CN110761898B - Device for generating super-enthalpy detonation by utilizing micro-scale spiral channel - Google Patents
Device for generating super-enthalpy detonation by utilizing micro-scale spiral channel Download PDFInfo
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- CN110761898B CN110761898B CN201910912786.7A CN201910912786A CN110761898B CN 110761898 B CN110761898 B CN 110761898B CN 201910912786 A CN201910912786 A CN 201910912786A CN 110761898 B CN110761898 B CN 110761898B
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- detonation
- spiral
- spiral channel
- channel
- combustion chamber
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- 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
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
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- 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
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
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- 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
- F02C3/22—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 gaseous at standard temperature and pressure
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
Abstract
The invention discloses a device for generating detonation by utilizing a microscale spiral pipeline, which comprises: a substrate with a cross-sectional dimension of 1-10mm extending from the center on the upper surface2The spiral channel, the spiral channel locates at one end of the centre of the base plate and has air intake and ignition channels, the other end of the spiral channel has exhaust and pressure measuring channels; the cover plate is attached to the upper surface of the substrate and seals the spiral channel to form a spiral combustion chamber. The detonation device provided by the invention utilizes the microscale spiral pipeline to create a condition easier to detonate, ensures that the detonation is more stable on the premise of shortening the detonation time, has the characteristics of small volume and strong portability, can be moved and applied to various occasions needing energy supply, and can generate high-temperature and high-speed airflow which can be directly used for power propulsion and also can be combined with a gas turbine and a generator to output electric power.
Description
Technical Field
The invention relates to the technical field of detonation and combustion, in particular to a device for generating super-enthalpy detonation by utilizing a microscale spiral channel.
Background
Detonation combustion is a combustion mode similar to constant volume combustion, and is characterized by extremely high flame propagation speed, self-pressurization, high thermal cycle efficiency and the like, so that an engine utilizing the detonation combustion mode has higher efficiency compared with an engine adopting slow combustion. In the future advanced propulsion mode of aerospace vehicles, detonation combustion mode engines are a very ideal choice. It is very difficult to control detonation combustion in an engine due to the fact that the flame has a propagation speed of the order of kilometers per second, and the mode of pulse detonation is a relatively easy control implementation scheme. However, the actual performance of the pulse detonation engine at the present stage has a considerable difference from a theoretical target value, mainly because the frequency of the pulse detonation is difficult to increase, and the high-frequency stable power output is difficult to realize.
Among the factors that affect the operation of a pulse detonation engine, there are two factors that dominate: (1) time and distance to transition from Detonation to Detonation state (DDT), (2) initial state of the combustion chamber before ignition. That is, a certain time and distance are required for the flame to accelerate from rest to detonation, and after the end of one detonation combustion, a certain time is also required for the burnt gas to be discharged from the combustion chamber and to fill the combustion chamber with fresh fuel and air for the next detonation, and the two times determine the working frequency range of the engine. The direct increase of the mixture flow rate can shorten the preparation time of the initial state of the combustion chamber, but ignition is difficult at high flow rates, and slight changes in the initial conditions can cause unstable detonation or even fail to generate detonation, which is extremely disadvantageous to the stable operation of the engine. Therefore, how to stabilize the rapid detonation is a crucial technical problem for the pulse engine.
The adoption of a straight tube form and the reduction of the tube diameter is an effective solution for realizing the acceleration of detonation at present. However, the length of the detonation combustion chamber adopting the scheme is generally about 1 meter or several meters, and the actual combustion space and volume cannot be further reduced. And ignition is more difficult due to the reduced dimensions under the same operating conditions.
Disclosure of Invention
The invention aims to provide a device for generating super-enthalpy detonation by utilizing a microscale spiral channel, which creates a condition of easier detonation by utilizing the microscale spiral channel and ensures that the detonation is more stable on the premise of shortening the detonation time.
In order to achieve the purpose, the technical scheme of the invention is as follows:
a device for generating detonation utilizing a microscale helical channel, comprising:
the upper surface of the substrate is provided with a spiral channel extending outwards from the center, one end of the spiral channel positioned at the center of the substrate is provided with an air inlet and ignition channel, and the other end of the spiral channel is provided with an exhaust and pressure measuring channel;
the cover plate is attached to the upper surface of the substrate and seals the spiral channel to form a spiral combustion chamber.
When the gas-air mixed combustion chamber works, the mixed gas of the prepared gas and air is sent into the combustion chamber through the gas inlet and ignition channel and reaches the set pressure value in the combustion chamber. The igniter at the tail end of the air inlet and ignition channel is instantaneously ignited, so that flame can be accelerated from static state to detonation in a very short time and in a very short distance, and the generated high-temperature and high-speed fuel gas can be discharged through the exhaust and pressure measuring channel. After purging, the steps are repeated to obtain single millisecond pulse detonation.
The application has adopted the helical conduit extremely favorable to reflection of pressure wave and shock wave for the flame just can develop the detonation in the extremely short space.
Because the pressure wave and the shock wave are extremely favorable for accelerating flame propagation in structure, the heat value and the concentration of mixed gas in the combustion chamber required for generating detonation are greatly reduced, and the detonation can be realized only by taking hydrogen/air mixed gas as an example and by taking the pressure higher than 1.5 atmospheric pressures. The detonation combustion is realized under the condition of low heat value, the total energy is greatly reduced, and the requirements on the structural strength and the materials of the combustor are greatly reduced.
The spiral channel can preheat the gas and air in the last cycle by utilizing the heat generated in the previous cycle, so that the effect of super enthalpy heat return is achieved, and the combustion efficiency is further improved.
In the helical combustion chamber, the characteristic of the super enthalpy combustion is used. If the flame propagation velocity during the entire detonation exceeds the theoretical CJ detonation velocity of the hydrogen/air mixture many times as calculated from DDT, the flame propagation velocity is effectively maintained and enhanced.
Due to the adoption of the scheme of intermittent air intake and static ignition, the realization of detonation combustion at each time can be ensured, and the working stability of the detonation engine is greatly improved.
Detonation in the combustion chamber of this application, its DDT position is only for the ten millimeter level with the straight-line distance of ignition position, and whole combustion chamber diameter has effectively reduced the requirement of detonation combustor to the space at hundred millimeter levels.
Because the volume of the combustion chamber is very small, the time required by the scavenging process and the charging process in a single cycle of the detonation engine is greatly shortened, so that the detonation engine can work at higher frequency.
Further, the cover plate and the top surface of the spiral groove are provided with a gap. The gap is small, the main combustion area is not affected, but shock waves and burnt gas can heat unburnt gas on the outer ring through the gap, so that the unburnt gas is detonated in advance, the effect of enthalpy-exceeding preheating is generated, the flame propagation speed is further improved, and the time required by the combustion process in the single circulation of the engine is shortened.
Compared with the prior art, the invention has the beneficial effects that:
1. through the micro-scale spiral pipeline, a condition that pressure waves and shock waves can easily affect flame propagation can be created, so that the flame can develop detonation in a very short space (millimeter-scale length).
2. The detonation device can greatly shorten the space required by the DDT, can realize detonation combustion in a small-volume space more easily, and takes hydrogen/air mixed gas as an example, the displacement from ignition to triggering the DDT is about 10 mm.
3. The detonation device has the characteristics of small volume and strong portability, can be moved and applied to various occasions needing energy supply, and the generated high-temperature and high-speed airflow can be directly used for power propulsion and can also be combined with a gas turbine and a generator to output electric power.
Drawings
FIG. 1 is a front view of a detonation device substrate of the present invention;
FIG. 2 is an axial view of the detonation device cover plate of the present invention;
FIG. 3 is a schematic view of the flame path of the detonation device of the present invention;
FIG. 4 is a schematic illustration of the super enthalpy effect of the detonation device of the present invention;
FIG. 5 is a schematic view of an ignition element externally attached to the detonation device of the present invention;
FIG. 6 is a schematic view of the detonation device circumscribing the gas turbine components of the present invention;
FIG. 7 is a photograph of a flame of an embodiment of a detonation device of the present invention;
description of reference numerals: 1-a substrate; 2-intake and ignition channels; 3-a helical channel; 4-exhaust and pressure measurement channel; 5-an ignition component; 6-gas turbine components; 7-cover plate.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
As shown in fig. 1 and 2, an apparatus for generating detonation using a micro-scale spiral pipe includes a metallic base plate 1 and a cover plate 7 of quartz glass.
The upper surface of the base plate 1 is provided with a spiral channel 3 extending outwards from the center, one end of the spiral channel 3 positioned at the center of the base plate 1 is provided with an air inlet and ignition channel 2, and the other end positioned at the outer side of the base plate 1 is provided with an exhaust and pressure measuring channel 4.
The air inlet and ignition channel 2 is used for introducing mixed gas of fuel and air, and an igniter is arranged at the tail end of the air inlet and ignition channel and is used for igniting the mixed gas after the mixed gas meets the requirement in the combustion chamber. The exhaust and pressure measuring channel 4 is used for real-time monitoring and acquiring the pressure of the combustion chamber and exhausting burned gas in the flame propagation process.
The spiral channel 3 is of a constant-speed spiral structure from the center to the outside, and the section of the spiral channel is 1-10mm2The cross-sectional shape is not limited, and may be, for example, a square, an oval, a circle, or the like.
The cover plate 7 is attached to the upper surface of the base plate 1 to close the spiral passage 3 and form a spiral combustion chamber.
After ignition from the center, the flame will spiral along the spiral channel 3 and rapidly accelerate to detonation, as shown in fig. 3.
As shown in fig. 4, the cover plate 7 has a gap with the top surface of the spiral passage 3, so that, in addition to the velocity of the flame in the main combustion zone of the spiral passage 3, the burnt gas can enter the outer ring through the gap above the spiral passage 3 to heat and burn the unburned gas in advance, thereby increasing the radial velocity of the flame propagation, so that the propagation velocity of the flame in the combustion chamber as a whole is higher than the C-J detonation velocity. Meanwhile, the high-temperature wall surface of the spiral combustion chamber after the last combustion can heat the fresh mixed gas of the next circulation, and the super-enthalpy combustion effect of preheating and heat returning can be realized.
When the device works, the prepared gas and air mixture is sent into a combustion chamber through the air inlet and ignition channel 2, when the pressure value in the combustion chamber reaches the set value, an igniter at the tail end of the air inlet and ignition channel 2 is ignited, flame can be obtained from static acceleration to detonation in a short time and a short distance, and the generated high-temperature and high-speed gas is discharged through the gas discharge and pressure measurement channel 4.
As shown in fig. 5, an ignition unit 5 is connected to the rear of the exhaust and pressure measurement channel 4, the length and size of the ignition unit 5 can be designed as required, and the ignition operation using the high-temperature and high-speed combusted gas after detonation combustion can be realized by placing the outlet of the ignition unit 5 at a required position.
As shown in fig. 6, a gas turbine component 6 is connected to the rear of the exhaust and pressure measurement channel 4, and the size and shape of the gas turbine can be selected according to requirements, so that the high-temperature and high-speed gas after detonation combustion can be used for pushing the gas turbine to do work.
The detonation process of the present application is illustrated below in one specific example:
as shown in figure 7, hydrogen/propane/air mixture with an equivalence ratio of 1.0 and hydrogen accounting for 90% of the fuel volume is prepared and filled into a combustion chamber, the initial pressure of the combustion chamber is adjusted to 2.5 atmospheric pressure, ignition is carried out at the center of the combustion chamber in an electric spark discharge mode after the combustion chamber is static, DDT phenomenon occurs between 0.5 and 0.6ms, and the linear distance between the DDT occurrence position and the ignition center position is only 9-15 mm. It can be seen that the pre-ignition hyperpenthalpy phenomenon occurs outside the main flame zone at the 0.7ms and 0.8ms moments. According to measurement and calculation, the peak velocity in the combustion chamber after detonation is larger than 4000m/s, and the global average velocity is larger than 2300 m/s.
The above embodiments are only for illustrating the technical concept and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and implement the present invention accordingly, and not to limit the protection scope of the present invention accordingly. All equivalent changes or modifications made in accordance with the spirit of the present disclosure are intended to be covered by the scope of the present disclosure.
Claims (5)
1. A device for generating detonation by utilizing a microscale spiral channel is characterized in that: the method comprises the following steps:
the upper surface of the substrate is provided with a spiral channel extending outwards from the center, one end of the spiral channel positioned at the center of the substrate is provided with an air inlet and ignition channel, and the other end of the spiral channel is provided with an exhaust and pressure measuring channel;
the cover plate is attached to the upper surface of the substrate and seals the spiral channel to form a spiral combustion chamber;
the cover plate and the top surface of the spiral channel are provided with a gap.
2. The apparatus for generating detonation utilizing micro-scale helical channels of claim 1, wherein: the cross section of the spiral channel is 1-10mm2。
3. The apparatus for generating detonation utilizing micro-scale helical channels of claim 2, wherein: the section of the spiral channel is square, oval or round.
4. The apparatus for generating detonation utilizing micro-scale helical channels of claim 2, wherein: the spiral channel is of a constant-speed spiral structure.
5. The apparatus for generating detonation utilizing micro-scale helical channels of claim 1, wherein: the cover plate is a quartz glass cover plate.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910912786.7A CN110761898B (en) | 2019-09-25 | 2019-09-25 | Device for generating super-enthalpy detonation by utilizing micro-scale spiral channel |
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| CN201910912786.7A CN110761898B (en) | 2019-09-25 | 2019-09-25 | Device for generating super-enthalpy detonation by utilizing micro-scale spiral channel |
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| CN110761898A CN110761898A (en) | 2020-02-07 |
| CN110761898B true CN110761898B (en) | 2020-09-29 |
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| CN111413367B (en) * | 2020-05-15 | 2021-08-13 | 天津大学 | Combustion device and measurement system for realizing space multipoint spontaneous combustion |
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|---|---|---|---|---|
| CN103075271A (en) * | 2013-01-21 | 2013-05-01 | 西北工业大学 | High-frequency conical spiral tube type pulse detonation engine |
| CN103292954A (en) * | 2013-04-15 | 2013-09-11 | 西北工业大学 | Device for measuring knocking combustion pressure in millimeter-level circular tube |
| CN104698121A (en) * | 2015-02-03 | 2015-06-10 | 北京理工大学 | Deflagration to detonation experimental device for gas in microscale pipeline |
| CN106338083A (en) * | 2016-09-06 | 2017-01-18 | 西北工业大学 | Microscale detonation system with variable boundary conditions |
| RU2672240C1 (en) * | 2016-07-20 | 2018-11-12 | Виталий Валериевич Кожевин | Pulsejet engine |
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2019
- 2019-09-25 CN CN201910912786.7A patent/CN110761898B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103075271A (en) * | 2013-01-21 | 2013-05-01 | 西北工业大学 | High-frequency conical spiral tube type pulse detonation engine |
| CN103292954A (en) * | 2013-04-15 | 2013-09-11 | 西北工业大学 | Device for measuring knocking combustion pressure in millimeter-level circular tube |
| CN104698121A (en) * | 2015-02-03 | 2015-06-10 | 北京理工大学 | Deflagration to detonation experimental device for gas in microscale pipeline |
| RU2672240C1 (en) * | 2016-07-20 | 2018-11-12 | Виталий Валериевич Кожевин | Pulsejet engine |
| CN106338083A (en) * | 2016-09-06 | 2017-01-18 | 西北工业大学 | Microscale detonation system with variable boundary conditions |
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