CN115164235B - Rotary detonation combustion chamber utilizing detonation wave radial expansion - Google Patents
Rotary detonation combustion chamber utilizing detonation wave radial expansion Download PDFInfo
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- CN115164235B CN115164235B CN202210875280.5A CN202210875280A CN115164235B CN 115164235 B CN115164235 B CN 115164235B CN 202210875280 A CN202210875280 A CN 202210875280A CN 115164235 B CN115164235 B CN 115164235B
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- detonation
- combustion chamber
- radial expansion
- turbine
- heat exchange
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a rotary detonation combustion chamber utilizing detonation wave radial expansion, which comprises a hollow cylindrical rotary detonation combustion chamber, a shaft power output device and a cooling heat exchange pipeline. The axial work output device is arranged at the center of the hollow cylindrical rotary detonation combustion chamber, so that kinetic energy of radial expansion of detonation waves is converted into axial work and is output outwards, and the axial work can be used for driving a motor to generate electricity, driving a power turbine to drive a propeller or a rotor wing and the like; meanwhile, the cooling heat exchange device regenerates and cools the countercurrent oxidant or fuel, so that the service life of the combustion chamber is prolonged, the atomization effect of the fuel or the oxidant is improved, and the combustion efficiency is improved; different cooling heat exchange effects can be realized by changing the working medium of the cooling heat exchange pipeline. The invention not only effectively utilizes the kinetic energy of radial expansion of the rotary detonation wave, but also fully absorbs the waste heat of radial expansion of the high-temperature and high-pressure product, and utilizes the radial expansion of the rotary detonation wave to output various forms of energy. 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 combustion chamber utilizing detonation wave radial expansion.
Background
Rotary detonation combustion is one of the important forms of detonation combustion, has potential advantages of high thermal efficiency, single ignition and the like, and has become a research hot spot in the field of aerospace propulsion in recent years. Rotary detonation combustion generally occurs in an annular combustion chamber open at one end, forming a detonation wave at the head of the combustion chamber and propagating rotationally in the circumferential direction; at the same time, the rotary detonation wave axially expands, and the high-temperature and high-pressure product is discharged from the opening end to generate thrust.
With the intensive research, when the requirement of heat protection needs to be reduced, researchers cancel the inner column on the basis of the annular combustion chamber, and for the hollow cylindrical combustion chamber without the inner column, the detonation wave expands simultaneously in the radial direction and the axial direction. The axial expansion of the detonation wave has the beneficial effects of impacting the turbine and generating thrust; but radial expansion not only can cause the peak pressure of the detonation wave to be reduced, but also can cause unstable propagation and even explosion extinguishment; 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, it is very critical to design a rotary detonation combustion chamber capable of effectively utilizing the radial expansion of the detonation wave, and the invention provides the rotary detonation combustion chamber utilizing the radial expansion of the detonation wave, which can just meet the requirements and has important value for improving the performance and practical application of a rotary detonation combustion mode.
Disclosure of Invention
Technical problem to be solved
Aiming at the problem that radial expansion of rotary detonation waves is not fully utilized when lateral expansion phenomenon occurs to the detonation waves in an empty can-type combustion chamber, 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 aeroengine/gas turbine based on rotary detonation combustion. The axial work output device is arranged at the center of the hollow cylindrical rotary detonation combustion chamber, so that kinetic energy of radial expansion of detonation waves is converted into axial work and is output outwards, and the axial work can drive a motor to generate electricity, drive a power turbine to drive a propeller or a rotor wing and the like; meanwhile, a cooling heat exchange pipeline is arranged at the front end of the combustion chamber and inside the turbine guide vane column, and the counter-flow oxidant or fuel is utilized for regeneration 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 heat exchange effects can be realized by changing the working medium in the cooling heat exchange pipeline, for example, water is used as the working medium, and the extracted waste heat of the combustion chamber is used for life heating. The invention can be used in the fields of detonation propulsion, cogeneration and the like.
In order to achieve the above purpose, the invention adopts the following technical scheme:
a rotary detonation combustor using detonation wave radial expansion comprises a hollow cylindrical rotary detonation combustor, a shaft work output device and a cooling heat exchange pipeline.
The hollow cylindrical rotary detonation combustor body consists of a front end of a combustion chamber, an oxidant circumferential gap, fuel spray holes, an annular wall surface of the combustion chamber 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. The method comprises the steps that at the front end head of a combustion chamber, an oxidant and fuel are mixed in a circular seam-spray hole mode, the oxidant is compressed by a compressor, and enters a rotary knocking combustion chamber through a circular seam in a high-pressure airflow mode; the fuel is injected into the annular flow passage through injection holes uniformly distributed along the circumferential direction; the mixing impact position of the oxidant and the fuel is close to the annular wall surface of the combustion chamber, so that a backflow area is formed, and the mixing effect is effectively improved. In actual operation, various mixing modes such as hole impact, coaxial centrifugation and the like should be selected according to the physical properties of fuel and oxidant, the actual requirements such as supply flow and the like.
The shaft work output device consists of a turbine guide vane column, a turbine vane column, a guide cone, a bracket and a transmission shaft. In the detonation combustion chamber, turbine guide vane columns are coaxial with the annular wall surface of the combustion chamber and are circumferentially arranged and fixedly connected to the position of the maximum radius of the front end wall surface of the combustion chamber; its circumferential pitch is the same as the radial width of the turbine guide vane post and its length is 1/3 of the length of the rotating detonation combustor. The turbine blade column is connected with the transmission shaft through the 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 length of the blade grid section 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 post after passing through the turbine guide blade post, 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 the motor to generate electricity and drive the power turbine to drive the screw propeller or the rotor wing and the like.
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 mediums can be connected into the cooling heat exchange pipeline according to actual needs, such as: when heating is performed, the working medium is water, so that the temperatures 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 regeneration cooling is performed, the working medium is fuel or oxidant, and the initial temperature rise of the reactant can help to improve the detonation success rate.
The beneficial effects are that:
the rotary detonation combustor utilizing the radial expansion of the detonation wave provided by the invention optimizes and improves the aeroengine/gas turbine based on rotary detonation combustion, and the axial work output device is arranged at the center of the hollow cylindrical rotary detonation combustor to convert the kinetic energy of the radial expansion of the detonation wave into axial work and output the axial work outwards, wherein the axial work can be used for driving a motor to generate power, driving a power turbine to drive a propeller or a rotor wing and the like; meanwhile, a cooling heat exchange pipeline is arranged at the front end of the combustion chamber and inside the turbine guide vane column, and the counter-flow oxidant or fuel is utilized for regeneration 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 heat exchange effects can be realized by changing working media in the cooling heat exchange pipeline. The invention can effectively utilize the radial expansion energy of the rotary detonation wave, and convert the radial expansion kinetic energy into shaft work to be output; meanwhile, the working medium in the cooling heat exchange pipeline extracts waste heat of the radial expansion area, so that various cooling heat exchange effects are realized, and the long-time reliable operation 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 detonation wave radial expansion in accordance with the present invention;
FIG. 2 is a schematic diagram of the general structure of a hollow cylinder-shaped rotary detonation combustor and an axial cross-section thereof utilizing radial expansion of detonation waves in the rotary detonation combustor of the present invention;
FIG. 3 is an axial cross-sectional view and a radial cross-sectional view of a rotary detonation combustor shaft work output device utilizing detonation wave radial expansion in accordance with the present invention;
FIG. 4 is an axial cross-sectional view of a rotary detonation combustor hollow barrel rotary detonation combustor utilizing detonation wave radial expansion and an enlarged schematic view of a cooling heat exchange pipeline of the present invention.
Wherein, 1 is a hollow cylindrical rotary detonation combustion chamber, 2 is a shaft work output device, 3 is a circular seam, 4 is an injection hole, 5 is an ignition device, 6-1 is a front end head of the combustion chamber, 6-2 is a front end wall surface of the combustion chamber, 7 is a turbine guide vane column, 8 is an annular wall surface of the combustion chamber, 9 is a guide cone, 10 is a turbine vane column, 11 is a transmission shaft, 12 is a bracket, 13-1 is a cooling heat exchange pipeline (1), and 13-2 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:
referring to FIG. 1, the invention is a rotary detonation combustor utilizing radial expansion of detonation waves, comprising a hollow cylindrical rotary detonation combustor 1 (such as a circular seam 3, a jet 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 (a cooling heat exchange pipeline (1) 13-1 and a cooling heat exchange pipeline (2) 13-2).
Referring to fig. 1 and 2, in operation, the oxidant and the fuel enter the annular flow passage of the hollow cylindrical rotary detonation combustor 1 through the annular gap 3 and the injection hole 4 respectively, and the offset design of the annular gap outlet enables the fuel and the oxidant to form a backflow area when being mixed, so that detonation waves are easier to form after the ignition device 5 is started. The detonation wave is rotated and propagated in the combustion chamber along the circumferential direction at a high speed, and lateral expansion occurs; the expansion wave along the axial direction drives the burnt gas to be discharged to the open end; the radial expansion wave drives the turbine blade column 10 to rotate through the turbine guide blade column 7, so that the transmission shaft 11 is driven 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 way.
Referring to fig. 1 and 3, the shaft work output device 2 is arranged coaxially with the hollow cylindrical rotary detonation combustor 1. The turbine blade columns 10 are circumferentially arranged with a radius of 3/5 of the radius of the front end wall surface of the combustion chamber and with a circumferential pitch equal to the length of the cross section of the blade row of the turbine blade columns, the length of the turbine blade columns being 1/3 of the length of the rotary detonation combustion chamber. The turbine blade post 10 should go deep to the combustor front end wall surface 6-2, and the same axial position as the turbine guide blade post 7 ensures that the radial expansion wave of detonation combustion can directly impact the turbine blade post 10 after passing through the turbine guide blade post 7, reduces flow loss and improves shaft work output efficiency. The shaft work can be used for driving a motor to generate electricity, driving a power turbine to drive a propeller or a rotor wing and the like.
Referring to fig. 1 and 4, the cooling heat exchange device mainly comprises cooling heat exchange pipelines at different positions, and only one pipeline is schematically illustrated in the drawing due to the periodic characteristics of the structure. The cooling heat exchange pipeline 13-1 is arranged inside the front end 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 medium. In actual operation, the cooling heat exchange pipeline can be arranged more complicated according to the requirements, so that the heat of radial expansion of the high-temperature and high-pressure product is fully absorbed, the experimental equipment is cooled, and the combustion chamber is ensured to work reliably for a long time. Different working mediums can be connected into the cooling heat exchange pipeline according to actual needs, such as: when heating is performed, the working medium is water, so that the temperatures 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 regeneration cooling is performed, the working medium is fuel or oxidant, and the initial temperature rise of the reactant can help to improve the detonation success rate.
The present invention is not limited to the above embodiments, and various changes and modifications can be made to the above-described method by those skilled in the art without departing from the principles of the invention.
Claims (1)
1. The rotary detonation combustor utilizing the radial expansion of the detonation wave comprises a hollow cylindrical rotary detonation combustor, a shaft work output device and a cooling heat exchange pipeline, and is characterized in that the shaft work output device arranged in the hollow cylindrical rotary detonation combustor is used for converting the kinetic energy of the radial expansion of the rotary detonation wave into shaft work, the shaft work is used for driving a motor to generate electricity and driving a power turbine to drive a propeller or a rotor wing, in addition, the cooling heat exchange pipeline arranged in the shaft work output device is used for absorbing the waste heat of a radial expansion area of the detonation wave, the extracted heat energy is used for regenerating cooling, deicing or life heating fields, the radial expansion of the rotary detonation wave is fully utilized, the combustion efficiency of the rotary detonation can be improved, the application scene of rotary detonation combustion is widened, the hollow cylindrical rotary detonation combustor body is composed of a front end of the combustor, an oxidant circumferential seam, a fuel injection hole, a circular wall surface of the combustor and an ignition device, the front end of the combustor is mainly composed of the front end head of the combustor, the oxidant and the fuel are mixed in a circumferential seam-jet hole mode, and the oxidant is compressed by a compressor, and enters the rotary detonation chamber in the form of a high-pressure airflow; the fuel is injected into the annular flow passage through injection holes uniformly distributed along the circumferential direction; the mixing impact position of the oxidant and the fuel is close to the annular wall surface of the combustion chamber, a backflow area is formed, the mixing effect is effectively improved, in actual work, multiple mixing modes of hole impact and coaxial centrifugation are selected according to the physical properties of the fuel and the oxidant and the actual demand of supply flow, the shaft work output device consists of a turbine guide vane column, a turbine vane column, a guide cone, a support and a transmission shaft, and in a detonation combustion cavity, the turbine guide vane column and the annular wall surface of the combustion chamber are coaxial and are circumferentially arranged and fixedly connected to the maximum radius position of the front end wall surface of the combustion chamber; the circumferential pitch of the turbine blade column is the same as the radial width of the turbine guide blade column, the length of the turbine blade column is 1/3 of the length of the detonation combustion chamber, and the turbine blade column is connected with the transmission shaft through the bracket to form a whole; the turbine blade columns are circumferentially arranged, 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 length of the blade grid section of the turbine blade columns, the length of the turbine blade columns is 1/3 of the length of the detonation combustion chamber, radial expansion waves of detonation combustion directly impact the turbine blade columns after passing through the turbine guide blade columns, and then are discharged backwards through the guide cone, so that flow loss is effectively reduced, shaft work output by the transmission shaft drives the motor to generate power, the power turbine drives the propeller or the rotor wing, and the cooling heat exchange pipeline is arranged inside the front end of the combustion chamber and the turbine guide blade columns to realize waste heat absorption and equipment cooling; the inlet and outlet of the working medium are arranged, different working mediums are connected into the cooling heat exchange pipeline according to actual needs, when heating is carried out, the working medium is water, the temperatures of the front end of the combustion chamber and the turbine guide vane column are rapidly reduced, and the combustion efficiency is improved; when regeneration cooling is performed, the working medium is fuel or oxidant, and the initial temperature rise of the reactant can help to improve 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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| CN115164235B true CN115164235B (en) | 2023-08-25 |
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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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