CN116537956A - Method and device for regulating and controlling combustion of scramjet engine in real time by actively supplementing oxygen - Google Patents
Method and device for regulating and controlling combustion of scramjet engine in real time by actively supplementing oxygen Download PDFInfo
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- CN116537956A CN116537956A CN202310717712.4A CN202310717712A CN116537956A CN 116537956 A CN116537956 A CN 116537956A CN 202310717712 A CN202310717712 A CN 202310717712A CN 116537956 A CN116537956 A CN 116537956A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 323
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 315
- 239000001301 oxygen Substances 0.000 title claims abstract description 315
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 315
- 230000001502 supplementing effect Effects 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 24
- 230000001276 controlling effect Effects 0.000 title claims abstract description 16
- 230000001105 regulatory effect Effects 0.000 title claims abstract description 14
- 238000002347 injection Methods 0.000 claims abstract description 215
- 239000007924 injection Substances 0.000 claims abstract description 215
- 230000005855 radiation Effects 0.000 claims abstract description 42
- 230000033228 biological regulation Effects 0.000 claims abstract description 26
- 239000000523 sample Substances 0.000 claims description 42
- 238000011144 upstream manufacturing Methods 0.000 claims description 27
- 238000009530 blood pressure measurement Methods 0.000 claims description 20
- 239000000446 fuel Substances 0.000 claims description 20
- 230000008033 biological extinction Effects 0.000 claims description 12
- 239000013589 supplement Substances 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 4
- 230000009469 supplementation Effects 0.000 claims description 2
- 230000001706 oxygenating effect Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 3
- 238000012544 monitoring process Methods 0.000 description 10
- 239000000243 solution Substances 0.000 description 6
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 5
- 239000001257 hydrogen Substances 0.000 description 5
- 229910052739 hydrogen Inorganic materials 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 5
- 239000003350 kerosene Substances 0.000 description 4
- 230000009467 reduction Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000009123 feedback regulation Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000002699 waste material Substances 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
-
- 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
- F02K7/10—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention provides a method and a device for regulating and controlling the combustion of a scramjet engine by actively supplementing oxygen in real time, wherein the method comprises the following steps: acquiring pressure data of the inner wall surface of the combustion chamber and self-luminous radiation data of flame in real time; determining the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired pressure data of the inner wall surface of the combustion chamber and the self-luminous flame radiation data; and generating corresponding control signals to oxygen injection valves corresponding to the combustion chambers according to the current flame combustion state to realize active oxygen supplementing and active combustion regulation. The invention can strengthen the combustion effect, improve the combustion efficiency and improve the accuracy and stability of combustion control.
Description
Technical Field
The invention mainly relates to the technical field of scramjet engines, in particular to a method and a device for regulating and controlling the combustion of a scramjet engine in real time and actively supplementing oxygen.
Background
The scramjet engine is one of the most rapidly developed hypersonic aircraft power devices at present, and has the greatest characteristics of high efficiency, high thrust, high energy density and the like. However, in hypersonic speed, the incoming flow speed is high, the residence time of fuel is short, and the scramjet engine is difficult to ignite and stably burn under extreme working conditions, so that flameout phenomenon is very easy to occur, and the performance and the service life of the engine are adversely affected.
The current methods for enhancing ignition and stabilizing combustion are as follows:
(1) Hydrogen guided ignition
The high heat value and flammability of the hydrogen are utilized in the hydrogen guide ignition, and a high-temperature and high-pressure flame core is formed in the combustion chamber, so that the supersonic speed enhanced combustion is realized, the combustion efficiency and the power output of the engine can be improved, and the generation of emissions is reduced. But intensified hydrogen ignition does not address ignition at lean air and near blow out limits.
The hydrogen guide ignition and the like belong to passive regulation and control, cannot be regulated and controlled in real time according to the combustion state, have limited action range, are used for carrying out intensified ignition from the angle of input energy, cannot realize the monitoring and real-time feedback regulation of the combustion state, and can generate the conditions of energy waste, no action effect and the like.
(2) Ignition of spark plug
When the spark plug is used for enhanced ignition, the frequency of discharge is limited, and under extreme conditions such as near-lean combustion, stable combustion of the scramjet engine is difficult to realize.
For the scheme of using the spark plug to strengthen ignition and combustion, the spark plug has serious ablation, belongs to direct current pulse discharge, has low discharge frequency, limited expansion of kerosene stable flame boundary, and is difficult to realize strengthened ignition and stable combustion under the condition of near lean combustion limit at a certain kerosene flow, and cannot realize active regulation and control of combustion state.
(3) Stable combustion by means of a recessed flame holder
When stable combustion is realized by means of the cavity flame stabilizer, the cavity with a specific configuration has ignition and flame stability limits due to the influence of factors such as incoming flow conditions, fuel types, injection modes, equivalence ratios and the like. The concave cavity flame stabilizer is used as a passive stable combustion device, when the ignition and flame stability limit of the concave cavity is exceeded, the phenomena of ignition failure and flame blow-out of the engine occur, the combustion state of the engine cannot be actively regulated and controlled, and the combustion state cannot be fed back and regulated in real time.
Disclosure of Invention
Aiming at the technical problems existing in the prior art, the invention provides a method and a device for actively supplementing oxygen in real time during combustion of a scramjet engine.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
a method for actively and actively supplementing oxygen in real time during combustion of a scramjet engine comprises the following steps:
acquiring pressure data of the inner wall surface of the combustion chamber and self-luminous radiation data of flame in real time;
determining the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired pressure data of the inner wall surface of the combustion chamber and the self-luminous flame radiation data;
And generating corresponding control signals to oxygen injection valves corresponding to the combustion chambers according to the current flame combustion state to realize active oxygen supplementing and active combustion regulation.
Further, the combustion chamber is a concave cavity combustion chamber, the lower wall surface of the combustion chamber is provided with a concave cavity, and an igniter is arranged on the bottom wall surface of the concave cavity 。
Further, in the present invention: along the moving direction of supersonic incoming flow, a plurality of groups of pressure measuring points are arranged at different combustion chamber length positions of the lower wall surface of the combustion chamber and are used for measuring pressure data at different positions of the inner wall surface of the combustion chamber in real time; a plurality of groups of photoelectric probes are arranged at different positions of the length of the combustion chamber on the upper wall surface of the combustion chamber and are used for measuring flame self-luminous radiation data at different positions of the inner wall surface of the combustion chamber in real time.
Further, in the present invention: the multiple groups of pressure measuring points are arranged on the lower wall surface of the combustion chamber at the upstream of the concave cavity, the multiple groups of pressure measuring points are arranged on the bottom wall surface of the concave cavity at the upstream of the igniter, at least one group of pressure measuring points are arranged on the bottom wall surface of the concave cavity at the downstream of the igniter, and at least one group of pressure measuring points are arranged on the lower wall surface of the combustion chamber at the downstream of the concave cavity.
Further, a group of photoelectric probes are correspondingly arranged on the upper wall surface of the combustion chamber above each group of pressure measuring points, and the pressure measuring points and the photoelectric probes are vertically corresponding to each other.
Further, in the invention, at least one group of oxygen injection holes are arranged on the wall surface of the concave cavity at the upstream of the igniter, at least one group of oxygen injection holes are arranged on the wall surface of the concave cavity at the downstream of the igniter, an oxygen source supplies oxygen to each group of oxygen injection holes through an oxygen supply pipeline, each group of oxygen injection holes respectively corresponds to an independent oxygen supply branch communicated with the oxygen source, independent oxygen injection valves are arranged on the oxygen supply branches corresponding to each group of oxygen injection holes, and independent control of each group of oxygen injection holes is realized through the oxygen injection valves.
Further, the concave cavity wall surface comprises a concave cavity front wall, a concave cavity bottom wall surface and a concave cavity rear wall, wherein the concave cavity front wall is vertically arranged with the lower wall surface of the combustion chamber at the upstream of the adjacent concave cavity, and forms a vertical step with the bottom wall of the concave cavity; the rear wall of the concave cavity is obliquely arranged relative to the bottom wall surface of the concave cavity to form an oblique transition between the concave cavity and the lower wall surface of the combustion chamber at the downstream of the concave cavity.
Further, in the invention, at least one group of oxygen injection holes are arranged on the front wall of the concave cavity, at least one group of oxygen injection holes are arranged on the bottom wall surface of the concave cavity at the upstream of the igniter, and at least one group of oxygen injection holes are arranged on the rear wall of the concave cavity.
Further, in the present invention, the current flame combustion state is determined by the steps of:
setting wall pressure intervals and flame self-luminous radiation intensity intervals of different positions in a combustion chamber under different flame combustion states, wherein the flame combustion states comprise a flame normal combustion state, a flame local weak combustion state, a flame global extinction or near extinction state and a flame intensified combustion state;
judging the current flame combustion state according to the currently acquired wall pressure data at different positions in the combustion chamber and the flame self-luminous radiation intensity data.
Further, according to the current flame combustion state, the method generates a corresponding control signal to the oxygen injection valve corresponding to the combustion chamber to realize active oxygen supplementing and active combustion regulation and control, and comprises the following steps:
according to the pressure data and the photoelectric signal data conditions of all the measuring point positions fed back in real time, the opening/closing conditions of the oxygen injection valves of all the groups of oxygen injection holes are adjusted in real time, specifically, the oxygen injection valves of all the groups of oxygen injection holes close to the positions of the measuring points with relatively smaller pressure data and photoelectric signal data are opened, and the oxygen injection valves of all the groups of oxygen injection holes close to the positions of the measuring points with relatively larger pressure data and photoelectric signal data are closed, so that the self-adaption adjustment is carried out until all the measuring point positions are monitored to be in a stable and normal combustion state.
Further, according to the current flame combustion state, the method generates a corresponding control signal to the oxygen injection valve corresponding to the combustion chamber to realize active oxygen supplementing and active combustion regulation and control, and comprises the following steps:
if the wall pressure data measured by the pressure measuring point at a certain position is positioned between the wall pressure areas under the corresponding flame local weak combustion state or the flame self-luminous radiation intensity data measured by the photoelectric probe corresponding to the position is positioned between the flame self-luminous radiation intensity areas under the corresponding flame local weak combustion state, opening an oxygen injection valve corresponding to a group of oxygen injection holes closest to the position to perform oxygen supplementing injection until the wall pressure data measured by the pressure measuring point at the position is positioned between the wall pressure areas under the corresponding flame normal combustion state, and closing an oxygen injection valve corresponding to a group of oxygen injection holes closest to the position;
if the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure interval in which the corresponding flame is globally extinguished or is close to the extinguishing state or the flame self-luminous radiation intensity data measured by the photoelectric probes corresponding to all positions are in the flame self-luminous radiation intensity interval in which the corresponding flame is globally extinguished or is close to the extinguishing state, opening the oxygen injection valves corresponding to all groups of oxygen injection holes to perform oxygen supplementing injection until the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure interval in which the corresponding flame is in the normal combustion state, and closing the oxygen injection valves corresponding to all groups of oxygen injection holes;
If the combustion performance of the combustion chamber needs to be improved currently, starting the igniter and the oxygen injection valves corresponding to all groups of oxygen injection holes, so that the wall pressure data measured by the pressure measurement points at all positions are located in the wall pressure interval of the corresponding flame enhanced combustion state, and combustion enhancement is realized.
On the other hand, the invention provides a real-time active oxygen supplementing and regulating device for the combustion of the scramjet engine, which comprises the following components:
the combustion chamber is a concave cavity combustion chamber, a concave cavity is arranged on the lower wall surface of the combustion chamber, and an igniter is arranged on the bottom wall surface of the concave cavity ； Along the moving direction of supersonic incoming flow, a plurality of groups of pressure measuring points are arranged at different combustion chamber length positions of the lower wall surface of the combustion chamber and are used for measuring pressure data at different positions of the inner wall surface of the combustion chamber in real time; a plurality of groups of photoelectric probes are arranged at different combustion chamber length positions of the upper wall surface of the combustion chamber and are used for measuring flame self-luminous radiation data at different positions of the inner wall surface of the combustion chamber in real time; at least one group of oxygen injection holes are formed in the concave cavity wall surface at the upstream of the igniter, at least one group of oxygen injection holes are formed in the concave cavity wall surface at the downstream of the igniter, an oxygen source supplies oxygen to each group of oxygen injection holes through an oxygen supply pipeline, each group of oxygen injection holes corresponds to an independent oxygen supply branch communicated with the oxygen source, independent oxygen injection valves are arranged on the oxygen supply branches corresponding to each group of oxygen injection holes, and independent control of each group of oxygen injection holes is realized through the oxygen injection valves;
The signal control system is used for determining the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired pressure data of the inner wall surface of the combustion chamber and the flame self-luminous radiation data; and generating corresponding control signals to oxygen injection valves corresponding to the combustion chambers according to the current flame combustion state to realize active oxygen supplementing and active combustion regulation.
The invention can prevent the scramjet engine from flameout under the high-speed flight state, and simultaneously monitors the combustion state in real time and actively supplements oxygen to regulate the combustion state, and has the following advantages:
(1) And monitoring the combustion state in real time. The combustion state is monitored by means of the pressure sensor and the photoelectric probe and fed back to the signal control system in real time, the measurement and control positions are adjustable, the measurement and control quantity is variable, and the combustion state monitoring system has high programmability and reconfigurability, so that the combustion monitoring system and the feedback control algorithm can be optimized according to actual needs, and the accuracy and the stability of combustion control are improved.
(2) And (5) actively regulating and controlling in real time. The rapid response combustion process is characterized in that the signal change transmitted by the sensor timely and rapidly regulates and controls the valve of the oxygen supplementing device to supply oxygen, the combustion state can be monitored in real time, and the oxygen supplementing valve is timely closed when the flame state is stable.
(3) The active combustion state is enhanced. The enhanced combustion is realized by increasing the local equivalent ratio through oxygen supplementing, the defect of air quality exchange rate in the concave cavity is overcome, the local equivalent ratio of ignition is improved, the combustion effect is enhanced, and the combustion efficiency is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart in one embodiment;
FIG. 2 is a schematic view of a combustion chamber according to an embodiment;
FIG. 3 is a schematic diagram of an embodiment;
FIG. 4 is a schematic diagram showing a distribution of pressure measurement points and photoelectric probes in an embodiment;
fig. 5 is a control flow diagram of an embodiment.
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
Detailed Description
The embodiments described in this section are merely some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
Furthermore, descriptions such as those referred to as "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implying an order of magnitude of the indicated technical features in the present disclosure. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; the device can be mechanically connected, electrically connected, physically connected or wirelessly connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, the technical solutions of the embodiments of the present invention may be combined with each other, but it is necessary to be based on the fact that those skilled in the art can implement the technical solutions, and when the technical solutions are contradictory or cannot be implemented, the combination of the technical solutions should be considered as not existing, and not falling within the scope of protection claimed by the present invention.
Referring to fig. 1, an embodiment provides a method for controlling active oxygen supplement in real time during combustion of a scramjet engine, including:
acquiring pressure data of the inner wall surface of the combustion chamber and self-luminous radiation data of flame in real time;
determining the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired pressure data of the inner wall surface of the combustion chamber and the self-luminous flame radiation data;
and generating corresponding control signals to oxygen injection valves corresponding to the combustion chambers according to the current flame combustion state to realize active oxygen supplementing and active combustion regulation.
According to the embodiment, the pressure data of the inner wall surface of the combustion chamber and the self-luminous flame radiation data are obtained, the current flame combustion state is determined based on the established combustion state discrimination criteria, the real-time dynamic monitoring of the engine combustion state is realized, corresponding control signals are generated for the oxygen injection valve corresponding to the combustion chamber according to the current flame combustion state, active oxygen supplementing and combustion active regulation are realized, namely the oxygen supplementing valve is dynamically opened according to the combustion state and the requirements, and real-time active regulation and control of the real-time active oxygen supplementing and the combustion state are realized based on the real-time combustion state signal feedback.
The problems of unstable combustion of the scramjet engine under extreme working conditions are solved through the scheme, and meanwhile combustion enhancement and improvement of the combustion efficiency of the engine are realized under a weak combustion state.
In order to acquire pressure data of an inner wall surface of a combustion chamber and self-luminous radiation data of flame in real time, referring to fig. 2, in one embodiment, a combustion chamber is provided, the combustion chamber is a concave cavity combustion chamber, a concave cavity 20 is provided on a lower wall surface of the combustion chamber, an igniter 5 is provided on a bottom wall surface of the concave cavity 20, and a plurality of fuel injection holes 1 are provided on a lower wall surface of the combustion chamber upstream of the concave cavity 20. In fig. 2, 4 fuel injection holes 1 are provided on the same straight line in the combustion chamber width direction and 4 fuel injection holes 1 are provided at equal intervals.
A plurality of groups of pressure measuring points are arranged on the lower wall surface of the combustion chamber at different positions of the length of the combustion chamber along the movement direction of supersonic incoming flow on the upper side of the concave cavity 20 and are used for measuring the pressure data at different positions of the inner wall surface of the combustion chamber in real time; a plurality of groups of photoelectric probes are arranged at different positions of the length of the combustion chamber on the upper wall surface of the combustion chamber and are used for measuring flame self-luminous radiation data at different positions of the inner wall surface of the combustion chamber in real time. It can be understood that the number of the pressure measuring points and the photoelectric probes is not limited, and those skilled in the art can reasonably adjust according to the length, the structure and the measurement accuracy of the combustion chamber, and the invention is not limited. A group of photoelectric probes are correspondingly arranged on the upper wall surface of the combustion chamber above each group of pressure measuring points, and the pressure measuring points and the photoelectric probes are vertically corresponding to each other. The pressure measuring point and the photoelectric probe corresponding to the pressure measuring point are used for detecting wall surface pressure data and flame self-luminous radiation data of the same length position of the combustion chamber.
Without loss of generality, a plurality of groups of pressure measuring points are arranged on the lower wall surface of the combustion chamber at the upstream of the concave cavity, a plurality of groups of pressure measuring points are arranged on the bottom wall surface of the concave cavity at the upstream of the igniter, at least one group of pressure measuring points are arranged on the bottom wall surface of the concave cavity at the downstream of the igniter, and at least one group of pressure measuring points are arranged on the lower wall surface of the combustion chamber at the downstream of the concave cavity.
As shown in fig. 2, seven sets of pressure measurement points are provided, and a first set of pressure measurement points 6 is provided on the lower wall surface of the combustion chamber upstream of the fuel injection hole 1. The second set of pressure measurement points 7 and the third set of pressure measurement points 8 are arranged on the lower wall surface of the combustion chamber downstream of the fuel injection hole 1 and upstream of the concave cavity. The fourth set of pressure measurement points 9 are arranged on the bottom wall surface of the concave cavity at the upstream of the igniter 5, the fifth set of pressure measurement points 10 and the sixth set of pressure measurement points 11 are arranged on the bottom wall surface of the concave cavity at the downstream of the igniter 5, and the seventh set of pressure measurement points 12 are arranged on the lower wall surface of the combustion chamber at the downstream of the concave cavity. Each group of pressure measuring points is provided with two pressure sensors, and the same group of two pressure sensors are arranged on the same straight line in the width direction of the combustion chamber. Correspondingly, seven groups of photoelectric probes are arranged, each group of photoelectric probes is provided with two photoelectric sensors, and the two photoelectric sensors in the same group correspond to the two pressure sensors in the same group of pressure measuring points under the photoelectric sensors respectively. The seven sets of photoelectric probes in fig. 2 are a first set of photoelectric probes 13, a second set of photoelectric probes 14, a third set of photoelectric probes 15, a fourth set of photoelectric probes 16, a fifth set of photoelectric probes 17, a sixth set of photoelectric probes 18, and a seventh set of photoelectric probes 19, respectively. The fuel injection holes 1 are connected with the kerosene storage tank through pipelines, the number of the fuel valves F1-i and i arranged on the pipelines is not limited, and the fuel valves are arranged according to the requirements and represent single fuel injection holes in a group of fuel injection holes.
In the invention, at least one group of oxygen injection holes are arranged on the wall surface of the concave cavity at the upstream of the igniter 5, at least one group of oxygen injection holes are arranged on the wall surface of the concave cavity at the downstream of the igniter, an oxygen source supplies oxygen to each group of oxygen injection holes through an oxygen supply pipeline, each group of oxygen injection holes respectively corresponds to an independent oxygen supply branch communicated with the oxygen source, independent oxygen injection valves are arranged on the oxygen supply branches corresponding to each group of oxygen injection holes, and independent control of each group of oxygen injection holes is realized through the oxygen injection valves.
The cavity wall surface comprises a cavity front wall, a cavity bottom wall surface and a cavity rear wall, wherein the cavity front wall is vertically arranged with the lower wall surface of the combustion chamber at the upstream of the adjacent cavity, and forms a vertical step with the cavity bottom wall; the rear wall of the concave cavity is obliquely arranged relative to the bottom wall surface of the concave cavity to form an oblique transition between the concave cavity and the lower wall surface of the combustion chamber at the downstream of the concave cavity. In the invention, at least one group of oxygen injection holes are arranged on the front wall of the concave cavity, at least one group of oxygen injection holes are arranged on the bottom wall surface of the concave cavity at the upstream of the igniter, and at least one group of oxygen injection holes are arranged on the rear wall of the concave cavity.
As shown in fig. 2, a first group of oxygen injection holes 2 are formed in the front wall of the concave cavity, a second group of oxygen injection holes 3 are formed in the bottom wall surface of the concave cavity at the upstream of the igniter 5, a third group of oxygen injection holes 4 are formed in the rear wall of the concave cavity, 4 oxygen injection holes in each group are formed, and 4 oxygen injection holes in the same group are formed in the same straight line in the width direction of the combustion chamber and are formed in equal intervals. An oxygen source (such as an oxygen storage tank in fig. 3) supplies oxygen to each group of oxygen injection holes through an oxygen supply pipeline, each group of oxygen injection holes corresponds to an independent oxygen supply branch communicated with the oxygen source, independent oxygen injection valves are arranged on the oxygen supply branches corresponding to each group of oxygen injection holes, and independent control of each group of oxygen injection holes is realized through the oxygen injection valves.
Further, in the present invention, the current flame combustion state is determined by the steps of:
setting wall pressure intervals and flame self-luminous radiation intensity intervals of different positions in a combustion chamber under different flame combustion states, wherein the flame combustion states comprise a flame normal combustion state, a flame local weak combustion state, a flame global extinction or near extinction state and a flame intensified combustion state;
judging the current flame combustion state according to the currently acquired wall pressure data at different positions in the combustion chamber and the flame self-luminous radiation intensity data.
When the scramjet engine is in a transition or extreme working state of the flight condition, the flame state in the combustion chamber is changed, so that combustion heat release is changed, and further wall pressure is changed. And each pressure sensor in 7 groups of pressure measuring points is used for dynamically monitoring the wall pressure changes at different positions of the combustion chamber in real time to determine the flame combustion state. Secondly, the self-luminous radiation and the flame position of the flame are recorded through a photoelectric sensor arranged at the top of the combustion chamber, when the flame is nearly blown out, the self-luminous intensity is weaker, and then the state of the flame is dynamically monitored in real time.
An embodiment proposes an active oxygen replenishment and combustion active control scheme as follows: if the engine is in a quick flameout phenomenon, incomplete combustion is caused, the wall pressure is reduced, the self-luminous radiation intensity of the flame is weakened, the signal control system is used for judging the threshold value of the collected pressure data and extracting a pressure characteristic matrix, a convolution kernel is calculated on the collected self-luminous image data of the flame, and an image characteristic matrix is extracted. The pressure characteristic matrix and the image characteristic matrix are processed to obtain a multi-source characteristic matrix, the combustion state is judged by comparing the combustion state type database, the judgment of the combustion state is realized, the judgment is output and controlled to an oxygen valve, oxygen is injected into the combustion chamber of the engine, and the oxygen concentration in the combustion chamber is improved, so that oxygen supplementing and reinforced combustion is carried out during quick flameout, the quick flameout phenomenon is effectively controlled, and the normal operation of the engine is ensured. When the combustion state is changed, the data signal is compared with the set threshold value and judged, so that a control signal is output to the oxygen pipeline valve to realize active oxygen supplementing and active combustion regulation.
Referring to fig. 5, in an embodiment, a method for controlling combustion real-time active oxygen supplement of a scramjet engine is provided, including:
Firstly, establishing a combustion state judgment criterion, such as setting a wall pressure interval and a flame self-luminous radiation intensity interval of different positions in a combustion chamber under different flame combustion states, wherein the flame combustion states comprise a flame normal combustion state, a flame local weak combustion state, a flame global extinction or close extinction state and a flame intensified combustion state;
judging the current combustion state of each area according to the currently acquired wall pressure data at different positions in the combustion chamber and the flame self-luminous radiation intensity data.
When the combustion state is abnormal, if the combustion state is local and no combustion exists, regional oxygen supplementing is carried out, an oxygen supplementing valve closest to the region is opened, and an igniter is opened, so that directional combustion enhancement is realized;
if the overall combustion is not carried out, overall oxygen supplementing is carried out, all oxygen supplementing valves are opened, and an igniter is opened, so that overall combustion enhancement is realized.
When the combustion state is normal, if the performance of the engine is required to be further improved and the combustion efficiency is required to be further improved according to the requirements, global oxygen supplementing is performed, all oxygen supplementing valves are opened, and an igniter is opened, so that global combustion enhancement is realized; otherwise, the igniter and the valve are closed, the pressure and the photoelectric signal in the combustion chamber are dynamically monitored in real time, and the combustion state is adjusted in real time based on feedback of the pressure signal and the photoelectric signal.
In another embodiment, generating a corresponding control signal to an oxygen injection valve corresponding to a combustion chamber according to a current flame combustion state to realize active oxygen supplementation and active combustion regulation includes:
and according to the pressure data and the photoelectric signal data conditions of all the measuring point positions fed back in real time, the opening/closing conditions of the oxygen injection valves of all the groups of oxygen injection holes are adjusted in real time, for example, the oxygen injection valves of all the groups of oxygen injection holes close to the position of the measuring point with relatively smaller pressure data and photoelectric signal data are opened, and the oxygen injection valves of all the groups of oxygen injection holes close to the position of the measuring point with relatively larger pressure data and photoelectric signal data are closed, so that the self-adaption adjustment is carried out until all the measuring point positions are monitored to be in a stable and normal combustion state.
If the wall pressure data measured by the pressure measuring point at a certain position is positioned between the wall pressure areas under the corresponding flame local weak combustion state or the flame self-luminous radiation intensity data measured by the photoelectric probe corresponding to the position is positioned between the flame self-luminous radiation intensity areas under the corresponding flame local weak combustion state, opening an oxygen injection valve corresponding to a group of oxygen injection holes closest to the position to perform oxygen supplementing injection until the wall pressure data measured by the pressure measuring point at the position is positioned between the wall pressure areas under the corresponding flame normal combustion state, and closing an oxygen injection valve corresponding to a group of oxygen injection holes closest to the position;
If the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure region in the corresponding flame overall extinction state or the wall pressure region in the state close to extinction state or the flame self-luminous radiation intensity data measured by the photoelectric probes corresponding to all positions are in the flame self-luminous radiation intensity region in the corresponding flame overall extinction state or the state close to extinction state, opening the igniter and simultaneously opening at least oxygen injection valves corresponding to all groups of oxygen injection holes close to the igniter for oxygen supplementing injection until the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure region in the corresponding flame normal combustion state, and closing the igniter and the oxygen injection valves corresponding to all groups of oxygen injection holes;
if the combustion performance of the combustion chamber needs to be improved currently, starting the igniter and the oxygen injection valves corresponding to all groups of oxygen injection holes, so that the wall pressure data measured by the pressure measurement points at all positions are located in the wall pressure interval of the corresponding flame enhanced combustion state, and combustion enhancement is realized.
Referring to fig. 2, 3 and 4, a real-time active oxygen supplementing regulation device for combustion of a scramjet engine is provided, which comprises:
the combustion chamber is a concave cavity combustion chamber, a concave cavity is arranged on the lower wall surface of the combustion chamber, and an igniter is arranged on the bottom wall surface of the concave cavity ； Along the moving direction of supersonic incoming flow, a plurality of groups of pressure measuring points are arranged at different combustion chamber length positions of the lower wall surface of the combustion chamber and are used for measuring pressure data at different positions of the inner wall surface of the combustion chamber in real time; a plurality of groups of photoelectric probes are arranged at different combustion chamber length positions of the upper wall surface of the combustion chamber and are used for measuring flame self-luminous radiation data at different positions of the inner wall surface of the combustion chamber in real time; at least one group of oxygen injection holes are formed in the concave cavity wall surface at the upstream of the igniter, at least one group of oxygen injection holes are formed in the concave cavity wall surface at the downstream of the igniter, an oxygen source (such as an oxygen storage tank) supplies oxygen to each group of oxygen injection holes through an oxygen supply pipeline, each group of oxygen injection holes corresponds to an independent oxygen supply branch communicated with the oxygen source, independent oxygen injection valves are arranged on the oxygen supply branches corresponding to each group of oxygen injection holes, and independent control of each group of oxygen injection holes is realized through the oxygen injection valves;
the signal control system is used for determining the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired pressure data of the inner wall surface of the combustion chamber and the flame self-luminous radiation data; and generating corresponding control signals to oxygen injection valves corresponding to the combustion chambers according to the current flame combustion state to realize active oxygen supplementing and active combustion regulation.
As shown in fig. 2, seven sets of pressure measurement points are provided, and a first set of pressure measurement points 6 is provided on the lower wall surface of the combustion chamber upstream of the fuel injection hole 1. The second set of pressure measurement points 7 and the third set of pressure measurement points 8 are arranged on the lower wall surface of the combustion chamber downstream of the fuel injection hole 1 and upstream of the concave cavity. The fourth set of pressure measurement points 9 are arranged on the bottom wall surface of the concave cavity at the upstream of the igniter 5, the fifth set of pressure measurement points 10 and the sixth set of pressure measurement points 11 are arranged on the bottom wall surface of the concave cavity at the downstream of the igniter 5, and the seventh set of pressure measurement points 12 are arranged on the lower wall surface of the combustion chamber at the downstream of the concave cavity. Each group of pressure measuring points is provided with two pressure sensors, and the same group of two pressure sensors are arranged on the same straight line in the width direction of the combustion chamber. Correspondingly, seven groups of photoelectric probes are arranged, each group of photoelectric probes is provided with two photoelectric sensors, and the two photoelectric sensors in the same group correspond to the two pressure sensors in the same group of pressure measuring points under the photoelectric sensors respectively. The seven sets of photoelectric probes in fig. 2 are a first set of photoelectric probes 13, a second set of photoelectric probes 14, a third set of photoelectric probes 15, a fourth set of photoelectric probes 16, a fifth set of photoelectric probes 17, a sixth set of photoelectric probes 18, and a seventh set of photoelectric probes 19, respectively.
The fuel injection holes 1 are connected with the kerosene storage tank through pipelines, the number of the fuel valves F1-i and i arranged on the pipelines is not limited, and the fuel valves are arranged according to the requirements and represent single fuel injection holes in a group of fuel injection holes.
The pressure sensors in the first group of pressure measuring points 6, the second group of pressure measuring points 7, the third group of pressure measuring points 8, the fourth group of pressure measuring points 9, the fifth group of pressure measuring points 10 and the sixth group of pressure measuring points 11 are respectively defined as P1-j, P2-j, P3-j, P4-j, P5-j, P6-j and P7-j, wherein j=1 and 2 respectively represent single pressure sensors in one group of pressure measuring points. The photosensors in the first 13, second 14, third 15, fourth 16, fifth 17, sixth 18 and seventh 19 sets of photodetectors are defined as G1-j, G2-j, G3-j, G4-j, G5-j, G6-j, G-j, respectively, where j=1, 2, respectively, represent individual photosensors in a set of photodetectors.
As shown in fig. 2, a first group of oxygen injection holes 2 are formed in the front wall of the concave cavity, a second group of oxygen injection holes 3 are formed in the bottom wall surface of the concave cavity at the upstream of the igniter 5, a third group of oxygen injection holes 4 are formed in the rear wall of the concave cavity, 4 oxygen injection holes in each group are formed, and 4 oxygen injection holes in the same group are formed in the same straight line in the width direction of the combustion chamber and are formed in equal intervals. An oxygen source (such as an oxygen storage tank in fig. 3) supplies oxygen to each group of oxygen injection holes through an oxygen supply pipeline, each group of oxygen injection holes corresponds to an independent oxygen supply branch communicated with the oxygen source, independent oxygen injection valves are arranged on the oxygen supply branches corresponding to each group of oxygen injection holes, and independent control of each group of oxygen injection holes is realized through the oxygen injection valves. The first group of oxygen injection holes 2 corresponds to the first oxygen supply branch 01, the first oxygen supply branch 01 is provided with a first oxygen injection valve 01-i, the second group of oxygen injection holes 3 corresponds to the second oxygen supply branch 02, the first oxygen supply branch 02 is provided with a second oxygen injection valve 02-i, the third group of oxygen injection holes 4 corresponds to the third oxygen supply branch 03, the third oxygen supply branch 03 is provided with a third oxygen injection valve 03-i, i=1, 2,3,4, and the oxygen injection holes represent single oxygen injection holes in each group of oxygen injection holes.
The real-time active oxygen supplementing and controlling device for the combustion of the scramjet engine provided by the embodiment can realize the dynamic monitoring of the combustion of the scramjet engine and timely oxygen supplementing based on the real-time active oxygen supplementing and controlling combustion of pressure and photoelectric signal feedback, and further realize the active control of the combustion state.
In one embodiment, the signal control system operates as follows:
(1) Flame local weak combustion (50% pressure reduction or 50% photoelectric signal intensity reduction)
By monitoring the pressure data and the photoelectric signal intensity data of the set measuring point positions, when the pressure data or the photoelectric signal intensity data measured by the local measuring point positions are reduced by more than 50%, the oxygen injection valves of the corresponding oxygen injection holes are adaptively selected and opened, so that directional regulation and control are realized. And when the pressure data or the photoelectric signal intensity data measured at the position of the local measuring point is recovered to a normal combustion state, closing the corresponding oxygen injection valve to complete combustion regulation. Preferably, the oxygen injection valve of at least one group of oxygen injection holes adjacent to the igniter is selectively opened to realize directional regulation; or, selectively opening at least one group of oxygen injection valves of the oxygen injection holes close to the position of the local measuring point where the measured pressure data or the photoelectric signal intensity data is reduced, so as to realize directional regulation. Or firstly opening the oxygen injection valves of at least one group of oxygen injection holes close to the igniter, then adjusting the opening/closing conditions of the oxygen injection valves of each group of oxygen injection holes in real time according to the pressure data and the photoelectric signal data conditions of the fed back measuring point positions, specifically opening the oxygen injection valves of each group of oxygen injection holes close to the position of the measuring point with relatively smaller pressure data and photoelectric signal data, closing the oxygen injection valves of each group of oxygen injection holes close to the position of the measuring point with relatively larger pressure data and photoelectric signal data, and adaptively adjusting until all the measuring point positions are monitored to be in a stable and normal combustion state. Or firstly opening the oxygen injection valves of at least one group of oxygen injection holes close to the local measuring point positions where the measured pressure data or the photoelectric signal intensity data is reduced, then adjusting the opening/closing conditions of the oxygen injection valves of each group of oxygen injection holes in real time according to the pressure data and the photoelectric signal data conditions of each measuring point position fed back in real time, specifically opening the oxygen injection valves of each group of oxygen injection holes close to the position where the pressure data and the photoelectric signal data are relatively smaller, closing the oxygen injection valves of each group of oxygen injection holes close to the position where the pressure data and the photoelectric signal data are relatively larger, and adaptively adjusting until all the measuring point positions are monitored to be in a stable and normal combustion state.
(2) Flame close to flameout (90% pressure reduction, 90% photoelectric signal intensity reduction)
When the combustion state is detected to be that the flame is close to flameout, namely the pressure data measured at each measuring point position is reduced by more than 90 percent, or the photoelectric signal intensity measured at each measuring point position is reduced by more than 90 percent, the oxygen injection valve is selectively opened through the signal control system. When the stable and normal combustion state is monitored, the signal control system automatically closes the oxygen injection valve, so that the real-time active oxygen supplementing regulation and control of the combustion of the scramjet engine are realized, and the stable working performance of the scramjet engine under the flight working condition and the extreme working condition is improved. Preferably, the oxygen injection valve of at least one set of oxygen injection holes adjacent to the igniter is selectively opened; or selecting oxygen injection valves for fully opening all groups of oxygen injection holes; or sequentially opening the oxygen injection valves of each group of oxygen injection holes from the near to the far or from the far to the near according to the distance between the oxygen injection valves and the igniter; or, firstly, all oxygen injection valves of all groups of oxygen injection holes are opened, then, according to pressure data and photoelectric signal data conditions of all measuring point positions fed back in real time, the opening/closing conditions of the oxygen injection valves of all groups of oxygen injection holes are adjusted in real time, specifically, the oxygen injection valves of all groups of oxygen injection holes close to the position of a relatively small measuring point of the pressure data and the photoelectric signal data are opened, and the oxygen injection valves of all groups of oxygen injection holes close to the position of a relatively large measuring point of the pressure data and the photoelectric signal data are closed, so that the self-adaption adjustment is carried out until all the measuring point positions are monitored to be in a stable and normal combustion state.
(3) Active enhanced combustion
When the combustion performance of the engine needs to be improved, all oxygen injection valves and igniters are opened to realize combustion enhancement, and dynamic adjustment is performed according to signals fed back by the pressure sensor and the photoelectric sensor. Specifically, according to the pressure data and the photoelectric signal data conditions of all measuring point positions fed back in real time, the opening/closing conditions of the oxygen injection valves of all groups of oxygen injection holes are adjusted in real time, specifically, the oxygen injection valves of all groups of oxygen injection holes close to the positions of relatively smaller measuring point positions of the pressure data and the photoelectric signal data are opened, and the oxygen injection valves of all groups of oxygen injection holes close to the positions of relatively larger measuring point positions of the pressure data and the photoelectric signal data are closed, so that dynamic adjustment is performed, and combustion reinforcement of the whole combustion chamber is realized.
The real-time monitoring of the combustion state of the combustion chamber is realized through real-time monitoring and dynamic feedback based on the pressure signal and the photoelectric signal of the combustion chamber of the scramjet engine; the active enhanced combustion and the regulation and control of the combustion state are realized by the oxygen supplementing method in the concave cavity of the combustion chamber.
The invention is not a matter of the known technology.
The technical features of the above embodiments may be arbitrarily combined, and for brevity, all of the possible combinations of the technical features of the above embodiments are not described, however, as long as there is no contradiction between the combinations of the technical features, they should be regarded as the scope of loading of the present specification.
The above examples merely represent a few embodiments of the present application, which are described in more detail and are not to be construed as limiting the scope of the invention. It should be noted that it would be apparent to those skilled in the art that various modifications and improvements could be made without departing from the spirit of the present application, which would be within the scope of the present application. Accordingly, the scope of protection of the present application is to be determined by the claims appended hereto.
Claims (12)
1. The method for actively supplementing oxygen in real time during combustion of the scramjet engine is characterized by comprising the following steps of:
acquiring pressure data of the inner wall surface of the combustion chamber and self-luminous radiation data of flame in real time;
determining the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired pressure data of the inner wall surface of the combustion chamber and the self-luminous flame radiation data;
and generating corresponding control signals to oxygen injection valves corresponding to the combustion chambers according to the current flame combustion state to realize active oxygen supplementing and active combustion regulation.
2. The method for real-time active oxygen supply regulation and control of scramjet engine combustion according to claim 1, wherein the combustion chamber is a concave cavity combustion chamber, a concave cavity is arranged on the lower wall surface of the combustion chamber, and an igniter is arranged on the bottom wall surface of the concave cavity 。
3. The method for regulating and controlling the real-time active oxygen supplement of the combustion of the scramjet engine according to claim 2, wherein a plurality of groups of pressure measuring points are arranged at different combustion chamber length positions of the lower wall surface of the combustion chamber along the movement direction of the supersonic incoming flow and are used for measuring the pressure data at different positions of the inner wall surface of the combustion chamber in real time; a plurality of groups of photoelectric probes are arranged at different positions of the length of the combustion chamber on the upper wall surface of the combustion chamber and are used for measuring flame self-luminous radiation data at different positions of the inner wall surface of the combustion chamber in real time.
4. The method for real-time active oxygen supply regulation of scramjet engine combustion according to claim 2, wherein a plurality of sets of pressure measuring points are arranged on the lower wall surface of the combustion chamber upstream of the concave cavity, a plurality of sets of pressure measuring points are arranged on the bottom wall surface of the concave cavity upstream of the igniter, at least one set of pressure measuring points are arranged on the bottom wall surface of the concave cavity downstream of the igniter, and at least one set of pressure measuring points are arranged on the lower wall surface of the combustion chamber downstream of the concave cavity.
5. The method for regulating and controlling the real-time active oxygen supplementing of the combustion of the scramjet engine according to claim 3 or 4, wherein a group of photoelectric probes are correspondingly arranged on the upper wall surface of the combustion chamber corresponding to the upper part of each group of pressure measuring points, and the pressure measuring points and the photoelectric probes are correspondingly arranged up and down.
6. The method for regulating and controlling the real-time active oxygen supplement of the combustion of the scramjet engine according to claim 5, wherein at least one group of oxygen injection holes are formed in the wall surface of the concave cavity at the upstream of the igniter, at least one group of oxygen injection holes are formed in the wall surface of the concave cavity at the downstream of the igniter, an oxygen source supplies oxygen to each group of oxygen injection holes through an oxygen supply pipeline, each group of oxygen injection holes corresponds to an independent oxygen supply branch communicated with the oxygen source, independent oxygen injection valves are arranged on the oxygen supply branches corresponding to each group of oxygen injection holes, and independent control of each group of oxygen injection holes is realized through the oxygen injection valves.
7. The method for controlling the real-time active oxygen supplement of the combustion of the scramjet engine according to claim 6, wherein the cavity wall surface comprises a cavity front wall, a cavity bottom wall surface and a cavity rear wall, the cavity front wall is vertically arranged with the lower wall surface of the combustion chamber at the upstream of the adjacent cavity, and forms a vertical step with the bottom wall of the cavity; the rear wall of the concave cavity is obliquely arranged relative to the bottom wall surface of the concave cavity to form an oblique transition between the concave cavity and the lower wall surface of the combustion chamber at the downstream of the concave cavity.
8. The method for regulating and controlling the oxygen supply of the scramjet engine in real time according to claim 7, wherein the front wall of the concave cavity is provided with at least one group of oxygen injection holes, the bottom wall surface of the concave cavity at the upstream of the igniter is provided with at least one group of oxygen injection holes, and the rear wall of the concave cavity is provided with at least one group of oxygen injection holes.
9. The method of real-time active oxygen replenishment regulation of scramjet engine combustion of claim 8, wherein determining the current flame combustion state comprises:
setting wall pressure intervals and flame self-luminous radiation intensity intervals of different positions in a combustion chamber under different flame combustion states, wherein the flame combustion states comprise a flame normal combustion state, a flame local weak combustion state, a flame global extinction or near extinction state and a flame intensified combustion state;
judging the current flame combustion state according to the currently acquired wall pressure data at different positions in the combustion chamber and the flame self-luminous radiation intensity data.
10. The method for actively controlling oxygen supplementation and combustion in real time of a scramjet engine according to claim 9, wherein generating corresponding control signals to oxygen injection valves corresponding to the combustion chambers according to the current flame combustion state comprises the following steps: according to the pressure data and the photoelectric signal data conditions of all the measuring point positions fed back in real time, the opening/closing conditions of the oxygen injection valves of all the oxygen injection holes are adjusted in real time, the oxygen injection valves of all the oxygen injection holes close to the measuring point positions with relatively smaller pressure data and photoelectric signal data are opened, and the oxygen injection valves of all the oxygen injection holes close to the measuring point positions with relatively larger pressure data and photoelectric signal data are closed, so that the self-adaption adjustment is performed until all the measuring point positions are monitored to be in a stable and normal combustion state.
11. The method for regulating and controlling the combustion real-time active oxygen supplementing of the scramjet engine according to claim 9, wherein if wall pressure data measured by a pressure measuring point at a certain position are located between wall pressure areas in a corresponding flame local weak combustion state or flame self-luminous radiation intensity data measured by a photoelectric probe corresponding to the position are located between flame self-luminous radiation intensity areas in a corresponding flame local weak combustion state, oxygen supplementing injection is carried out by opening an oxygen injection valve corresponding to a group of oxygen injection holes closest to the position until the wall pressure data measured by the pressure measuring point at the position are located between wall pressure areas in a corresponding flame normal combustion state, and the oxygen injection valve corresponding to the group of oxygen injection holes closest to the position is closed;
if the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure interval in which the corresponding flame is globally extinguished or is close to the extinguishing state or the flame self-luminous radiation intensity data measured by the photoelectric probes corresponding to all positions are in the flame self-luminous radiation intensity interval in which the corresponding flame is globally extinguished or is close to the extinguishing state, opening the oxygen injection valves corresponding to all groups of oxygen injection holes to perform oxygen supplementing injection until the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure interval in which the corresponding flame is in the normal combustion state, and closing the oxygen injection valves corresponding to all groups of oxygen injection holes;
If the combustion performance of the combustion chamber needs to be improved currently, starting the igniter and the oxygen injection valves corresponding to all groups of oxygen injection holes, so that the wall pressure data measured by the pressure measurement points at all positions are located in the wall pressure interval of the corresponding flame enhanced combustion state, and combustion enhancement is realized.
12. The utility model provides a real-time initiative oxygenating regulation and control device of scramjet engine burning which characterized in that includes:
the combustion chamber is a concave cavity combustion chamber, a concave cavity is arranged on the lower wall surface of the combustion chamber, and an igniter is arranged on the bottom wall surface of the concave cavity ； Along the movement direction of supersonic incoming flow, the fuel is burntA plurality of groups of pressure measuring points are arranged at different combustion chamber length positions of the lower wall surface of the combustion chamber and are used for measuring pressure data at different positions of the inner wall surface of the combustion chamber in real time; a plurality of groups of photoelectric probes are arranged at different combustion chamber length positions of the upper wall surface of the combustion chamber and are used for measuring flame self-luminous radiation data at different positions of the inner wall surface of the combustion chamber in real time; at least one group of oxygen injection holes are formed in the concave cavity wall surface at the upstream of the igniter, at least one group of oxygen injection holes are formed in the concave cavity wall surface at the downstream of the igniter, an oxygen source supplies oxygen to each group of oxygen injection holes through an oxygen supply pipeline, each group of oxygen injection holes corresponds to an independent oxygen supply branch communicated with the oxygen source, independent oxygen injection valves are arranged on the oxygen supply branches corresponding to each group of oxygen injection holes, and independent control of each group of oxygen injection holes is realized through the oxygen injection valves;
The signal control system is used for determining the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired pressure data of the inner wall surface of the combustion chamber and the flame self-luminous radiation data; and generating corresponding control signals to oxygen injection valves corresponding to the combustion chambers according to the current flame combustion state to realize active oxygen supplementing and active combustion regulation.
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