CN116697404A - Support-stem mutual-excitation burner - Google Patents
Support-stem mutual-excitation burner Download PDFInfo
- Publication number
- CN116697404A CN116697404A CN202210791682.7A CN202210791682A CN116697404A CN 116697404 A CN116697404 A CN 116697404A CN 202210791682 A CN202210791682 A CN 202210791682A CN 116697404 A CN116697404 A CN 116697404A
- Authority
- CN
- China
- Prior art keywords
- combustion
- excitation
- mutual
- branch
- burner
- 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.)
- Pending
Links
- 230000005284 excitation Effects 0.000 claims description 38
- 230000002000 scavenging effect Effects 0.000 claims description 12
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 238000009825 accumulation Methods 0.000 claims 1
- 238000002485 combustion reaction Methods 0.000 abstract description 111
- 150000001875 compounds Chemical class 0.000 abstract 1
- 239000000446 fuel Substances 0.000 description 31
- 230000035939 shock Effects 0.000 description 15
- 238000004200 deflagration Methods 0.000 description 14
- 238000005474 detonation Methods 0.000 description 13
- 239000007789 gas Substances 0.000 description 12
- 238000001816 cooling Methods 0.000 description 10
- 230000010355 oscillation Effects 0.000 description 9
- 125000000217 alkyl group Chemical group 0.000 description 6
- 230000000694 effects Effects 0.000 description 6
- 238000004880 explosion Methods 0.000 description 6
- 239000007788 liquid Substances 0.000 description 6
- 239000003595 mist Substances 0.000 description 6
- 238000010926 purge Methods 0.000 description 4
- 230000002238 attenuated effect Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 125000000449 nitro group Chemical group [O-][N+](*)=O 0.000 description 3
- IAYPIBMASNFSPL-UHFFFAOYSA-N Ethylene oxide Chemical compound C1CO1 IAYPIBMASNFSPL-UHFFFAOYSA-N 0.000 description 2
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical group OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- LYGJENNIWJXYER-UHFFFAOYSA-N nitromethane Chemical compound C[N+]([O-])=O LYGJENNIWJXYER-UHFFFAOYSA-N 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000036284 oxygen consumption Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 206010010356 Congenital anomaly Diseases 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000004480 active ingredient Substances 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 238000003421 catalytic decomposition reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000009514 concussion Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 239000003502 gasoline Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000029058 respiratory gaseous exchange Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R7/00—Intermittent or explosive combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The application discloses a branch and trunk mutually-excited burner. The branch-trunk mutual-excitation burner is a compound pulse mutual-excitation burner formed by branch mutual-excitation vibration combustion and trunk mutual-excitation resonance combustion. Combustion systems for pulse jet engines, combustion systems for pulse turbine shaft engines.
Description
Technical Field
The disclosure relates to the field of combustion technology, in particular to a branch-stem mutual-excitation combustion technology.
Background
The pulse combustion chamber needs scavenging air intake, oil-gas mixing and ignition combustion, belongs to intermittent combustion, and has low compression ratio pulse combustion chamber and congenital deficiency of per liter of power.
Disclosure of Invention
1. Support-stem mutual-excitation burner
The combustion chamber A1 and the combustion chamber A2 are shared by an air inlet pipe and an air outlet pipe, and branch alignment association is established to form a combustion group A.
The combustion chamber B1 and the combustion chamber B2 are shared by an air inlet pipe and an air outlet pipe, and branch alignment association is established to form a combustion group B.
And the combustion group A and the combustion group B commonly establish alignment association through an air inlet pipeline and an air outlet pipeline of the trunk. See fig. 1.
The combustible mixture in the combustion chamber A1 is detonated by the initiation of the chamber detonation. The detonation shock wave or detonation wave propagates along the branch pipe at high speed, and the high-speed shock wave has no obvious energy overflow at the branch-trunk junction. The combustible mixture in the combustion chamber A2 detonates under the action of high-energy shock waves. The detonation expansion wave and the impact rebound wave propagate along a common pipeline at high speed and bombard the combustion chamber A1. Unburned components in the combustion chamber A1 are post-combusted under the action of high-energy impact waves. The afterburning expansion wave and the stamping rebound wave propagate along the common branch pipe to bombard the combustion chamber A2. The unburnt components in the combustion chamber A2 are afterburned under the action of the shock wave. The post-combustion expansion wave and the stamping rebound wave propagate along the common branch pipe to bombard the combustion chamber A1 … …, and the combustion chamber A1 and the combustion chamber A2 form mutual excitation oscillation type combustion. When the fuel is near to burn-out, the combustion expansion wave is attenuated, the vibration intensity is reduced, the combustion expansion gas starts to be released to the trunk road at the branch-trunk junction, the energy release enables the branch vibration to be attenuated rapidly, and the combustion expansion gas is released to the trunk road rapidly in a shock wave mode.
The combustion shock wave of the group A propagates to the group B along the dry path, about 50% of the energy of the shock wave is output through the exhaust pipe and the overflow port, and about 30% of the shock wave covers the exhaust port of the combustion group B and bombards the combustion group B.
About 20% of the impact wave energy is converted into the static pressure energy of the stamping chamber, and after the impact wave crest is ejected through the rear stamping chamber, the combustion group is forced to be purged by directional release of energy and jet ejection. Under the triple actions of forced purging, supercharging air intake and inertial scavenging of an exhaust pipeline, the scavenging speed, the scavenging rate and the air intake speed of the combustion group are all improved.
The combustion group B is stamped by the shock wave of the combustion group A, and is ignited by timing injection of fuel liquid mist and timing detonation of the small chamber of the combustion chamber B1, and the combustion chamber B1 and the combustion chamber B2 generate branch mutually-excited oscillation combustion. When the fuel is near to burn-out, the vibration intensity of the branch is reduced, and the combustion expansion gas of the combustion group B is rapidly released to the trunk road in the form of shock waves. About 30% of the shock wave energy propagates along the main road and bombards combustion group a.
The combustion group A is stamped by the shock wave of the combustion group B, injected by the timing of fuel liquid mist and ignited by the timing of the deflagration small chamber of the combustion chamber A1, and the combustion chamber A1 and the combustion chamber A2 generate branch mutually excited oscillation combustion.
By means of a plurality of pressure sensors in the main road, the combustion chamber A1 and the combustion chamber A2 form branch mutual excitation oscillation type combustion by means of sensing data and a combustion control program, and the combustion chamber B1 and the combustion chamber B2 form branch mutual excitation oscillation type combustion. The combustion group A and the combustion group B form a dry-path mutually excited resonant combustion.
The branch-dry inter-excitation burner adopts excessive scavenging type inner surface cooling and outer cooling fin airflow type cooling. The deflagration chamber uses high-activity fuel with low oxygen consumption, and consists of nitromethane, ethylene oxide and the like.
The fuel for main combustion is alkyl composite fuel, and mainly consists of gasoline, kerosene and additive. The rapid combustion of the medium active fuel is stimulated by the explosion of the chamber, so that the fuel cost is controlled. Before the fuel is burnt out, the branch is positioned in the combustion chamber at high pressure by multiple pulses, the gas in the combustion chamber moves violently, and the relative movement of fuel droplets and high-temperature gas is sufficient, so that the combustion speed and the combustion margin are improved. The compression ratio of the combustion chamber is improved by the dry-path shock wave mutual excitation, and the combustion chamber has power per liter higher than 400 kilowatts by being matched with high-frequency combustion supported by valveless high-speed gas distribution.
The burner employs oversteered internal purge cooling and air flow cooling of the external fins.
The high-frequency reinforced branch dry mutual-excitation combustor is mainly used for pulse jet-suction stamping hypersonic gas compressors, pulse jet fan engines, pulse jet engines, pulse turbine paddle aeroengines, pulse turbine fan aeroengines, pulse turbine shaft marine engines, pulse turbine shaft generators, pulse turbine shaft automotive engines, pulse turbine shaft gas compressors, pulse turbine shaft high-power pumps and the like.
2. Valveless valve assembly
And converting partial energy of pulse combustion shock wave or detonation wave output by the branch-trunk mutual excitation combustion into static pressure energy of the stamping chamber, and jetting the impact wave crest through the rear stamping chamber. The jet flow of the directional jet of the stamping chamber forms enhanced scavenging power, and jet flow jet suction, supercharged air intake and inertial scavenging of an exhaust pipeline form auxiliary power of scavenging air intake. The valve-free distribution assembly is formed by a stamping chamber, a compressed gas inlet pipe, an overflow port and an inertial scavenging exhaust pipe. The pulse mixture overflowed from the overflow port is used for driving the air inlet booster.
The gas distribution flow comprises 5 seconds of purging before starting, pulse energy output after the mutual excitation oscillation combustion of the combustion group A, scavenging air intake of the combustion group A and pulse energy output after the mutual excitation oscillation combustion of the combustion group B, and the structure is symmetrical and the cycle is performed in sequence. See fig. 2.
3. Branch mutual excitation and mutual excitation resonance dual-mode burner
In the branch-trunk mutual-excitation burner, the branch-branch mutual-excitation concussion combustion has high mutual-excitation intensity, and the main combustion chamber cannot use high-activity fuel.
When a fuel with low or medium oxygen consumption is used outside the atmosphere, the fuel contains high active ingredients such as nitromethane and ethylene oxide.
In order to meet the universality of aerospace, the dual-mode combustion in which the branch mutual excitation combustion and the mutual excitation resonance combustion can be switched is adopted. See fig. 3.
And a detonation igniter is arranged between the A1 and A2 combustion chambers of the branch mutual excitation combustor A group and between the B1 and B2 combustion chambers of the branch mutual excitation combustor B group. See fig. 4.
The deflagration igniter is internally provided with a main deflagration small chamber which is communicated with the adjacent related deflagration small chamber through a small-aperture channel. The low-oxygen consumption high-activity fuel liquid mist in the main deflagration chamber is ignited at the timing through the spark plug to generate deflagration. The detonation expansion wave carries flame formed by unburnt fuel liquid drops, the flame bombards opposite main combustion chambers through the main channels, the adjacent associated detonation chambers are bombarded through the small-aperture channels, when fuel nozzles in the associated detonation chambers do not jet fuel liquid mist, detonation wave transmitted by the small-aperture channels rushes to be attenuated, the detonation igniter generates unidirectional ignition, and ignition of the two main combustion chambers aligned by the branch is asynchronous, so that branch mutual excitation oscillation type combustion is generated.
When the associated explosion chambers and the main explosion chambers synchronously spray fuel liquid mist, the main explosion chambers explode and burn detonation waves to excite the adjacent associated explosion chambers to explode through the small-aperture channels, the explosion igniters generate bidirectional bombardment type ignition, the ignition of the two combustion chambers with the opposite branches tends to be synchronous, the branch mutual excitation oscillation combustion disappears, and the branch mutual excitation combustor is converted into a double-chamber parallel type mutual excitation resonant combustor. The branch mutual excitation combustion mode is used in the atmosphere layer, when the alkyl fuel is used outside the atmosphere layer, the branch mutual excitation combustion mode is selected, and when the nitro fuel is used outside the atmosphere layer, the mutual excitation resonance combustion mode is selected.
The interconversion of the branch mutual excitation combustion and the mutual excitation resonance combustion is realized through the opening and closing of the fuel injection of the associated deflagration small chamber, and the branch mutual excitation and mutual excitation resonance dual-mode combustor is formed. And in the atmosphere, adopting excessive scavenging type internal purging type cooling and external cooling fin airflow type cooling. The outside of the atmosphere layer is cooled by oxidant evaporation, and oxygen and water mist generated by catalytic decomposition of hydrogen peroxide are relatively mild in physical and chemical properties, so that the catalyst can be used for cooling and supporting combustion of a system.
Drawings
FIG. 1 is a branched dry inter-exciting burner. In the figure, 1. A high pressure ignition spark plug. 2. A deflagration cell. 3. High activity fuel nozzles. 4. Alkyl fuel nozzles. 5. Combustion chamber a1. Fig. 6. Branch cross-excitation tube also serves as an outlet manifold. 7. Branch junction. 8. Combustion chamber a2, 9. Exhaust trunk line doubles as trunk line inter-excitation line. 10. Exhaust port of combustion group B. 11. Exhaust ports of combustion group a. 12. Alkyl fuel nozzles. 13. Combustion chamber b2, combustion chamber b1, branch mutual excitation pipe and air inlet branch pipe. 16. The air inlet main road pipe is also used as a main road mutual excitation pipe. 17. And an overflow port. 18. Compressed gas inflow pipe. 19. A punching chamber. 20. A pressure sensor.
FIG. 2 is a branch-and-stem mutual-excitation and mutual-excitation resonance dual-mode burner. In the figure 1. Combustion chamber A1. In the figure 2. Alkyl fuel nozzle. 3. A nitro fuel nozzle. 4. The branch mutual excitation pipe and the exhaust branch pipe. 5. A deflagration igniter. 6. Combustion chamber A2.
7. The branch mutual excitation pipe is also used as an air inlet branch pipe. 8. A pressure sensor. 9. The air inlet assembly is also combined with a main road mutual excitation pipe. 10. The exhaust main pipe and the main mutual excitation pipe. 11. Combustion chamber B1. Fig. 12. Combustion chamber B2.
FIG. 3 is a branch and stem mutual excitation and mutual excitation resonance dual-mode burner. In the figure, 1. Combustion chamber A1.2. Alkyl fuel nozzles. 3. A nitro fuel nozzle. 4. The branch mutual excitation pipe and the exhaust pipe. 5. A deflagration igniter. 6. Combustion chamber A2.7. The branch mutual excitation pipe is also used as an air inlet pipe. 8. A pressure sensor. 9. The main road mutual excitation pipe also serves as an air inlet assembly. 10. The main-way mutual excitation pipe and the exhaust assembly. 11. A combustion chamber B1. 12. Combustion chamber B2.
Fig. 4 is a deflagration igniter. In the figure, 1. A high pressure ignition spark plug. 2. A main deflagration cell. 3. High activity fuel nozzles. 4. Breathing type ventilation tube. 5. A small-aperture communicating pipe. 6. Associated with the deflagration cell. 7. High activity fuel nozzles. 8. And orienting the squib. 9. A mutual shock channel. 10. And orienting the squib.
Detailed description of the preferred embodiments
The branch mutual-excitation burner and the mutual-excitation resonance burner used by the aircraft need to reduce the weight on the premise of ensuring the mechanical strength. The combustion chamber adopts a high-temperature resistant lining, transition layer treatment and an outer casting titanium alloy reinforcing layer. The aerospace general-purpose burner needs to be integrally packaged, and meets the working requirements of an atmospheric external cooling system.
Claims (3)
1. A branch-stem mutual-excitation burner.
2. Ram chamber energy accumulation, directional injection enhanced scavenging.
3. A branch mutual excitation and mutual excitation resonance dual-mode burner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210791682.7A CN116697404A (en) | 2022-07-07 | 2022-07-07 | Support-stem mutual-excitation burner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210791682.7A CN116697404A (en) | 2022-07-07 | 2022-07-07 | Support-stem mutual-excitation burner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116697404A true CN116697404A (en) | 2023-09-05 |
Family
ID=87832763
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210791682.7A Pending CN116697404A (en) | 2022-07-07 | 2022-07-07 | Support-stem mutual-excitation burner |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116697404A (en) |
-
2022
- 2022-07-07 CN CN202210791682.7A patent/CN116697404A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112879178B (en) | Solid rocket ramjet based on detonation combustion | |
| US8683780B2 (en) | Gas turbine engine and pulse detonation combustion system | |
| JP5985613B2 (en) | Turbo engine with detonation chamber and flying vehicle equipped with turbo engine | |
| CN100549399C (en) | A kind of high-frequency pulse pinking engine and controlling method thereof | |
| US7367194B2 (en) | Pulse detonation engine system for driving turbine | |
| CN112902225B (en) | Multistage afterburning chamber with outer ring rotary detonation supercharged combustion chamber | |
| CN108869095B (en) | Boundary suction control method with stable and self-sustaining supersonic detonation | |
| JP6132979B2 (en) | Engine that uses combustion gas as driving force | |
| CN106949498A (en) | It is a kind of that the punching engine that energetic material powder lifts thrust is sprayed into based on combustion chamber | |
| CN112196701A (en) | Shock wave focusing detonation combustion chamber based on multi-zone ignition | |
| CN116696596A (en) | Tandem double-combustion-chamber rotary knocking ramjet engine and working method | |
| CN111305972A (en) | Pulse detonation combustion chamber and air turbine rocket engine based on pulse detonation | |
| US20110146286A1 (en) | Self-starting turbineless jet engine | |
| US20120192545A1 (en) | Pulse Detonation Combustor Nozzles | |
| CN116697404A (en) | Support-stem mutual-excitation burner | |
| CN116291952A (en) | Double continuous detonation mode rocket-based combined cycle engine | |
| CN209469512U (en) | Jet flow single point crash engine with compression and combustion and axial symmetry aircraft and lifting body aircraft | |
| US8272221B2 (en) | Hydrogen gas generator for jet engines | |
| CN213899116U (en) | Device for improving efficiency of engine by exciting flame with microwave | |
| CN212029599U (en) | Pulse detonation combustor | |
| CN109931185B (en) | Integral detonation ramjet engine | |
| CN116734292A (en) | Valveless mutual excitation resonance combustor | |
| CN109681344B (en) | Jet single-point impact compression combustion engine, axisymmetric aircraft and lifting body aircraft | |
| CN114320659B (en) | Low-cost closed pulse detonation wind source engine | |
| LU501304B1 (en) | A Hybrid Combined Power System |
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 |