CN114608834B - Model device applied to aeroengine spray combustion research - Google Patents
Model device applied to aeroengine spray combustion research Download PDFInfo
- Publication number
- CN114608834B CN114608834B CN202210380668.8A CN202210380668A CN114608834B CN 114608834 B CN114608834 B CN 114608834B CN 202210380668 A CN202210380668 A CN 202210380668A CN 114608834 B CN114608834 B CN 114608834B
- Authority
- CN
- China
- Prior art keywords
- section
- air inlet
- downstream
- channel
- cyclone
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Business, Economics & Management (AREA)
- Educational Administration (AREA)
- Educational Technology (AREA)
- Theoretical Computer Science (AREA)
- Testing Of Engines (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to a model device applied to aeroengine spray combustion research, 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 and positioned at the downstream of the honeycomb 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 face of the arc-shaped diversion channel, and the transition from the tail end of the cyclone blade to the outlet is realized by a venturi; the fuel nozzle is arranged in the center of the end face of the arc-shaped diversion channel and is concentric with the cyclone; and a visual combustion chamber, the inlet of which is connected with the air inlet channel; the incoming air enters the air inlet channel and forms a rotational flow through the swirler, so that fuel atomization sprayed by the fuel nozzle is promoted. The model device has strong structural universality, is convenient for structural improvement and component replacement, and can adapt to 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 the fuel are key physical processes before the fuel fires, and determine the mixing effect of the fuel and the air, thereby influencing the combustion efficiency and the combustion characteristics. The fuel oil atomization device is used as one of the core components of the main combustion chamber, has complex structure and various functions, is a technical problem in the development of the main combustion chamber, and is one of the core technologies of high locking of aviation countries to China.
At present, the effect of a fuel atomization device is developed from single fuel atomization into fuel atomization, oil-gas mixing and combustion chamber head flow field organization, and the effect is more and more important. From theoretical research, the fuel atomization and evaporation characteristics directly influence key performances such as flameout characteristics, combustion efficiency, outlet temperature distribution, pollutant emission and the like of the main combustion chamber. However, the research on the microscopic working process of the fuel atomization device and the mechanism of fuel atomization evaporation in China is not deep enough, the knowledge of the fuel atomization evaporation process under the extremely complex flow condition is unclear, 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 a starting stage in the experimental exploration of the fuel atomization/evaporation process in the limited space under the typical working condition of the combustion chamber, especially the knowledge on the fuel atomization, evaporation and blending mechanism under the complicated rotational flow pneumatic and transcritical conditions is not comprehensive, the engineering development of the main combustion chamber of the aero-engine/fuel engine in China is seriously influenced, and the experimental exploration is a key symptom for preventing the trial production and the performance optimization of the parts of the main combustion chamber of the two engines.
Therefore, the model device applied to aero-engine spray combustion research is designed and used for researching the fuel atomization mechanism of the novel combined fuel atomization device with the cyclone and the venturi tube, has the advantages of wide application range and capability of performing visual experiments, and has display significance and good application prospect.
Disclosure of Invention
The invention aims to provide a model device applied to aeroengine spray combustion research so as to solve the problems. For this purpose, the invention adopts the following specific technical scheme:
a modeling apparatus for use in aero-engine spray combustion studies may include:
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 rectifying plate and forms an annular cavity serving as an air inlet channel with the air inlet adjusting section;
the cyclone is interchangeably arranged on the end face of the arc-shaped diversion channel, and the ends of the cyclone blades of the cyclone are in venturi transition between the ends and the outlets;
the fuel nozzle is arranged at the center of the end face of the arc-shaped diversion channel and is concentric with the cyclone; and
the inlet of the visual combustion chamber is connected with the air inlet channel;
the incoming air enters the annular cavity and forms a rotational flow through the swirler, so that fuel atomization sprayed by the fuel nozzle is promoted, the venturi tube is used for promoting spray breaking, and the spray is combusted in the visual combustion chamber.
Further, 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 rectifying plate and the lower honeycomb 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, an adapter ring is fixedly installed on the visual combustion chamber, and the downstream air inlet straight pipe section is movably and hermetically installed in the adapter ring and the visual combustion chamber.
Further, a replaceable head is mounted at the end of the downstream straight air inlet pipe section, and the cyclone is fixedly mounted on the arc-shaped diversion channel and the replaceable head.
Further, a plurality of screw holes are circumferentially distributed at the lower end of the replaceable head part and are used for installing a cylindrical glass cover or a circular ring.
Further, the downstream intake straight pipe section is engaged with the replaceable head portion by a stepped structure.
Further, the arc-shaped flow guide channel comprises an upstream section and a downstream section, wherein two ends of the upstream section are respectively connected with the downstream section and a scroll flange, two ends of the downstream section are respectively connected with the cyclone and the upstream section, the scroll flange is arranged in the downstream air inlet straight pipe section and is positioned below the honeycomb rectifying plate.
Further, quartz glass windows are arranged around the visual combustion chamber.
Further, the cyclone can be replaced according to experimental requirements to change geometric parameters, and preferably, the cyclone is a two-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 explored;
2) The air inlet adjusting section can move relative to the visual combustion chamber, so that spray is ensured to be formed in the middle of an optical visual window and in the optimal visual field range of an experimental instrument, and the experimental requirement is met.
3) Through the visual combustion chamber, the spray form, spray particle size, spray flow field, spray combustion flow field and other parameters can be measured by utilizing high-speed camera, PIV, PDPA and other experimental technologies, and the mechanism of fuel atomization and combustion is deeply explored;
4) The model device has strong structural universality, is convenient for structural improvement and component replacement, and can adapt to different experimental requirements.
Drawings
For further illustration of the various embodiments, the invention is provided with the accompanying drawings. The accompanying drawings, which are incorporated in and constitute a part of this disclosure, illustrate embodiments and together with the description, serve to explain the principles of the embodiments. With reference to these matters, one of ordinary skill in the art will understand other possible embodiments and advantages of the present invention. The components in the figures are not drawn to scale and like reference numerals are generally used to designate like components.
FIG. 1 is a perspective view of a modeling apparatus of the present invention for use in an aircraft engine spray combustion study;
FIG. 2 is a cross-sectional view of the modeling apparatus shown in FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 3 is an exploded perspective view of the intake tuning section of the modeling apparatus shown in FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 4 is a perspective view of the adapter ring of the modeling apparatus shown in FIG. 1 as applied to an aircraft engine spray combustion study;
FIG. 5 is a perspective view of the arcuate flow channels of the model apparatus shown in FIG. 1 as applied to aero-engine spray combustion studies;
FIG. 6 is a perspective view of the banner flange of the modeling apparatus of FIG. 1 applied to an aircraft engine spray combustion study;
FIG. 7 is a perspective view of the replaceable head portion of the model apparatus shown in 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;
fig. 9 is a perspective view of the swirler of the model device of fig. 1 applied to an aero-engine spray combustion study.
In the figure, 1, an air inlet adjusting section; 11. an upstream inlet diffuser; 12. a middle air inlet straight pipe section; 121. a straight hole; 122. partition wall constant diameter two-way joint; 13. a downstream intake straight section; 131. a seal ring mounting groove; 132. a height adjusting bolt; 133. an O-ring seal; 2. an arc-shaped diversion channel; 21. an upstream section; 211. the second fixing screw hole; 22. a downstream section; 221. a circular groove; 3. a visual combustion chamber; 31. a window; 32. a mounting hole; 4. a cyclone; 41. a venturi; 42. a primary blade; 43. a secondary blade; 5. a fuel nozzle; 61. a honeycomb rectifying plate is arranged on the upper part; 62. a lower honeycomb rectifying plate; 7. an adapter ring; 8. a banner flange; 81. a central tube; 811. a first fixing screw hole; 9. a replaceable head; 91. a circular groove; 92. tightly fixing the screw hole; 93. a round hole; 94. circular grooves.
Detailed Description
It should be noted that the experimental methods described in the following embodiments, unless otherwise specified, are all conventional methods, and the reagents and materials, unless otherwise specified, are all commercially available; in the description of the present application, the terms "transverse," "longitudinal," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used for convenience in describing the present invention and simplifying the description, and do not denote or imply that the apparatus or elements referred to must have a particular orientation, be configured and operated in a particular orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "horizontal," "vertical," "overhang," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its 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 should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "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 terms in this application will be understood by those of ordinary skill in the art in a specific context.
The invention will now be further described with reference to the drawings and detailed description.
As shown in fig. 1 and 2, a model device for use in aero-engine spray combustion research may include an intake trim section 1, an arcuate pilot channel 2, a visual combustor 3, a swirler 4, and a fuel nozzle 5. Wherein an upper honeycomb rectifying plate 61 and a lower honeycomb rectifying plate 62 are installed in the intake adjusting section 1 to rectify the inflow air. The arc-shaped flow guide channel 2 is installed in the air intake adjusting section 1, is positioned downstream of the lower honeycomb rectifying plate 62, and forms an annular cavity as an air intake channel with the air intake adjusting section 1 (inner wall). The arc-shaped diversion 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, and is used as a combustion cavity, can bear the pressure in the cavity of up to 50bar, and can adapt to the working condition requirements of different spray back pressures and combustion pressures. The visual combustion chamber 3 adopts an optical visual window, can perform visual experiments, and can measure parameters such as spray form, spray particle size, spray flow field, spray combustion flow field and the like by utilizing experimental technologies such as a high-speed camera, PIV, PDPA and the like, so as to deeply explore the mechanism of fuel atomization and combustion. The swirler 4 is interchangeably mounted between the arcuate diversion channel 2 and the visual combustion chamber 3 and centrally provided with a venturi 41, the venturi 41 being adapted to promote spray breakup. Specifically, the swirler 4 is replaceably mounted on the end face of the arcuate flow guide channel 2 and its swirl vane tips transition to the outlet with a venturi 41. 8 swirl blades are reasonably arranged in the circumferential direction of the cyclone 4, so that the gas swirl strength is ensured, and the flow separation of gas and the generation of wake vortexes at the downstream of the cyclone are reduced. The fuel nozzle 5 is mounted in the arcuate pilot channel 2 and extends into the venturi 41. Specifically, the fuel nozzle 5 is mounted at the center of the end face of the arc-shaped diversion channel 2 and concentric with the swirler. The structure of the fuel nozzle 5 is well known and can be replaced to study the spray and combustion effects of different nozzles, and will not be described in detail here. When the cyclone device works, incoming air enters the air inlet adjusting section 1 to be subjected to speed reduction and diffusion, flows in a tidying way through the upper honeycomb rectifying plate 61 and the lower honeycomb rectifying plate 62, enters an annular cavity formed by the arc-shaped flow guide channel 2 and the air inlet adjusting section 1, and forms a cyclone through the cyclone 4; 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 flow guide channel 2 separates the oil way from the air way, so that the uniformity of air at the inlet of the cyclone 4 is ensured, and the flow loss is reduced.
Referring to fig. 2, 3 and 4, the intake trim section 1 includes an upstream intake diffuser section 11, an intermediate intake straight pipe section 12 and a downstream intake straight pipe section 13 that are sealingly connected (e.g., by respective flanges and sealing rings). The upstream inlet diffuser 11 has a conical cylindrical shape and is used for reducing speed and diffusing the incoming air. The middle intake straight pipe section 12 is provided with a straight hole 121 with a diameter of 4mm and a partition wall constant diameter two-way joint 122 for connecting fuel pipes on the inner and outer sides of the device. The downstream intake manifold section 13 is movably mounted on the visual combustion chamber 3 to accommodate the 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 (e.g., 6) bolts, a seal ring mounting groove 131 is provided on the outer peripheral wall of the downstream intake straight pipe section 13, and a plurality of (3) height adjusting bolts 132 are provided on the flange thereof. The seal ring mounting groove 131 is sleeved with an O-shaped seal ring 133 so that the downstream air inlet straight pipe section 13 is mounted in the adapter ring 7 and the visual combustion chamber 3 in a sealing manner. When the height is to be adjusted, the height adjustment can be realized by screwing the height adjusting bolt 132, which is very convenient. The upper honeycomb rectifying plate 61 and the lower honeycomb rectifying plate 62 are installed between the upstream intake diffuser 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 into the lower end of the upstream intake diffuser 11, and a lower honeycomb rectifying plate 62 is built into the lower end of the intermediate intake straight pipe section 12.
Referring to fig. 2, 5 and 6, the arcuate flow guide channel 2 is coaxially mounted within the downstream inlet straight tube section 13. The arcuate flow channel 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 step 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 pipe section 12 and the downstream intake straight pipe section 13, below the lower honeycomb rectifying plate 62. The central tube 81 of the banner flange 8 is provided with a plurality of (e.g. 2) first fixing screw holes 811, the upper end of the upstream section 21 is provided with a corresponding second fixing screw hole 211, and when the banner flange is mounted, the upper end of the upstream section 21 is inserted into the central tube 81 and aligned with the first fixing screw holes 811 and the second fixing screw holes 211, and finally the banner flange is locked by screws. The bottom of the downstream section 22 is provided with a circular groove 221 of external diameter 40mm, internal diameter 35mm and depth 1.8mmm for assembling the cyclone 4; and screw holes of the intermediate design M10 for fixing the fuel nozzles 5.
Referring to fig. 2, 3, 7 and 8, the end of the downstream air intake straight pipe section 13 of the air intake adjusting section 1 is provided with a replaceable head 9, the replaceable head 9 is provided with a circular groove 91, 4 tightening screw holes 92 are circumferentially distributed, a cylindrical glass cover or a circular ring (not shown) can be tightened by screws, and the head is assembled differently according to different experimental requirements. The exchangeable head 9 is further 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 1.8mmm for fitting the swirler 4 and a number 6 of M1 screws for fixing the swirler 4. That is, the rotator 4 is fixedly mounted on the exchangeable head 9 and the venturi 41 passes through the circular hole 93 into the visual combustion chamber 3.
In this embodiment, the downstream intake straight pipe section 13 is cooperatively connected with the replaceable head 9 by a stepped structure, so as to facilitate installation and reduce weight and avoid waste of materials. In addition, the downstream intake straight pipe section 13 and the replaceable head 9 can be replaced by transparent materials or opaque materials according to different requirements.
As shown in fig. 9, the rotator 4 is a two-stage cyclone. The rotator 4 can be replaced with different geometrical parameters according to experimental requirements. In the illustrated embodiment, the number of primary vanes 42 and secondary vanes 43 of the swirler 4 is 8, and each has an arc shape. The heights of the primary and secondary vanes 42, 43 may be designed as desired, and in one embodiment, the heights of the primary and secondary vanes 42, 43 are 2.7mm and 4.7mm, respectively, with an exit angle of about 55 degrees.
Referring to fig. 1, four sides of the visual combustion chamber 3 are provided with circular windows 31, 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 the window 31 may be other shapes and need not be made of quartz glass. In addition, a smoke exhaust pipe is also connected to the downstream of the visual combustion chamber 3, and a muffler is arranged on the smoke exhaust pipe to avoid noise influence.
The model device has the following advantages:
1) The upstream of the device is provided with an air flow adjusting pipeline for reducing air flow separation, so that the air flow uniformity of 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, and the venturi can be made of transparent materials according to an experimental scheme, so that the internal spray atomization phenomenon of the venturi can be represented, spraying and combustion experiments under different cyclone numbers can be conveniently carried out, and the influence of different venturi geometric parameters on spraying is explored;
3) Through the visual combustion chamber, the spray form, spray particle size, spray flow field, spray combustion flow field and other parameters can be measured by utilizing high-speed camera, PIV, PDPA and other experimental technologies, and the mechanism of fuel atomization and combustion is deeply explored;
4) The model device has strong structural universality, is convenient for structural improvement and component replacement, and can adapt to different experimental requirements.
The existing spray combustion research device is mostly used for simulating combustion of an internal combustion engine, the spray combustion of an aeroengine is rarely simulated, the spray research visual field range in the combined combustion device is mostly limited to the downstream of the combined spray device, and the research on the atomization phenomenon and mechanism inside a venturi tube is hardly carried out. Existing devices rarely consider ensuring uniform downstream cyclone inlet airflow. The model device is designed with a flow channel for reducing gas flow separation, a replaceable combined nozzle and a visual combustion chamber, has rich experimental variables, is particularly designed with a venturi tube made of transparent materials, can measure and characterize spraying inside the venturi tube through an optical test scheme, and is convenient for fully understanding 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 details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. A modeling apparatus for use in aero-engine spray combustion studies, 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 adjusting section, is positioned at the downstream of the honeycomb rectifying plate, is assembled with the air inlet adjusting section to form an annular cavity serving as an air inlet channel, the cross section area of the annular cavity is gradually reduced along the air flow direction, and separates an air circuit from an oil circuit, wherein the oil circuit is arranged in the arc-shaped flow guide channel;
a cyclone which is replaceably arranged centrally on the end face of the arc-shaped diversion channel and whose cyclone blade ends transition to the outlet with a venturi, wherein the venturi is made of transparent material;
the fuel nozzle is arranged at the center of the end face of the arc-shaped diversion channel and is concentric with the cyclone; and
the inlet of the visual combustion chamber is connected with the air inlet channel;
the incoming air enters the air inlet channel and forms a rotational flow through the cyclone, so that fuel atomization sprayed by the fuel nozzle is promoted, the venturi tube is used for promoting spray breaking, and the spray is combusted in the visual combustion chamber.
2. The model device for aeroengine spray combustion research according to claim 1, wherein 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, an upper honeycomb rectifying plate and a lower honeycomb rectifying plate are respectively arranged 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 arranged in the downstream air inlet straight pipe section.
3. The modeling apparatus for use in an aircraft engine spray combustion study of claim 2, wherein the upstream inlet diffuser section, the intermediate inlet straight section, and the downstream inlet straight section are flanged to one another.
4. The model device for aeroengine spray combustion research of claim 2 wherein said visual combustion chamber has an adapter ring fixedly mounted thereon and said downstream inlet straight tube section is movably sealingly mounted in said adapter ring and said visual combustion chamber.
5. The model device for aeroengine spray combustion research of claim 4 wherein the end of the downstream straight intake pipe section is fitted with a replaceable head, and the swirler is fixedly mounted on the arcuate flow guide passage end face and the replaceable head.
6. The model device for aeroengine spray combustion research according to claim 5, wherein the lower end of the replaceable head is circumferentially provided with a plurality of screw holes for mounting a cylindrical glass cover or a circular ring.
7. The modeling apparatus for use in an aircraft engine spray combustion study of claim 5, wherein the downstream intake manifold section and the replaceable head section are mated by a stepped configuration.
8. The modeling apparatus for an aircraft engine spray combustion study of claim 5, wherein the arcuate flow channel comprises an upstream section and a downstream section that are removably coupled together, wherein two ends of the upstream section are coupled to the downstream section and a scroll flange, respectively, and two ends of the downstream section are coupled to the swirler and the upstream section, respectively, wherein the scroll flange is embedded in the downstream intake straight section below the lower honeycomb rectifying plate.
9. The model device for aeroengine spray combustion research according to claim 1, wherein quartz glass windows are installed around the visual combustion chamber.
10. The modeling apparatus for use in an aircraft engine spray combustion study of claim 1, wherein the swirler is a dual stage swirler.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210380668.8A CN114608834B (en) | 2022-04-12 | 2022-04-12 | Model device applied to aeroengine spray combustion research |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210380668.8A CN114608834B (en) | 2022-04-12 | 2022-04-12 | Model device applied to aeroengine spray combustion research |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114608834A CN114608834A (en) | 2022-06-10 |
| CN114608834B true CN114608834B (en) | 2023-07-18 |
Family
ID=81869775
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210380668.8A Active CN114608834B (en) | 2022-04-12 | 2022-04-12 | Model device applied to aeroengine spray combustion research |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114608834B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114992632A (en) * | 2022-06-22 | 2022-09-02 | 西北工业大学 | Detachable multifunctional fuel nozzle based on ball head pipeline |
| CN114963237B (en) * | 2022-06-28 | 2023-06-23 | 重庆科技学院 | Opposite-impact type high-pressure combustion chamber with annular nozzle |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101435585B (en) * | 2008-11-28 | 2010-10-13 | 北京大学 | Gas turbine combined type fuel evaporating and atomizing combustion apparatus |
| CN103244330A (en) * | 2013-05-16 | 2013-08-14 | 大连民族学院 | Novel fuel spray visual experiment device |
| CN203232016U (en) * | 2013-05-16 | 2013-10-09 | 大连民族学院 | Novel fuel spray visualized experimental apparatus |
| CN105738139B (en) * | 2016-02-06 | 2018-09-04 | 中国科学院工程热物理研究所 | Burner and burn test method |
| CN207516038U (en) * | 2017-11-21 | 2018-06-19 | 嘉兴学院 | A kind of diesel engine oil mist jet uniformity detection device |
| CN108412616B (en) * | 2018-03-01 | 2019-07-23 | 中国人民解放军空军工程大学 | Aeroengine combustor buring room guide vane formula DBD Plasma Assisted Combustion driver |
| CN108758625B (en) * | 2018-05-08 | 2019-11-12 | 北京航空航天大学 | A kind of oil-poor direct-injection air atomizer spray nozzle of fuel oil grazing incidence film forming |
| CN110398372B (en) * | 2019-07-16 | 2021-03-19 | 上海理工大学 | Optical visual combustion system for engine |
| CN111765492B (en) * | 2020-06-12 | 2021-08-06 | 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 |
| CN113969849B (en) * | 2021-09-26 | 2023-07-11 | 中国人民解放军战略支援部队航天工程大学 | Single-nozzle rocket engine with modularized design |
| CN113864822A (en) * | 2021-10-13 | 2021-12-31 | 西北工业大学 | Machining ring type prefilming swirler |
-
2022
- 2022-04-12 CN CN202210380668.8A patent/CN114608834B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN114608834A (en) | 2022-06-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114608834B (en) | Model device applied to aeroengine spray combustion research | |
| US8387358B2 (en) | Gas turbine engine steam injection manifold | |
| JP3789133B2 (en) | Low NOx fuel nozzle assembly | |
| CN208333872U (en) | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research | |
| CA2630721A1 (en) | Gas turbine engine premix injectors | |
| EP4279813A1 (en) | Oblique spraying non-premix annular combustion chamber ignition mechanism research device | |
| CN113969849B (en) | Single-nozzle rocket engine with modularized design | |
| CN111174233B (en) | Central-grading lean-oil premixed low-pollution combustion chamber | |
| CN111766058B (en) | Multi-interval double-gas-liquid coaxial centrifugal nozzle test device | |
| CN114151825A (en) | Heavy gas turbine double combustion chamber ignition flame test air inlet device | |
| CN113294808A (en) | Air atomizing nozzle of combustion chamber of gas turbine | |
| CN113944575B (en) | Mixer | |
| CN211692664U (en) | Large-scale gas engine mixer | |
| CN111043625A (en) | Combustion chamber of micro gas turbine and micro gas turbine | |
| CN114636171B (en) | Pre-combustion-stage double-oil-way pre-film type air atomizing nozzle | |
| CN218469081U (en) | Hydrogen combustion premixing device | |
| CN213746854U (en) | Swirl nozzle device suitable for combustion chamber of gas turbine | |
| CN115342385B (en) | Weak internal-rotation two-stage axial precombustion stage central staged combustion chamber | |
| CN219140829U (en) | Gas nozzle seat | |
| CN216143778U (en) | Combustor and premixed air inlet type backflow annular combustion chamber | |
| CN219300733U (en) | Abnormal shape flame combustor | |
| CN219530928U (en) | Flame tube, engine and helicopter | |
| CN116557905A (en) | Annular diffuser and combustion chamber | |
| CN117309408A (en) | Measuring section for fuel atomization characteristic test of engine nozzle and swirler assembly | |
| CN2585076Y (en) | Diffusion deflection mixing gas burner |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Yu Bowen Inventor after: Xia Xi Inventor after: Qi Fei Inventor after: Chen Tao Inventor after: Xu Liangliang Inventor after: Li Linye Inventor before: Xia Xi Inventor before: Qi Fei Inventor before: Chen Tao Inventor before: Xu Liangliang Inventor before: Yu Bowen Inventor before: Li Linye |
|
| CB03 | Change of inventor or designer information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |