CN116772235A - Method for conveying and injecting powder fuel of outer duct of turbofan engine - Google Patents
Method for conveying and injecting powder fuel of outer duct of turbofan engine Download PDFInfo
- Publication number
- CN116772235A CN116772235A CN202310750435.7A CN202310750435A CN116772235A CN 116772235 A CN116772235 A CN 116772235A CN 202310750435 A CN202310750435 A CN 202310750435A CN 116772235 A CN116772235 A CN 116772235A
- Authority
- CN
- China
- Prior art keywords
- powder
- powder fuel
- venturi
- engine
- turbofan engine
- 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
- 239000000446 fuel Substances 0.000 title claims abstract description 78
- 239000000843 powder Substances 0.000 title claims abstract description 76
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000007789 sealing Methods 0.000 claims abstract description 4
- 238000009792 diffusion process Methods 0.000 claims description 6
- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 4
- 239000002245 particle Substances 0.000 claims description 4
- 230000008602 contraction Effects 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 description 10
- 239000007789 gas Substances 0.000 description 8
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000005243 fluidization Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000005514 two-phase flow Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/26—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being solid or pulverulent, e.g. in slurry or suspension
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Air Transport Of Granular Materials (AREA)
Abstract
The invention relates to a method for conveying and injecting powder fuel of an outer duct of a turbofan engine, which comprises an air guide pipe, an annular powder fuel storage bin and a powder suction device; the air entraining pipe is arranged on the outer side of the engine casing, the air entraining pipe is communicated with the outer duct of the turbofan engine and the annular powder fuel storage bin, air flow of the outer duct of the turbofan engine is led into the annular powder fuel storage bin, the internal air pressure of the annular powder fuel storage bin is balanced, and the air entraining pipe is subjected to sealing treatment at the joint. The invention utilizes the high-speed air flow of the outer duct of the turbofan engine, and can realize the mixing and ejection of the powder fuel and the gas without an additional power source.
Description
Technical Field
The invention belongs to the technical field of aviation power, and particularly provides a method for conveying and injecting powder fuel of an outer duct of a turbofan engine.
Background
To increase engine thrust output, enhance the performance of military fighter aircraft, afterburners may be added between the jet turbine and the tail nozzle. The method utilizes the fuel gas flowing out from the main combustion chamber to carry out secondary combustion on the rest oxygen and the injected fuel oil in the afterburner, thereby enhancing the thrust output of the engine. Because the turbine still has high temperature, the injected fuel is quickly ignited and quickly combusted, and expansion work is performed to generate thrust. However, the oxygen content of the gas flowing out of the main combustion chamber is low, the flow rate of the gas is high, the fuel combustion of the afterburner is insufficient, the combustion efficiency is low, the oil consumption is too high when the afterburner is started, and the air combat time of the fighter aircraft is reduced.
It can be seen that improving the combustion efficiency in afterburning is a key to ensuring the cruising performance of the aircraft. In order to solve the problems, on one hand, the afterburner structure is optimized, for example, a concave cavity structure is adopted, and a stable vortex structure is generated to promote the mixing of fuel and air while a low-speed area is formed; on the other hand, the fuel with higher combustion heat value is used to replace the existing fuel. Compared with fuel oil, the powder fuel has the characteristics of high energy heat value and volume heat value, convenience in transportation and storage, low cost and the like. The powder fuel has good gas-solid two phases after fluidization, and can be more easily combusted in a gas turbine. In addition, the oxidant of the powder fuel is rich in variety, and other byproducts in the gas after the turbine can also be used as the oxidant (such as magnesium powder, carbon dioxide, aluminum powder and water vapor) of the powder fuel. Therefore, the powder fuel is widely used in the military and aviation fields to improve the performance and the superiority of the equipment.
The use of pulverized fuel requires consideration of a range of problems associated with its storage, supply and injection. For aircraft engines, it is desirable to select suitable powder fuel delivery and injection methods, while considering methods to reduce dust and other emissions nuisance. The key points for realizing the transportation and injection of the powder fuel are as follows: firstly, mixing powder with gas to form a gas-solid two-phase flow; and secondly, uniformly injecting the gas-solid two phases into the afterburner. Therefore, two key points are fully considered when designing a powder fuel delivery and injection method suitable for an aeroengine, so that the existing space of the engine is utilized in practical application, and the powder supply process is stable and reliable.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a method for conveying and injecting powder fuel of an outer duct of a turbofan engine, and the device can realize the mixing and the ejection of the powder fuel and the gas by utilizing high-speed airflow of the outer duct of the turbofan engine without an additional power source.
The invention is realized by the following technical scheme.
A method for conveying and injecting powder fuel of an outer duct of a turbofan engine comprises an air guide pipe, an annular powder fuel storage bin and a powder suction device;
the air-entraining pipe is arranged at the outer side of the engine casing, the air-entraining pipe is communicated with the outer duct of the turbofan engine and the annular powder fuel storage bin, the air flow of the outer duct of the turbofan engine is introduced into the annular powder fuel storage bin, the internal air pressure of the annular powder fuel storage bin is balanced, and the air-entraining pipe is subjected to sealing treatment at the joint;
the powder sucking devices are uniformly distributed in 4-8 sets along the circumferential direction of the engine casing, each set of powder sucking device comprises a valve, a conveying pipe and a venturi tube, each venturi tube comprises a contraction section, a throat and a diffusion section, the venturi tubes are arranged on the inner side of the engine casing, the conveying pipe penetrates through the engine casing to communicate an annular powder fuel storage bin with the throat of each venturi tube, the valves are arranged on the conveying pipe, the valves of each set of powder sucking device are independently controlled, and the flow of powder fuel can be controlled by adjusting the position of a valve rod of the valve;
when the air flow of the outer duct flows through the venturi constriction section, the air flow is accelerated, and when the accelerated high-speed air flow flows through the venturi throat, the high-speed air flow at the venturi throat can generate low pressure nearby according to the venturi effect, so that powder fuel stored in the annular powder fuel storage bin is sucked out through the conveying pipe, powder fuel particles are fully mixed with the high-speed air flow when flowing through the venturi diffusion section, and finally the powder fuel particles are ejected from the rear end of the venturi in the form of fluidized powder and flow into the afterburner to participate in afterburning.
Further, the annular pulverized fuel reservoir is an annular cavity disposed outside the engine case (), which is a cavity for storing pulverized fuel.
Further, the venturi is disposed within the turbofan engine outer duct.
Further, the turbofan engine comprises an engine rotor and an engine casing.
Compared with the prior art, the invention has the advantages that:
(1) The device utilizes the high-speed air flow of the outer duct of the turbofan engine, and can realize the mixing and the ejection of the powder fuel and the gas without an additional power source.
(2) The design of the external annular bin also makes the storage space of the powder fuel larger and more free.
(3) The venturi-based pulverized fuel suction device utilizes a venturi effect to efficiently suck pulverized fuel stored in an annular pulverized fuel reservoir by a low pressure generated nearby when a high-speed gas flows through a throat of the venturi.
(4) The powder fuel is used as the fuel of the afterburner, so that the oxygen content requirement of the traditional liquid fuel in the combustion process is reduced, the influence of low propulsion efficiency caused by insufficient combustion of the traditional fuel in the afterburner is further reduced, and the oil consumption is effectively reduced. Meanwhile, the combustion heat value of the powder fuel is higher than that of the fuel, so that the temperature of the afterburner can be greatly increased, and the effective thrust of the engine can be effectively increased.
Drawings
FIG. 1 is a schematic cross-sectional view of the general arrangement of the present invention;
FIG. 2 is a three-dimensional schematic of the present invention;
FIG. 3 is a schematic cross-sectional view of the present invention;
fig. 4 is a schematic partial cross-sectional view of the present invention.
The names corresponding to the reference numerals in the drawings are: 1-engine rotor parts, 2-engine casings, 3-induced air pipes, 4-annular powder fuel storage bins, 5-valves, 6-conveying pipes, 7-venturi pipes, 701-venturi pipe constriction sections, 702-venturi pipe throats and 703-venturi pipe expansion sections.
Detailed Description
The invention is further described below with reference to the drawings and specific examples, which are not intended to be limiting.
As shown in fig. 1 to 4, the method for conveying and injecting the powder fuel of the outer duct of the turbofan engine comprises an air guide pipe 3, an annular powder fuel storage bin 4 and a powder suction device;
the air entraining pipe 3 is arranged at the outer side of the engine case 2, the air entraining pipe 3 is communicated with an outer duct of the turbofan engine and the annular powder fuel storage bin 4, air flow of the outer duct of the turbofan engine is introduced into the annular powder fuel storage bin 4, the internal air pressure of the annular powder fuel storage bin 4 is balanced, and the air entraining pipe 3 is subjected to sealing treatment at a joint;
the powder sucking devices are uniformly distributed in 4-8 sets along the circumferential direction of the engine casing 2, each set of powder sucking device comprises a valve 5, a conveying pipe 6 and a venturi tube 7, each venturi tube 7 comprises a contraction section 701, a throat 702 and a diffusion section 703, the venturi tubes 7 are arranged on the inner side of the engine casing 2, the conveying pipe 6 penetrates through the engine casing 2 to communicate an annular powder fuel storage bin 4 with the throat 702 of the venturi tube, the valves 5 are arranged on the conveying pipe 6, the valves 5 of each set of powder sucking device are independently controlled, the flow of powder fuel can be controlled by adjusting the position of a valve rod of the valve 5, and the total output quantity of powder can be regulated and controlled;
when the air flow of the outer duct flows through the venturi constriction 701, the air flow is accelerated, and when the accelerated high-speed air flow flows through the venturi throat 702, the high-speed air flow at the venturi throat 702 can generate low pressure nearby according to the venturi effect, so that the powder fuel stored in the annular powder fuel storage bin 4 is sucked out through the conveying pipe 6, and the powder fuel particles are fully mixed with the high-speed air flow when flowing through the venturi diffusion 703, and finally are ejected from the rear end of the venturi 7 in the form of fluidized powder, and flow into the afterburner to participate in afterburning.
Further, the annular pulverized fuel reservoir 4 is an annular cavity disposed outside the engine case (2), and is a cavity for storing pulverized fuel.
Further, the venturi 7 is arranged in the turbofan engine outer duct.
Further, the turbofan engine comprises an engine rotor 1 and an engine casing 2.
The foregoing description is only illustrative of the preferred embodiments of the present invention and is not to be construed as limiting the scope of the invention, and it will be appreciated by those skilled in the art that equivalent substitutions and obvious variations may be made using the description and illustrations of the present invention, and are intended to be included within the scope of the present invention.
Claims (4)
1. The method for conveying and injecting the powder fuel of the outer duct of the turbofan engine is characterized by comprising an air guide pipe (3), an annular powder fuel storage bin (4) and a powder suction device;
the air entraining pipe (3) is arranged at the outer side of the engine case (2), the air entraining pipe (3) is communicated with an outer duct of the turbofan engine and the annular powder fuel storage bin (4), air flow of the outer duct of the turbofan engine is introduced into the annular powder fuel storage bin (4), the internal air pressure of the annular powder fuel storage bin (4) is balanced, and the air entraining pipe (3) is subjected to sealing treatment at a joint;
the powder sucking devices are uniformly distributed in 4-8 sets along the circumferential direction of the engine casing (2), each set of powder sucking device comprises a valve (5), a conveying pipe (6) and a venturi tube (7), each venturi tube (7) comprises a contraction section (701), a throat (702) and a diffusion section (703), the venturi tubes (7) are arranged on the inner side of the engine casing (2), the conveying pipe (6) penetrates through the engine casing (2) to communicate an annular powder fuel storage bin (4) with the throat (702) of the venturi tube, the valves (5) are arranged on the conveying pipe (6), the valves (5) of each set of powder sucking device are independently controlled, and the flow of powder fuel can be controlled by adjusting the position of the valve rod of the valve (5);
when the air flow of the outer duct flows through the venturi constriction section (701), the air flow is accelerated, and when the accelerated high-speed air flow flows through the venturi throat (702), the high-speed air flow at the venturi throat (702) can generate low pressure nearby according to the venturi effect, so that powder fuel stored in the annular powder fuel storage bin (4) is sucked out through the conveying pipe (6), powder fuel particles are fully mixed with the high-speed air flow when flowing through the venturi diffusion section (703), and finally the powder fuel is sprayed out from the rear end of the venturi (7) in the form of fluidized powder and flows into the afterburner to participate in afterburning.
2. A method of transportation and injection of a turbofan engine external duct pulverized fuel according to claim 1, characterized in that the annular pulverized fuel reservoir (4) is an annular cavity arranged outside the engine casing (2) and is a cavity for storing pulverized fuel.
3. A turbofan engine external duct pulverized fuel delivery and injection method according to claim 1, characterized in that the venturi (7) is arranged in the turbofan engine external duct.
4. The method for conveying and injecting the powder fuel of the outer duct of the turbofan engine according to claim 1, wherein the turbofan engine comprises an engine rotor (1) and an engine casing (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310750435.7A CN116772235A (en) | 2023-06-25 | 2023-06-25 | Method for conveying and injecting powder fuel of outer duct of turbofan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310750435.7A CN116772235A (en) | 2023-06-25 | 2023-06-25 | Method for conveying and injecting powder fuel of outer duct of turbofan engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116772235A true CN116772235A (en) | 2023-09-19 |
Family
ID=88007637
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310750435.7A Pending CN116772235A (en) | 2023-06-25 | 2023-06-25 | Method for conveying and injecting powder fuel of outer duct of turbofan engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116772235A (en) |
-
2023
- 2023-06-25 CN CN202310750435.7A patent/CN116772235A/en active Pending
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