CN109057995A - The partition nozzle best clearance design method and partition nozzle that can be dissipated based on sound - Google Patents
The partition nozzle best clearance design method and partition nozzle that can be dissipated based on sound Download PDFInfo
- Publication number
- CN109057995A CN109057995A CN201810874442.7A CN201810874442A CN109057995A CN 109057995 A CN109057995 A CN 109057995A CN 201810874442 A CN201810874442 A CN 201810874442A CN 109057995 A CN109057995 A CN 109057995A
- Authority
- CN
- China
- Prior art keywords
- nozzle
- partition
- sound
- partition nozzle
- gap
- Prior art date
- 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.)
- Granted
Links
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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
A kind of partition nozzle best clearance design method that can be dissipated based on sound provided by the invention and partition nozzle, using the method for asymptotics, slow variable area channel between adjacent nozzle is reduced to several cross-section channels interconnected, pass through step condition, the sound system in adjacent cross-section channel is connected, the relationship that partition nozzle gap and sound can dissipate is established；The sound calculated under different partition nozzle gaps can dissipate, and when sound can dissipate maximum, corresponding partition nozzle gap is partition nozzle best clearance.Method of the invention is suitable for the design of all kinds of rocket engine partition nozzle best clearances, and convenient and efficient, low in cost, high reliablity can reduce the workload of the experiment in design, greatly reduce the lead time.The present invention also provides the partition nozzles using the design of above-mentioned design method.
Description
Technical field
The invention belongs to rocket engine rough burning control fields, are related to rocket chamber's partition nozzle,
More particularly to a kind of partition nozzle best clearance design method that can be dissipated based on sound and partition nozzle.
Background technique
Liquid-propellant rocket engine during the work time, due to being in the environment of high temperature, high pressure, easily causes unstable combustion
It burns.Rough burning can cause high burn rate and heat transfer efficiency, cause violent oscillation, and spray panel is caused to burn
Erosion, or even explode, it influences entire dynamical system and operates normally.Wherein destructive strongest somatic sypermutation, be by
Fuel combustion process is coupled to form with combustion chamber acoustic characteristic, therefore combustion chamber acoustic characteristic is the important of influence rough burning
Link.Partition nozzle can change acoustic characteristic in combustion chamber, be widely used in inhibiting rough burning in rocket engine.Such as
It is rocket chamber's partition nozzle schematic diagram shown in Fig. 1.The installation of rocket chamber head is used for propellant mist
The ejector filler (i.e. nozzle) of change, the end face that ejector filler is constituted are spray panel, and partition nozzle is by extending to combustion on spray panel
The series of spray nozzles for burning room is constituted, and radially distributed nozzle is known as radial partition nozzle, and the nozzle being circumferentially distributed is known as hub
Partition nozzle, radial partition nozzle and hub partition nozzle are all the cylinder rows arranged along particular arrangement mode, form column grid-type and inhale
Sound channel.According to it is domestic and international the study found that in column grid-type channel adjacent intercolumniation there are gaps compared to gapless when, sound absorption effect
More preferably, it is more advantageous to inhibition rough burning, gap when to rough burning inhibitory effect preferably is known as best clearance.In order to
Obtain the best effects for inhibiting rough burning, it is necessary to be designed to partition nozzle best clearance.But at present for partition
The design of nozzle best clearance is more to test by experience or repeatedly so far still without the effective design method of complete set
Obtain final design result.And rocket engine working environment (high temperature, high pressure) is extremely severe, to experimental method and operator
Requirement it is harsher, experimental cost is higher.Therefore it is badly in need of a kind of convenient and efficient, low-cost partition nozzle best clearance set
Meter method.
Summary of the invention
For defect present in above-mentioned background and deficiency, the invention proposes a kind of partition nozzles that can be dissipated based on sound
The design method of best clearance, it is convenient and efficient, at low cost suitable for the design of all kinds of rocket engine partition nozzle best clearances
Honest and clean, high reliablity can reduce the workload of the experiment in design, greatly reduce the lead time.The present invention also provides using upper
State the partition nozzle of design method design.
Technical scheme is as follows:
1. a kind of design method for the partition nozzle best clearance that can be dissipated based on sound, which is characterized in that forced using progressive
Slow variable area channel between adjacent nozzle is reduced to several cross-section channels interconnected, passes through step item by close method
Part connects the sound system in adjacent cross-section channel, establishes the relationship that partition nozzle gap and sound can dissipate；It calculates not
It can dissipate with the sound under partition nozzle gap, when sound can dissipate maximum, corresponding partition nozzle gap is partition nozzle
Best clearance.
2. wherein, establishing partition nozzle gap and sound can dissipate that specific step is as follows for relationship:
Each cross-section path clearance s obtained by asymptotics methodmAre as follows:
Wherein D is partition nozzle diameter, and b is adjacent separator nozzle gap, xmFor the position coordinates in each cross-section channel；
At adjacent cross-section channel, pressure conservation equation is utilized:
At adjacent cross-section channel, mass-conservation equation is utilized:
Equation (2), in (3),WithFor m cross-section channel sonic wave amplitude,WithIt is logical for m+1 cross-section
Road sonic wave amplitude, k=ω/c are sound wave wave number, and the π of ω=2 f is angular frequency, and f is working frequency, and c is acoustic velocity, and Δ x is each
The width in cross-section channel；
Pressure conservation equation and quality side's conservation equation are arranged, can be obtained:
WhereinWithFor sonic wave amplitude before partition nozzle,WithFor sonic wave amplitude after partition nozzle；Then sound wave passes through
After partition nozzle act, sound can dissipate expression formula are as follows:
By equation (1), (4), (5), it can establish partition nozzle diameter D, partition nozzle gap b and sound can dissipate the relationship of e
Formula.
3. calculating the sound under different partition nozzle gaps can dissipate, the work of setting rocket engine is in certain work frequency
Under the conditions of rate, fuel gas temperature, according to given partition nozzle diameter, change partition nozzle gap, carry out sound can dissipate size
It calculates.
4. further including being modified for different spray nozzles diameter to the partition nozzle best clearance value being calculated；It is elected
When nozzle diameter increases, reduction trend is presented in partition nozzle best clearance, therefore designs in rocket engine partition nozzle
When, when the nozzle diameter of selection increases, it should accordingly reduce adjacent separator nozzle gap, until gap is under respective nozzle diameter
Best clearance.
5 further include for the different working frequency of rocket engine, to the partition nozzle best clearance value being calculated into
Row amendment；When rocket engine rated operation frequency increases, reduction trend is presented in partition nozzle best clearance, therefore in rocket
When engine partition nozzle designs, when rated operation frequency increases, it should accordingly reduce adjacent separator nozzle gap, until gap
For the best clearance under relevant work frequency.
6. further include for the different fuel gas temperature of rocket engine, to the partition nozzle best clearance value being calculated into
Row amendment；When rocket chamber's fuel gas temperature increases, increase tendency is presented in partition nozzle best clearance, therefore in fire
When arrow engine partition nozzle designs, when propellant fuel gas temperature increases, adjacent separator nozzle gap should be increased accordingly, until
Gap is the best clearance under corresponding fuel gas temperature.
7. a kind of partition nozzle designed according to above-mentioned design method, the partition nozzle is by extending to a system of combustion chamber
Column nozzle is constituted, and the nozzle includes the cylinder row by the arrangement of certain arrangement mode, forms column grid-type sound absorption channel, and feature exists
In having between adjacent nozzle, which enables sound to dissipate, reaches maximum best clearance.
The beneficial effects of the present invention are: the partition nozzle best clearance of all kinds of rocket engines, method can be designed
Simple and efficient, low in cost, high reliablity can reduce the experimental work amount in design, greatly reduce the lead time.
Detailed description of the invention
The rocket chamber Fig. 1 partition nozzle schematic diagram.
Fig. 2 partition nozzle gradual change cross-sectional passage model.
Fig. 3 is designed a model figure based on the partition nozzle best clearance that sound can dissipate.
Fig. 4 partition nozzle gap can dissipate affecting laws figure to sound.
Influence of Fig. 5 nozzle diameter to partition nozzle best clearance.
Influence of Fig. 6 working frequency to partition nozzle best clearance.
Influence of Fig. 7 fuel gas temperature to partition nozzle best clearance.
Specific embodiment
To be more clear the object of the invention, technical solution and advantage, below in conjunction with attached drawing to specific reality of the invention
Applying method is described further.In the present embodiment, using design method of the invention, for partition spray in liquid-propellant rocket engine
The design of mouth best clearance is compared by the experimental result to different partition nozzle gaps, demonstrates effectiveness of the invention.Tool
Body implementation method is described as follows:
In rocket engine partition nozzle, play main sound absorption is exactly the slow variable area channel that adjacent nozzle is constituted,
As shown in Figure 2.Due to the complex nature of the problem, the column grid-type channel of partition nozzle is subjected to Rational Simplification, can be reduced to
Individually, two, three or more gradual change cross-sectional passage in the present embodiment, only considers single gradual change cross-sectional passage.For adjacent spray
The single gradual change cross-sectional passage that mouth is constituted, at present solves it still without a kind of suitable model.The present invention is using progressive
The method approached establishes the figure that designs a model as shown in Figure 3, and single gradual change cross-sectional passage is reduced to several squares interconnected
Shape cross-section channel is connected the sound system in adjacent rectangle cross-section channel by step condition, finally set up every
The relational expression that plate nozzle gap and sound can dissipate.
A kind of design method for the partition nozzle best clearance that can be dissipated based on sound, using the method for asymptotics, by phase
Slow variable area channel between adjacent nozzle is reduced to several cross-section channels interconnected, by step condition, by adjacent equal section
The sound system in face channel connects, and establishes the relationship that partition nozzle gap and sound can dissipate；It calculates between different partition nozzles
Sound under gap can dissipate, and when sound can dissipate maximum, corresponding partition nozzle gap is partition nozzle gap best clearance.
Wherein, it establishes partition nozzle gap and sound can dissipate that specific step is as follows for relationship:
Each cross-section path clearance s obtained by asymptotics methodmAre as follows:
Wherein D is partition nozzle diameter, and b is adjacent separator nozzle gap, xmFor the position coordinates in each cross-section channel；
At adjacent cross-section channel, pressure conservation equation is utilized:
At adjacent cross-section channel, mass-conservation equation is utilized:
Equation (2), in (3),WithFor m cross-section channel sonic wave amplitude,WithIt is logical for m+1 cross-section
Road sonic wave amplitude, k=ω/c are sound wave wave number, and the π of ω=2 f is angular frequency, and f is working frequency, and c is acoustic velocity, and Δ x is each
The width in cross-section channel；
Pressure conservation equation and quality side's conservation equation are arranged, can be obtained:
WhereinWithFor sonic wave amplitude before partition nozzle,WithFor sonic wave amplitude after partition nozzle；Then sound wave passes through
After partition nozzle act, sound can dissipate expression formula are as follows:
By equation (5) it is found that sound can dissipate sonic wave amplitude before and after e and partition nozzleWithIt is related；By
Equation (4) is it is found that partition nozzle front and back sonic wave amplitudeWithWith each cross-section path clearance smAnd sm+1It is related；
By equation (1) it is found that each cross-section path clearance smAnd sm+1It is related with partition nozzle diameter D, partition nozzle gap b；While by
The expression formula of sound wave wave number is it is found that energy dissipation e is related with working frequency f and acoustic velocity c；Thus partition nozzle is just established
Diameter D, partition nozzle gap b and sound can dissipate the relational expression of e.
When calculating the sound under different partition nozzle gaps can dissipate, the rocket engine work of setting is in certain work frequency
Under the conditions of rate, fuel gas temperature, according to given partition nozzle diameter, change partition nozzle gap, carry out sound can dissipate size
It calculates.
In the present embodiment, at normal temperatures and pressures, selection working frequency f is 400Hz, and partition nozzle diameter D is 10mm, is changed
Adjacent separator nozzle gap b is 0~0.5mm.The expression formula that can be dissipated by partition nozzle gap and sound, i.e. equation (5) obtain
The changing rule that sound can dissipate with partition nozzle gap, as shown in Figure 4.It is 400Hz, partition nozzle that Fig. 4, which gives working frequency f,
Diameter D be 10mm when, sound can dissipate e with partition nozzle gap b changing rule.It can be seen that with the increasing of partition nozzle gap
Add, sound can dissipate first to increase to be reduced afterwards, and the sound at extreme point can dissipate maximum, and corresponding nozzle gap is partition nozzle at this time
Best clearance.Solid dot is that the present invention obtains as a result, hollow dots are that experiment obtains as a result, due to inevitable in experimentation in Fig. 4
The sound of appearance system can dissipate, therefore experiment value is slightly larger than theoretical value.By being compared to experimental result under different gap, demonstrate
Effectiveness of the invention.
Due to being had differences between different model rocket engine, in nozzle model (diameter) selection, rated operation frequency
There are greatest differences with combustion chamber fuel gas temperature.It is wanted to meet the design of all kinds of rocket engine partition nozzle best clearances
It asks, needs under different spray nozzles diameter, working frequency and fuel gas temperature, partition nozzle best clearance value is modified.
Fig. 5 gives under normal temperature and pressure working frequency f when being 400Hz, partition nozzle diameter D be respectively 5mm, 10mm,
When 15mm, 20mm, 25mm and 30mm, change adjacent separator nozzle gap b is 0~0.5mm, and sound can dissipate with partition nozzle gap
Changing rule.It can be seen that sound can dissipate first increases and then decreases with the increase of nozzle gap, extreme point place it is corresponding every
Plate nozzle gap is best clearance.With the increase of partition nozzle diameter, reduction trend is presented in optimal clapboard nozzle gap.Therefore
In the design of rocket engine partition nozzle, when the nozzle diameter of selection increases, it should accordingly reduce adjacent separator nozzle gap,
Until gap is the best clearance value under respective nozzle diameter.
Fig. 6 give normal temperature and pressure lower clapboard nozzle diameter D be 10mm when, working frequency f be respectively 400Hz, 800Hz,
When 1200Hz, 1600Hz and 2000Hz, change adjacent separator nozzle gap b is 0~0.5mm, and sound can dissipate between partition nozzle
The changing rule of gap.It can be seen that sound can dissipate first increases and then decreases with the increase of partition nozzle gap, institute is right at extreme point
The partition nozzle gap answered is best clearance.With the increase of working frequency, reduction trend is presented in optimal clapboard nozzle gap.Cause
This rocket engine partition nozzle design in, when rocket engine rated operation frequency increase when, should accordingly reduce it is adjacent every
Plate nozzle gap, until gap is the best clearance value under relevant work frequency.
Fig. 7 give partition nozzle diameter D be 10mm, working frequency f be 400Hz when, fuel gas temperature T be respectively 2800K,
When 3000K, 3200K, 3400K, 3600K and 3800K, change adjacent separator nozzle gap b be 0~0.02mm, sound can dissipate with
The changing rule of partition nozzle gap.It can be seen that sound can dissipate first increases and then decreases, pole with the increase of partition nozzle gap
The corresponding partition nozzle gap in value point place is best clearance.With the raising of fuel gas temperature, optimal clapboard nozzle gap is presented
Increase tendency.Therefore in the design of rocket engine partition nozzle, when rocket chamber's fuel gas temperature increases, Ying Xiang
Adjacent separator nozzle gap should be increased, until gap is the best clearance value under corresponding fuel gas temperature.
Correspondingly, the partition nozzle is by extending to the one of combustion chamber according to the partition nozzle that above-mentioned design method designs
Series of jets is constituted, and the nozzle includes the cylinder row by the arrangement of certain arrangement mode, forms column grid-type sound absorption channel；Adjacent spray
Having between mouth, which enables sound to dissipate, reaches maximum best clearance.
It should be pointed out that specific embodiment described above can make those skilled in the art that the present invention be more fully understood
It creates, but do not limit the invention in any way is created.All do not depart from the technical solution of the spirit and scope of the invention
And its improve, it is encompassed by the protection scope of the invention patent.
Claims (7)
1. a kind of design method for the partition nozzle best clearance that can be dissipated based on sound, which is characterized in that using asymptotics
Slow variable area channel between adjacent nozzle is reduced to several cross-section channels interconnected by method, will by step condition
The sound system in adjacent cross-section channel connects, and establishes the relationship that partition nozzle gap and sound can dissipate；Calculate it is different every
Sound under plate nozzle gap can dissipate, and when sound can dissipate maximum, corresponding partition nozzle gap is that partition nozzle is best
Gap.
2. the method according to claim 1, wherein establishing partition nozzle gap and sound can dissipate the specific of relationship
Steps are as follows:
Each cross-section path clearance s obtained by asymptotics methodmAre as follows:
Wherein D is partition nozzle diameter, and b is adjacent separator nozzle gap, xmFor the position coordinates in each cross-section channel；
At adjacent cross-section channel, pressure conservation equation is utilized:
At adjacent cross-section channel, mass-conservation equation is utilized:
Equation (2), in (3),WithFor m cross-section channel sonic wave amplitude,WithFor m+1 cross-section channel sound
Wave-amplitude, k=ω/c are sound wave wave number, and the π of ω=2 f is angular frequency, and f is working frequency, and c is acoustic velocity, and Δ x is that each wait is cut
The width in face channel；
Pressure conservation equation and quality side's conservation equation are arranged, can be obtained:
WhereinWithFor sonic wave amplitude before partition nozzle,WithFor sonic wave amplitude after partition nozzle；Then sound wave is sprayed through partition
After mouth effect, sound can dissipate expression formula are as follows:
By equation (1), (4), (5), it can establish partition nozzle diameter D, partition nozzle gap b and sound can dissipate the relational expression of e.
3. according to the method described in claim 2, it is characterized in that, when the sound for calculating under different partition nozzle gaps can dissipate,
Rocket engine work is set under the conditions of certain working frequency, fuel gas temperature, according to given partition nozzle diameter, is changed
Partition nozzle gap, carry out sound can dissipate the calculating of size.
4. method according to claim 1 to 3, which is characterized in that further include for different spray nozzles diameter, to calculating
Obtained partition nozzle best clearance value is modified；When the nozzle diameter of selection increases, partition nozzle best clearance is presented
Reduction trend, therefore in the design of rocket engine partition nozzle, when the nozzle diameter of selection increases, should accordingly reduce adjacent
Partition nozzle gap, until gap is the best clearance under respective nozzle diameter.
5. method according to claim 1 to 3, which is characterized in that further include the work different for rocket engine
Working frequency is modified the partition nozzle best clearance value being calculated；When rocket engine rated operation frequency increases,
Reduction trend is presented in partition nozzle best clearance, therefore in the design of rocket engine partition nozzle, when rated operation frequency increases
Added-time should accordingly reduce adjacent separator nozzle gap, until gap is the best clearance under relevant work frequency.
6. method according to claim 1 to 3, which is characterized in that further include the combustion different for rocket engine
Temperature degree is modified the partition nozzle best clearance value being calculated；When rocket chamber's fuel gas temperature increases
When, increase tendency is presented in partition nozzle best clearance, therefore in the design of rocket engine partition nozzle, when propellant combustion gas temperature
When degree increases, adjacent separator nozzle gap should be increased accordingly, until gap is the best clearance under corresponding fuel gas temperature.
7. a kind of partition nozzle of method according to claim 1 to 6 design, the partition nozzle is by extending to combustion
The series of spray nozzles for burning room is constituted, and the nozzle includes the cylinder row by the arrangement of certain arrangement mode, and it is logical to form the sound absorption of column grid-type
Road, which is characterized in that having between adjacent nozzle, which enables sound to dissipate, reaches maximum best clearance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810874442.7A CN109057995B (en) | 2018-08-03 | 2018-08-03 | Baffle nozzle optimal gap design method based on acoustic energy dissipation and baffle nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810874442.7A CN109057995B (en) | 2018-08-03 | 2018-08-03 | Baffle nozzle optimal gap design method based on acoustic energy dissipation and baffle nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109057995A true CN109057995A (en) | 2018-12-21 |
| CN109057995B CN109057995B (en) | 2020-09-11 |
Family
ID=64832886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810874442.7A Active CN109057995B (en) | 2018-08-03 | 2018-08-03 | Baffle nozzle optimal gap design method based on acoustic energy dissipation and baffle nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109057995B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111307465A (en) * | 2020-03-02 | 2020-06-19 | 北京航天动力研究所 | Multifunctional test device for realizing integrated verification of combustion and heat transfer technologies |
| CN112163292A (en) * | 2020-09-24 | 2021-01-01 | 北京航空航天大学 | Ribbed partition nozzle modification method for improving acoustic energy dissipation |
| CN112196696A (en) * | 2020-09-24 | 2021-01-08 | 北京航空航天大学 | Modification method for improving acoustic energy dissipation of partition plate nozzle |
| CN112199787A (en) * | 2020-09-24 | 2021-01-08 | 北京航空航天大学 | Elliptical partition plate nozzle shaping method for increasing acoustic energy dissipation |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2291975C1 (en) * | 2005-09-14 | 2007-01-20 | Владимир Викторович Черниченко | Mixing head of chamber of liquid rocket engine |
| US20100221570A1 (en) * | 2005-12-23 | 2010-09-02 | Jason Nadler | Porous Metal Bodies Used for Attenuating Aviation Turbine Noise |
| CN102525334A (en) * | 2010-12-16 | 2012-07-04 | 乐金电子(天津)电器有限公司 | Diverting and bypassing denoising structure of dust collector motor shell |
| 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 |
| CN107939551A (en) * | 2017-11-29 | 2018-04-20 | 北京航天动力研究所 | A kind of precombustion chamber ejector filler structure |
-
2018
- 2018-08-03 CN CN201810874442.7A patent/CN109057995B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2291975C1 (en) * | 2005-09-14 | 2007-01-20 | Владимир Викторович Черниченко | Mixing head of chamber of liquid rocket engine |
| US20100221570A1 (en) * | 2005-12-23 | 2010-09-02 | Jason Nadler | Porous Metal Bodies Used for Attenuating Aviation Turbine Noise |
| 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 |
| CN102525334A (en) * | 2010-12-16 | 2012-07-04 | 乐金电子(天津)电器有限公司 | Diverting and bypassing denoising structure of dust collector motor shell |
| CN107939551A (en) * | 2017-11-29 | 2018-04-20 | 北京航天动力研究所 | A kind of precombustion chamber ejector filler structure |
Non-Patent Citations (1)
| Title |
|---|
| 郭灿琳: "喷嘴式隔板与纵向肋式隔板阻尼效应分析", 《火箭推进》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111307465A (en) * | 2020-03-02 | 2020-06-19 | 北京航天动力研究所 | Multifunctional test device for realizing integrated verification of combustion and heat transfer technologies |
| CN112163292A (en) * | 2020-09-24 | 2021-01-01 | 北京航空航天大学 | Ribbed partition nozzle modification method for improving acoustic energy dissipation |
| CN112196696A (en) * | 2020-09-24 | 2021-01-08 | 北京航空航天大学 | Modification method for improving acoustic energy dissipation of partition plate nozzle |
| CN112199787A (en) * | 2020-09-24 | 2021-01-08 | 北京航空航天大学 | Elliptical partition plate nozzle shaping method for increasing acoustic energy dissipation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109057995B (en) | 2020-09-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109057995A (en) | The partition nozzle best clearance design method and partition nozzle that can be dissipated based on sound | |
| CN104061595B (en) | Continuous burning bushing for the burner of combustion gas turbine | |
| CN204063127U (en) | Combustion gas turbine and the system for controlling compression working fluid flow velocity | |
| US9267436B2 (en) | Fuel distribution manifold for a combustor of a gas turbine | |
| CN101776027B (en) | Air suction type liquid fuel pulse detonation engine | |
| JP2016099106A (en) | Bundled tube fuel nozzle | |
| CN110762555B (en) | Pneumatic auxiliary type cavity support plate flame stabilizer | |
| US20180195430A1 (en) | Ducted combustion systems utilizing flow field preparation | |
| RU2013125135A (en) | FUEL COMBUSTION SYSTEM, GAS TURBINE, METHOD FOR REGULATING THE PROFILE OF DISTRIBUTING HEAT LOADS ON THE TRANSITION CHANNEL AND METHOD FOR MANUFACTURING THE SUBSYSTEM OF THE COMBUSTION CHAMBER FOR A GAS TURBINE | |
| CA2496908A1 (en) | Stress relief feature for aerated gas turbine fuel injector | |
| CN105180212A (en) | Combustion chamber of supersonic combustion ramjet engine | |
| CN107339166B (en) | A kind of pulse-knocking engine combustion chamber | |
| US20060016193A1 (en) | Turbo-jet engine with a protective screen of the fuel manihold of a burner ring, the burner ring and the protective screen | |
| CN109915855A (en) | Double oil circuits liquidate simple nozzle | |
| EP3180565B1 (en) | Multi-functional fuel nozzle with a dual-orifice atomizer | |
| CN105102789A (en) | Turbo machine combustion assembly comprising an improved fuel supply circuit | |
| CN109723577A (en) | A kind of unstable Active Control Method of high-frequency combustion based on plasma | |
| US20050241321A1 (en) | Transition duct apparatus having reduced pressure loss | |
| CN204385279U (en) | A kind of gas turbine blades thermal barrier coating spray equipment | |
| CN108151062B (en) | A kind of engine supersonic speed combustion chamber based on embedded central plasma torch | |
| CN110030580A (en) | Method of the control for the fuel injection in the reheat combustion chamber of burner unit | |
| CN110319456B (en) | Solid rocket scramjet engine adopting multistage combustion enhancing device | |
| CN109630319B (en) | Active cooling type pintle injector suitable for embedded ignition device | |
| CN102606343A (en) | Detonation chamber of pulse detonation engine | |
| KR101579122B1 (en) | Combuster of gas turbine, gasturbineincluding the same, and cooling method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |