CN115164235A - Rotary detonation combustion chamber utilizing radial expansion of detonation waves - Google Patents
Rotary detonation combustion chamber utilizing radial expansion of detonation waves Download PDFInfo
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- CN115164235A CN115164235A CN202210875280.5A CN202210875280A CN115164235A CN 115164235 A CN115164235 A CN 115164235A CN 202210875280 A CN202210875280 A CN 202210875280A CN 115164235 A CN115164235 A CN 115164235A
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- detonation
- combustion chamber
- radial expansion
- rotary
- turbine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
Abstract
The invention provides a rotary detonation combustion chamber utilizing radial expansion of detonation waves. The shaft work output device is arranged at the center of the hollow cylindrical rotary detonation combustion chamber, so that the kinetic energy of the radial expansion of the detonation waves is converted into shaft work which is output outwards, and the shaft work can be used for driving a motor to generate electricity and driving a power turbine to drive a propeller or a rotor wing and the like; meanwhile, the cooling heat exchange device carries out regenerative cooling by using the countercurrent oxidant or fuel, thereby prolonging the service life of the combustion chamber, improving the atomization effect of the fuel or the oxidant and improving the combustion efficiency; different cooling and heat exchange effects can be realized by changing the working medium of the cooling and heat exchange pipeline. The invention not only effectively utilizes the kinetic energy of the radial expansion of the rotary detonation wave, but also fully absorbs the waste heat of the radial expansion of the high-temperature and high-pressure product, and utilizes the radial expansion of the rotary detonation wave to output energy in various forms. The invention can be used in the fields of detonation propulsion, cogeneration and the like.
Description
Technical Field
The invention belongs to the fields of detonation propulsion, cogeneration and the like, and particularly relates to a rotary detonation combustor utilizing radial expansion of detonation waves.
Background
The rotary detonation combustion is one of important forms of detonation combustion, has potential advantages of high thermal efficiency, single ignition and the like, and has become a research hotspot in the field of aerospace propulsion in recent years. The rotary detonation combustion generally occurs in an annular combustion chamber with an opening at one end, forms a detonation wave at the head of the combustion chamber, and rotationally propagates along the circumferential direction; meanwhile, the rotary detonation wave expands axially, and high-temperature and high-pressure products are discharged from the opening end to generate thrust.
With the progress of research, when it is necessary to reduce the thermal protection requirement, researchers have eliminated the inner column from the annular combustion chamber, and for such an empty cylindrical combustion chamber without the inner column, the detonation wave will expand in both the radial and axial directions. The axial expansion of the detonation wave has the beneficial effects of impacting a turbine and generating thrust; but the radial expansion not only causes the peak pressure of the detonation wave to drop, but also causes the instability of propagation and even blowout; in addition, the energy of the radial expansion of the detonation wave is not fully utilized, so that the thermal efficiency is reduced.
Therefore, aiming at the problems, the design of the rotary detonation combustion chamber capable of effectively utilizing the radial expansion of the detonation wave is very critical, the rotary detonation combustion chamber utilizing the radial expansion of the detonation wave can just meet the requirements, and the performance improvement and the practical application of the rotary detonation combustion mode have important values.
Disclosure of Invention
Technical problem to be solved
Aiming at the problem that radial expansion of rotary detonation waves is not fully utilized when the detonation waves in the hollow cylindrical combustion chamber expand laterally, the invention provides a rotary detonation combustion chamber utilizing the radial expansion of the detonation waves, and the rotary detonation combustion chamber is used for optimizing and improving an aero-engine/gas turbine based on rotary detonation combustion. The shaft work output device is arranged at the center of the hollow cylindrical rotary detonation combustion chamber, so that the kinetic energy of the radial expansion of the detonation waves is converted into shaft work which is output outwards, and the shaft work can drive a motor to generate electricity and drive a power turbine to drive a propeller or a rotor wing and the like; meanwhile, cooling heat exchange pipelines are arranged at the front end of the combustion chamber and inside the turbine guide vane column, and the countercurrent oxidant or fuel is used for regenerative cooling, so that the rotary detonation combustion chamber is protected, the service life of the combustion chamber is prolonged, the fuel or oxidant atomization effect is improved, and the combustion efficiency is improved; in addition, different cooling and heat exchange effects can be realized by changing working media in the cooling and heat exchange pipeline, for example, water is used as the working media, and the extracted waste heat of the combustion chamber is used for domestic heating. The invention can be used in the fields of detonation propulsion, cogeneration and the like.
In order to achieve the purpose, the invention adopts the technical scheme that:
a rotary detonation combustion chamber utilizing detonation wave radial expansion comprises a hollow cylindrical rotary detonation combustion chamber, a shaft work output device and a cooling heat exchange pipeline.
The hollow cylinder-shaped rotary detonation combustion chamber body is composed of a combustion chamber front end, an oxidant annular seam, fuel spray holes, a combustion chamber annular wall surface and an ignition device. The front end of the combustion chamber mainly comprises a front end head of the combustion chamber and a front end wall surface of the combustion chamber. At the front end of the combustion chamber, an oxidant and fuel are mixed in a circular seam-jet hole mode, the oxidant is compressed by a compressor and enters the rotary detonation combustion chamber through a circular seam in a high-pressure airflow mode; injecting fuel into the annular flow channel through injection holes uniformly distributed along the circumferential direction; the mixing and impacting position of the oxidant and the fuel is close to the annular wall surface of the combustion chamber, so that a backflow zone is formed, and the mixing effect is effectively improved. In actual operation, various mixing methods such as orifice impingement and coaxial centrifugation should be selected according to actual requirements such as physical properties of the fuel and the oxidant and the supply flow rate.
The shaft work output device consists of a turbine guide blade column, a turbine blade column, a guide cone, a support and a transmission shaft. In the detonation combustion cavity, the turbine guide vane columns and the annular wall surface of the combustion chamber are coaxial and arranged along the circumferential direction and are fixedly connected to the maximum radius position of the front end wall surface of the combustion chamber; the circumferential pitch of the rotating detonation combustor is the same as the radial width of a turbine guide vane column, and the length of the rotating detonation combustor is 1/3 of the length of the rotating detonation combustor. The turbine blade column is connected with the transmission shaft through a bracket to form a whole; the turbine blade columns are arranged along the circumferential direction, the circumferential radius of the turbine blade columns is 3/5 of the radius of the front end wall surface of the combustion chamber, the circumferential pitch of the turbine blade columns is the same as the section length of the turbine blade columns, and the length of the turbine blade columns is 1/3 of the length of the detonation combustion chamber. The radial expansion wave of knocking combustion directly impacts the turbine blade columns after passing through the turbine guide blade columns, and then is discharged backwards through the guide cone, so that the flow loss is effectively reduced, and the shaft work output efficiency is improved. The shaft work output by the transmission shaft can drive a motor to generate power and drive a power turbine to drive a propeller or a rotor wing and the like.
And the cooling heat exchange pipeline is arranged at the front end of the combustion chamber and inside the turbine guide vane column and is provided with an inlet and an outlet of working medium. Different working media can be connected into the cooling heat exchange pipeline according to actual needs, such as: when heating is carried out, the working medium is water, the temperature of the front end of the combustion chamber and the turbine guide vane column can be rapidly reduced, and the combustion efficiency is improved; when the regeneration cooling is carried out, the working medium is fuel or oxidant, and the initial temperature rise of the reactant is helpful for improving the detonation success rate.
Has the advantages that:
the rotary detonation combustion chamber utilizing the radial expansion of the detonation waves provided by the invention is adopted to optimize and improve an aero-engine/gas turbine based on rotary detonation combustion, and an axial work output device is arranged at the center of the hollow cylindrical rotary detonation combustion chamber to convert the kinetic energy of the radial expansion of the detonation waves into axial work which is output outwards and can be used for driving a motor to generate electricity and driving a power turbine to drive a propeller or a rotor wing and the like; meanwhile, cooling heat exchange pipelines are arranged at the front end of the combustion chamber and inside the turbine guide vane column, and the countercurrent oxidant or fuel is used for regenerative cooling, so that the rotary detonation combustion chamber is protected, the service life of the combustion chamber is prolonged, the fuel or oxidant atomization effect is improved, and the combustion efficiency is improved; in addition, different cooling and heat exchange effects can be realized by changing working media in the cooling and heat exchange pipeline. The invention can effectively utilize the energy of the radial expansion of the rotary detonation wave, and convert the kinetic energy of the radial expansion into the shaft work to be output outwards; meanwhile, the working medium in the cooling heat exchange pipeline extracts waste heat in the radial expansion area, so that various cooling heat exchange effects are realized, and the long-time reliable work of the combustion chamber is ensured. The invention can be used in the fields of detonation propulsion, cogeneration and the like.
Drawings
FIG. 1 is a schematic diagram of the general structure of a rotary detonation combustor utilizing the radial expansion of a detonation wave in accordance with the present invention;
FIG. 2 is a schematic diagram of the general structure of a hollow cylindrical rotary detonation combustor utilizing the radial expansion of the detonation wave and an axial cross-sectional view thereof;
FIG. 3 is an axial cross-sectional view and a radial cross-sectional view of a rotary detonation combustor shaft work output device utilizing radial expansion of a detonation wave in accordance with the present invention;
FIG. 4 is an axial cross-sectional view of a hollow cylindrical rotary detonation combustor utilizing the radial expansion of the detonation wave and an enlarged schematic view of a cooling heat exchange pipeline.
The combustion chamber comprises a hollow cylindrical rotary detonation combustion chamber 1, a shaft work output device 2, a circumferential seam 3, an injection hole 4, an ignition device 5, a combustion chamber front end head 6-1, a combustion chamber front end wall 6-2, a turbine guide blade column 7, a combustion chamber annular wall 8, a guide cone 9, a turbine blade column 10, a transmission shaft 11, a support 12, a cooling heat exchange pipeline 1 13-1 and a cooling heat exchange pipeline 2, wherein the combustion chamber front end head 6-2 is a combustion chamber front end wall, the turbine guide blade column 7 is a turbine guide blade column 8, the combustion chamber annular wall 9 is a guide cone, the turbine blade column 10 is a turbine blade column 11, the transmission shaft 12 is a support, the cooling heat exchange pipeline 1 is 13-1, and the cooling heat exchange pipeline 2 is a cross section of the cooling heat exchange pipeline 2.
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
referring to fig. 1, the invention relates to a rotary detonation combustor utilizing detonation wave radial expansion, which comprises a hollow cylindrical rotary detonation combustor 1 (such as a circular seam 3, an injection hole 4, an ignition device 5, a combustor front end head 6-1, a combustor front end wall 6-2 and a combustor annular wall 8), a shaft work output device 2 (such as a turbine guide vane column 7, a turbine vane column 10, a transmission shaft 11 and a bracket 12) and a cooling heat exchange device (cooling heat exchange pipelines (1 and 13-1) and cooling heat exchange pipelines (2 and 13-2)).
Referring to fig. 1 and 2, in operation, oxidant and fuel enter an annular flow channel of the hollow cylindrical rotary detonation combustor 1 through an annular gap 3 and an injection hole 4 respectively, the offset design of an annular gap outlet enables the fuel and the oxidant to form a backflow zone during mixing, and a detonation wave is easier to form after an ignition device 5 is started. The detonation wave is transmitted in the combustion chamber in a high-speed rotating mode along the circumferential direction, and lateral expansion occurs; the expansion wave along the axial direction drives the burnt gas to be discharged to the opening end; the radial expansion wave drives the turbine blade column 10 to rotate through the turbine guide blade column 7, and further drives the transmission shaft 11 to output shaft work; the high-temperature and high-pressure products expanded along the radial direction are discharged to the opening end through the guide cone 9, and the turbine is driven to do work in an auxiliary mode.
Referring to fig. 1 and 3, a shaft power output device 2 is disposed coaxially with an empty cylindrical rotary knocking combustion chamber 1. The turbine blade columns 10 are arranged along the circumferential direction, the radius of the circumference of the turbine blade columns is 3/5 of the radius of the front end wall surface of the combustion chamber, the circumferential pitch of the turbine blade columns is the same as the length of the section of the blade grids of the turbine blade columns, and the length of the turbine blade columns is 1/3 of the length of the rotary detonation combustion chamber. The turbine blade column 10 should go deep into the combustion chamber front end wall 6-2, the same with the axial position of turbine guide blade column 7, ensure that the radial expansion wave of the detonation combustion can directly impact the turbine blade column 10 after passing through the turbine guide blade column 7, reduce the flow loss, and improve the shaft work output efficiency. The shaft work can be used for driving a motor to generate power and driving a power turbine to drive a propeller or a rotor wing and the like.
Referring to fig. 1 and 4, the cooling and heat exchanging device mainly comprises cooling and heat exchanging pipes at different positions, and only one pipe is briefly illustrated in the figures due to the periodic characteristics of the structure. The cooling heat exchange pipeline 13-1 is arranged inside the front end 6 of the combustion chamber; the cooling heat exchange pipeline 13-2 is arranged inside the turbine guide vane column 7 and is provided with an inlet and an outlet of working media. In actual work, the cooling heat exchange pipeline can be arranged more complexly according to requirements, the heat of radial expansion of high-temperature and high-pressure products is fully absorbed, the temperature of experimental equipment is reduced, and the long-time reliable work of a combustion chamber is guaranteed. Different working media can be connected into the cooling heat exchange pipeline according to actual needs, such as: when heating is carried out, the working medium is water, the temperature of the front end of the combustion chamber and the turbine guide vane column can be rapidly reduced, and the combustion efficiency is improved; when the regeneration cooling is carried out, the working medium is fuel or oxidant, and the initial temperature rise of the reactant is helpful for improving the detonation success rate.
While the invention has been described in detail and with reference to specific embodiments thereof, it will be apparent to one skilled in the art that the invention is not limited thereto, and that various changes and modifications can be made therein without departing from the spirit and scope thereof.
Claims (6)
1. The rotary detonation combustion chamber utilizing the radial expansion of the detonation waves comprises a hollow cylindrical rotary detonation combustion chamber, a shaft work output device and a cooling heat exchange pipeline. The method is characterized in that an aircraft engine/gas turbine based on rotary detonation combustion is optimized and improved, kinetic energy of radial expansion of rotary detonation waves is converted into available shaft work through a shaft work output device arranged in an empty cylindrical rotary detonation combustion chamber, and the shaft work can be used for driving a motor to generate electricity and driving a power turbine to drive a propeller or a rotor wing and the like. In addition, waste heat in the radial expansion area of the detonation wave can be absorbed through a cooling heat exchange pipeline arranged in the shaft work output device, and the extracted heat energy can be used in the fields of regenerative cooling, engine deicing, domestic heating and the like. The invention makes full use of the radial expansion of the rotary detonation wave, is beneficial to improving the combustion efficiency of the rotary detonation, and widens the application scene of the rotary detonation combustion.
2. The rotary detonation combustor of claim 1, in which the detonation wave radially expands: the hollow cylinder rotary detonation combustor body consists of a combustor front end, an oxidant annular seam, a fuel spray hole, a combustor annular wall surface and an ignition device.
3. The rotary detonation combustor of claim 2, in which: the front end of the combustion chamber mainly comprises a front end head of the combustion chamber and a front end wall surface of the combustion chamber. At the front end of the combustion chamber, an oxidant and fuel are mixed in a circular seam-jet hole mode, the oxidant is compressed by a compressor and enters the rotary detonation combustion chamber through a circular seam in a high-pressure airflow mode; injecting fuel into the annular flow channel through injection holes uniformly distributed along the circumferential direction; the mixing and impacting position of the oxidant and the fuel is close to the annular wall surface of the combustion chamber, so that a backflow zone is formed, and the mixing effect is effectively improved. In actual operation, various mixing methods such as orifice impingement and coaxial centrifugation should be selected according to actual requirements such as physical properties of the fuel and the oxidant and the supply flow rate.
4. The rotary detonation combustor of claim 1, in which: the shaft work output device consists of a turbine guide blade column, a turbine blade column, a guide cone, a support and a transmission shaft.
5. The rotary detonation combustor of claim 4, in which: in the detonation combustion cavity, the turbine guide vane columns and the annular wall surface of the combustion chamber are coaxial and arranged along the circumferential direction and are fixedly connected to the maximum radius position of the front end wall surface of the combustion chamber; the circumferential pitch of the detonation combustor is the same as the radial width of a turbine guide vane column, and the length of the detonation combustor is 1/3 of the length of the detonation combustor. The turbine blade column is connected with the transmission shaft through a bracket to form a whole; the turbine blade columns are arranged along the circumferential direction, the circumferential radius of the turbine blade columns is 3/5 of the radius of the front end wall surface of the combustion chamber, the circumferential pitch of the turbine blade columns is the same as the section length of the turbine blade columns, and the length of the turbine blade columns is 1/3 of the length of the detonation combustion chamber. The radial expansion wave of detonation combustion directly impacts the turbine blade columns after passing through the turbine guide blade columns, and then is discharged backwards through the guide cone, so that the flow loss is effectively reduced, and the shaft work output efficiency is improved. The shaft work output by the transmission shaft can drive a motor to generate power and drive a power turbine to drive a propeller or a rotor wing and the like.
6. The rotary detonation combustor of claim 1, in which: the cooling heat exchange pipeline is arranged at the front end of the combustion chamber and inside the turbine guide vane column, so that waste heat absorption and equipment cooling are realized; be provided with the import and export of working medium, can insert different working mediums into cooling heat transfer pipeline according to actual need, for example: when heating is carried out, the working medium is water, the temperature of the front end of the combustion chamber and the turbine guide vane column can be rapidly reduced, and the combustion efficiency is improved; when the regeneration cooling is carried out, the working medium is fuel or oxidant, and the initial temperature rise of the reactant is helpful for improving the detonation success rate.
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| CN202210875280.5A CN115164235B (en) | 2022-07-25 | 2022-07-25 | Rotary detonation combustion chamber utilizing detonation wave radial expansion |
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| CN202210875280.5A CN115164235B (en) | 2022-07-25 | 2022-07-25 | Rotary detonation combustion chamber utilizing detonation wave radial expansion |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115750138A (en) * | 2022-10-12 | 2023-03-07 | 哈尔滨工业大学 | Annular rotary detonation engine with tail nozzle flow channel constraint and design method |
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