CN114215653A - Combustion mode conversion method for ramjet engine - Google Patents
Combustion mode conversion method for ramjet engine Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
- F02D41/02—Circuit arrangements for generating control signals
- F02D41/18—Circuit arrangements for generating control signals by measuring intake air flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- 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
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Abstract
The invention provides a combustion mode conversion method for a ramjet engine, which comprises the following steps of firstly, acquiring the current combustion heat release spatial distribution of a combustion area; then, determining the current combustion mode of the combustion chamber according to the current combustion heat release spatial distribution; secondly, determining the working frequency of the driving power supply according to the current combustion mode and the target combustion mode; finally, controlling a driving power supply to drive a plasma igniter to emit plasma flow along the air inlet direction according to the working frequency; the plasma flow directly acts in the combustion area, and the combustion heat release spatial distribution in the combustion area realizes quick dynamic response, so that the combustion mode in the combustion area is quickly changed, the thermal energy consumption is reduced, and a new method is provided for solving the problem of quickly and accurately converting the combustion mode of the ramjet.
Description
Technical Field
The invention relates to the technical field of engine improvement, in particular to a combustion mode conversion method for a ramjet engine.
Background
The ramjet is one of the core aircrafts in the technical field of hypersonic propulsion, and has become a research hotspot in countries around the world in recent years. In the wide mach number flight process, the ramjet has extreme thermophysical problems of high speed, high temperature and the like, which affect the thrust performance and safety performance of the aircraft and generate impact on the autonomy and stability of a control system, and the basic working state of the ramjet is usually expressed by a combustion mode. The nature of the combustion modes is the spatial distribution of the aerodynamic thermodynamic parameters in the engine, with different combustion modes corresponding to different aircraft performances. The engine is subjected to compression under different flight conditions to achieve different combustion modes, during which the spatial distribution characteristics of the engine flow field, combustion field parameters along the channels are large. It is therefore important to control and influence the combustion mode formation and conversion of the ramjet engine to extend the operating range of the ramjet engine and to exploit the potential of the engine.
In order to obtain high thrust, high specific impulse and other performances when the ramjet engine operates in a wide mach number range, the conversion of combustion modes needs to be optimally designed, and a combustion mode cluster capable of realizing good conversion and change under different flight conditions is obtained. The traditional idea of controlling combustion mode conversion is pneumatic thermal regulation or geometric regulation of an engine configuration, the current pneumatic thermal regulation way is generally a graded injection mode, although the use is wide, the effectiveness of a combustion organization is low, and even the heat release among an air inlet, a combustion chamber and a tail injection device is not coordinated; the geometric adjustment of the engine generally changes the characteristic section area of the engine, adopts the variable geometric continuous adjustment and other modes, and is complex and difficult to realize.
In view of the above problems, it is necessary to provide a combustion mode conversion method for a ramjet engine, which realizes a quick and accurate conversion between combustion modes of the ramjet engine.
Disclosure of Invention
The invention aims to provide a combustion mode conversion method for a ramjet engine, which solves the problem that the combustion mode conversion of the ramjet engine by adopting the traditional method is complex and difficult to realize.
To achieve the above object, the present invention provides a combustion mode conversion method for a ramjet engine, comprising the steps of:
acquiring the current combustion heat release spatial distribution of a combustion area;
determining the current combustion mode of the combustion chamber according to the current combustion heat release spatial distribution;
determining the working frequency of a driving power supply according to the current combustion mode and the target combustion mode; the target combustion mode is a required combustion mode;
and controlling a driving power supply to drive the plasma igniter to emit plasma flow along the air inlet direction according to the working frequency.
Determining the current combustion mode of the combustion chamber according to the current combustion heat release spatial distribution specifically comprises:
the spatial distribution of the heat release of combustion and the combustion mode follow the following relation:
wherein,
representing the spatial distribution of the aerodynamic thermodynamic parameter, corresponding to the combustion mode,
the spatial distribution of the cross section of the engine is shown,
representing the spatial distribution of heat release from combustion, Ma representing the Mach-ZehnderNumber, AxDenotes a cross-sectional area, x denotes a position in the combustion chamber, k denotes a specific heat ratio, T denotes a temperature, and T denotes a time.
Optionally, determining the operating frequency of the driving power supply according to the current combustion mode and the target combustion mode specifically includes:
judging whether the current combustion mode is consistent with the target combustion mode or not to obtain a judgment result;
when the judgment result is consistent, keeping the current working frequency of the driving power supply unchanged;
and when the judgment result is inconsistent, adjusting the current working frequency of the driving power supply to a target working frequency corresponding to a target combustion mode.
Optionally, the plasma igniter is installed in the center of the combustion chamber, the generated plasma flow is located at the central axis of the combustion chamber, and the plasma emitting end of the plasma igniter can act on the combustion area to realize the adjustment of the spatial distribution of the combustion heat release in the combustion area.
Optionally, the driving power source is at least one of a low-frequency direct-current power source or a high-frequency pulse power source.
Optionally, the current combustion heat release spatial distribution of the combustion zone is obtained by means of a plurality of measuring devices, and the plurality of measuring devices are uniformly distributed along the central axis of the combustion chamber.
According to the specific invention content provided by the invention, the invention discloses the following technical effects:
the invention provides a combustion mode conversion method for a ramjet engine, which comprises the following steps of firstly, acquiring the current combustion heat release spatial distribution of a combustion area; then, determining the current combustion mode of the combustion chamber according to the current combustion heat release spatial distribution; secondly, determining the working frequency of the driving power supply according to the current combustion mode and the target combustion mode; finally, controlling a driving power supply to drive a plasma igniter to emit plasma flow along the air inlet direction according to the working frequency; the plasma flow directly acts on the combustion area, so that the combustion heat release spatial distribution in the combustion area realizes rapid dynamic response, and the combustion mode in the combustion area is rapidly changed; the invention is different from the traditional method for carrying out combustion mode conversion by changing the fuel staged injection mode or changing the structure of the engine, and the invention utilizes plasma to change the combustion mode of a combustion chamber; specifically, the current combustion mode is determined by collecting the current combustion heat release spatial distribution of the combustion chamber, according to the relation between the combustion heat release spatial distribution and the combustion mode, the working frequency of a driving power supply connected with the plasma igniter is determined according to the current combustion mode and the target combustion mode, the driving power supply drives the plasma igniter to generate plasma flows with different high-energy active particle concentrations, the plasma flows directly act in the combustion area, the combustion heat release spatial distribution of the combustion area realizes rapid dynamic response, the combustion mode in the combustion area is rapidly changed, the thermal energy consumption is reduced, and a new method is provided for solving the problem of rapid and accurate change of the combustion mode of the ramjet engine.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a flowchart of a combustion mode conversion method A1-A4 for a ramjet engine according to embodiment 1 of the present invention;
fig. 2 is a detailed flowchart of step a3 in the method according to embodiment 1 of the present invention;
fig. 3 is a schematic structural diagram of a combustion mode conversion device for a ramjet engine according to embodiment 2 of the present invention;
fig. 4 is a schematic diagram showing the change of the ram engine on-way mass weighted mach number in the test provided in embodiment 3 of the present invention.
Symbol interpretation: 1: fixing the module; 2: a plasma igniter; 3: a combustion chamber wall; 4: and a measuring module.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a combustion mode conversion method for a ramjet engine, which solves the problem that the combustion mode conversion of the ramjet engine by adopting the traditional method is complex and difficult to realize.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example 1:
as shown in fig. 1, the present invention provides a combustion mode conversion method for a ramjet engine, comprising the steps of:
a1, acquiring the current combustion heat release spatial distribution of the combustion zone;
a2, determining the current combustion mode of the combustion chamber according to the current combustion heat release spatial distribution;
the spatial distribution of the combustion heat release and the spatial distribution of the aerodynamic heat parameter follow the following relation:
wherein,
representing the spatial distribution of the aerodynamic thermal parameter,
the spatial distribution of the cross section of the engine is shown,
representing the spatial distribution of heat release from combustion, Ma representing the flight Mach number, AxRepresents a cross-sectional area, x represents a position in the combustion chamber, k represents a specific heat ratio, T represents a temperature, and T represents a time;
at flight Mach number Ma and engine cross-sectional area AxOn the premise of fixation, the spatial distribution of heat release of combustion
Left side of the sum relation
There is a fixed correspondence;
and different aerodynamic thermal parameters
The current combustion heat release spatial distribution of the combustion chamber is input into the relational expression to determine the corresponding current combustion mode;
a3, determining the working frequency of the driving power supply according to the current combustion mode and the target combustion mode; the target combustion mode is a required combustion mode;
in practical application, as shown in fig. 2, the step a3 specifically includes:
a31, judging whether the current combustion mode is consistent with the target combustion mode, and obtaining a judgment result;
a32, when the judgment result is consistent, keeping the current working frequency of the driving power supply unchanged;
a33, when the judgment results are inconsistent, adjusting the current working frequency of the driving power supply to a target working frequency corresponding to a target combustion mode;
the working frequency of the driving power supply has an obvious corresponding relation with the concentration of high-energy active particles in the plasma flow generated by the plasma igniter; as the operating frequency of the driving power supply increases, the concentration of energetic active particles in the plasma stream generated by the plasma igniter also increases;
in the combustion chamber, the combustion zone is induced to move to the high-energy active particle dense region to generate the temperature change rate
In a high-speed co-flow environment, changes in the rate of temperature change result in a spatial distribution of combustion heat release
A change occurs;
according to the relation between the spatial distribution of the combustion heat release and the spatial distribution of the aero-thermal power parameter, the spatial distribution of the combustion heat release is obtained
The change necessarily causes the change of the spatial distribution of the aerodynamic thermal parameters, namely, the combustion mode of the combustion chamber is changed;
and A4, controlling the driving power supply to drive the plasma igniter to emit the plasma flow along the air inlet direction according to the working frequency.
When the driving power supply works at a lower working frequency and the plasma flow generated by the plasma igniter does not act on the combustion area, the combustion mode of the combustion area is in a supersonic combustion mode, at the moment, the concentration of the plasma flow generated by the plasma igniter is increased by increasing the working frequency of the driving power supply, the attraction force on the combustion area is increased, the temperature change rate is generated, and therefore the combustion heat release spatial distribution and the pneumatic heat parameter spatial distribution are changed successively, and the subsonic combustion mode is formed in the combustion chamber of the engine;
on the contrary, when the subsonic combustion mode in the combustion chamber is required to be converted into the supersonic combustion mode, the working frequency of the driving power supply is reduced, the concentration of the generated plasma flow is gradually reduced, the attraction to the combustion area is reduced, the spatial distribution of combustion heat release and the spatial distribution of aerodynamic heat parameters are changed successively, and the supersonic combustion mode is formed in the combustion chamber of the engine.
In specific implementation, in order to enable the plasma flow to act on the combustion area better, the plasma igniter is arranged in the center of the combustion chamber, the generated plasma flow is located at the central axis of the combustion chamber, the plasma emission end of the plasma igniter can act on the combustion area, and the adjustment of the combustion heat release spatial distribution is realized in the combustion area.
In some embodiments, the driving power source is at least one of a low frequency direct current power source or a high frequency pulsed power source. The current combustion heat release spatial distribution of the combustion area is obtained by means of a plurality of measuring devices, and the plurality of measuring devices are uniformly distributed along the central axis of the combustion chamber and are respectively used for measuring the pressure intensity of different positions of the combustion area to obtain the pressure intensity distribution in the combustion area.
Converting the temperature change rate by using a formula obtained by combining the collected pressure data distribution with a one-dimensional mass, momentum and energy equation:
wherein, CfRepresenting a friction resistance coefficient, D representing a flow channel equivalent diameter, and p representing a pressure value;
and obtaining the combustion heat release spatial distribution in the combustion zone according to the temperature change rate.
According to the combustion mode conversion method for the ramjet engine, the current combustion mode is correspondingly determined according to the current combustion heat release spatial distribution obtained by the measuring module and the operation rule corresponding to the combustion mode and the combustion heat release spatial distribution, the working frequency of the driving power supply is determined according to the current combustion mode and the target combustion mode, the plasma igniter is driven to generate plasma flows with different high-energy active particle concentrations, the high-energy active particles directly act in the combustion chamber, the combustion heat release spatial distribution is enabled to achieve rapid dynamic response, the combustion mode in the combustion chamber is rapidly enabled to be changed, thermal energy consumption is reduced, and a new method is provided for solving the problem of rapid and accurate conversion of the combustion mode of the ramjet engine.
Example 2:
as shown in the schematic structural diagram of fig. 3, on the other hand, the present embodiment further provides a combustion mode conversion device for a ramjet engine, where the ramjet engine includes an air inlet channel and a combustion chamber, and the combustion mode conversion device includes a fixed module 1, a plasma igniter 2, a driving power supply, a measurement module 4, and a control module;
the fixing module 1 is fixed in the combustion chamber, is connected with the plasma igniter 2 and fixes the plasma igniter 2 in the combustion chamber along the air inlet direction; the plasma igniter 2 is used for changing the combustion mode of the combustion area in a mode of emitting plasma;
the driving power supply is connected with the plasma igniter 2 and is used for driving the plasma igniter 2 to emit plasma flow; the driving power supply is at least one of a low-frequency direct current power supply or a high-frequency pulse power supply.
The measuring module 4 is arranged on the wall 3 of the combustion chamber and is used for detecting the spatial distribution of the combustion heat release of the combustion area;
the control module is connected with the driving power supply and the measuring module 4 and used for obtaining the combustion heat release spatial distribution of the combustion area, determining the current combustion mode according to the combustion heat release spatial distribution of the combustion area, and determining and adjusting the working frequency of the driving power supply according to the current combustion mode and the target combustion mode.
In order to monitor the temperature distribution in the combustion zone comprehensively, the measuring module 4 includes a plurality of measuring devices, which are distributed uniformly along the central axis of the combustion chamber.
According to the combustion mode conversion device for the ramjet engine, the plasma igniter 2 is erected at the central axis of the combustion chamber through the fixing module 1 in the ramjet engine, the driving power supply is used for driving the plasma igniter 2 to emit plasma flow along the air inlet direction, the plasma flow is directly acted on the combustion chamber, and the combustion mode of a combustion area is changed.
Example 3:
in this embodiment, a specific test is performed to verify the combustion mode conversion method provided by the present invention, specifically including the following steps:
(1) air flows into the engine; (2) engine fuel injection into the engine; (3) forming a supersonic combustion mode in a combustion chamber of the engine; (4) the plasma igniter is converted into a certain strong power to work, and a subsonic combustion mode is formed in the engine combustion chamber.
The verification result shown in fig. 4 is obtained by implementing the above technical scheme. Wherein, when T is 0, the curve of the mass weighted Mach number under the common combustion condition is obtained. After the plasma igniter is started at a certain strong excitation power, a path mass weighted Mach number curve of the engine is recorded every 0.2s, the curve is stable until T is 0.8s, a large-area subsonic velocity region appears, and the lowest point of the Mach number moves forwards. The result of the operation according to the above steps can be seen: judging a super-combustion mode with the overall Mach number larger than 1 when T is 0 according to the combustion mode; with the enhancement of the action of the discharge plasma, the Mach number in the combustion chamber is gradually reduced, the flow velocity of the air flow is changed, and black arrows represent the Mach number change sequence along with time. At T0.8 s, the curve exhibits a large area of subsonic velocity in the main combustion zone and the combustion chamber inlet is also subsonic, which is judged to be a completely subsonic mode. This shows that the combustion heat release in the combustion chamber is enhanced, and the large-area supersonic airflow is changed into the subsonic airflow, thereby realizing the regulation of the speed from the total temperature along the way to the airflow along the way and the conversion of the combustion mode.
Portions of the technology may be considered "articles" or "articles of manufacture" in the form of executable code and/or associated data, which may be embodied or carried out by a computer readable medium. Tangible, non-transitory storage media may include memory or storage for use by any computer, processor, or similar device or associated module. For example, various semiconductor memories, tape drives, disk drives, or any similar device capable of providing a storage function for software.
All or a portion of the software may sometimes communicate over a network, such as the internet or other communication network. Such communication may load software from one computer device or processor to another. For example, the following examples: from a server or host computer of the video object detection device to a hardware platform of a computer environment, or other computer environment implementing a system, or similar functionality associated with providing information needed for object detection. Therefore, another medium capable of transferring the software elements may also be used as a physical connection between local devices, such as optical waves, electric waves, electromagnetic waves, etc., and the propagation is realized through cables, optical cables, air, etc. The physical medium used for the carrier wave, such as an electric, wireless or optical cable or the like, may also be considered as the medium carrying the software. As used herein, unless limited to a tangible "storage" medium, other terms referring to a computer or machine "readable medium" refer to media that participate in the execution of any instructions by a processor.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; those skilled in the art will appreciate that the modules or steps of the invention described above can be implemented using general purpose computing devices, or alternatively, they can be implemented using program code executable by computing devices, such that they are stored in a storage device and executed by computing devices, or they can be separately fabricated into individual integrated circuit modules, or multiple ones of them can be fabricated into a single integrated circuit module. The present invention is not limited to any specific combination of hardware and software.
Meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (6)
1. A combustion mode conversion method for a ramjet engine, characterized by comprising:
acquiring the current combustion heat release spatial distribution of a combustion area;
determining the current combustion mode of the combustion chamber according to the current combustion heat release spatial distribution;
determining the working frequency of a driving power supply according to the current combustion mode and the target combustion mode; the target combustion mode is a required combustion mode;
and controlling a driving power supply to drive the plasma igniter to emit plasma flow along the air inlet direction according to the working frequency.
2. The combustion mode conversion method according to claim 1, wherein the determining a current combustion mode of the combustion chamber according to the current combustion heat release spatial distribution specifically comprises:
the spatial distribution of the heat release of combustion and the combustion mode follow the following relation:
wherein,
representing the spatial distribution of the aerodynamic thermodynamic parameter, corresponding to the combustion mode,
the spatial distribution of the cross section of the engine is shown,
representing the spatial distribution of heat release from combustion, Ma representing the flight Mach number, AxDenotes a cross-sectional area, x denotes a position in the combustion chamber, k denotes a specific heat ratio, T denotes a temperature, and T denotes a time.
3. The combustion mode conversion method according to claim 1, wherein the determining an operating frequency of a driving power supply according to the current combustion mode and a target combustion mode specifically comprises:
judging whether the current combustion mode is consistent with the target combustion mode or not to obtain a judgment result;
when the judgment result is consistent, keeping the current working frequency of the driving power supply unchanged;
and when the judgment result is inconsistent, adjusting the current working frequency of the driving power supply to a target working frequency corresponding to a target combustion mode.
4. The combustion model conversion method according to claim 1, wherein the plasma igniter is installed at the center of the combustion chamber, the generated plasma flow is at the central axis position of the combustion chamber, and the plasma emitting end of the plasma igniter is capable of acting on the combustion zone, thereby realizing the adjustment of the spatial distribution of the combustion heat release in the combustion zone.
5. The combustion mode conversion method according to claim 1, wherein the driving power source is at least one of a low-frequency direct-current power source or a high-frequency pulse power source.
6. The combustion mode conversion method according to claim 1, wherein the current combustion heat release spatial distribution of the combustion zone is obtained by means of a plurality of measuring instruments, which are uniformly distributed along the central axis of the combustion chamber.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4381642A (en) * | 1980-06-20 | 1983-05-03 | The Boeing Company | Ramjet engine |
| US20040050061A1 (en) * | 2002-09-13 | 2004-03-18 | Schmotolocha Stephen N. | Compact swirl augmented afterburners for gas turbine engines |
| CN107576446A (en) * | 2017-08-02 | 2018-01-12 | 南京航空航天大学 | A kind of active probe device and method of scramjet engine distance piece shock train leading edge |
| FR3068766A1 (en) * | 2017-07-10 | 2019-01-11 | Office National D'etudes Et Recherches Aerospatiales | COMBUSTION IGNITION OR STABILIZATION SYSTEM |
| CN209163956U (en) * | 2018-11-15 | 2019-07-26 | 厦门大学 | A kind of three power combination engines that sub- combustion can be switched with super burn channel |
| CN111594346A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Mesoscale rocket-based combined cycle engine |
-
2021
- 2021-12-13 CN CN202111514234.4A patent/CN114215653A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4381642A (en) * | 1980-06-20 | 1983-05-03 | The Boeing Company | Ramjet engine |
| US20040050061A1 (en) * | 2002-09-13 | 2004-03-18 | Schmotolocha Stephen N. | Compact swirl augmented afterburners for gas turbine engines |
| FR3068766A1 (en) * | 2017-07-10 | 2019-01-11 | Office National D'etudes Et Recherches Aerospatiales | COMBUSTION IGNITION OR STABILIZATION SYSTEM |
| CN107576446A (en) * | 2017-08-02 | 2018-01-12 | 南京航空航天大学 | A kind of active probe device and method of scramjet engine distance piece shock train leading edge |
| CN209163956U (en) * | 2018-11-15 | 2019-07-26 | 厦门大学 | A kind of three power combination engines that sub- combustion can be switched with super burn channel |
| CN111594346A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Mesoscale rocket-based combined cycle engine |
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| Title |
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| 张岩;朱韶华;刘刚;李轩;徐旭;: "双模态冲压发动机中的模态转换研究综述", 推进技术, no. 12 * |
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