CN116537953A - Turbine afterburner matching system of small turbojet engine booster afterburner - Google Patents
Turbine afterburner matching system of small turbojet engine booster afterburner Download PDFInfo
- Publication number
- CN116537953A CN116537953A CN202310717595.1A CN202310717595A CN116537953A CN 116537953 A CN116537953 A CN 116537953A CN 202310717595 A CN202310717595 A CN 202310717595A CN 116537953 A CN116537953 A CN 116537953A
- Authority
- CN
- China
- Prior art keywords
- afterburner
- booster
- annular cavity
- runner
- turbine
- 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
- 238000002156 mixing Methods 0.000 claims abstract description 69
- 239000012530 fluid Substances 0.000 claims abstract description 14
- 239000007789 gas Substances 0.000 claims description 74
- 238000002955 isolation Methods 0.000 claims description 21
- 239000000295 fuel oil Substances 0.000 abstract description 6
- 238000002485 combustion reaction Methods 0.000 description 33
- 239000000203 mixture Substances 0.000 description 26
- 238000005474 detonation Methods 0.000 description 25
- 239000002737 fuel gas Substances 0.000 description 18
- 239000000446 fuel Substances 0.000 description 15
- 230000002829 reductive effect Effects 0.000 description 15
- 239000003921 oil Substances 0.000 description 10
- 230000002269 spontaneous effect Effects 0.000 description 6
- 230000002401 inhibitory effect Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 238000004891 communication Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000002441 reversible effect Effects 0.000 description 3
- 239000003381 stabilizer Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000670 limiting effect Effects 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention discloses a turbine stress application matching system of a small turbojet engine booster combustor, which comprises a mixing runner and a booster annular cavity, wherein the mixing runner is communicated with the booster annular cavity, and an anti-return unit is arranged between the mixing runner and the booster annular cavity; the anti-return unit is used for controlling the fluid to directionally flow into the pressurizing ring cavity through the mixing flow channel. Therefore, the front-rear pressure drop ratio of the turbine of the supercharging afterburner of the small turbojet engine is ensured, fuel oil is not spontaneously combusted in advance, and the stability of the working state of the turbine is ensured.
Description
Technical Field
The invention relates to the field of small turbojet engines with afterburners, in particular to a turbine afterburner matching system of a supercharging afterburner of a small turbojet engine.
Background
The afterburner is an important part of the aeroengine, and the afterburner can greatly increase the unit head-on thrust and thrust-weight ratio of the engine, comprehensively improve the maneuverability of the aircraft and enlarge the flight envelope. Conventional afterburners are long in size and heavy in weight, thereby limiting further increases in thrust-to-weight ratio performance of the afterburner engine. The length and the diameter of the cylinder body of the afterburner for the small turbojet engine are correspondingly reduced, so that the residence time of fuel in the combustor is greatly shortened, a large amount of fuel is combusted outside the tail nozzle, and the performance of the combustor is reduced.
The booster combustion chamber has the advantages of combustion boosting, high combustion speed, high combustion efficiency and the like, and can continuously boost and burn by primary detonation; the booster combustion chamber can realize stable operation under subsonic to supersonic inflow speeds. Therefore, the structure length of the combustion chamber can be greatly shortened by constructing the booster afterburner through the booster combustion technology, the structure size and the weight of the afterburner are greatly reduced, and the thrust-weight ratio of the engine is greatly improved. However, as the booster combustion can generate high-frequency pressure pulsation of more than thousands of hertz at the head of the booster annular cavity, and the pressure pulsation amplitude is very large, the pressure is easily transmitted back to the turbine, the turbine drop ratio is reduced and deviates from the design point, the output power of the turbine is further reduced, and the normal operation of the turbine is seriously disturbed; in addition, high-temperature and high-pressure gas generated after knocking flows back to the air inlet flow passage of the pressurizing annular cavity, and injected fuel oil can be automatically ignited in advance; the temperature distribution design of the turbine blade is influenced due to the pressure return and the flame return generated by the early spontaneous combustion of injected fuel, the local temperature of the turbine blade is increased, and the turbine performance and the service life are reduced; the problem that a turbine in a supercharged afterburner constructed by a supercharged combustion technology is susceptible is urgently solved.
Disclosure of Invention
The invention aims to overcome the defect that a turbine of a booster combustor is easily influenced by detonation waves in the prior art, and provides a turbine booster matching system of the booster combustor of a small turbojet engine, which comprises a mixing runner, a booster ring cavity and an anti-return unit, wherein the anti-return unit is arranged between the mixing runner and the booster ring cavity; the anti-return unit can inhibit the return of high-temperature and high-pressure gas generated by the detonation wave, reduces the influence of the high-temperature and high-pressure gas on the turbine, and solves the problem that the turbine in the supercharged afterburner constructed by the supercharged combustion technology is easily influenced by the detonation wave.
The aim of the invention is mainly realized by the following technical scheme:
the turbine stress application matching system of the small turbojet engine supercharging afterburner comprises a mixing runner and a supercharging annular cavity, wherein the mixing runner is communicated with the supercharging annular cavity, an anti-return unit is arranged at the joint of the mixing runner and the supercharging annular cavity, and the anti-return unit is used for controlling fluid to directionally flow into the supercharging annular cavity through the mixing runner.
Currently, in order to achieve a large increase in engine thrust in a short period of time, afterburners are often used in aircraft engines to inject, ignite and burn gas or fan post-air streams on the afterburner engines to improve aircraft maneuverability. But since the combustion conditions of a conventional afterburner include: the gas entering the afterburner is firstly decelerated in a diffuser and mixed with the fuel injected by a nozzle to form a fuel-air mixed gas flow, and in order to ensure that the fuel concentration is well distributed in the whole afterburner, fuel is injected by tens or hundreds of centrifugal or direct-current nozzles; the nozzle is arranged on the oil supplying ring, and after flowing through the flame stabilizer, the oil-gas mixture flow forms a backflow area, so that the flow speed of local air flow is reduced to be beneficial to combustion, and meanwhile, the other part of fuel oil is directly sprayed near the flame stabilizer, so that an oil-rich area is generated after the flame stabilizer, and the combustion stability is improved. Thus, the pressure of the air flow in the afterburner is low and the flow rate is high, and the ignited mixed air flow can complete the combustion process only in a longer barrel; for the small turbojet engine, when the afterburner is adopted, the diameter and the length of the barrel of the afterburner are correspondingly reduced, the performance of the afterburner is greatly reduced, and in order to make up for the defects, the booster afterburner can be constructed by adopting the technology of booster combustion, which has the advantages of combustion boosting, high combustion efficiency and the like; therefore, the structural length of the afterburner is shortened, and the thrust-weight ratio of the engine is also greatly improved. However, the detonation wave generated by the supercharged combustion can lead the pressure to be transmitted back to the turbine, so that the turbine pressure drop ratio is reduced and deviates from the design point; in addition, high-temperature high-pressure gas generated by the detonation wave can also cause early spontaneous combustion of injected fuel oil due to returning to an air inlet channel of the pressurizing ring cavity so as to influence the combustion efficiency of the pressurizing afterburner, and in addition, the early spontaneous combustion of the injected fuel oil can also cause local temperature rise of the turbine blade; thus, both the turbine performance and life are affected by the high temperature and high pressure fuel return.
In an embodiment of the present application, the pressurized afterburner includes a blending flow passage and a pressurized annular chamber; the mixing flow passage is used for inputting an oil-gas mixture into the boosting afterburner, the boosting annular cavity is used for detonating the oil-gas mixture, detonation waves are generated after the oil-gas mixture is detonated, high-temperature and high-pressure fuel gas is formed, and the high-temperature and high-pressure fuel gas is easy to return in the mixing flow passage and the boosting annular cavity, so that the working state of a turbine can be influenced by the returned high-temperature and high-pressure fuel gas; in this application embodiment, in order to reduce the turbine receives high temperature high pressure gas's influence, booster afterburner still includes prevents the passback unit, prevent passback unit installs mixing runner with between the pressure boost ring chamber, prevent passback unit is used for controlling fluid can only pass through mixing runner orientation inflow in the pressure boost ring chamber, so, works as when the detonation wave takes place, through prevent passback unit's setting, mixing runner with the pressure boost ring chamber all possesses unidirectional circulation effect, the high temperature high pressure gas that detonation wave produced can't pass back to mixing runner or in the pressure boost ring chamber, and then avoided detonation wave passback to the influence that turbine normal operating condition led to the fact.
Further, the novel combustion engine further comprises a supercharging afterburner outer cylinder body, a supercharging annular cavity outer ring, a supercharging annular cavity inner ring and a supercharging afterburner inner cylinder body, wherein a first channel is reserved between the supercharging afterburner outer cylinder body and the supercharging annular cavity outer ring, a second channel is reserved between the supercharging afterburner inner cylinder body and the supercharging annular cavity inner ring, the supercharging annular cavity outer ring is sleeved outside the supercharging annular cavity inner ring, a main channel is formed between the supercharging annular cavity outer ring and the supercharging annular cavity inner ring, and the mixing runner, the supercharging annular cavity and the anti-return unit are all located in the main channel.
In the embodiment of the application, the combustion chamber further comprises a supercharging afterburner outer cylinder body and a supercharging afterburner inner cylinder body, wherein a first channel is reserved between the supercharging afterburner outer cylinder body and the supercharging annular cavity outer ring, and a second channel is reserved between the supercharging afterburner inner cylinder body and the supercharging annular cavity inner ring; therefore, in this embodiment of the present application, when the air flow is introduced into the first channel and the second channel, since the outer ring of the supercharging ring cavity is sleeved outside the inner ring of the supercharging ring cavity, a main channel is formed between the outer ring of the supercharging ring cavity and the inner ring of the supercharging ring cavity, and the mixing flow channel, the supercharging ring cavity and the anti-return unit are all installed in the main channel, the first channel and the second channel can radiate heat of the inner component of the main channel, so that the stability of the working state of the engine is improved.
Further, the mixing flow channel comprises a straight section and a converging section, the straight section is positioned at the inlet of the mixing flow channel, one end of the converging section is communicated with the straight section, and the other end of the converging section is gradually converged and communicated with the pressurizing annular cavity.
In this embodiment of the present application, the mixing flow channel includes a straight section and a converging section, where the straight section is located at an inlet of the mixing flow channel, one end of the converging section is communicated with the straight section, and the other end of the converging section gradually converges and is communicated with the supercharging annular cavity; in this way, the speed of the oil-gas mixture can be increased in the mixing runner through the cooperation of the converging section and the straight section, the booster afterburner can flow more oil-gas mixture in a shorter time, and the working efficiency of the booster afterburner can be improved; in addition, the flow of the oil-gas mixture in the pressurized afterburner is more stable because the straight section and the converging section reduce the pressure of the oil-gas mixture.
Further, the anti-return unit comprises an isolation section, the isolation section comprises a plurality of wedge-shaped barbs, the wedge-shaped barbs are sequentially connected and face the same direction, and the isolation section is installed in the mixing flow channel convergence section and used for inhibiting interference of pressure fluctuation in the pressurizing annular cavity to fluid flow of the mixing flow channel.
In this embodiment of the present application, the anti-return unit includes an isolation section, where the isolation section includes a plurality of wedge-shaped barbs, so that the isolation section is installed in the blending flow path convergence section, and since the wedge-shaped barbs have small obstruction to low-pressure high-temperature gas flow after the turbine flowing in the forward direction, the wedge-shaped barbs have large obstruction to high-temperature high-pressure gas flow flowing in the reverse direction; that is, through the unidirectional flow of the wedge-shaped structure to the fluid, in the embodiment of the application, through the isolation section comprising a plurality of wedge-shaped barbs, when the high-temperature and high-pressure gas generated after knocking is returned to the mixing runner, the problem that the pressure return of the detonation wave affects the turbine is restrained.
Further, the anti-return unit further comprises a tesla valve, and the tesla valve is installed at an inlet of the pressurizing annular cavity and used for inhibiting the high-temperature high-pressure gas from being returned to an air inlet end of the pressurizing annular cavity.
In the embodiment of the application, in order to realize the unidirectional conductivity of the supercharging annular cavity and avoid the excessively complex structure of the anti-return unit, the anti-return unit further comprises a tesla valve, and the tesla valve is installed at the inlet of the supercharging annular cavity; in the embodiment of the application, due to the unidirectional conductivity of the tesla valve, when the high-temperature high-pressure gas is returned to the pressurizing ring cavity, the tesla valve arranged at the inlet of the pressurizing ring cavity can inhibit the return of the high-temperature high-pressure gas, so that the reduction of the turbine pressure drop ratio caused by the pressure return of the high-temperature high-pressure gas after knocking is inhibited; in addition, the suppression of the return of the high-temperature high-pressure fuel also avoids the problems of early spontaneous combustion of the fuel and affected temperature of turbine blades, and the combustion efficiency of the booster afterburner and the turbine performance are improved.
Further, the tesla valve comprises a plurality of tesla valve unit bodies, and the tesla valve unit bodies are sequentially connected and axially distributed along the axis of the pressurizing annular cavity; the Tesla valve unit body comprises secondary flow channels and primary flow channels, and the secondary flow channels are matched with and communicated with the primary flow channels one by one.
In this embodiment of the present application, the tesla valve includes a plurality of tesla valve units, where the tesla valve includes a plurality of secondary flow channels and a plurality of primary flow channels, and the plurality of primary flow channels are in one-to-one paired communication with the plurality of secondary flow channels and form a plurality of tesla valve units; in the embodiment of the application, in order to avoid that high-temperature and high-pressure fuel gas flows through the tesla valve, the tesla valve unit bodies are improperly arranged, so that the high-temperature and high-pressure fuel gas can still be returned in the pressurizing ring cavity, and the tesla valve unit bodies are sequentially connected and axially distributed along the axis of the pressurizing ring cavity.
Further, a runner selection valve capable of opening or closing an air inlet runner of the blending runner is arranged at the inlet of the blending runner.
In an embodiment of the present application, in order to adapt to different working states of the engine, the booster afterburner further includes a runner selector valve, where the runner selector valve is located at an inlet of the blending runner and is used to open or close an intake flow path of the blending runner; therefore, under different states of the engine, the supercharging afterburner can realize adjustment of different working states through switching of the runner selector valve on the air inlet flow path so as to adapt to different working states of the engine, and therefore the working stability of the engine is improved.
In summary, compared with the prior art, the invention has the following beneficial effects: the device comprises an isolation section for inhibiting high-temperature high-pressure gas return to cause the turbine to reduce the pressure drop ratio and further influence the output power of the turbine, and a Tesla valve for inhibiting the high-temperature high-pressure gas return to the inlet runner of the supercharging annular cavity to cause early spontaneous combustion of injected fuel to influence the working efficiency of a combustion chamber; in addition, through the arrangement of the isolation section and the Tesla valve between the mixing flow passage and the pressurizing annular cavity, the problem of performance and service life reduction of the turbine caused by the fact that the temperature of the returned high-temperature high-pressure gas influences the temperature of the blades to be not in accordance with a design value is also restrained; in this way, for the supercharged afterburner in the present application, the turbine is less affected by the high temperature and high pressure gas, and the operation performance of the small turbojet engine is ensured.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention. In the drawings:
FIG. 1 is a schematic view of a pressurized afterburner in accordance with the present invention;
FIG. 2 is a schematic view of a wedge barb of an isolated segment in accordance with the present invention;
FIG. 3 is a schematic diagram of the forward flow of gas in a Tesla valve of the present invention;
FIG. 4 is a schematic diagram of the reverse flow of gas in a Tesla valve of the present invention;
FIG. 5 is a schematic diagram of a Tesla valve unit according to the present invention;
FIG. 6 is a schematic view of a turbo mode of operation of the supercharged afterburner of the present invention;
FIG. 7 is a schematic illustration of a boost afterburner boost operating mode in accordance with the present invention;
and → represents the gas trend.
The names corresponding to the reference numerals are: 1. a blending flow channel; 2. an isolation section; 3. a tesla valve; 4. pressurizing the annular cavity; 5. pressurizing the outer ring of the annular cavity; 6. pressurizing the ring cavity inner ring; 7. a pressurized afterburner chamber cylinder; 8. a cylinder in the pressurized afterburner; 9. a flow passage selector valve; 10. an air collection cavity; 11. a deflector; 12. an outer oil screen; 13. an inner oil baffle; 14. a fuel injection rod; 15. initiating an electric nozzle; 16. a pneumatic plug nozzle; 17. an inner cone; 21. wedge-shaped barbs; 31. a tesla valve inlet; 32. a tesla valve outlet; 33. an inlet flow passage; 34. a secondary flow passage; 35. a main flow passage; 36. an outlet flow passage; 37. tesla valve unit body.
Detailed Description
For the purpose of making apparent the objects, technical solutions and advantages of the present invention, the present invention will be further described in detail with reference to the following examples and the accompanying drawings, wherein the exemplary embodiments of the present invention and the descriptions thereof are for illustrating the present invention only and are not to be construed as limiting the present invention.
Examples:
as shown in fig. 1 to 7, in this embodiment, the mixing flow channel 1 and the pressurizing ring cavity 4 are included, after the mixing flow channel 1 inputs the oil-gas mixture into the pressurizing ring cavity 4, the oil-gas mixture is detonated in the pressurizing ring cavity 4, the gas mixture forms a detonation wave and generates high-temperature and high-pressure gas, the high-temperature and high-pressure gas with huge energy expands vigorously in the pressurizing ring cavity 4, and the severely expanded high-temperature and high-pressure gas generates pressure fluctuation higher than that of the mixing flow channel 1 in the pressurizing ring cavity 4. When the high-temperature high-pressure gas returns, the turbine pressure drop ratio is easy to reduce, so that the turbine performance is reduced, and in addition, the high-temperature high-pressure gas fuel is easy to lead the fuel to be spontaneously combusted in advance during the returning due to the higher temperature, so that the combustion efficiency of the booster afterburner is reduced; in this way, in this embodiment, in order to avoid the influence of the returned high-temperature high-pressure gas on the operation of the turbine, the return of the high-temperature high-pressure gas needs to be suppressed; therefore, the boosting afterburner further comprises an anti-return unit, wherein the anti-return unit is positioned at the joint of the mixing flow channel (1) and the boosting annular cavity (4) and is used for controlling fluid to be only transmitted into the boosting annular cavity (4) through the mixing flow channel 1, so that the communicated mixing flow channel 1 and the boosting annular cavity (4) can be similar to a unidirectional channel; through the setting of preventing the passback unit, the high temperature high pressure gas that produces after the fluid detonates can't passback, has avoided because the high temperature high pressure gas passback causes the influence to the turbine to engine operating condition's stability has also realized improving.
In this embodiment, in order to improve the stability of each component in the boost afterburner, the engine further comprises a boost afterburner outer cylinder 7, a boost annular cavity outer ring 5, a boost annular cavity inner ring 6 and a boost afterburner inner cylinder 8, wherein a first channel is reserved between the boost afterburner outer cylinder 7 and the boost annular cavity outer ring 5, a second channel is reserved between the boost afterburner inner cylinder 8 and the boost annular cavity inner ring 6, the boost annular cavity outer ring 5 is sleeved outside the boost annular cavity inner ring 6, and a main channel is formed between the boost annular cavity outer ring 5 and the boost annular cavity inner ring 6. In addition, in the present embodiment, a baffle 11 and a pneumatic plug nozzle 16 are also included; thus, in this embodiment, after the air flows through the baffle 11, the air flows are input into the first channel and the second channel on the basis of flowing into the main channel. In this way, since the mixing runner 1, the pressurizing ring cavity 4 and the anti-return unit are all located in the main channel, the first channel and the second channel can realize heat dissipation of all components located in the main channel, and the working stability of the pressurizing afterburner can be improved. In addition, the exhaust end of the second passage may be connected to the air plug nozzle 16, so that the air flow of the second passage, after the cooling operation is completed, may be exhausted through the air plug nozzle 16 and further power the engine.
In this embodiment, in order to achieve sufficient detonation of the oil-gas mixture in the pressurizing ring cavity 4, the height of the pressurizing ring cavity 4 may be 5mm, and the length may be 200mm. Furthermore, in the present embodiment, the mixing flow path 1 as the input oil-gas mixture passage includes a converging section and a straight section, the straight section being located at the inlet of the mixing flow path 1, one end of the converging section being in communication with the straight section, and the other end thereof being gradually converging and being in communication with the supercharging annular chamber 4. In this way, the oil-gas mixture can be increased in speed in the mixing channel 1 by the cooperation of the converging section and the straight section, while the pressure of the oil-gas mixture is reduced. In this embodiment, when the oil-gas mixture flows through the mixing runner 1, the speed of the oil-gas mixture increases and the pressure decreases after passing through the straight section and the converging section; thus, the oil-gas mixture can flow to the pressurizing ring cavity 4 more quickly and smoothly.
In this embodiment, the anti-return unit includes an isolation section 2, where the isolation section 2 is disposed in the mixing flow channel 1, and in order to further avoid the influence of the high temperature and high pressure gas return on the turbine, the isolation section 2 may be disposed in the convergence section of the mixing flow channel 1 and used to inhibit the interference of the pressure fluctuation in the supercharging annular cavity 4 on the fluid flow of the mixing flow channel 1; in addition, the isolating section 2 comprises a plurality of wedge-shaped barbs 21, and the wedge-shaped barbs 21 are sequentially connected and face the same direction, so that the isolating section 2 can more accurately inhibit the return of the high-temperature high-pressure fuel gas; in this embodiment, in order to effectively inhibit the return of the high-temperature and high-pressure fuel gas by the isolation section 2, the number of the wedge-shaped barbs 21 may be 4, the width w of the wedge-shaped barbs 21 may be 1/12 of the diameter of the outer ring 5 of the pressurizing ring cavity, the height h may be 1/12 of the diameter of the outer ring 5 of the pressurizing ring cavity, and the inclination angle α may be 60 °. In this way, when the low-pressure high-temperature fuel gas after the turbine flows forward through the wedge-shaped barb 21, the wedge-shaped barb 21 has little obstruction to the flow of the low-pressure high-temperature fuel gas flowing forward through the wedge-shaped structure of the wedge-shaped barb 21, and the low-pressure high-temperature fuel gas can smoothly pass through the isolation section 2; when the high-pressure high-temperature fuel gas generated after knocking flows back through the wedge-shaped barb 21 in the reverse direction, the high-temperature high-pressure fuel gas is influenced by the wedge-shaped barb 21 to have large flow obstruction and pressure loss, namely the high-pressure high-temperature fuel gas cannot smoothly pass through the isolation section 2, so that the isolation section 2 can effectively inhibit the high-temperature high-pressure fuel gas pressure back.
In this embodiment, the anti-return unit further comprises a tesla valve 3, the tesla valve 3 being mounted at the inlet of the pressurizing ring cavity 4; in this way, when the high-temperature and high-pressure gas generated by the detonation wave is returned, the return of the high-temperature and high-pressure gas is suppressed due to the unidirectional flow of the tesla valve 3. In this embodiment, the tesla valve 3 further includes a tesla valve inlet 31, a tesla valve outlet 32, an inlet flow channel 33, a secondary flow channel 34, a main flow channel 35, and an outlet flow channel 36, where the main flow channel 35 and the secondary flow channel 34 are paired to form a tesla valve unit 37; in order to enable the tesla valve 3 to achieve the effect of inhibiting the high-temperature high-pressure gas from returning, the tesla valve 3 comprises a plurality of tesla valve unit bodies 37, and the tesla valve unit bodies 37 are axially arranged along the axis of the pressurizing annular cavity 4; one of the application scenarios of this embodiment is a small turbojet engine booster combustor, so that the number of tesla valve units 37 can be 4, the diameter Φ of the blunt body of the tesla valve units 37 can be 1/3 of the height of the annular cavity, the included angle β of the blunt body can be 15 °, and the flow channel width L of the primary flow channel 35 and the secondary flow channel 34 of the tesla valve units 37 can be 1/4 of the diameter Φ of the blunt body. Thus, when the low-pressure high-temperature gas after the turbine positively flows into the tesla valve 3 from the tesla valve inlet 31, the low-pressure high-temperature gas after the turbine enters the tesla valve 3 through the inlet flow passage 33 and is split into the main flow passage 35 and the secondary flow passage 34, but because the included angle between the secondary flow passage 34 and the inlet flow passage 33 is large enough and the secondary flow passage 34 has a bend, the flow rate of the low-pressure high-temperature gas after the turbine flowing into the main flow passage 35 is much larger than the flow rate of the low-pressure high-temperature gas after the turbine flowing into the secondary flow passage 34; when the low-pressure high-temperature gas after the turbine merges in the outlet flow passage 36, the flowing-out gas included angle between the main flow passage 35 and the secondary flow passage 34 is small enough, so that the flow of the fluid in the secondary flow passage 34 hardly hinders the flow of the fluid in the main flow passage 35; when the high-temperature high-pressure gas generated by the detonation wave reversely flows into the tesla valve 3 and flows in through the tesla valve outlet 32, the high-temperature high-pressure gas is split into the main runner 35 and the secondary runner 34 in the outlet runner 36, and the included angle between the secondary runner 34 and the outlet runner 36 is small enough, so that the flow in the secondary runner 34 is equivalent to the flow in the main runner 35; when the high-temperature high-pressure gas merges in the inlet flow passage 33, the flow of the fluid in the secondary flow passage 34 may greatly block the flow of the fluid in the primary flow passage 35 because the included angle between the primary flow passage 35 and the gas flowing out of the secondary flow passage 34 is large. In this way, in the present embodiment, the pressurizing annular chamber 4 provided with the tesla valve 3 is approximately a channel with only one-way conductivity, so that the return of the detonation wave is suppressed, and the influence degree of the turbine by the returned high-temperature high-pressure gas is correspondingly reduced.
In this embodiment, the boost afterburner applied to the system further comprises a flow passage selector valve 9, wherein the flow passage selector valve 9 is positioned at the inlet of the blending flow passage 1 and is used for opening or closing the air inlet flow passage of the blending flow passage 1, so that the working mode of the boost afterburner is changed through the arrangement of different air inlet flow passages of the blending flow passage 1, and the boost afterburner can be more accurately adapted to different working states of an engine. In this embodiment, the pressurizing afterburner applied by the system further comprises an air collecting cavity 10, an outer oil baffle 12, an inner oil baffle 13, an oil injection rod 14, an inner cone 17 and a detonation electric nozzle 15; when the flow path selection valve 9 is operated to change the intake flow path of the blending flow path 1 in the booster afterburner, when the flow path selection valve 9 is closed, the air flow is only input through the inner cone 17 as the problem of the return of the detonation wave no longer needs to be considered when the booster afterburner is in turbine operation mode. When the flow passage selector valve 9 is opened, the air flow is introduced into the first passage, the second passage and the main flow passage; at this time, the booster combustor is in a booster combustion mode, the air flow is guided by the guide plate 11, and meanwhile, the operation of inputting the oil-gas mixture into the mixing runner 1 is realized by the air collecting cavity 10 which can realize circumferential rectification on the air flow, the outer oil baffle 12 which can prevent fuel from splashing, the inner oil baffle 13 and the oil injection rod 14 which can provide fuel, when the oil-gas mixture enters the mixing runner 1, the oil-gas mixture firstly enters the straight section of the mixing runner 1 and then enters the convergent section, so that the speed of the oil-gas mixture is increased, and meanwhile, the pressure of the oil-gas mixture is reduced, and when the oil-gas mixture input by the mixing runner 1 works through the detonation electric nozzle 15, the detonation of the oil-gas mixture in the detonation electric nozzle 15 is also more smoothly progressed, the detonation wave is formed by the detonation of the oil-gas mixture in the pressurizing ring cavity 4, and the high-temperature high-pressure air flow after the combustion reaction passes through the channel selector valve 9, the booster combustion cylinder 7, the booster piston cylinder 8 and the second booster piston cylinder 16, and the high-pressure expansion type jet pipe 16 are formed by the booster piston cylinder; in addition, when the high-temperature high-pressure fuel gas flows through the pressurizing ring cavity 4, the Tesla valve 3 arranged at the inlet of the pressurizing ring cavity 4 has an approximately unidirectional flow effect on the high-temperature high-pressure fuel gas, so that on one hand, the influence of the high-temperature high-pressure fuel gas pressure return on the turbine drop pressure ratio is inhibited, and on the other hand, the high Wen Huichuan of the high-temperature high-pressure fuel gas generated by the detonation wave is inhibited from flowing into the mixing runner 1, thereby avoiding the occurrence of the problem of spontaneous combustion of injected fuel oil in advance; meanwhile, the isolation section 2 arranged at the convergence section of the mixing runner 1 can also inhibit the pressure return of the detonation wave through the wedge-shaped barbs 21 with the same orientation, so that the problem that the turbine is disturbed due to the reduction of the pressure drop ratio of the turbine is avoided.
The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the invention, and is not meant to limit the scope of the invention, but to limit the invention to the particular embodiments, and any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (7)
1. The turbine stress application matching system of the small turbojet engine supercharging afterburner comprises a mixing runner (1) and a supercharging annular cavity (4), and is characterized in that the mixing runner (1) is communicated with the supercharging annular cavity (4), an anti-return unit is arranged at the joint of the mixing runner (1) and the supercharging annular cavity (4), and the anti-return unit is used for controlling fluid to directionally flow into the supercharging annular cavity (4) through the mixing runner (1).
2. The turbine afterburner matching system for the small turbojet engine according to claim 1, further comprising a booster afterburner outer cylinder (7), a booster annular cavity outer ring (5), a booster annular cavity inner ring (6) and a booster afterburner inner cylinder (8), wherein a first channel is reserved between the booster afterburner outer cylinder (7) and the booster annular cavity outer ring (5), a second channel is reserved between the booster afterburner inner cylinder (8) and the booster annular cavity inner ring (6), the booster annular cavity outer ring (5) is sleeved outside the booster annular cavity inner ring (6), a main channel is formed between the booster annular cavity outer ring (5) and the booster annular cavity inner ring (6), and the mixing flow channel (1), the booster annular cavity (4) and the anti-return unit are all positioned in the main channel.
3. Turbine boost matching system of a small turbojet engine boost afterburner according to claim 1, characterized in that said mixing channel (1) comprises a straight section at the inlet of said mixing channel (1) and a converging section with one end communicating with said straight section and with the other end gradually converging and communicating with said boost ring cavity (4).
4. A turbine boost matching system of a small turbojet engine boost afterburner according to claim 3, characterized in that said anti-return unit comprises an isolation section (2), said isolation section (2) comprising a number of wedge-shaped barbs (21), a number of said wedge-shaped barbs (21) being connected in sequence and oriented in correspondence, said isolation section (2) being mounted in the converging section of said mixing channel (1) and being adapted to suppress the disturbance of the pressure fluctuation in said boost ring cavity (4) to the fluid flow of said mixing channel (1).
5. A turbo-boost matching system for a pressurized afterburner of a small turbojet engine according to any one of claims 1 to 4, wherein said anti-backhauling unit further comprises a tesla valve (3), said tesla valve (3) being mounted at the inlet of said pressurized annular chamber (4) and being adapted to inhibit the backhauling of said high temperature and high pressure gases to the inlet end of said pressurized annular chamber (4).
6. A turbo-boost matching system of a small turbojet engine boost afterburner according to claim 5, characterized in that said tesla valve (3) comprises several tesla valve units (37), several of said tesla valve units (37) being connected in sequence and distributed axially along the axis of said boost ring cavity (4);
the Tesla valve unit body (37) comprises a secondary runner (34) and a main runner (35), and the secondary runner (34) is matched with and communicated with the main runner (35) one by one.
7. Turbine boost matching system for a small turbojet engine boost afterburner according to claim 1, characterized in that a runner selection valve (9) is provided at the inlet of the blending runner (1) capable of opening or closing the intake runner of the blending runner (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310717595.1A CN116537953A (en) | 2023-06-16 | 2023-06-16 | Turbine afterburner matching system of small turbojet engine booster afterburner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310717595.1A CN116537953A (en) | 2023-06-16 | 2023-06-16 | Turbine afterburner matching system of small turbojet engine booster afterburner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116537953A true CN116537953A (en) | 2023-08-04 |
Family
ID=87452648
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310717595.1A Pending CN116537953A (en) | 2023-06-16 | 2023-06-16 | Turbine afterburner matching system of small turbojet engine booster afterburner |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116537953A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117738816A (en) * | 2024-02-19 | 2024-03-22 | 北京大学 | Array type back pressure resistant injection structure of continuous detonation engine |
| CN117759453A (en) * | 2024-02-22 | 2024-03-26 | 北京大学 | Continuous detonation ramjet engine capable of inhibiting pressure back transmission |
-
2023
- 2023-06-16 CN CN202310717595.1A patent/CN116537953A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117738816A (en) * | 2024-02-19 | 2024-03-22 | 北京大学 | Array type back pressure resistant injection structure of continuous detonation engine |
| CN117738816B (en) * | 2024-02-19 | 2024-04-26 | 北京大学 | Array type back pressure resistant injection structure of continuous detonation engine |
| CN117759453A (en) * | 2024-02-22 | 2024-03-26 | 北京大学 | Continuous detonation ramjet engine capable of inhibiting pressure back transmission |
| CN117759453B (en) * | 2024-02-22 | 2024-05-07 | 北京大学 | Continuous detonation ramjet engine capable of inhibiting pressure back transmission |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2958286C (en) | Torch igniter | |
| CN116537953A (en) | Turbine afterburner matching system of small turbojet engine booster afterburner | |
| JP6262986B2 (en) | Combustion turbine engine fuel injection assembly | |
| CN108019775B (en) | Compact hybrid fuel nozzle assembly with mixing sleeve | |
| CN112902225B (en) | Multistage afterburning chamber with outer ring rotary detonation supercharged combustion chamber | |
| JP6708380B2 (en) | Combustion turbine engine fuel injector assembly | |
| CN109028142B (en) | Propulsion system and method of operating the same | |
| US10228137B2 (en) | Dual fuel nozzle with swirling axial gas injection for a gas turbine engine | |
| US6928804B2 (en) | Pulse detonation system for a gas turbine engine | |
| US10794596B2 (en) | Dual fuel nozzle with liquid filming atomization for a gas turbine engine | |
| EP3250856B1 (en) | Fuel injector including a lobed mixer and vanes for injecting alternate fuels in a gas turbine | |
| RU2570480C2 (en) | Mixing of diluting air in gas turbine sequential combustion system | |
| CN113154458B (en) | Continuous rotation detonation combustion chamber and ramjet | |
| JP5814651B2 (en) | Ejector purge of the cavity adjacent to the exhaust flow path | |
| CN108870441B (en) | Afterburner adopting circular arc fan-shaped nozzle and concave cavity structure | |
| CN112503571A (en) | Afterburner structure of combined flame stabilizer and control method | |
| CN111520749A (en) | Preheating type double-oil-way opposite-impact type annular combustion chamber structure | |
| CN115342382A (en) | Single-channel oxygen supply detonation combustion chamber module and detonation combustion chamber | |
| CN114877378A (en) | Inner ring detonation combustion chamber | |
| US8991189B2 (en) | Side-initiated augmentor for engine applications | |
| EP3486570B1 (en) | Second-stage combustor for a sequential combustor of a gas turbine | |
| CN111520766A (en) | Radial grading detonation afterburner | |
| JPH0583814B2 (en) | ||
| CN112066414A (en) | Combustion chamber, gas turbine and method for suppressing oscillatory combustion | |
| CN117145632A (en) | Kerosene/liquid methane external parallel turbine-based rotary detonation engine |
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 |