CN109519303A - Eccentric variable cross-section flow distribution baffle - Google Patents
Eccentric variable cross-section flow distribution baffle Download PDFInfo
- Publication number
- CN109519303A CN109519303A CN201811032749.9A CN201811032749A CN109519303A CN 109519303 A CN109519303 A CN 109519303A CN 201811032749 A CN201811032749 A CN 201811032749A CN 109519303 A CN109519303 A CN 109519303A
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- Prior art keywords
- runner
- propellant
- flow
- distribution
- fuel
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- 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
- F02K9/56—Control
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The present invention provides a kind of eccentric variable cross-section flow distribution baffles, specifically, for the high chamber pressure precise tracking ejector filler of big flow, including propellant distribution runner (21) and propellant runner hole (22): it is that off-centre operation combines cavity structure that propellant, which distributes runner (21), propellant runner hole (22) is with concentric circles, symmetrical, varied angle or is angularly distributed, propellant runner hole (22) size is calculated by formula, and propellant runner hole (22) position is iterated to calculate by numerical value emulation method to be optimized.The present invention realizes the low flow resistance assignment of traffic of the high uniformity of propellant by improving propellant distribution runner (21) and propellant runner hole (22) size design and position distribution.
Description
Technical field
The present invention relates to liquid-propellant rocket engine fields, and in particular, to for the high chamber pressure precise tracking spray of big flow
Infuse the eccentric variable cross-section flow distribution baffle of device.The assignment of traffic of the low flow resistance of high uniformity suitable for high-speed large-flow ejector filler
Plate significantly improves the uniformity of downstream flow distribution to adapt to the use environment of greater flow higher flow rate
Background technique
The high chamber pressure precise tracking of high specific impulse performance is harsher to size envelope and weight demands, mostly uses comprising stream
Measure " laminate-direct current " combined type ejector filler of distribution plate.The discharge characteristic of each nozzle directly affects the combustion of engine on ejector filler
The Warm status for burning efficiency, combustion chamber spray panel and locular wall finally will affect overall performance, therefore rationally design the stream of ejector filler
It is extremely important to measure distribution plate.
Currently, the ejector filler technology of high chamber pressure attitude control thrustor comparative maturity, established in engineering a set of
Perfect design criteria and test screen method.Flow distribution structure is simple, and it is small to be only applicable to propellant flow rate, nozzle ring number,
The few ejector filler of quantity, stream and flow resistance require easily to meet.
Due to the use environment of the high chamber pressure precise tracking ejector filler high-speed large-flow of high thrust, multiinjector circle number, number
The spray core of amount designs and the requirement of assignment of traffic high uniformity, low flow resistance, existing flow distribution baffle can not expire
Sufficient requirement, so overcoming the above deficiency is the key that the novel ejector filler flow distribution baffle of design.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of eccentric variable cross-section flow distribution baffles.
A kind of eccentric variable cross-section flow distribution baffle provided according to the present invention, comprising: propellant distributes runner 21 and promotes
Agent runner hole 22.
Preferably, it when the eccentric variable cross-section flow distribution baffle is placed between ejector filler shell 1 and spray core 3, promotes
Agent distributes runner 21 and propellant runner hole 22 and corresponding oxidant flow path import 11, fuel flow path import 12, conduit 31, directly
Flow nozzle 32 is connected to；
Wherein, ejector filler shell 1 includes oxidant flow path import 11, fuel flow path import 12, and spray core 3 includes conduit
31, smooth-bore tip 32；Oxidant flow path import 11, fuel flow path import 12 are symmetrical.
Preferably, using double layered discal plate structure, upper layer is that propellant distributes runner 21, and lower layer is that propellant distributes runner 21
Corresponding propellant runner hole 22.
Preferably, including fuel distributes runner 211 and fuel flow channel hole 221；
It is that off-centre operation combines cavity structure that fuel, which distributes runner 211, along the stream of fuel flowing direction fuel distribution runner 211
Road section gradually becomes smaller, and the runner corner of fuel distribution runner 211 passes through arc transition；It is above fuel distribution runner 211
Fuel flow path import 12, lower section are fuel flow channel hole 221；
The every collar aperture diameter in fuel flow channel hole 221 is identical, with concentric circles, symmetrical, varied angle or waits in fuel distribution runner 211
Angular distribution.
Preferably, including Oxidizer distribution runner 212 and oxidant flow channel hole 222.
Oxidizer distribution runner 212 is that off-centre operation combines cavity structure, along oxidant flow direction Oxidizer distribution runner
212 cross section of fluid channel gradually becomes smaller, and runner corner passes through arc transition；It is oxidant stream above Oxidizer distribution runner 212
Road import 11, lower section are oxidant flow channel hole 222；
The every collar aperture diameter in oxidant flow channel hole 222 is identical, with concentric circles, symmetrical, varied angle in Oxidizer distribution runner 212
Or it is angularly distributed.
Preferably, propellant distribution runner 21 includes a plurality of branch flow channel, and branch flow channel quantity and position are by downstream spray
The conduit 31 of core 3 determines that branch flow channel width is determined by the conduit 31 and 32 flow of smooth-bore tip of downstream spray core 3, leads to
Following formula is crossed to be calculated:
wiFor branch flow channel width, QiFor branch flow channel flow, ρ is propellant density, hdFor branch flow channel design height,
vdTo design peak flow rate (PFR), N in branch flow channelj、Nj+1Spray core slot is corresponded to for the branch flow channel end far from propellant import
Two circle nozzle quantity in road, N are total nozzle logarithm, QmFor mass-flow rate of propellant；
Branch flow channel eccentricity is determined by width of flow path and inside and outside radius of circle, is calculated by the following formula to obtain:
L is branch flow channel eccentricity, and R, r are respectively that branch flow channel is outer, inner circle radius, and θ, θ ' are respectively width of flow path wiPosition
Set corresponding outer, inner circle drift angle.
Preferably, the propellant runner hole 22 is distributed with concentric circles, symmetrical, varied angle or angularly, propellant stream
The flow passage aperture in road hole 22 is calculated by the following formula to obtain:
dlFor flow passage aperture, AlFor runner hole total sectional area, n is runner hole design quantity, vlTo design highest in runner hole
Flow velocity.
Compared with prior art, the present invention have it is following the utility model has the advantages that
The present invention distributes runner 21 and 22 size design of propellant runner hole and position distribution by improving propellant, realizes
The low flow resistance assignment of traffic of the high uniformity of propellant.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is a kind of eccentric variable cross-section flow distribution baffle cross-sectional view schematic diagram of the present invention；
Fig. 2 is flow distribution baffle in ejector filler mounted inside schematic diagram；
Fig. 3 is flow distribution baffle cross-sectional view；
Fig. 4 is that the fuel of flow distribution baffle distributes runner and runner hole schematic diagram；
Fig. 5 is the Oxidizer distribution runner and runner hole schematic diagram of flow distribution baffle；
Fig. 6 is that flow distribution baffle branch flow channel eccentricity calculates schematic diagram；
It is shown in figure:
1- ejector filler shell, 11- oxidant flow path import, 12- fuel flow path import；
2- flow distribution baffle, 21- propellant distribution runner, 211- fuel distribution runner, 212- Oxidizer distribution runner,
22- propellant runner hole, 221- fuel flow channel hole, 222- oxidant flow channel hole；
3- spray core, 31- spray core conduit, 32- smooth-bore tip.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
The present invention relates to a kind of flow distribution baffles of eccentric variable cross-section, specifically, for the high chamber pressure rail control hair of big flow
Motivation ejector filler realizes the low flow resistance assignment of traffic of the high uniformity of propellant.
As shown in Figure 1, the flow distribution baffle 2 of eccentric variable cross-section, including propellant distribution runner 21 and propellant runner hole
22。
As shown in Fig. 2, flow distribution baffle 2 is placed between ejector filler shell 1 and spray core 3, the oxidation of ejector filler shell 1
Agent flow path import 11 and fuel flow path import 12 are symmetrical；Spray core 3 has conduit 31, smooth-bore tip 32；Propellant point
It is sprayed with runner 21, propellant runner hole 22 with corresponding oxidant flow path import 11, fuel flow path import 12, conduit 31, direct current
Mouth 32 is connected to.
As shown in figure 3, flow distribution baffle 2 uses double layered discal plate structure, upper layer is that propellant distributes runner 21, and lower layer is to push away
The corresponding propellant runner hole 22 of runner 21 is distributed into agent.Provide 2 height H of flow distribution baffle2, propellant distribution runner 21 design
Height H21With 22 design height H of propellant runner hole22。
As shown in figure 4, the fuel road of flow distribution baffle 2 includes fuel distribution runner 211 and fuel flow channel hole 221.
It is that off-centre operation combines cavity structure that fuel, which distributes runner 211, along the stream of fuel flowing direction fuel distribution runner 211
Road section gradually becomes smaller, and fuel distributes the runner corner of runner 211 by arc transition, so that along the pressure point of runner circumferential direction
Cloth tends to uniformly substantially, while local flow resistance being controlled in reduced levels, avoids flow distortion.Fuel distributes runner 211 top
For fuel flow path import 12, lower section is fuel flow channel hole 221.
The every collar aperture diameter in fuel flow channel hole 221 is identical, with concentric circles, symmetrical, varied angle or waits in fuel distribution runner 211
Angular distribution guarantees that the pressure distribution of 31 circumferential direction of the traffic flows such as each fuel flow channel hole 221 and downstream spray core conduit is basic
Tend to be uniform.
As shown in figure 5, the oxidant road of flow distribution baffle 2 includes Oxidizer distribution runner 212 and oxidant flow channel hole
222。
Oxidizer distribution runner 212 is that off-centre operation combines cavity structure, along oxidant flow direction Oxidizer distribution runner
212 cross section of fluid channel gradually becomes smaller, and runner corner is by arc transition, so that the pressure distribution along runner circumferential direction tends to substantially
Uniformly, while local flow resistance can be controlled in reduced levels, avoids flow distortion.It is oxygen above Oxidizer distribution runner 212
Agent flow path import 11, lower section are oxidant flow channel hole 222.
The every collar aperture diameter in oxidant flow channel hole 222 is identical, with concentric circles, symmetrical, varied angle in Oxidizer distribution runner 212
Or be angularly distributed, guarantee that the pressure distribution of 31 circumferential direction of the traffic flows such as each runner hole 222 and downstream spray core conduit is basic
Tend to be uniform.
Branch flow channel flow QiIt can be according to two circle nozzle quantity N in the corresponding spray core conduit 31 in distal endj、Nj+1, total to spray
Mouth logarithm N and mass-flow rate of propellant QmIt is calculated.
Branch flow channel width wiIt can be according to design peak flow rate (PFR) v in runnerdWith runner design height hdIt is calculated.
In formula: ρ is propellant density.
As shown in fig. 6, branch flow channel eccentricity l can be according to branch flow channel inner circle radius r and width of flow path wiPosition pair
Outer, inner circle bias angle theta, θ ' is answered to be calculated.
Width of flow path wiPosition correspond to inner circle bias angle theta ' can according to outside branch flow channel, inner circle radius R, r, width of flow path wi
It is calculated with corresponding outer circle bias angle theta:
Runner hole total sectional area AlIt can be according to branch flow channel flow QiWith design peak flow rate (PFR) v in runner holelIt calculates
It arrives.
Flow passage aperture dlIt can be according to runner hole total sectional area AlIt is calculated with runner hole design quantity n.
Runner hole site is iterated to calculate by numerical value emulation method to be optimized.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (7)
1. a kind of bias variable cross-section flow distribution baffle characterized by comprising propellant distributes runner (21) and propellant runner
Hole (22).
2. bias variable cross-section flow distribution baffle according to claim 1, which is characterized in that the bias variable cross-section flow point
When matching board is placed between ejector filler shell (1) and spray core (3), propellant distributes runner (21) and propellant runner hole (22)
It is connected to corresponding oxidant flow path import (11), fuel flow path import (12), conduit (31), smooth-bore tip (32)；
Wherein, ejector filler shell (1) includes oxidant flow path import (11), fuel flow path import (12), and spray core (3) includes
Conduit (31), smooth-bore tip (32)；Oxidant flow path import (11), fuel flow path import (12) are symmetrical.
3. bias variable cross-section flow distribution baffle according to claim 1, which is characterized in that double layered discal plate structure is used, on
Layer is that propellant distributes runner (21), and lower layer is that propellant distributes runner (21) corresponding propellant runner hole (22).
4. bias variable cross-section flow distribution baffle according to claim 1, which is characterized in that distribute runner including fuel
(211) and fuel flow channel hole (221)；
It is that off-centre operation combines cavity structure that fuel, which distributes runner (211), along the stream of fuel flowing direction fuel distribution runner (211)
Road section gradually becomes smaller, and the runner corner of fuel distribution runner (211) passes through arc transition；Fuel distributes on runner (211)
Side is fuel flow path import (12), and lower section is fuel flow channel hole (221)；
The every collar aperture diameter in fuel flow channel hole (221) is identical, with concentric circles, symmetrical, varied angle or waits in fuel distribution runner (211)
Angular distribution.
5. bias variable cross-section flow distribution baffle according to claim 1, which is characterized in that including Oxidizer distribution runner
(212) and oxidant flow channel hole (222).
Oxidizer distribution runner (212) is that off-centre operation combines cavity structure, along oxidant flow direction Oxidizer distribution runner
(212) cross section of fluid channel gradually becomes smaller, and runner corner passes through arc transition；It is oxidation above Oxidizer distribution runner (212)
Agent flow path import (11), lower section are oxidant flow channel hole (222)；
The every collar aperture diameter in oxidant flow channel hole (222) is identical, with concentric circles, symmetrical, varied angle in Oxidizer distribution runner (212)
Or it is angularly distributed.
6. bias variable cross-section flow distribution baffle according to claim 1, which is characterized in that propellant distributes runner (21) packet
It includes a plurality of branch flow channel, branch flow channel quantity and position to be determined by the conduit (31) of downstream spray core (3), branch flow channel width
It is determined by the conduit (31) and smooth-bore tip (32) flow of downstream spray core (3), is calculated by the following formula to obtain:
wiFor branch flow channel width, QiFor branch flow channel flow, ρ is propellant density, hdFor branch flow channel design height, vdFor branch
Peak flow rate (PFR), N are designed in the runner of roadj、Nj+1It is corresponded to two in spray core conduit for the branch flow channel end far from propellant import
Nozzle quantity is enclosed, N is total nozzle logarithm, QmFor mass-flow rate of propellant；
Branch flow channel eccentricity is determined by width of flow path and inside and outside radius of circle, is calculated by the following formula to obtain:
L is branch flow channel eccentricity, and R, r are respectively that branch flow channel is outer, inner circle radius, and θ, θ ' are respectively width of flow path wiPosition pair
It should outer, inner circle drift angle.
7. bias variable cross-section flow distribution baffle according to claim 1, which is characterized in that the propellant runner hole
(22) it is distributed with concentric circles, symmetrical, varied angle or angularly, the flow passage aperture of propellant runner hole (22) passes through following formula meter
It obtains:
dlFor flow passage aperture, AlFor runner hole total sectional area, n is runner hole design quantity, vlTo design highest stream in runner hole
Speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811032749.9A CN109519303A (en) | 2018-09-05 | 2018-09-05 | Eccentric variable cross-section flow distribution baffle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811032749.9A CN109519303A (en) | 2018-09-05 | 2018-09-05 | Eccentric variable cross-section flow distribution baffle |
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| Publication Number | Publication Date |
|---|---|
| CN109519303A true CN109519303A (en) | 2019-03-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811032749.9A Pending CN109519303A (en) | 2018-09-05 | 2018-09-05 | Eccentric variable cross-section flow distribution baffle |
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| CN (1) | CN109519303A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111664026A (en) * | 2020-06-08 | 2020-09-15 | 西安航天动力研究所 | Disc-shaped annular cavity type high-energy detonator of rotary detonation engine |
| CN114165359A (en) * | 2021-12-03 | 2022-03-11 | 北京航天动力研究所 | Injector structure for preventing body from overheating |
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| CN108224474A (en) * | 2017-12-06 | 2018-06-29 | 中国联合重型燃气轮机技术有限公司 | A kind of rear flame fuel injection apparatus of gas turbine |
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| CN106134392B (en) * | 2009-12-03 | 2013-12-11 | 上海空间推进研究所 | A kind of method of combination of ejector filler spray unit of double elements liquid-propellant rocket engine |
| CN102400815A (en) * | 2011-03-18 | 2012-04-04 | 北京航空航天大学 | Layer-board type injection device for oxygen/ methane low-thrust engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111664026A (en) * | 2020-06-08 | 2020-09-15 | 西安航天动力研究所 | Disc-shaped annular cavity type high-energy detonator of rotary detonation engine |
| CN111664026B (en) * | 2020-06-08 | 2021-03-30 | 西安航天动力研究所 | Disc-shaped annular cavity type high-energy detonator of rotary detonation engine |
| CN114165359A (en) * | 2021-12-03 | 2022-03-11 | 北京航天动力研究所 | Injector structure for preventing body from overheating |
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| PB01 | Publication | ||
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Application publication date: 20190326 |