CN116293802B - Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization - Google Patents
Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization Download PDFInfo
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- CN116293802B CN116293802B CN202310241738.6A CN202310241738A CN116293802B CN 116293802 B CN116293802 B CN 116293802B CN 202310241738 A CN202310241738 A CN 202310241738A CN 116293802 B CN116293802 B CN 116293802B
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- 230000035939 shock Effects 0.000 title claims abstract description 99
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 90
- 230000006641 stabilisation Effects 0.000 title description 11
- 238000011105 stabilization Methods 0.000 title description 11
- 239000000446 fuel Substances 0.000 claims abstract description 32
- 239000007921 spray Substances 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 238000002156 mixing Methods 0.000 description 4
- 239000007800 oxidant agent Substances 0.000 description 4
- 230000001590 oxidative effect Effects 0.000 description 4
- 239000004215 Carbon black (E152) Substances 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 229930195733 hydrocarbon Natural products 0.000 description 3
- 150000002430 hydrocarbons Chemical class 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000010992 reflux Methods 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The invention belongs to the technical field of jet propulsion devices, and discloses a combustion chamber of a scramjet engine based on shock wave system ignition and backflow stable flame, wherein the combustion chamber comprises fuel spray holes arranged on the wall surface of the combustion chamber and a plurality of shock wave generators positioned on the upper side and the lower side of the combustion chamber, the shock wave generators are arranged on the upper side and the lower side of the combustion chamber at intervals, and the included angles and interval distances between all the shock wave generators and the inner wall of the combustion chamber are as follows: the shock wave generated from the previous shock wave generator in the incoming flow direction reaches the bottom of the next shock wave generator. The invention solves the problem that the combustion chamber of the high Mach number scramjet engine capable of realizing reliable ignition and stable combustion is not available in the prior art, and is suitable for stable ignition combustion of the combustion chamber under hypersonic flow conditions.
Description
Technical Field
The invention relates to the technical field of jet propulsion devices, in particular to a combustion chamber of a scramjet engine based on shock wave system ignition and back flow flame stabilization.
Background
The scramjet engine is a jet propulsion power unit with hypersonic flight, and comprises an air inlet channel, an isolation section, a combustion chamber, a tail jet pipe and other parts, wherein the working speed range of the scramjet engine can reach Ma 4-Ma 10.
The function of the combustion chamber in a scramjet engine is to achieve reliable ignition and stable combustion of the fuel. While reliable ignition requires that the pressure, temperature and speed within the combustion chamber meet certain constraints under which the time required for the physicochemical processes of fuel atomization, breaking, evaporation and chemical ignition delay is called ignition time. Under typical conditions of a hypersonic combustor, the ignition time of the fuel is about 5 to 10 milliseconds. However, to achieve reliable ignition, the residence time of the fuel in the combustion chamber must be greater than the ignition time. The length of a typical hypersonic combustion chamber is only 1m, and under hypersonic flow conditions, the flow speed of air flow in the combustion chamber exceeds 1000m/s, so that the residence time of the air flow in the combustion chamber is only about 1 millisecond, and the ignition time requirement is difficult to meet.
Stable combustion requires flame propagation speeds greater than airflow speeds. Whereas the current typical hypersonic combustion chamber has an air flow speed exceeding 1000m/s, and the flame propagation speed is typically several tens of meters per second, flame stabilization is difficult to achieve depending on the propagation speed of the flame itself, so that the back flow motion of the air flow must be designed such that the air flow speeds of the "back flow" and the "forward flow" are "offset" each other, thereby maintaining flame stabilization.
In the field of subsonic and supersonic combustion chambers with lower airflow speed, a spark plug, a pyrotechnic igniter or a plasma igniter is often adopted to realize auxiliary ignition, and a support plate, a step or a groove is adopted to realize flame stabilization, but the method can increase the complexity of the combustion chamber, and the aerodynamic resistance can be obviously increased under the hypersonic flow condition with Mach number reaching more than 4, so that the method is not suitable for the combustion chamber of the high Mach number scramjet engine. According to the analysis of the published data, a technical scheme of a high Mach number scramjet engine combustion chamber capable of realizing reliable ignition and stable combustion is not available at home and abroad at present.
Disclosure of Invention
The invention aims to provide a combustion chamber of a scramjet engine based on shock wave system ignition and back flow flame stabilization, so as to solve the problem that the combustion chamber of the scramjet engine with high Mach number, which can realize reliable ignition and stable combustion, is not available in the prior art.
In order to achieve the above object, the present invention provides the following technical solutions: the utility model provides a scramjet engine combustion chamber based on shock wave system ignition and backward flow steady flame, includes the fuel orifice that sets up in the combustion chamber and is located a plurality of shock generators of orifice low reaches, a plurality of shock generator interval sets up in the inside upper and lower both sides of combustion chamber, all shock generator and the contained angle and the interval distance of combustion chamber inner wall satisfy: the shock wave generated from the previous shock wave generator in the incoming flow direction reaches the bottom of the next shock wave generator.
Further, the position and geometry of a plurality of said shock generators are matched to the airflow at the inlet of the combustion chamber.
Further, the number of the shock wave generators is three, the included angle between each shock wave generator and the inner wall of the combustion chamber is 45 degrees, and the distances between the three shock wave generators and the inlet of the combustion chamber are 60mm, 100mm and 220mm respectively.
Compared with the prior art, the invention has the beneficial effects that:
According to the scheme, a group of shock wave generators are matched and designed according to the air flow condition of the inlet of the combustion chamber, a shock wave system with specific air flow parameters is generated, the mixing proportion of fuel and oxidant required by ignition and the ignition time requirement are met, and the reliable ignition of fuel is realized. Meanwhile, the shock wave generator can generate a backflow area, so that the flame propagation speed requirement is met, and the flame stability is kept.
Drawings
Fig. 1 is a schematic structural view of the hypersonic combustion chamber in the working state in the present embodiment 1;
FIG. 2 is a schematic diagram showing calculation of parameters of wave front and wave back of the shock wave in embodiment 1;
FIG. 3 is a graph showing the results of the calculation of the shock generator values in example 1;
FIG. 4 is a schematic view of a combustion chamber of a scramjet engine based on shock ignition and back-flow flame stabilization in example 2;
FIG. 5 is a graph of wall pressure profile of the combustor for different fuel flow conditions in example 2.
The names of the corresponding marks in the drawings are: fuel injection hole 1, large-size drop fuel 2, shock wave generator 3, oblique shock wave 4, reflux zone 5, fuel vapor 6 and fire kernel 7.
Detailed Description
The invention is described in further detail below with reference to the attached drawings and embodiments:
Description of related art names in this embodiment:
shock wave: in an instantaneous compression process in the gas flow, after the gas is subjected to a shock, the gas flow parameters of the gas are obviously changed, the speed is reduced, the pressure and the temperature are increased, the shock waves can be generally divided into normal shock waves and oblique shock waves, the shock wave angle of the normal shock waves is 90 degrees, namely, the normal shock waves are perpendicular to the gas flow direction, and the shock wave angle of the oblique shock waves is smaller than 90 degrees, namely, the oblique shock waves are inclined to the gas flow direction;
excitation system: a wave system structure composed of a plurality of shock waves and having specific wave front wave back airflow parameters;
Reflux: the gas in the combustion chamber flows from the inlet to the outlet, the flow direction is downstream, and the reverse flow is back flow;
High mach number: the aerospace field generally refers to a speed range reaching more than 4 times the sound speed, namely more than Ma 4;
a combustion chamber: a component of the engine achieves injection mixing, reliable ignition and stable combustion of fuel.
Example 1
As shown in fig. 1, a combustion chamber of a scramjet engine based on laser system ignition and back flow flame stabilization comprises a fuel spray hole 1 arranged in the combustion chamber and a plurality of shock wave generators 3 positioned at the downstream of the spray hole 1, wherein the spray hole 1 is close to the inlet of the combustion chamber; in this embodiment, the number of the shock generators 3 is three, and the positions and geometric dimensions of the three shock generators 3 are designed to match with the airflow at the inlet of the combustion chamber, in this embodiment, the included angle between each shock generator and the inner wall of the combustion chamber is 45 °, and the distances between the three shock generators 3 and the inlet of the combustion chamber are 60mm, 100mm, and 220mm, respectively. The shock generators 3 are arranged at the upper side and the lower side of the combustion chamber at intervals, and the included angles between all the shock generators 3 and the inner wall of the combustion chamber meet the following requirements: the shock wave generated from the last shock wave generator 3 in the incoming flow direction reaches just the bottom of the next shock wave generator 3.
The working procedure of this embodiment is:
The combustion chamber is injected with liquid hydrocarbon fuel through the spray hole 1, and the liquid hydrocarbon fuel enters the combustion chamber to form large-size liquid drop fuel 2. Then three shock wave generators 3 generate three oblique shock waves 4, the three oblique shock waves 4 have the common functions of decelerating, pressurizing and heating the airflow in the combustion chamber, and the other three oblique shock waves 4 have respective special functions: the first shock wave 4 breaks up the large-size droplet fuel 2 in the combustion chamber into small-size droplet fuel. The second ramp shock wave 4 further atomizes and evaporates the small droplet fuel into fuel vapor 6. The third oblique shock wave 4 ignites the fuel vapor 6 to form an initial flame kernel 7.
The combustion chamber is divided into four areas by three-way shock waves (as shown in fig. 2), wherein an inlet of the combustion chamber is enclosed with a first-way oblique shock wave 4 to form a first area, the first-way oblique shock wave 4 is enclosed with a second-way oblique shock wave 4 to form a second area, the second-way oblique shock wave 4 is enclosed with a third-way oblique shock wave 4 to form a third area, an outlet of the combustion chamber is enclosed with the third-way oblique shock wave 4 to form a fourth area, and airflow parameters of each area comprise speed V, pressure P and temperature T. The air flow parameters of the first region are known design conditions under which the inclination angle delta of the shock wave generator 3 is optimally designed according to the ignition and flame stabilization requirements of the combustion chamber. The design requirements for the tilt angle delta are: after the air flow flows through the first shock wave generator 3, the generated oblique shock wave 4 has an angle epsilon, and under the angle epsilon, the first oblique shock wave 4 can just strike the bottom of the inclined plane of the second shock wave generator 3, so that the reflected wave of the first oblique shock wave 4 on the wall surface of the combustion chamber is overlapped with the second oblique shock wave 4 generated by the second shock wave generator 3, and the intensity of the shock wave is increased. The airflow parameters after the shock wave can be calculated by using the parameters before shock wave and the shock wave angle, and the pressure calculation formula before and after the oblique shock wave 4 is shown as formula (1) by taking the pressure as an example, whereinWhere γ is the gas constant of the first region.
（1）
The three shock generators 3 can also generate three recirculation zones 5, by means of which recirculation zones 5 flames can be stabilized, wherein the two recirculation zones 5 near the inlet of the combustion chamber have the effect of increasing the mixing distance and time of fuel and combustion chamber air flow, improving the mixing uniformity of the two, and creating more favorable conditions for ignition combustion downstream of the combustion chamber. The purpose of the recirculation zone 5 near the outlet of the combustion chamber is to increase the residence time of the gas flow in this localized region, to achieve a more adequate mass exchange between the fuel and oxidant mixture to be reacted and the combustion products inside the initial core 7, maintaining the fuel to oxidant ratio inside the initial core 7, so that the combustion reaction propagates from the initial core 7 to other regions of the combustion chamber, achieving flame stabilization.
The typical hypersonic combustor was validated based on computational fluid dynamics (Computation Folw Dynamic, CFD) methods. The combustion chamber inlet airflow parameter is V 1=2338 m/s,P1=8813 Pa, T1 =846K, the inclination angles of the three shock generators 3 are 45 degrees, the first shock generator 3 is away from the combustion chamber inlet 60 mm, the second shock generator 3 is away from the combustion chamber inlet 100 mm, the third shock generator 3 is away from the combustion chamber inlet 220 mm, and numerical calculation and evaluation (shock system structure and airflow streamline shown in fig. 3) are carried out on the design parameters, and the results show that: the airflow parameters of the second region are: v 2=2238 m/s,P2=21524 Pa,T2 = 1173K; the airflow parameters of the third zone are: v 3=2051 m/s,P3=33239 Pa,T3 = 1392K; the airflow parameters of the fourth zone are: v 4=1272 m/s,P4=51088 Pa,T4 = 2004K. The ignition first takes place in the fourth zone, and there is a back flow flame stabilizing zone downstream of the three shock generators 3, and the liquid hydrocarbon fuel can be reliably ignited and stably burned under the design scheme.
Example 2
The scramjet combustion chamber based on excimer ignition and flashback flame holding in example 1 was subjected to experimental verification based on experimental hydrodynamic methods (Experiment Folw Dynamic, EFD). Experiments were carried out at the combustion laboratory of the China center for aerodynamic research and development, with the dimensions of the engine combustion chamber shown in FIG. 4. The experiment injects fuel with different flow rates into the combustion chamber, so that reliable ignition and stable combustion are realized. The pressure distribution of the wall surface of the engine under different fuel flow working conditions is shown in fig. 5, wherein the equivalence ratio in the diagram represents the quantity of fuel flow, when the equivalence ratio is equal to 1, the fuel flow and the flow of the oxidant inhaled by the engine exactly accord with the proportion of complete chemical reaction, and the engine generally works under the working condition that the equivalence ratio is smaller than 1. As can be seen from fig. 5, the wall pressure of the engine is significantly increased compared with the cold flow pressure (i.e., no-fuel condition) over a wide range of equivalence ratios from 0.29 to 0.71, indicating that the engine achieves reliable ignition and stable combustion, thereby facilitating an increase in the range of applications of the scramjet engine.
The present embodiment is only for explanation of the present invention and is not to be construed as limiting the present invention, and modifications to the present embodiment, which may not creatively contribute to the present invention as required by those skilled in the art after reading the present specification, are all protected by patent laws within the scope of claims of the present invention.
Claims (3)
1. The utility model provides a scramjet engine combustion chamber based on shock wave system ignition and stable flame of backward flow which characterized in that: including setting up at the fuel orifice in the combustion chamber and being located a plurality of shock wave generators of orifice low reaches, a plurality of shock wave generator interval sets up in the inside upper and lower both sides of combustion chamber, all shock wave generator and the contained angle and the interval distance of combustion chamber inner wall satisfy: the shock wave generated from the previous shock wave generator in the incoming flow direction reaches the bottom of the next shock wave generator.
2. The shock ignition and back flow flame holding based scramjet engine combustion chamber of claim 1, wherein: the position and geometry of a plurality of said shock generators are matched to the airflow at the inlet of the combustion chamber.
3. The shock ignition and back flow flame holding based scramjet engine combustion chamber of claim 2, wherein: the number of the shock wave generators is three, the included angle between each shock wave generator and the inner wall of the combustion chamber is 45 degrees, and the distances between the three shock wave generators and the inlet of the combustion chamber are 60mm, 100mm and 220mm respectively.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310241738.6A CN116293802B (en) | 2023-03-14 | 2023-03-14 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310241738.6A CN116293802B (en) | 2023-03-14 | 2023-03-14 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
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| CN116293802A CN116293802A (en) | 2023-06-23 |
| CN116293802B true CN116293802B (en) | 2024-05-14 |
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