head.The partition both sides gas axial hole of 12 second circle fan section outer rings is cancelled and the outmost turns of spray segmental arc board group
It increase accordingly the small axial hole of outer ring fluid.Body portion is that cylindrical section internal diameter is contracted to 0.65-1.05m and the biography with liquid hydrogen re-generatively cooled
Unite body portion.Partition is the cooling discharge of 19 area's liquid oxygen of homalographic made of cancelling third circumferential direction partition and 18 pieces of third circle radial direction partitions
Partition.What the radial partition ragged edge of the second circle was opened is the small axial hole of outer ring fluid.Thus it constitutes with single flow head and cold
But the large-scale liquid oxygen liquid hydrogen thrust chamber of discharge partition i.e. the 4th kind of derivative type thrust chamber.
For basic model rocket thrust chamber, head is to cancel 18 third circle fan sections, 12 the second circle fan sections, third
Head is reduced again made of load connector and the second load connector.The partition both sides gas axis of 6 first lap fan sections outer ring
Cancelled to hole and the outmost turns of spray segmental arc board group increase accordingly the small axial hole of outer ring fluid.Body portion is the contracting of cylindrical section internal diameter
As low as 0.3-0.65m and traditional body portion with liquid hydrogen re-generatively cooled.Partition be cancel third circumferential direction partition, the second circumferential partition,
The cooling discharge partition of 7 area's liquid oxygen of homalographic made of 18 pieces of third circle radial direction partitions and the radial partition of 12 piece of second circle.First lap
What radial partition ragged edge was opened is the small axial hole of outer ring fluid.Thus it constitutes with single flow head and cooling discharge partition
Medium-sized liquid oxygen liquid hydrogen thrust chamber i.e. the 5th kind of derivative type thrust chamber.
For basic model rocket thrust chamber, the turbine exhaust on head introduces the oxygen rich air that pipe enters and is changed to decompose intermediate concentration
70%-79% hydrogen peroxide generates 322-485 degrees Celsius of temperature of oxygen rich air.The outer ring gas axial hole of ejector filler disk is cancelled
And corresponding outer ring fluid inclined hole is changed to the small axial hole of outer ring fluid.Fluid increases to 0-60 degree from the angular region of hitting certainly hit pair.
Articulation set ring is changed to cancel the articulation set ring A of coolant sprocket hole and increase a fuel on the outside to enter pipe, so that
Fluid from hit to, the small axial hole of fluid and the small axial hole spray of outer ring fluid be kerosene or liquid hydrogen or with hydrogen peroxide spontaneous combustion
NHMF fuel.It uses porose head body connection attachment strap instead and adds coolant efferent duct on it.Body portion is that cylindrical section internal diameter is
1.05-1.5m and traditional body portion with intermediate concentration 70%-79% hydrogen peroxide re-generatively cooled, and make the big portion of the hydrogen peroxide
Divide and is sprayed from the output of coolant efferent duct and sub-fraction from annular gap.Partition is cooling with fuel such as kerosene, liquid hydrogen, NHMF
The cooling discharge partition in 37th area of homalographic of spray, and two minor diameter end sprays that third circle radial direction partition ragged edge is opened are oblique
Hole is changed to the small axial hole of outer ring fluid.Cancel igniter fuel collector and igniter fuel enters pipe and changes into force-bearing base and spray
Infuse the center setting electric igniter pipeline of device disk.Thus the ultra-large type peroxidating with single flow head and cooling discharge partition is constituted
Hydrogen thrust chamber i.e. the 6th kind derivative type thrust chamber.
For basic model rocket thrust chamber, head is made of cancelling 18 third circle fan sections and third load connector
Reduce head.The partition both sides gas axial hole of 12 second circle fan section outer rings is cancelled and the outmost turns of spray segmental arc board group
It increase accordingly the small axial hole of outer ring fluid.Body portion is that cylindrical section internal diameter is contracted to 0.65-1.05m and with intermediate concentration 70%-
Traditional body portion of 79% hydrogen peroxide re-generatively cooled.Partition is that cancellation third circumferential direction partition and 18 pieces of third circle radial direction partitions form
The cooling discharge partition of 19 area's fuel of homalographic.What the radial partition ragged edge of the second circle was opened is the small axial hole of outer ring fluid.
Thus large-scale hydrogen peroxide thrust chamber i.e. the 7th kind derivative type thrust chamber with single flow head and cooling discharge partition is constituted.
For basic model rocket thrust chamber, head is to cancel 18 third circle fan sections, 12 the second circle fan sections, third
Head is reduced again made of load connector and the second load connector.The partition both sides gas axis of 6 first lap fan sections outer ring
Cancelled to hole and the outmost turns of spray segmental arc board group increase accordingly the small axial hole of outer ring fluid.Body portion is the contracting of cylindrical section internal diameter
As low as 0.3-0.65m and traditional body portion with intermediate concentration 70%-79% hydrogen peroxide re-generatively cooled.Partition is to cancel third week
To 7 area's fuel of homalographic made of partition, the second circumferential partition, 18 pieces of third circle radial direction partitions and the radial partition of 12 piece of second circle
Cooling discharge partition.What first lap radial direction partition ragged edge was opened is the small axial hole of outer ring fluid.Thus it constitutes and uses single flow
Medium-sized hydrogen peroxide thrust chamber i.e. the 8th kind derivative type thrust chamber on head and cooling discharge partition.
The beneficial effect and advantage of the rocket series thrust chamber of present invention single flow head and cooling discharge partition are:
1. thrust cell structure is simpler.Single flow head strength is high and rigidity is big.It is used coaxial with direct current spray orifice substitution
Formula nozzle greatly reduces thrust chamber number of components.Liquid oxygen thrust chamber hits angle using the spray of 0-30 degree certainly and mutually hits angle, Ji Nengbao
It is not ablated to protect ejector filler face, and can guarantee that propellant constituent element is atomized mixing quality.There was only 5- in the inclination angle of end spray inclined hole
20 degree are also as a same reason.There is the turbine exhaust input unit of bipyramid shell to rectify.The structure of cooling discharge partition is simple, cooling
Reliably, homalographic subregion is reasonable, and end spray inclined hole and partition both sides gas axial hole form another spray unit, can effectively press down
Somatic sypermutation processed.Technology inheritance with traditional body portion is good.
2. thrust cell structure versatility is good.Suitable for oxygen kerosene or methane, liquid oxygen liquid hydrogen, intermediate concentration 70-79% mistake
The three types such as hydrogen oxide kerosene or liquid hydrogen or NHMF fuel totally six kinds of Non-toxic bipropellants.Each type propellant
Three kinds of medium-sized (30-150 tons of thrust), large-scale (150-400 tons of thrust), ultra-large type (400-800 tons of thrust) etc. is separately included again
Thrust chamber.A kind of basic structure adds two liquid in-out pressure inlets again, suitable for what is be made of basic model and eight kinds of derivative types
Rocket series thrust chamber.Almost cover all common Non-toxic bipropellant rocket thrust chambers.
3. the interior cooling improved procedure of annular gap is provided, to adapt to increase interior cooling flow and single engine reliable
Property is increased to 0.9999.This interior cooling structure make interior cooling liquid film or air film more evenly with adherent, interior good cooling results.It can
So that oxygen kerosene thrust chamber is cancelled its three traditional cooling ring band, simplifies structure.
4. providing two kinds of sparking mode.One is from igniter fuel inclined hole spray special ignition fuel, for oxygen kerosene,
The igniting of the thrust chambers such as liquid oxygen methane.Another kind is that electric igniter pipeline is arranged in thrust chamber center, and power supply igniter sprays
Square of getting angry is used, for the igniting of the thrust chambers such as liquid oxygen liquid hydrogen, hydrogen peroxide.
5. rocket series thrust chamber can meet the requirement that rocket engine repeatedly uses.The burning of liquid oxygen thrust chamber
Temperature is up to 3200-3500 degrees Celsius, and reusing number will be less: oxygen kerosene 10 times, liquid oxygen methane 25 times, and liquid oxygen liquid
Hydrogen 50 times.The ignition temperature of intermediate concentration hydrogen peroxide thrust chamber only has 1958-2228 degrees Celsius, the cooling of this hydrogen peroxide
Performance is good and flow is big, and reusing number can up to 200 times.
The rocket series thrust chamber of present invention single flow head and cooling discharge partition is suitable for improving by a relatively large margin
Reliability and the oxygen kerosene repeatedly used or methane, liquid oxygen liquid hydrogen, intermediate concentration hydrogen peroxide kerosene or liquid hydrogen or
The bipropellant thrusters such as NHMF fuel.Thrust range: 30-150 tons medium-sized, 150-400 tons large-scale, ultra-large type
400-800 tons.
Detailed description of the invention
Fig. 1 basic model rocket thrust chamber schematic diagram
The a quarter on Fig. 2 basic model rocket thrust chamber head and partition side elevational cross-section
/ 6th of the basic model rocket thrust chamber head Fig. 3 and partition spray face
The connection figure with ejector filler disk such as Fig. 4 basic model rocket thrust chamber partition
The fillet welding connection figure of Fig. 4-1 circumferential direction partition and ejector filler disk
The groove angle that enters of Fig. 4-2 radial direction partition and ejector filler disk welds connection figure
The fillet welding connection figure of Fig. 4-3 spray radial plate and ejector filler disk
The flange soldering connection figure of Fig. 4-4 spray arc panel and ejector filler disk
Fig. 5 the 4th, seven kind of derivative type thrust chamber head and partition side elevational cross-section a quarter
Fig. 6 the 4th, seven kind of derivative type thrust chamber head and partition spray face 1/6th
The a quarter of the porous interior conical shell front view of Fig. 7 first, fourth, seven kind of derivative type thrust chamber
Fig. 8 the 5th, eight kind of derivative type thrust chamber head and partition side elevational cross-section a quarter
Fig. 9 the 5th, eight kind of derivative type thrust chamber head and partition spray face 1/6th
Specific embodiment
Fig. 1 to Fig. 9 is the preferred implementation of the rocket series thrust chamber of present invention single flow head and cooling discharge partition
Example.
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, a kind of basic model rocket thrust chamber is made of head 1, body portion 2 and partition 3
And it is welded.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, whirlpool
Wheel exhaust introduce pipe 8, the first load connector 9, the second load connector 9A, third load connector 9B, articulation set ring 10,
Ejector filler disk 11, spray segmental arc board group 12, spray radial plate 13, head body connection attachment strap 14, igniter fuel collector 15 and igniting
Fuel enters pipe 16.Head 1 be thick ejector filler disk 11 is integrally connected with each load connector with porous interior conical shell 6 it is high-strength
Spend head 1A1.Introduce the entrance of pipe 8 from turbine exhaust is that whole liquid oxygen and a small amount of kerosene or methane carry out burning and generates temperature not
Oxygen rich air more than 800K.Porous interior conical shell 6, outer conical shell 7 and turbine exhaust introduce pipe 8 and form turbine exhaust input unit.Body
Portion 2 is that cylindrical section internal diameter is 1.05--1.5m and with kerosene or methane re-generatively cooled and traditional body portion for having coolant to enter pipe 17
2A1.Partition 3 is to flow through the cooling discharge partition 3A1 put side by side from inside with kerosene or methane.Thickness preferably takes the spray of 10% diameter
It is 19,12 second, the first lap fan section in center circle 18,6 circle fan section 19A and 18 that device disk 11, which is infused, by equal area partition
A third circle fan section 19B.In each area by concentric two row and it is single intensively be provided with aperture be preferably less than 10mm gas axial hole 20,
Partition both sides gas axial hole 20A and outer ring gas axial hole 20B is used to spray turbine exhaust.Segmental arc board group 12 and spray radial plate 13
The double and single liquid aperture that is provided with is preferably less than the fluid of 2mm from hitting to the small axial hole of 21, fluid 22 and outer ring fluid inclined hole 23
For spray kerosene or methane.One fluid for hitting angle 0-30 degree certainly hits to hit certainly to 21 with a composition of gas axial hole 20 certainly and mutually hit
Spray unit and an outer ring fluid inclined hole 23 and an outer ring gas axial hole 20B composition mutually hit the mutual of angle 0-30 degree and hit spray list
Member.Articulation set ring 10 is circumferentially uniformly provided with igniter fuel inclined hole 24, coolant sprocket hole 25 and annular gap 26.Thus structure
At the ultra-large type oxygen kerosene or methane thrust chamber with single flow head and cooling discharge partition.
As shown in Figure 2, Figure 3 and Figure 4, for basic model rocket thrust chamber, cooling discharge partition 3A1 is by the first circumferential partition
27, the second circumferential partition 27A, third circumferential direction partition 27B, the radial partition 28A of 6 pieces of first lap radial direction partitions, 28,12 piece of second circle
It is formed with 18 pieces of third circle radial direction partition 28B and welded.The inside radius R of first circumferential partition 27 and each radial septum plate length
The numerical relation of H is for R=0.61H separator lined at 37th area of homalographic.Each partition it is single or it is double be uniformly provided with it is elongated defeated
Send blind hole 29 and it is double be provided with end spray inclined hole 30 be used in the kerosene or methane spray to thrust chamber for flowing through partition and with
The oxygen rich air of partition both sides gas axial hole 20A spray is mixed and burned.What third circle radial direction partition 28B ragged edge was opened is two
The inclination angle of minor diameter end spray inclined hole 30A, end spray inclined hole 30 and minor diameter end spray inclined hole 30A are all 5-20
Degree.The height of each partition is equal and preferably takes 80-100mm.Each partition is together with spray segmental arc board group 12 and spray radial plate 13 and spray
It infuses the corresponding slot matching merging fillet welding in the radial slot group 31 and annular groove group 32 that device disk 11 is opened or enters groove angle weldering or flange pricker
Weldering is connected and fixed.
As shown in Figures 2 and 3, for basic model rocket thrust chamber, annular gap 26 is opened in the gap of articulation set ring 10
Between inner wall 33 and gap outer wall 34.Gap outer wall 34 is circumferentially uniformly provided with small radial hole 35.It is flowed into from small radial hole 35
Kerosene or methane enter 90 degree of sprays of corner behind annular gap 26 and become improved procedure cooling in thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 5, Fig. 6 and Fig. 7, for basic model rocket thrust chamber, head 1 is to cancel 18 third circles
Head 1A2 is reduced made of fan section 19B and third load connector 9B.The partition two of the 12 second circle outer rings fan section 19A
Side gas axial hole 20A is changed to outer ring gas axial hole 20B and increase accordingly outer ring fluid inclined hole 23.Body portion 2 is the contracting of cylindrical section internal diameter
As low as 0.65-1.05m and with kerosene or traditional body portion 2A2 of methane re-generatively cooled.Partition 3 is to cancel third circumferential direction partition 27B
With the cooling discharge partition 3A2 of 19 area's fuel of homalographic made of 18 pieces of third circle radial direction partition 28B.Second encloses radial partition 28A
That ragged edge is opened is two minor diameter end spray inclined hole 30A.Thus it constitutes with single flow head and cools down the big of discharge partition
Type oxygen kerosene or methane thrust chamber i.e. the first derivative type thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 8 and Fig. 9, for basic model rocket thrust chamber, head 1 is to cancel 18 third circles sectors
Head is reduced again made of area 19B, 12 the second circle fan section 19A, third load connector 9B and the second load connector 9A
1A3.The partition both sides gas axial hole 20A of 6 first lap fan sections, 19 outer ring is changed to outer ring gas axial hole 20B and increase accordingly outer
Enclose fluid inclined hole 23.Body portion 2 is that cylindrical section internal diameter is contracted to 0.3-0.65m and traditional body portion with kerosene or methane re-generatively cooled
2A3.Partition 3 is to cancel third circumferential direction partition 27B, the second circumferential partition 27A, 18 pieces third circle radial direction partition 28B and 12 piece the
Two enclose the cooling discharge partition 3A3 of 7 area's fuel of homalographic made of radial partition 28A.28 ragged edge of first lap radial direction partition is opened
It is two minor diameter end spray inclined hole 30A.Thus the medium-sized oxygen kerosene with single flow head and cooling discharge partition is constituted
Or methane thrust chamber i.e. second of derivative type thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 5 and Fig. 6, for basic model rocket thrust chamber, the turbine exhaust on head 1 introduce pipe 8 into
The oxygen rich air entered is changed to a small amount of liquid oxygen and gas hydrogen or liquid hydrogen burning generates hydrogen rich gas of the temperature no more than 800K and becomes head
1B1.The outer ring gas axial hole 20B of ejector filler disk 11 is cancelled and corresponding outer ring fluid inclined hole 23 is changed to the small axis of outer ring fluid
To hole 22A.Articulation set ring 10 is changed to cancel the articulation set ring A10A of coolant sprocket hole 25 and increases by one on the outside
Liquid oxygen enters pipe 36 and fluid is made from hitting to the small axial hole of 21, fluid 22 and the small axial hole 22A spray of outer ring fluid to be liquid oxygen.
Head body connection attachment strap 14 is changed to porose head body connection attachment strap 14A and adds coolant efferent duct 37 on it.Body portion 2 is cylinder
Section internal diameter is 1.05-1.5m and with traditional body portion 2C1 of liquid hydrogen re-generatively cooled and makes endothermic transition at the major part of low temperature gas hydrogen
It is sprayed from the output of coolant efferent duct 37 and sub-fraction from annular gap 26.Partition 3 is the homalographic with the cooling spray of liquid oxygen
The cooling discharge partition 3C1 in 37th area simultaneously changes two minor diameter end spray inclined hole 30A that third circle radial direction partition 28B ragged edge is opened
For the small axial hole 22A of an outer ring fluid.Cancel igniter fuel collector 15 and igniter fuel enters pipe 16 and changes into force-bearing base 4
With the center setting electric igniter pipeline 38 of ejector filler disk 11.Thus the super large with single flow head and cooling discharge partition is constituted
Type liquid oxygen liquid hydrogen thrust chamber i.e. the third derivative type thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 5 to Fig. 7, for basic model rocket thrust chamber, head 1 is to cancel 18 third circles sectors
Head 1B2 is reduced made of area 19B and third load connector 9B.The partition both sides gas of the 12 second circle outer rings fan section 19A
Axial hole 20A is cancelled and the outmost turns of spray segmental arc board group 12 increase accordingly the small axial hole 22A of outer ring fluid.Body portion 2 is
Cylindrical section internal diameter is contracted to 0.65-1.05m and traditional body portion 2B2 with liquid hydrogen re-generatively cooled.Partition 3 be cancel third it is circumferential every
19 area's liquid oxygen of homalographic made of plate 27B and 18 pieces of third circle radial direction partition 28B cools down discharge partition 3B3.Second circle it is radial every
That plate 28A ragged edge is opened is the small axial hole 22A of an outer ring fluid.Thus it constitutes with single flow head and cooling discharge partition
Large-scale liquid oxygen liquid hydrogen thrust chamber i.e. the 4th kind of derivative type thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 8 and Fig. 9, for basic model rocket thrust chamber, head 1 is to cancel 18 third circles sectors
Head is reduced again made of area 19B, 12 the second circle fan section 19A, third load connector 9B and the second load connector 9A
1B3.The partition both sides gas axial hole 20A of 6 first lap fan sections, 19 outer ring cancelled and spray segmental arc board group 12 it is outermost
Circle increase accordingly the small axial hole 22A of outer ring fluid.Body portion 2 is that cylindrical section internal diameter is contracted to 0.3-0.65m and raw and cold again with liquid hydrogen
But traditional body portion 2B3.Partition 3 is to cancel third circumferential direction partition 27B, the second circumferential partition 27A, 18 pieces of third circle radial direction partitions
The cooling discharge partition 3B3 of 7 area's liquid oxygen of homalographic made of the radial partition 28A of 28B and 12 piece of second circle.First lap radial direction partition 28
That ragged edge is opened is the small axial hole 22A of an outer ring fluid.Thus it constitutes with single flow head and cools down the medium-sized of discharge partition
Liquid oxygen liquid hydrogen thrust chamber i.e. the 5th kind derivative type thrust chamber.
As shown in Fig. 2, Fig. 3, Fig. 5 and Fig. 6, for basic model rocket thrust chamber, the turbine exhaust on head 1 introduce pipe 8 into
The oxygen rich air that the oxygen rich air entered is changed to decompose 322-485 degrees Celsius of temperature of intermediate concentration 70%-79% hydrogen peroxide generation forms
For head 1C1.The outer ring gas axial hole 20B of ejector filler disk 11 is cancelled and corresponding outer ring fluid inclined hole 23 is changed to outer ring stream
The small axial hole 22A of body.Fluid hits certainly and increases to 0-60 degree to 21 angular region of hitting certainly.Articulation set ring 10 is changed to cancel coolant
The articulation set ring A10A of sprocket hole 25 and on the outside one fuel of increase enter pipe 36A and fluid are hit to 21, fluid certainly
Small axial hole 22 and the small axial hole 22A spray of outer ring fluid are kerosene or liquid hydrogen or the NHMF fuel with hydrogen peroxide spontaneous combustion.
It uses porose head body connection attachment strap 14A instead and adds coolant efferent duct 37 on it.Body portion 2 is that cylindrical section internal diameter is 1.05-
1.5m and with traditional body portion 2C1 of intermediate concentration 70%-79% hydrogen peroxide re-generatively cooled and make the major part of the hydrogen peroxide
It is sprayed from the output of coolant efferent duct 37 and sub-fraction from annular gap 26.Partition 3 is with fuel such as kerosene, liquid hydrogen, NHMF
Two minor diameters 37th area of homalographic of cooling spray cooling discharge partition 3C1 and third circle radial direction partition 28B ragged edge is opened
End spray inclined hole 30A is changed to the small axial hole 22A of an outer ring fluid.Cancel igniter fuel collector 15 and igniter fuel enters
Pipe 16 and the center setting electric igniter pipeline 38 for changing into force-bearing base 4 and ejector filler disk 11.Thus constitute with single flow head and
Ultra-large type hydrogen peroxide thrust chamber i.e. the 6th kind derivative type thrust chamber of cooling discharge partition.
As shown in Fig. 2, Fig. 3, Fig. 5 to Fig. 7, for basic model rocket thrust chamber, head 1 is to cancel 18 third circles sectors
Head 1C2 is reduced made of area 19B and third load connector 9B.The partition both sides gas of the 12 second circle outer rings fan section 19A
Axial hole 20A is cancelled and the outmost turns of spray segmental arc board group 12 increase accordingly the small axial hole 22A of outer ring fluid.Body portion 2 is
Cylindrical section internal diameter is contracted to 0.65-1.05m and traditional body portion 2C2 with intermediate concentration 70%-79% hydrogen peroxide re-generatively cooled.
Partition 3 is the cooling discharge of 19 area's fuel of homalographic made of cancelling third circumferential direction partition 27B and 18 pieces of third circle radial direction partition 28B
Partition 3C2.That the radial partition 28A ragged edge of the second circle is opened is the small axial hole 22A of an outer ring fluid.Thus it constitutes and uses single flow
Large-scale hydrogen peroxide thrust chamber i.e. the 7th kind derivative type thrust chamber on head and cooling discharge partition.
As shown in Fig. 2, Fig. 3, Fig. 8 and Fig. 9, for basic model rocket thrust chamber, head 1 is to cancel 18 third circles sectors
Head is reduced again made of area 19B, 12 the second circle fan section 19A, third load connector 9B and the second load connector 9A
1C3.The partition both sides gas axial hole 20A of 6 first lap fan sections, 19 outer ring cancelled and spray segmental arc board group 12 it is outermost
Circle increase accordingly the small axial hole 22A of outer ring fluid.Body portion 2 is that cylindrical section internal diameter is contracted to 0.3-0.65m and uses intermediate concentration
Traditional body portion 2C3 of 70%-79% hydrogen peroxide re-generatively cooled.Partition 3 be cancel third circumferential direction partition 27B, second it is circumferential every
The cooling discharge of 7 area's fuel of homalographic made of plate 27A, 18 pieces of third circle radial direction partition 28B and the radial partition 28A of 12 piece of second circle
Partition 3C3.That 28 ragged edge of first lap radial direction partition is opened is the small axial hole 22A of an outer ring fluid.Thus it constitutes and uses single flow
Medium-sized hydrogen peroxide thrust chamber i.e. the 8th kind derivative type thrust chamber on head and cooling discharge partition.
Claims (11)
1. a kind of basic model rocket thrust chamber is made of and welded head (1), body portion (2) and partition (3), head (1) and
The connector of this three parts includes force-bearing base (4), ring flange (5), porous interior conical shell (6), outer conical shell (7), turbine exhaust introducing
Manage (8), the first load connector (9), the second load connector (9A), third load connector (9B), articulation set ring (10),
Ejector filler disk (11), spray segmental arc board group (12), spray radial plate (13), head body connect attachment strap (14), igniter fuel collector
(15) and igniter fuel enters pipe (16), it is characterised in that: head (1) is thick each load connector of ejector filler disk (11)
The high-intensitive head (1A1) being integrally connected with porous interior conical shell (6), introduce pipe (8) entrance from turbine exhaust is whole liquid oxygen
With a small amount of kerosene or methane carry out burning generate temperature be no more than 800K oxygen rich air, porous interior conical shell (6), outer conical shell (7) and
Turbine exhaust introduces pipe (8) and forms turbine exhaust input unit, and body portion (2) are that cylindrical section internal diameter is 1.05-1.5m and uses kerosene
Or methane re-generatively cooled and the traditional body portion (2A1) for having coolant to enter pipe (17), partition (3) are with kerosene or methane from inside
The cooling discharge partition (3A1) for flowing through and discharging, thickness preferably take during the ejector filler disk (11) of 10% diameter by equal area partition is
Heart circle (18), 6 first lap fan sections (19), 12 second circle fan sections (19A) and 18 third circle fan sections
(19B), by concentric two row and single intensively being provided with aperture is preferably less than the gas axial hole (20) of 10mm, partition both sides gas in each area
Axial hole (20A) and outer ring gas axial hole (20B) are used to spray turbine exhaust, spray segmental arc board group (12) and spray radial plate
(13) the double and single liquid aperture that is provided with is preferably less than the fluid of 2mm from hitting to (21), the small axial hole of fluid (22) and outer ring stream
Body inclined hole (23) is used to spray kerosene or methane, and one is hit to (21) and a gas axial hole certainly from the fluid for hitting angle 0-30 degree
(20) composition is mutually hit from hitting mutually to hit spray unit and an outer ring fluid inclined hole (23) and form with outer ring gas axial hole (20B)
Angle 0-30 degree mutually hits spray unit, and it is defeated that articulation set ring (10) is circumferentially uniformly provided with igniter fuel inclined hole (24), coolant
Hole (25) and annular gap (26) are sent, ultra-large type oxygen kerosene or first with single flow head and cooling discharge partition are thus constituted
Alkane thrust chamber.
2. basic model rocket thrust chamber as described in claim 1, it is characterised in that: the cooling discharge partition (3A1) by
First circumferential partition (27), the second circumferential partition (27A), third circumferential direction partition (27B), 6 pieces of first lap radial direction partitions (28), 12
Block second encloses radial partition (28A) and 18 pieces of third circle radial direction partition (28B) compositions and welded, the first circumferential partition (27)
Inside radius R and each radial septum plate length H numerical relation be R=0.61H separator lined at 37th area of homalographic, each partition
The single or double elongated delivery blind hole (29) and the double end spray inclined hole (30) that is provided with of being uniformly provided with is for flowing through partition
It is mixed and burned in kerosene or methane spray to thrust chamber and with the oxygen rich air of partition both sides gas axial hole (20A) spray, the
Three enclose that radial partition (28B) ragged edges open is two minor diameter end spray inclined holes (30A), end spray inclined hole (30) and small
The inclination angle of diameter end spray inclined hole (30A) is 5-20 degree, and the height of each partition is equal and preferably takes 80-100mm, and each partition connects
The radial slot group (31) and annular groove group opened with spray segmental arc board group (12) and spray radial plate (13) and ejector filler disk (11)
(32) corresponding slot matching merging fillet welding in enters groove angle weldering or flange soldering connection is fixed.
3. basic model rocket thrust chamber as described in claim 1, it is characterised in that: the annular gap (26) is opened in connection
Between the gap inner wall (33) and gap outer wall (34) of ring assembly (10), gap outer wall (34) is circumferentially uniformly provided with small radial hole
(35), the kerosene or methane flowed into from small radial hole (35) enter annular gap (26) afterwards 90 degree sprays of corner and as thrust
The cooling improved procedure in interior.
4. basic model rocket thrust chamber as described in claim 1, it is characterised in that: the head (1) is to cancel 18 the
Diminution head (1A2) made of three circles fan section (19B) and third load connector (9B), 12 second circle fan sections (19A)
Partition both sides gas axial hole (20A) of outer ring are changed to outer ring gas axial hole (20B) and increase accordingly outer ring fluid inclined hole (23), body
Portion (2) is that cylindrical section internal diameter is contracted to 0.65-1.05m and traditional body portion (2A2) with kerosene or methane re-generatively cooled, partition
It (3) is the cooling row of 19 area's fuel of homalographic made of cancelling third circumferential direction partition (27B) and 18 pieces of third circle radial direction partitions (28B)
It puts partition (3A2), what radial partition (28A) ragged edge of the second circle was opened is two minor diameter end spray inclined holes (30A), thus structure
At the large-scale oxygen kerosene or methane thrust chamber i.e. the first derivative type thrust chamber with single flow head and cooling discharge partition.
5. basic model rocket thrust chamber as described in claim 1, it is characterised in that: the head (1) is to cancel 18 the
Three circles fan section (19B), 12 the second circles fan section (19A), third load connector (9B) and the second load connectors (9A)
Made of reduce again head (1A3), partition both sides gas axial hole (20A) of 6 first lap fan section (19) outer rings are changed to outer ring
Gas axial hole (20B) and increase accordingly outer ring fluid inclined hole (23), body portion (2) be cylindrical section internal diameter be contracted to 0.3-0.65m and
With traditional body portion (2A3) of kerosene or methane re-generatively cooled, partition (3) be cancel third circumferential direction partition (27B), second it is circumferential every
7 area's fuel of homalographic made of plate (27A), 18 pieces of third circle radial direction partitions (28B) and the radial partition (28A) of 12 piece of second circle is cold
But discharge partition (3A3), what first lap radial direction partition (28) ragged edge was opened is two minor diameter end spray inclined holes (30A), by
This constitutes the medium-sized oxygen kerosene or methane thrust chamber i.e. second of derivative type thrust with single flow head and cooling discharge partition
Room.
6. basic model rocket thrust chamber as described in claim 1, it is characterised in that: the turbine exhaust on the head (1) draws
The oxygen rich air for entering pipe (8) entrance is changed to the hydrogen rich gas that a small amount of liquid oxygen is no more than 800K with gas hydrogen or liquid hydrogen burning generation temperature and forms
Outer ring gas axial hole (20B) for head (1B1), ejector filler disk (11) is cancelled and corresponding outer ring fluid inclined hole (23) changes
For the small axial hole of outer ring fluid (22A), articulation set ring (10) is changed to cancel the articulation set ring A of coolant sprocket hole (25)
(10A) and on the outside increase a liquid oxygen enter pipe (36) make fluid from hit to (21), the small axial hole of fluid (22) and outside
The circle small axial hole of fluid (22A) spray is liquid oxygen, and head body connection attachment strap (14) is changed to porose head body connection attachment strap (14A) simultaneously
It adds on it coolant efferent duct (37), body portion (2) are that cylindrical section internal diameter is 1.05-1.5m and the biography with liquid hydrogen re-generatively cooled
System body portion (2B1) simultaneously makes endothermic transition at the most of from coolant efferent duct (37) output and sub-fraction from ring of low temperature gas hydrogen
Shape gap (26) sprays, and partition (3) is with 37th area of homalographic cooling discharge partition (3B1) of the cooling spray of liquid oxygen and third circle
Two minor diameter end spray inclined holes (30A) that radial partition (28B) ragged edge is opened are changed to the small axial hole of outer ring fluid
(22A), cancels igniter fuel collector (15) and igniter fuel enters pipe (16) and changes into force-bearing base (4) and ejector filler disk (11)
Center setting electric igniter pipeline (38), thus constitute the ultra-large type liquid oxygen liquid hydrogen with single flow head and cooling discharge partition
Thrust chamber i.e. the third derivative type thrust chamber.
7. basic model rocket thrust chamber as described in claim 1 or 6, it is characterised in that: the head (1) is to cancel 18
Head (1B2) is reduced made of third circle fan section (19B) and third load connector (9B), 12 second circle fan sections
Partition both sides gas axial hole (20A) of the outer ring (19A) are cancelled and the outmost turns of spray segmental arc board group (12) are increase accordingly outside
It encloses the small axial hole of fluid (22A), body portion (2) are that cylindrical section internal diameter is contracted to 0.65-1.05m and the tradition with liquid hydrogen re-generatively cooled
Body portion (2B2), partition (3) are homalographics made of cancelling third circumferential direction partition (27B) and 18 pieces of third circle radial direction partitions (28B)
19 area's liquid oxygen are cooling discharge partition (3B2), and what radial partition (28A) ragged edge of the second circle was opened is the small axial hole of outer ring fluid
(22A), thus large-scale liquid oxygen liquid hydrogen thrust chamber i.e. the 4th kind of derivative type of composition single flow head and cooling discharge partition pushes away
Power room.
8. basic model rocket thrust chamber as described in claim 1 or 6, it is characterised in that: the head (1) is to cancel 18
Third circle fan section (19B), 12 the second circles fan section (19A), third load connector (9B) and the second load connectors
It is reduced again made of (9A) head (1B3), partition both sides gas axial hole (20A) of 6 first lap fan section (19) outer rings give
Cancel and the outmost turns of spray segmental arc board group (12) increase accordingly the small axial hole of outer ring fluid (22A), body portion (2) are in cylindrical section
Diameter is contracted to 0.3-0.65m and traditional body portion (2B3) with liquid hydrogen re-generatively cooled, and partition (3) is to cancel third circumferential direction partition
(27B), the second circumferential partition (27A), 18 pieces of third circle radial direction partitions (28B) and the radial partition (28A) of 12 piece of second circle form
7 area's liquid oxygen of homalographic it is cooling discharge partition (3B3), what first lap radial direction partition (28) ragged edge was opened is that an outer ring fluid is small
Axial hole (22A), thus medium-sized liquid oxygen liquid hydrogen thrust chamber i.e. the 5th kind of composition single flow head and cooling discharge partition spreads out
Raw type thrust chamber.
9. basic model rocket thrust chamber as described in claim 1, it is characterised in that: the turbine exhaust on the head (1) draws
The oxygen rich air for entering pipe (8) entrance is changed to decompose the richness that intermediate concentration 70%-79% hydrogen peroxide generates 322-485 degrees Celsius of temperature
Oxygen and become head (1C1), outer ring gas axial hole (20B) of ejector filler disk (11) is cancelled and outer ring fluid is oblique accordingly
Hole (23) is changed to the small axial hole of outer ring fluid (22A), and fluid increases to 0-60 degree, connection collection from the angular region of hitting certainly hit to (21)
Cyclization (10) is changed to cancel the articulation set ring A (10A) of coolant sprocket hole (25) and increase a fuel on the outside to enter
It is kerosene that pipe (36A), which hits fluid to (21), the small axial hole of fluid (22) and the small axial hole of outer ring fluid (22A) spray certainly,
Or liquid hydrogen or the NHMF fuel with hydrogen peroxide spontaneous combustion, head body connection attachment strap (14) are changed to porose head body connection attachment strap (14A)
And coolant efferent duct (37) are added on it, body portion (2) are that cylindrical section internal diameter is 1.05-1.5m and with intermediate concentration 70%-
Traditional body portion (2C1) of 79% hydrogen peroxide re-generatively cooled simultaneously makes the most of defeated from coolant efferent duct (37) of the hydrogen peroxide
It is sprayed out with sub-fraction from annular gap (26), partition (3) the cooling spray of the fuel such as kerosene, liquid hydrogen, NHMF
The two minor diameter end sprays 37th area of area cooling discharge partition (3C1) and third circle radial direction partition (28B) ragged edge is opened
Inclined hole (30A) is changed to the small axial hole of outer ring fluid (22A), cancels igniter fuel collector (15) and igniter fuel enters pipe
(16) center setting electric igniter pipeline (38) of force-bearing base (4) and ejector filler disk (11) is changed into), it thus constitutes and uses single flow
Ultra-large type hydrogen peroxide thrust chamber i.e. the 6th kind derivative type thrust chamber on head and cooling discharge partition.
10. the basic model rocket thrust chamber as described in claim 1 or 9, it is characterised in that: the head (1) is cancellation 18
Head (1C2) is reduced made of a third circle fan section (19B) and third load connector (9B), 12 second circle fan sections
Partition both sides gas axial hole (20A) of the outer ring (19A) are cancelled and the outmost turns of spray segmental arc board group (12) are increase accordingly outside
It encloses the small axial hole of fluid (22A), body portion (2) are that cylindrical section internal diameter is contracted to 0.65-1.05m and with intermediate concentration 70%-79%
Traditional body portion (2C2) of hydrogen peroxide re-generatively cooled, partition (3) are to cancel third circumferential direction partition (27B) and 18 pieces of third circle diameters
Cooling discharge partition (3C2) to 19 area's fuel of homalographic made of partition (28B), second, which encloses radial partition (28A) ragged edge, opens
The large-scale peroxidating for being the small axial hole of outer ring fluid (22A), thus constituting with single flow head and cooling discharge partition
Hydrogen thrust chamber i.e. the 7th kind derivative type thrust chamber.
11. the basic model rocket thrust chamber as described in claim 1 or 9, it is characterised in that: the head (1) is cancellation 18
A third circle fan section (19B), 12 the second circles fan section (19A), third load connector (9B) and the second load connectors
It is reduced again made of (9A) head (1C3), partition both sides gas axial hole (20A) of 6 first lap fan section (19) outer rings give
Cancel and the outmost turns of spray segmental arc board group (12) increase accordingly the small axial hole of outer ring fluid (22A), body portion (2) are in cylindrical section
Diameter is contracted to 0.3-0.65m and traditional body portion (2C3) with intermediate concentration 70%-79% hydrogen peroxide re-generatively cooled, partition (3)
It is to cancel third circumferential direction partition (27B), the second circumferential partition (27A), 18 pieces of third circle radial direction partitions (28B) and 12 piece of second circle
7 area's fuel of homalographic made of radial partition (28A) is cooling discharge partition (3C3), and first lap radial direction partition (28) ragged edge is opened
The medium-sized peroxidating for being the small axial hole of outer ring fluid (22A), thus constituting with single flow head and cooling discharge partition
Hydrogen thrust chamber i.e. the 8th kind derivative type thrust chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810597642.2A CN108953002A (en) | 2018-06-12 | 2018-06-12 | With the rocket series thrust chamber on single flow head and cooling discharge partition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810597642.2A CN108953002A (en) | 2018-06-12 | 2018-06-12 | With the rocket series thrust chamber on single flow head and cooling discharge partition |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108953002A true CN108953002A (en) | 2018-12-07 |
Family
ID=64488220
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810597642.2A Withdrawn CN108953002A (en) | 2018-06-12 | 2018-06-12 | With the rocket series thrust chamber on single flow head and cooling discharge partition |
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| Country | Link |
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| CN (1) | CN108953002A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107152353A (en) * | 2017-06-15 | 2017-09-12 | 葛明龙 | New rocket and airship series hydrogen peroxide thrust chamber |
| CN110805506A (en) * | 2019-09-29 | 2020-02-18 | 北京航天动力研究所 | Combined combustion stabilizing device |
| 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 |
-
2018
- 2018-06-12 CN CN201810597642.2A patent/CN108953002A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107152353A (en) * | 2017-06-15 | 2017-09-12 | 葛明龙 | New rocket and airship series hydrogen peroxide thrust chamber |
| CN110805506A (en) * | 2019-09-29 | 2020-02-18 | 北京航天动力研究所 | Combined combustion stabilizing device |
| 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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Application publication date: 20181207 |