CN116698425B - Floating wall tile and experimental section device of aeroengine combustion chamber - Google Patents
Floating wall tile and experimental section device of aeroengine combustion chamber Download PDFInfo
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- CN116698425B CN116698425B CN202310687451.6A CN202310687451A CN116698425B CN 116698425 B CN116698425 B CN 116698425B CN 202310687451 A CN202310687451 A CN 202310687451A CN 116698425 B CN116698425 B CN 116698425B
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- 238000007667 floating Methods 0.000 title claims abstract description 89
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 36
- 239000000463 material Substances 0.000 claims abstract description 10
- 238000012360 testing method Methods 0.000 claims abstract description 7
- 238000002474 experimental method Methods 0.000 claims description 56
- 239000000112 cooling gas Substances 0.000 claims description 38
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 29
- 239000010453 quartz Substances 0.000 claims description 28
- 239000000446 fuel Substances 0.000 claims description 21
- 239000007788 liquid Substances 0.000 claims description 21
- 230000007246 mechanism Effects 0.000 claims description 13
- 239000007789 gas Substances 0.000 claims description 3
- 230000005684 electric field Effects 0.000 abstract description 21
- 238000001816 cooling Methods 0.000 abstract description 16
- 238000005516 engineering process Methods 0.000 abstract description 11
- 230000000694 effects Effects 0.000 abstract description 6
- 238000011160 research Methods 0.000 abstract description 6
- 238000004939 coking Methods 0.000 abstract description 5
- 230000003287 optical effect Effects 0.000 abstract description 5
- 238000000576 coating method Methods 0.000 description 12
- 239000011248 coating agent Substances 0.000 description 11
- 239000002131 composite material Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
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- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention belongs to the technical field of heat protection and combustion control of aero-engines, and particularly relates to a floating wall tile and experimental section device of an aero-engine combustion chamber; the electric field and the discharge technology are introduced into the combustion chamber of the aeroengine, and the electric field and the electrode discharge are utilized to control the flame, so that the effects of the flame on the heat exchange of the floating wall tiles and the different influences of the coking on the wall surface are achieved. The experimental device can provide different floating wall tile materials, different impact cooling floating wall tile forms, different electric fields and discharge forms are initiated, the comprehensive experimental conditions, the online optical test, the multi-field control combustion and cooling research environment are met, and the experimental device has the advantages of simple structure, replaceable parts, easiness in operation and the like.
Description
Technical Field
The invention belongs to the technical field of heat protection and combustion control of aero-engines, and particularly relates to a floating wall tile and experimental section device of an aero-engine combustion chamber.
Background
Aeroengines are called bright beads on industrial crowns, which involve the discipline of materials, energy, chemistry, machinery, etc., and are very complex. With the continuous improvement of the performance requirements of the aero-engine, the working environment of the combustion chamber is more and more severe, and a new technological breakthrough is particularly needed for improving the combustion efficiency and the heat resistance of the combustion chamber.
For the traditional heat protection scheme of the inner wall of the combustion chamber, the technology of air film cooling is generally adopted, for example, the technologies of reverse air flow cooling, impact cooling, splash air film cooling and the like are developed. Meanwhile, in order to meet different requirements, the corresponding combustion chamber structure is changed, for example, a multi-layer cooling structure, a floating wall tile structure and the like are designed. The floating wall tile has a plurality of advantages, can block and absorb heat radiation of the combustion chamber to effectively insulate heat, can reduce stress, can directly impact the tile for cooling, and the like, is easy to replace, and can use materials with higher heat resistance. However, with the increasing requirements for the combustion chamber, more excellent floating wall tiles are required, such as multi-wall layer tiles, special arc-shaped structural tiles, composite tiles and the like, the processing technology and requirements are higher and higher, besides the structural complexity of the tiles, special materials or tiles with composite coatings and the like can be adopted, so that the cost and weight of the aeroengine are greatly increased.
In order to reduce the consumption of cooling gas, improve the combustion efficiency and reduce the cost of the floating wall tile, a novel mode of controlling flame by an electric field can be introduced, namely, the chemical reaction process of flame combustion is controlled by an electric field or a discharge technology, or the flame is changed by changing a flow field, for example, the shape of the flame is changed by the electric field, so that a high-temperature core area is far away from the position of the floating wall tile, the combustion reaction process is activated by discharge, or the flow field is changed by discharge, so that the ignition delay time, the flame residence time and the like are changed, the combustion efficiency is improved, meanwhile, the emission of pollutants is reduced, and the carbon deposition condition of the tile wall surface can be changed by the electric field or the discharge technology. The electric field has the characteristics of continuous adjustability and convenient control, the technology is mature, the technical problem is solved by innovatively utilizing the advantages of the cross subjects when the electric field is introduced into the aero-engine flame control system, but the application research of combining the electric field or the discharge technology with the aero-engine combustion chamber is less, and a professional system research platform is lacked.
Disclosure of Invention
The invention aims to provide a floating wall tile and experimental section device of an aeroengine combustion chamber.
In order to solve the technical problem, the invention provides a floating wall tile of an aeroengine combustion chamber, which comprises the following components:
floating wall tile body, stud and electrode mechanism;
the studs are arranged on the bottom surface of the floating wall tile body;
the electrode mechanism is arranged on the top surface and/or the bottom surface of the floating wall tile body.
Further, a plurality of through holes are formed in the floating wall tile body.
Further, the electrode mechanism includes: a plurality of electrode needles;
the electrode needle is arranged on the top surface of the floating wall tile body.
Further, the electrode mechanism includes: a coated electrode;
and the coating electrode completely covers the bottom surface of the floating wall tile body.
Further, the electrode mechanism includes: a coated electrode;
the coating electrodes are arranged on the top surface and the bottom surface of the floating wall tile body at intervals;
the coated electrodes on the top and bottom surfaces of the floating wall tile are spaced apart from each other as viewed in the normal direction of the floating wall tile.
On the other hand, the invention also provides an experimental section device adopting the floating wall tile of the aeroengine combustion chamber, which comprises:
an experiment Duan Danying upper cavity, a semicircular quartz tube, an experiment section lower cavity, a nozzle slideway, a liquid fuel nozzle, a floating wall tile and an impact cooling gas deflector;
the experiment Duan Danying upper cavity is connected with the experiment section lower cavity, and the experiment section quartz upper cavity is arranged above the experiment section lower cavity;
the semicircular quartz tube is embedded into the upper cavity of the experiment Duan Danying;
the nozzle slideway is arranged on the table top of the lower cavity of the experimental section;
the liquid fuel nozzle is arranged on the nozzle slideway;
the floating wall tile is arranged on the table top of the lower cavity of the experimental section, and the semicircular quartz tube is covered above the floating wall tile;
the impact cooling gas deflector is arranged below the floating wall tile and is communicated with the lower cavity of the experimental section.
Further, the impingement cooling gas deflector comprises: a cooling gas outlet slot and a cooling gas deflector;
the cooling gas outlet groove is arranged on the lower cavity of the experimental section and is positioned below the floating wall tile;
the cooling gas guide vane is embedded into the cooling gas outlet groove;
the gas is suitable for entering the cavity consisting of the experiment Duan Danying upper cavity and the semicircular quartz tube from the lower cavity of the experiment section through the cooling gas guide vane.
Further, the liquid fuel nozzle is mounted on the nozzle slideway through a bolt;
the liquid fuel nozzle is adapted to slide along an internally disposed channel of the nozzle slide.
Further, the whole structure formed by the experiment Duan Danying upper cavity, the semicircular quartz tube and the experiment section lower cavity is sealed by adopting a high-temperature-resistant material.
Further, the upper chamber and the lower chamber of the experimental section of the experiment Duan Danying are suitable for sharing the table top of the lower chamber of the experimental section.
The invention has the beneficial effects that the invention passes through the experiment Duan Danying upper cavity, the semicircular quartz tube, the experiment section lower cavity, the nozzle slideway, the liquid fuel nozzle, the floating wall tile and the impact cooling gas deflector; the experiment Duan Danying upper cavity is connected with the experiment section lower cavity, and the experiment section quartz upper cavity is arranged above the experiment section lower cavity; the semicircular quartz tube is embedded into the upper cavity of the experiment Duan Danying; the nozzle slideway is arranged on the table top of the lower cavity of the experimental section; the liquid fuel nozzle is arranged on the nozzle slideway; the floating wall tile is arranged on the table top of the lower cavity of the experimental section, and the semicircular quartz tube is covered above the floating wall tile; the impact cooling gas deflector is arranged below the floating wall tile and is communicated with the lower cavity of the experimental section; the electric field and the discharge technology are introduced into the combustion chamber of the aeroengine, and the electric field and the electrode discharge are utilized to control the flame, so that the effects of the flame on the heat exchange of the floating wall tiles and the different influences of the wall coking are achieved. The experimental device can provide different floating wall tile materials, different impact cooling floating wall tile forms, different electric fields and discharge forms are initiated, the comprehensive experimental conditions, the online optical test, the multi-field control combustion and cooling research environment are met, and the experimental device has the advantages of simple structure, replaceable parts, easiness in operation and the like.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and drawings.
In order to make the above objects, features and advantages of the present invention more comprehensible, preferred embodiments accompanied with figures are described in detail below.
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 needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the experimental section apparatus of the present invention;
FIG. 2 is a schematic view of the internal structure of the experimental section apparatus of the present invention;
FIG. 3 is a schematic view of the installation location of the floating wall tile of the present invention;
FIG. 4 is a schematic view of a floating wall tile structure according to the present invention;
FIG. 5 is a schematic view of a second floating wall tile structure according to the present invention;
FIG. 6 is a schematic view of a third floating wall tile structure according to the present invention.
In the figure:
an upper cavity of experiment Duan Danying, 2 a semicircular quartz tube, 3 a lower cavity of an experiment section, 4 a nozzle slideway, 5 a liquid fuel nozzle, 6 a floating wall tile, 601 an electrode needle 602 is a floating wall tile, 603 is a stud, 7 is an impingement cooling gas deflector, 701 is a cooling gas outlet slot, 702 is a cooling gas deflector.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. 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.
Embodiment 1 as shown in fig. 1 to 6, embodiment 1 provides a floating wall tile for an aeroengine combustion chamber, comprising: a floating wall tile body 602, a stud 603 and an electrode mechanism; the stud 603 is arranged on the bottom surface of the floating wall tile 602; the electrode mechanism is arranged on the top surface and/or the bottom surface of the floating wall tile body 602; stud 603 is made of a high temperature resistant insulating material; different floating wall tiles 6 can be obtained by arranging electrode means at different positions.
In this embodiment, the floating wall tile 602 is provided with a plurality of through holes, which are shaped like multiple small holes.
In this embodiment, the electrode mechanism includes: a plurality of electrode pins 601; the electrode needle 601 is disposed on the top surface of the floating wall tile 602.
In this embodiment, the electrode mechanism includes: a coated electrode; the coated electrode completely covers the bottom surface of the floating wall tile 602.
In this embodiment, the electrode mechanism includes: a coated electrode; the coating electrodes are arranged at intervals on the top surface and the bottom surface of the floating wall tile body 602; the coated electrodes on the top and bottom surfaces of the floating wall tile 602 are spaced apart from each other as viewed in the normal direction of the floating wall tile 602. The electrode needle 601 and the coating electrode are communicated with an external high-voltage power supply, one surface is provided with the coating electrode, or the two surfaces are provided with the coating electrode intermittently, for the condition that the two surfaces are provided with the coating electrode, the coating electrode with the same surface is insulated between the coating electrodes intermittently, the other side of the floating wall tile 602 is correspondingly provided with the coating electrode, and the coating electrodes on the two sides have a certain interval distance when being observed from the normal direction of the floating wall tile 602. The purpose is to control flame by electric field and electrode discharge, and achieve the effect of different influences of flame on heat exchange of the floating wall tile 6 and coking of the wall surface.
Embodiment 2 on the basis of embodiment 1, embodiment 2 further provides an experimental section device using the floating wall tile of the aero-engine combustion chamber in embodiment 1, including: an experiment Duan Danying upper cavity 1, a semicircular quartz tube 2, an experiment section lower cavity 3, a nozzle slideway 4, a liquid fuel nozzle 5, a floating wall tile 6 and an impingement cooling gas deflector 7; the experiment Duan Danying upper cavity 1 is connected with the experiment section lower cavity 3, and the experiment Duan Danying upper cavity 1 is arranged above the experiment section lower cavity 3; the semicircular quartz tube 2 is embedded into the upper cavity 1 of the experiment Duan Danying; the nozzle slideway 4 is arranged on the table top of the lower cavity 3 of the experimental section; the liquid fuel nozzle 5 is arranged on the nozzle slideway 4; the floating wall tile 6 is arranged on the table top of the lower cavity 3 of the experimental section, and the semicircular quartz tube 2 is covered above the floating wall tile 6; the impingement cooling gas deflector 7 is arranged below the floating wall tile 6, and the impingement cooling gas deflector 7 is communicated with the experiment section lower cavity 3; the electric field and the discharge technology are introduced into the combustion chamber of the aeroengine, and the electric field and the electrode discharge are utilized to control the flame, so that the effects of the flame on the heat exchange of the floating wall tile 6 and the different influences of the wall coking are achieved. The experimental device can provide different floating wall tile 6 materials, different impact cooling floating wall tile 6 forms, different electric fields and discharge forms are initiated, comprehensive experimental conditions, online optical tests, multi-field control combustion and cooling research environments are met, and the experimental device has the advantages of being simple in structure, replaceable in parts, easy to operate and the like. Other physical quantities are introduced as variables, the coupling is applied to a traditional aeroengine combustion chamber, two tile models are provided, and the problem that a special experimental device for an electric field and discharge acting on a floating wall tile 6 of the aeroengine combustion chamber is lacking in the prior art is also solved.
In this embodiment, the floating wall tile 602 is mounted on the table surface of the lower chamber 3 of the experimental section through the stud 603, and the stud 603 is made of a high-temperature resistant insulating material.
In this embodiment, the semi-circular quartz tube 2 provides a closed combustion environment, and can provide a visual detection means, and air with a certain speed, temperature and pressure enters from the upper chamber 1 of the experiment Duan Danying, so as to provide an oxidant required for combustion and meet certain flow field conditions.
In this embodiment, the impingement cooling gas deflector 7 comprises: a cooling gas outlet groove 701 and a cooling gas baffle 702; the cooling gas outlet groove 701 is arranged on the lower cavity 3 of the experimental section and is positioned below the floating wall tile 6; the cooling gas guide vane 702 is embedded into the cooling gas outlet groove 701; the gas is suitable for entering a cavity formed by the upper cavity 1 of the experiment Duan Danying and the semicircular quartz tube 2 from the lower cavity 3 of the experiment section through the cooling gas guide vane 702; different impingement cooling gas deflectors 7 can be replaced according to different experimental requirements; the impingement cooling flow director is in the shape of a divergent multi-aperture.
In this embodiment, the liquid fuel nozzle 5 is mounted on the nozzle slide 4 by bolts; the liquid fuel nozzle 5 is suitable for sliding along the inner channel of the nozzle slideway 4 to any position, and the central line of the nozzle passes through the geometric center point of the floating wall tile 6; the liquid fuel nozzle 5 is used for simulating the working state of part of the aero-engine; the centre line of the liquid fuel nozzle 5 may be found at 0 ° -90 ° to the normal to the floating wall tile 6, in this embodiment the centre line of the liquid fuel nozzle 5 passing through the geometric centre point of the floating wall tile 6.
In the embodiment, the whole structure formed by the experiment Duan Danying upper cavity 1, the semicircular quartz tube 2 and the experiment section lower cavity 3 is sealed by adopting a high-temperature resistant material; the semicircular quartz tube 2 is made of transparent materials with good infrared penetrability, and aims to perform online tests, for example, an infrared thermal imager and the like are used, and the floating wall tile 6 is arranged at the center of the cross section of the semicircular quartz tube 2 so as to reduce adverse effects of refraction of quartz glass on test results of optical equipment.
In this embodiment, the upper chamber 1 and the lower chamber 3 of the experimental section of the experiment Duan Danying are suitable for sharing the table top of the lower chamber 3 of the experimental section, and the outer installation edges of the upper chamber 1 and the lower chamber 3 of the experimental section of the experiment Duan Danying are connected with other air chambers by bolts in the form of flange edges, and two air paths are respectively installed in the two chambers and respectively used as air supplied to the oxidant and the flow field and air for performing impact cooling.
In summary, according to the invention, the experiment Duan Danying is performed by the upper cavity 1, the semicircular quartz tube 2, the lower cavity 3 of the experimental section, the nozzle slideway 4, the liquid fuel nozzle 5, the floating wall tile 6 and the impact cooling gas deflector 7; the experiment Duan Danying upper cavity 1 is connected with the experiment section lower cavity 3, and the experiment Duan Danying upper cavity 1 is arranged above the experiment section lower cavity 3; the semicircular quartz tube 2 is embedded into the upper cavity 1 of the experiment Duan Danying; the nozzle slideway 4 is arranged on the table top of the lower cavity 3 of the experimental section; the liquid fuel nozzle 5 is arranged on the nozzle slideway 4; the floating wall tile 6 is arranged on the table top of the lower cavity 3 of the experimental section, and the semicircular quartz tube 2 is covered above the floating wall tile 6; the impingement cooling gas deflector 7 is arranged below the floating wall tile 6, and the impingement cooling gas deflector 7 is communicated with the experiment section lower cavity 3; the electric field and the discharge technology are introduced into the combustion chamber of the aeroengine, and the electric field and the electrode discharge are utilized to control the flame, so that the effects of the flame on the heat exchange of the floating wall tile 6 and the different influences of the wall coking are achieved. The experimental device can provide different floating wall tile 6 materials, different impact cooling floating wall tile 6 forms, different electric fields and discharge forms are initiated, comprehensive experimental conditions, online optical tests, multi-field control combustion and cooling research environments are met, and the experimental device has the advantages of being simple in structure, replaceable in parts, easy to operate and the like.
The components (components not illustrating specific structures) selected in the application are all common standard components or components known to those skilled in the art, and the structures and principles of the components are all known to those skilled in the art through technical manuals or through routine experimental methods.
In the description of embodiments of the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
With the above-described preferred embodiments according to the present invention as an illustration, the above-described descriptions can be used by persons skilled in the relevant art to make various changes and modifications without departing from the scope of the technical idea of the present invention. The technical scope of the present invention is not limited to the description, but must be determined according to the scope of claims.
Claims (5)
1. An experimental segment apparatus employing floating wall tiles for an aircraft engine combustion chamber, comprising:
an experiment Duan Danying upper cavity, a semicircular quartz tube, an experiment section lower cavity, a nozzle slideway, a liquid fuel nozzle, a floating wall tile and an impact cooling gas deflector;
the experiment Duan Danying upper cavity is connected with the experiment section lower cavity, and the experiment section quartz upper cavity is arranged above the experiment section lower cavity;
the semicircular quartz tube is embedded into the upper cavity of the experiment Duan Danying;
the nozzle slideway is arranged on the table top of the lower cavity of the experimental section;
the liquid fuel nozzle is arranged on the nozzle slideway;
the floating wall tile is arranged on the table top of the lower cavity of the experimental section, and the semicircular quartz tube is covered above the floating wall tile;
the impact cooling gas deflector is arranged below the floating wall tile and is communicated with the lower cavity of the experimental section;
the center line of the liquid fuel nozzle passes through the geometric center point of the floating wall tile;
the floating wall tile includes: floating wall tile body, stud and electrode mechanism;
the studs are arranged on the bottom surface of the floating wall tile body;
the electrode mechanism is arranged on the top surface and/or the bottom surface of the floating wall tile body;
the flame is controlled by an electrode mechanism.
2. The apparatus of claim 1, wherein the apparatus comprises a plurality of sensors,
the impingement cooling gas deflector comprises: a cooling gas outlet slot and a cooling gas deflector;
the cooling gas outlet groove is arranged on the lower cavity of the experimental section and is positioned below the floating wall tile;
the cooling gas guide vane is embedded into the cooling gas outlet groove;
the gas is suitable for entering the cavity consisting of the experiment Duan Danying upper cavity and the semicircular quartz tube from the lower cavity of the experiment section through the cooling gas guide vane.
3. The apparatus of claim 2, wherein the apparatus comprises a plurality of sensors,
the liquid fuel nozzle is arranged on the nozzle slideway through a bolt;
the liquid fuel nozzle is adapted to slide along an internally disposed channel of the nozzle slide.
4. The experimental section apparatus according to claim 3, wherein,
the whole structure consisting of the experiment Duan Danying upper cavity, the semicircular quartz tube and the experiment section lower cavity is sealed by adopting a high-temperature-resistant material.
5. The apparatus according to claim 4, wherein the test section is,
the upper cavity and the lower cavity of the experimental section of the experiment Duan Danying are suitable for sharing the table top of the lower cavity of the experimental section.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310687451.6A CN116698425B (en) | 2023-06-12 | 2023-06-12 | Floating wall tile and experimental section device of aeroengine combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310687451.6A CN116698425B (en) | 2023-06-12 | 2023-06-12 | Floating wall tile and experimental section device of aeroengine combustion chamber |
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| CN116698425A CN116698425A (en) | 2023-09-05 |
| CN116698425B true CN116698425B (en) | 2024-03-12 |
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