CN114608834A - Model device applied to aero-engine spray combustion research - Google Patents
Model device applied to aero-engine spray combustion research Download PDFInfo
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- CN114608834A CN114608834A CN202210380668.8A CN202210380668A CN114608834A CN 114608834 A CN114608834 A CN 114608834A CN 202210380668 A CN202210380668 A CN 202210380668A CN 114608834 A CN114608834 A CN 114608834A
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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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- 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
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B25/00—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes
Abstract
The invention relates to a model device applied to the research of the spray combustion of an aircraft engine, which can comprise: the air inlet adjusting section is internally provided with a honeycomb type rectifying plate; the arc-shaped flow guide channel is arranged in the air inlet adjusting section, is positioned at the downstream of the honeycomb type rectifying plate and is assembled with the air inlet adjusting section to form an annular cavity serving as an air inlet channel; the cyclone is replaceably arranged on the end surface of the arc-shaped flow guide channel, and the tail ends of the cyclone blades of the cyclone are transited to the outlet through a venturi; the fuel nozzle is arranged in the center of the end surface of the arc-shaped flow guide channel and is concentric with the swirler; the inlet of the visual combustion chamber is connected with the air inlet channel; wherein, the incoming air enters the air inlet channel and forms a rotational flow through the swirler, thereby promoting the atomization of the fuel sprayed by the fuel nozzle. The model device has strong structural universality, is convenient for structural improvement and part replacement, and can meet different experimental requirements.
Description
Technical Field
The invention belongs to the field of combustion experimental devices, and particularly relates to a model device applied to aero-engine spray combustion research.
Background
The atomization and evaporation of fuel oil are key physical processes before the fuel is on fire, determine the mixing effect of the fuel and air, and further influence the combustion efficiency and characteristics. The fuel oil atomizing device is one of the core components of the main combustion chamber, has a complex structure and multiple functions, and the fine design and the atomization performance control of the fuel oil atomizing device are always the technical problems in the development of the main combustion chamber and are also one of the core technologies of the great aviation countries for highly blocking China.
At present, the function of the fuel oil atomization device is developed from single fuel oil atomization to fuel oil atomization, oil-gas mixing and a combustion chamber head flow field structure, and the function is more and more important. From theoretical research, the key performances of flameout characteristics, combustion efficiency, outlet temperature distribution, pollutant emission and the like of the main combustion chamber are directly influenced by the characteristics of fuel atomization and evaporation. However, the domestic researches on the microscopic working process of the fuel atomization device and the mechanism of fuel atomization evaporation are not deep enough, the understanding of the fuel atomization evaporation process under the condition of extremely complicated flow is not clear, and a high-precision fuel atomization model available for engineering is lacked;
the research on the atomization mechanism of the novel combined fuel atomization device is still in the starting stage of experimental exploration of the fuel atomization/evaporation process in a limited space under the typical working condition of a combustion chamber, and particularly the understanding on the fuel atomization, evaporation and mixing mechanisms under the complex rotational flow pneumatic and transcritical conditions is not complete, so that the engineering development of the main combustion chamber of an aeroengine/combustion engine in China is seriously influenced, and the research becomes a key symptom for hindering the trial production and performance optimization of parts of a two-engine main combustion chamber.
Therefore, the model device applied to the research of the spray combustion of the aircraft engine is designed, is used for researching the fuel atomization mechanism of the novel combined fuel atomization device with the swirler and the venturi tube, has the advantages of wide application range and visual experiment, and has display significance and good application prospect.
Disclosure of Invention
The invention aims to provide a model device applied to the research of the spray combustion of an aircraft engine so as to solve the problems. Therefore, the invention adopts the following specific technical scheme:
a model apparatus for use in an aircraft engine spray combustion study, which may comprise:
the air inlet adjusting section is internally provided with a honeycomb type rectifying plate;
the arc-shaped flow guide channel is arranged in the air inlet adjusting section, is positioned at the downstream of the honeycomb type rectifying plate and forms an annular cavity serving as an air inlet channel together with the air inlet adjusting section;
the swirler is replaceably installed on the end surface of the arc-shaped flow guide channel, and the tip of the swirl vane of the swirler is transited to the outlet through a venturi;
the fuel nozzle is arranged in the center of the end face of the arc-shaped flow guide channel and is concentric with the swirler; and
the inlet of the visual combustion chamber is connected with the air inlet channel;
wherein incoming air enters the annulus and forms a swirling flow through the swirler to promote atomization of fuel ejected from the fuel nozzle, the venturi to promote spray breakup, the spray burning in the visual combustion chamber.
Furthermore, the air inlet adjusting section comprises an upstream air inlet diffusion section, a middle air inlet straight pipe section and a downstream air inlet straight pipe section which are connected together in a sealing mode, the upper honeycomb type rectifying plate and the lower honeycomb type rectifying plate are respectively installed between the upstream air inlet diffusion section and the middle air inlet straight pipe section and between the middle air inlet straight pipe section and the downstream air inlet straight pipe section, and the arc-shaped flow guide channel is coaxially installed in the downstream air inlet straight pipe section.
Further, the upstream air inlet diffusion section, the middle air inlet straight pipe section and the downstream air inlet straight pipe section are connected with each other through flanges.
Further, a switching ring is fixedly installed on the visual combustion chamber, and the downstream air inlet straight pipe section is movably and hermetically installed in the switching ring and the visual combustion chamber.
Furthermore, the tail end of the downstream air inlet straight pipe section is provided with a replaceable head, and the swirler is fixedly arranged on the arc-shaped flow guide channel and the replaceable head.
Furthermore, a plurality of screw holes are distributed on the periphery of the lower end of the replaceable head part and used for installing a cylindrical glass cover or a circular ring.
Further, the downstream air inlet straight pipe section is matched with the replaceable head part through a stepped structure.
Further, the arc-shaped flow guide channel comprises an upstream section and a downstream section, two ends of the upstream section are respectively connected with the downstream section and the banner flange, two ends of the downstream section are respectively connected with the swirler and the upstream section, the banner flange is arranged in the downstream air inlet straight pipe section and is positioned below the honeycomb type rectifying plate.
Furthermore, quartz glass windows are arranged around the visual combustion chamber.
Further, the cyclone is replaceable to change the geometrical parameters according to experimental requirements, preferably, the cyclone is a double-stage cyclone.
By adopting the technical scheme, the invention has the beneficial effects that:
1) the cyclone and the venturi tube are replaceable, so that spraying and combustion experiments under different cyclone numbers can be conveniently carried out, and the influence of different venturi tube geometric parameters on spraying and combustion can be researched;
2) the air inlet adjusting section can move relative to the visual combustion chamber, so that the spray is formed in the middle of an optical visual window and in the optimal visual field range of an experimental instrument, and the experimental requirements are met.
3) Through a visual combustion chamber, parameters such as spray form, spray particle size, spray flow field, spray combustion flow field and the like can be measured by using experimental technologies such as a high-speed camera, PIV, PDPA and the like, and the mechanisms of fuel atomization and combustion are deeply explored;
4) the model device has strong structural universality, is convenient for structural improvement and part replacement, and can meet different experimental requirements.
Drawings
To further illustrate the various embodiments, the invention provides the accompanying drawings. The accompanying drawings, which are incorporated in and constitute a part of this disclosure, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the embodiments. Those skilled in the art will appreciate still other possible embodiments and advantages of the present invention with reference to these figures. Elements in the figures are not drawn to scale and like reference numerals are generally used to indicate like elements.
FIG. 1 is a perspective view of a model apparatus of the present invention as applied to an aircraft engine spray combustion study;
FIG. 2 is a cross-sectional view of the model apparatus shown in FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 3 is an exploded perspective view of an air intake adjustment section of the model apparatus shown in FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 4 is a perspective view of an adapter ring of the model apparatus of FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 5 is a perspective view of an arcuate flow guide passage of the model apparatus of FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 6 is a perspective view of a banner flange of the model apparatus of FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 7 is a perspective view of a replaceable head portion of the model device of FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 8 is another perspective view of the replaceable head portion of the model device of FIG. 1 as applied to an aircraft engine spray combustion study;
figure 9 is a perspective view of the swirler of the model apparatus shown in figure 1 as applied to an aircraft engine spray combustion study.
In the figure, 1, an air intake adjusting section; 11. an upstream air intake diffuser section; 12. a middle air inlet straight pipe section; 121. a straight hole; 122. the partition wall is provided with two through joints with equal diameters; 13. a downstream straight intake pipe section; 131. a sealing ring mounting groove; 132. a height adjustment bolt; 133. an O-shaped sealing ring; 2. an arc-shaped flow guide channel; 21. an upstream section; 211. a second fixing screw hole; 22. a downstream section; 221. a circular groove; 3. a visual combustion chamber; 31. a window; 32. mounting holes; 4. a swirler; 41. a venturi; 42. a first stage blade; 43. a secondary blade; 5. a fuel nozzle; 61. a honeycomb rectifying plate is arranged; 62. a lower honeycomb fairing; 7. a transfer ring; 8. a scroll flange; 81. a central tube; 811. a first fixing screw hole; 9. a replaceable head; 91. a circular groove; 92. tightening the screw hole; 93. a circular hole; 94. a circular groove.
Detailed Description
It is to be noted that the experimental methods described in the following embodiments are all conventional methods unless otherwise specified, and the reagents and materials, if not otherwise specified, are commercially available; in the description of the present application, the terms "lateral," "longitudinal," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like refer to orientations or positional relationships that are based on the orientation shown in the drawings, are used for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and therefore, are not to be considered as limiting the present invention.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present application, it is further noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
The invention will now be further described with reference to the accompanying drawings and detailed description.
As shown in fig. 1 and 2, a model device applied to an aircraft engine spray combustion research may include an air intake adjusting section 1, an arc-shaped guide passage 2, a visual combustion chamber 3, a swirler 4 and a fuel nozzle 5. Wherein, install upper honeycomb cowling panel 61 and lower honeycomb cowling panel 62 in the adjustment section 1 that admits air, in order to rectify the incoming flow air. The arc-shaped flow guide passage 2 is installed in the air inlet adjusting section 1, is positioned at the downstream of the lower honeycomb-type rectifying plate 62, and forms an annular cavity serving as an air inlet passage with the air inlet adjusting section 1 (inner wall). The arc-shaped guide channel 2 can reduce gas flow separation, so that the gas flow at the inlet of the cyclone 4 is more uniform. The visual combustion chamber 3 is connected to the downstream end of the air inlet adjusting section 1, serves as a combustion cavity, can bear the pressure in the cavity of 50bar, and can meet the working condition requirements of different spraying backpressure and combustion pressure. The visual combustion chamber 3 adopts an optical visual window, can be used for visual experiments, can measure parameters such as spray form, spray particle size, spray flow field, spray combustion flow field and the like by using experimental technologies such as a high-speed camera, a PIV, a PDPA and the like, and deeply explores the mechanisms of fuel atomization and combustion. The swirler 4 is replaceably installed between the arc-shaped guide passage 2 and the visual combustion chamber 3 and is centrally provided with a venturi 41, and the venturi 41 is used for promoting spray breaking. Specifically, the swirler 4 is replaceably installed on the end surface of the arc-shaped guide passage 2, and the end of the swirl vane of the swirler is transited to the outlet by the venturi 41. 8 swirl blades are arranged circumferentially and reasonably in the cyclone 4, so that the gas swirl strength is ensured, and the flow separation of gas and the generation of downstream wake vortexes of the cyclone are reduced. The fuel nozzle 5 is installed in the arc-shaped guide passage 2 and extends into the venturi 41. Specifically, the fuel nozzle 5 is installed in the center of the end surface of the arc-shaped diversion passage 2 and is concentric with the swirler. The construction of the fuel nozzle 5 is well known and can be substituted to investigate the spray and combustion effect of different nozzles and will not be described in detail here. During operation, incoming air enters the air inlet adjusting section 1 for speed reduction and pressure expansion, is rectified by the upper honeycomb rectifying plate 61 and the lower honeycomb rectifying plate 62 to flow into an annular cavity formed by the arc-shaped flow guide channel 2 and the air inlet adjusting section 1, and forms rotational flow through the swirler 4; the fuel is injected into the swirling air through the fuel nozzle 5 to form a spray, and the spray is combusted in the visual combustion chamber 3. The arc-shaped diversion channel 2 separates the oil path from the air path, so that the uniformity of air at the inlet of the swirler 4 is ensured, and the flow loss is reduced.
Referring to fig. 2, 3 and 4, the inlet trim section 1 comprises an upstream inlet diffuser section 11, an intermediate inlet straight pipe section 12 and a downstream inlet straight pipe section 13, which are sealingly connected together (e.g. by respective flanges and sealing rings). The upstream air inlet diffusion section 11 is in a cone shape and is used for reducing the speed and diffusing the incoming air. The middle air inlet straight pipe section 12 is provided with a straight hole 121 with the diameter of 4mm and a bulkhead equal-diameter two-way joint 122 for connecting fuel pipelines at the inner side and the outer side of the device. The downstream straight intake pipe section 13 is movably mounted on the visual combustion chamber 3 to accommodate assembly of swirlers 4 of different heights. Specifically, the adapter ring 7 with a flange is fixed to the visual combustion chamber 3 by a plurality of (for example, 6) bolts, and the outer peripheral wall of the downstream intake straight pipe section 13 is provided with a seal ring installation groove 131 and the flange thereof is provided with a plurality of (3) height adjusting bolts 132. The seal ring installation groove 131 is sleeved with an O-shaped seal ring 133 so that the downstream air inlet straight pipe section 13 is installed in the adapter ring 7 and the visual combustion chamber 3 in a sealing mode. When the height is to be adjusted, it is convenient to do so by screwing the height-adjusting bolt 132. An upper honeycomb rectifying plate 61 and a lower honeycomb rectifying plate 62 are installed between the upstream intake diffuser section 11 and the intermediate intake straight pipe section 12 and between the intermediate intake straight pipe section 12 and the downstream intake straight pipe section 13, respectively. Specifically, an upper honeycomb rectifying plate 61 is built in the lower end of the upstream intake diffuser section 11, and a lower honeycomb rectifying plate 62 is built in the lower end of the intermediate intake straight pipe section 12.
Referring to figures 2, 5 and 6, the arcuate guide channels 2 are mounted coaxially within the downstream straight inlet duct section 13. The arc-shaped guide passage 2 is divided into two parts (i.e., an upstream section 21 and a downstream section 22) to facilitate experimental assembly. The upstream section 21 and the downstream section 22 are clamped together through a stepped structure to form a streamline shape so as to reduce flow loss; meanwhile, the ladder structure is designed, so that the weight can be reduced, and the waste of materials can be avoided. The upper end of the upstream section 21 is secured by a banner flange 8. Specifically, the banner flange 8 is interposed between the intermediate intake straight tube section 12 and the downstream intake straight tube section 13, below the lower honeycomb fairing 62. The central tube 81 of the banner flange 8 is provided with a plurality (e.g. 2) of first fixing screw holes 811, and the upper end of the upstream section 21 is provided with corresponding second fixing screw holes 211, and when mounting, the upper end of the upstream section 21 is inserted into the central tube 81 and the first fixing screw holes 811 and the second fixing screw holes 211 are aligned, and finally, locked with screws. The bottom of the downstream section 22 is provided with a circular groove 221 with the outer diameter of 40mm, the inner diameter of 35mm and the depth of 1.8mmm, and the circular groove is used for assembling the swirler 4; and a screw hole of the middle design M10 for fixing the fuel nozzle 5.
Referring to fig. 2, 3, 7 and 8, the end of the downstream air inlet straight pipe section 13 of the air inlet adjusting section 1 is provided with a replaceable head 9, the replaceable head 9 is provided with a circular groove 91, 4 fastening screw holes 92 are circumferentially arranged, and the head can be assembled differently according to different experimental requirements by fastening a cylindrical glass cover or a circular ring (not shown) with screws. The replaceable head 9 is also provided with a circular hole 93 of diameter 30mm for placing the swirler 4 and with a circular recess 94 of outer diameter 40mm, inner diameter 35mm and depth 1.8mm for assembling the swirler 4, the number 6M 1 screws for fixing the swirler 4. That is, the spinner 4 is fixedly mounted on the replaceable head 9 and the venturi 41 passes through the circular hole 93 into the visual combustion chamber 3.
In the present embodiment, the downstream air intake straight pipe section 13 and the replaceable head 9 are connected by a step structure in a matching manner, so as to facilitate installation and reduce weight and avoid material waste. In addition, the downstream air inlet straight pipe section 13 and the replaceable head part 9 can be replaced by transparent materials or opaque materials according to different requirements.
As shown in fig. 9, the spinner 4 is a dual stage swirler. The spinner 4 can be changed for different geometrical parameters according to experimental requirements. In the illustrated embodiment, the number of the first-stage vanes 42 and the second-stage vanes 43 of the swirler 4 is 8, and each of the vanes has a circular arc shape. The heights of the primary blades 42 and the secondary blades 43 can be designed as desired, and in one embodiment, the heights of the primary blades 42 and the secondary blades 43 are 2.7mm and 4.7mm, respectively, and the outlet angle is about 55 degrees.
Referring to fig. 1, the visual combustion chamber 3 has circular windows 31 on four sides, and is sealed by quartz glass; and a plurality of mounting holes 32 are formed for mounting various detectors or sensors, etc. It should be understood that window 31 may be other shapes and need not be quartz glass. In addition, the downstream of the visual combustion chamber 3 is also connected with a smoke exhaust pipeline, and a silencer is arranged on the smoke exhaust pipeline to avoid noise influence.
The model device has the following advantages:
1) the upstream of the device is provided with an airflow adjusting pipeline for reducing the flow separation of the gas, so that the uniformity of the airflow at the inlet of the downstream cyclone is ensured.
2) The cyclone can be replaced by a single-stage or double-stage structure and is provided with a venturi tube, the cyclone can be set to be a transparent material according to an experimental scheme, the spray atomization phenomenon in the venturi tube can be represented, the spray and combustion experiments under different cyclone numbers can be conveniently carried out, and the influence of different venturi tube geometric parameters on the spray can be researched;
3) through a visual combustion chamber, parameters such as spray form, spray particle size, spray flow field, spray combustion flow field and the like can be measured by using experimental technologies such as a high-speed camera, PIV, PDPA and the like, and the mechanisms of fuel atomization and combustion are deeply explored;
4) the model device has strong structural universality, is convenient for structural improvement and part replacement, and can meet different experimental requirements.
Most of the existing spray combustion research devices simulate the combustion of an internal combustion engine, and rarely relate to the spray combustion of a simulated aircraft engine, and the spray research visual field range in a combined combustion device is mostly limited to the downstream of the combined spray device, and the atomization phenomenon and mechanism in a venturi tube are hardly researched. Few considerations have been made in prior art devices to ensure uniform airflow at the downstream cyclone inlet. The model device is provided with a flow channel for reducing gas flow separation, a replaceable combined nozzle and a visual combustion chamber, has rich experimental variables, is specially provided with a venturi tube made of transparent materials, can measure and represent the spray in the venturi tube through an optical test scheme, and is convenient for fully understanding the fuel atomization and combustion mechanism through experiments.
While the invention has been particularly shown and described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. A model device applied to research on spray combustion of an aircraft engine is characterized by comprising:
the air inlet adjusting section is internally provided with a honeycomb type rectifying plate;
the arc-shaped flow guide channel is arranged in the air inlet section, is positioned at the downstream of the honeycomb type rectifying plate and is assembled with the air inlet adjusting section to form an annular cavity serving as an air inlet channel;
the swirler is replaceably arranged on the end surface of the arc-shaped guide channel, and the tip of a swirl vane of the swirler is transited to the outlet by a venturi;
the fuel nozzle is arranged in the center of the end face of the arc-shaped flow guide channel and is concentric with the swirler; and
the inlet of the visual combustion chamber is connected with the air inlet channel;
wherein incoming air enters the air inlet passage and forms a rotational flow through the swirler to promote atomization of fuel ejected from the fuel nozzle, and the venturi is used for promoting spray fragmentation, and the spray is combusted in the visual combustion chamber.
2. The model device applied to the research on the spray combustion of the aero-engine as claimed in claim 1, wherein the air inlet adjusting section comprises an upstream air inlet diffuser section, a middle air inlet straight pipe section and a downstream air inlet straight pipe section which are hermetically connected together, an upper honeycomb type rectifying plate and a lower honeycomb type rectifying plate are respectively installed between the upstream air inlet diffuser section and the middle air inlet straight pipe section and between the middle air inlet straight pipe section and the downstream air inlet straight pipe section, and the arc-shaped flow guide channel is coaxially installed in the downstream air inlet straight pipe section.
3. The model device applied to the aero-engine spray combustion research as claimed in claim 2, wherein the upstream air inlet diffuser section, the intermediate air inlet straight pipe section and the downstream air inlet straight pipe section are connected with each other through flanges.
4. The model device applied to the research on the aero-engine spray combustion as claimed in claim 2, wherein an adapter ring is fixedly mounted on the visual combustion chamber, and the downstream straight air inlet pipe section is movably and hermetically mounted in the adapter ring and the visual combustion chamber.
5. The model device applied to the aero-engine spray combustion research as claimed in claim 4, wherein a replaceable head is installed at the tail end of the downstream straight intake pipe section, and the swirler is fixedly installed on the arc-shaped diversion passage and the replaceable head.
6. The model device for an aircraft engine spray combustion study according to claim 5, wherein the replaceable head portion has a plurality of screw holes distributed around its lower end for receiving a cylindrical glass cover or ring.
7. The model device applied to the aero-engine spray combustion research as claimed in claim 5, wherein the downstream air inlet straight tube section and the replaceable head portion are matched through a stepped structure.
8. The model device applied to the research on the spray combustion of the aero-engine as claimed in claim 5, wherein the arc-shaped flow guiding channel comprises an upstream section and a downstream section which are detachably connected together, two ends of the upstream section are respectively connected to the downstream section and a banner flange, two ends of the downstream section are respectively connected to the swirler and the upstream section, wherein the banner flange is arranged in the downstream air inlet straight pipe section and is positioned below the lower honeycomb type rectifying plate.
9. The model device applied to the research on the spray combustion of the aero-engine as claimed in claim 1, wherein a quartz glass window is installed around the visual combustion chamber.
10. The model device applied to the research on the spray combustion of the aero-engine as claimed in claim 1, wherein the swirler is a double-stage swirler.
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Cited By (1)
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| CN114963237A (en) * | 2022-06-28 | 2022-08-30 | 重庆科技学院 | Opposed high-pressure combustion chamber with annular nozzle |
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| CN111765492A (en) * | 2020-06-12 | 2020-10-13 | 南京航空航天大学 | Visual full-ring model combustion chamber with replaceable head structure |
| CN215726809U (en) * | 2021-07-01 | 2022-02-01 | 中国航发商用航空发动机有限责任公司 | Aeroengine combustion test device |
| CN113969849A (en) * | 2021-09-26 | 2022-01-25 | 中国人民解放军战略支援部队航天工程大学 | Single-nozzle rocket engine with modular design |
| CN113864822A (en) * | 2021-10-13 | 2021-12-31 | 西北工业大学 | Machining ring type prefilming swirler |
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| CN114963237A (en) * | 2022-06-28 | 2022-08-30 | 重庆科技学院 | Opposed high-pressure combustion chamber with annular nozzle |
| CN114963237B (en) * | 2022-06-28 | 2023-06-23 | 重庆科技学院 | Opposite-impact type high-pressure combustion chamber with annular nozzle |
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