CN117030212A - Swirl cup atomization performance test structure and swirl cup atomization performance test device - Google Patents
Swirl cup atomization performance test structure and swirl cup atomization performance test device Download PDFInfo
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- CN117030212A CN117030212A CN202310728102.4A CN202310728102A CN117030212A CN 117030212 A CN117030212 A CN 117030212A CN 202310728102 A CN202310728102 A CN 202310728102A CN 117030212 A CN117030212 A CN 117030212A
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- cyclone
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- swirler
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- 238000000889 atomisation Methods 0.000 title claims abstract description 74
- 238000011056 performance test Methods 0.000 title claims abstract description 63
- 239000000446 fuel Substances 0.000 claims abstract description 73
- 230000002093 peripheral effect Effects 0.000 claims abstract description 20
- 238000009434 installation Methods 0.000 claims description 31
- 230000003068 static effect Effects 0.000 claims description 13
- 239000002828 fuel tank Substances 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 3
- 238000004088 simulation Methods 0.000 abstract description 15
- 238000002485 combustion reaction Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 description 13
- 230000008569 process Effects 0.000 description 9
- 230000001105 regulatory effect Effects 0.000 description 9
- 238000002474 experimental method Methods 0.000 description 6
- 238000011160 research Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 239000003921 oil Substances 0.000 description 3
- 230000001808 coupling effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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
- G01M13/00—Testing of machine parts
-
- 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
- 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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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention relates to the technical field of aero-engine combustion chambers, in particular to a swirl cup atomization performance test structure and a swirl cup atomization performance test device. The swirl cup atomization performance test structure comprises: the bottom wall of the cyclone mounting seat is provided with a mounting hole; one end of the secondary cyclone is suitable for being connected with the mounting hole, and the other end of the secondary cyclone is suitable for being connected with the primary cyclone; the nozzle mounting seat is fixedly arranged on the outer peripheral wall of the cyclone mounting seat; one end of the fuel nozzle is arranged on the nozzle mounting seat, and the other end of the fuel nozzle is connected with the primary cyclone; the adjusting pad is suitable for adjusting the eccentric size of the fuel nozzle, the primary cyclone and/or the secondary cyclone along the first direction; and the eccentric ring is suitable for adjusting the eccentric size of the fuel nozzle, the primary swirler and/or the secondary swirler along the second direction by changing the eccentric distance of the eccentric ring. The swirl cup atomization performance test structure provided by the invention can ensure numerical simulation precision and improve the reliability of analysis results.
Description
Technical Field
The invention relates to the technical field of aero-engine combustion chambers, in particular to a swirl cup atomization performance test structure and a swirl cup atomization performance test device.
Background
The fuel nozzle of the aeroengine combustion chamber is of a cantilever beam structure, the fuel nozzle is usually fixed on a combustion chamber casing, for a swirl cup structure, a nozzle opening of the swirl cup structure is inserted into a horn opening of a primary swirler through clearance fit, a secondary swirler is welded at the head of a flame tube, and the primary swirler has a movable clearance in a baffle plate, so that the position of the primary swirler is determined by the fuel nozzle. The out-of-tolerance in the processing of parts of the combustion chamber and the thermal expansion of the flame tube can cause the eccentricity of the fuel nozzle, the primary cyclone and the secondary cyclone, influence the atomization performance of the cyclone cup and lead the performance of the combustion chamber to change. Therefore, the influence rule of the eccentricity of the fuel nozzle and the swirler on the atomization performance of the swirl cup needs to be studied.
In the prior art, the influence study of the eccentricity of the fuel nozzle and the cyclone on the atomization performance of the cyclone cup is only carried out by a numerical simulation method, the numerical simulation precision cannot be ensured, and the related rule obtained by the numerical simulation cannot be verified through a test.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect that the numerical simulation precision cannot be ensured in the prior art by researching the influence of the eccentricity of the fuel nozzle and the cyclone on the atomization performance of the cyclone cup only through a numerical simulation method, thereby providing the cyclone cup atomization performance test structure capable of ensuring the numerical simulation precision and the cyclone cup atomization performance test device with the same.
In order to solve the technical problems, the swirl cup atomization performance test structure provided by the invention comprises:
the cyclone installation seat comprises an inner side peripheral wall and a bottom wall which jointly surround to form a cyclone installation cavity; the bottom wall of the cyclone mounting seat is provided with a mounting hole; a first-stage cyclone and a second-stage cyclone are arranged in the cyclone installation cavity, one end of the second-stage cyclone is suitable for being connected with the installation hole, and the other end of the second-stage cyclone is suitable for being connected with the first-stage cyclone;
the nozzle mounting seat is fixedly arranged on the outer side peripheral wall of the cyclone mounting seat along the first direction; one end of the fuel nozzle is arranged on the nozzle mounting seat, and the other end of the fuel nozzle is connected with the primary cyclone;
the adjusting pad is arranged between the fuel nozzle and the nozzle mounting seat, one side of the adjusting pad in the thickness direction of the adjusting pad is abutted against the nozzle mounting seat, and the other side of the adjusting pad is abutted against the fuel nozzle; the adjustment pad is adapted to adjust the eccentric dimensions of the fuel nozzle, the primary swirler and/or the secondary swirler in a first direction by varying its own thickness;
the eccentric ring is arranged between the secondary cyclone and the mounting hole, an inner hole of the eccentric ring is matched with the secondary cyclone, and an outer circle of the eccentric ring is matched with the mounting hole; the eccentric ring is adapted to adjust the eccentric dimensions of the fuel nozzle, the primary swirler and/or the secondary swirler in a second direction by varying its own eccentricity.
Optionally, the inner hole of the eccentric ring is in clearance fit with the secondary cyclone; the fit clearance between the inner hole of the eccentric ring and the secondary cyclone is Q, and the value range of Q is more than or equal to 0.05mm and less than or equal to 0.2mm.
Optionally, the first-stage swirler and the second-stage swirler are mutually independent, a baffle is arranged at one end of the first-stage swirler away from the second-stage swirler, and the baffle is suitable for axially fixing the first-stage swirler and the second-stage swirler.
Optionally, a radial movable gap is formed between the inner peripheral wall of the baffle plate and the primary cyclone, the size of the radial movable gap is W, and the value range of W is more than or equal to 3mm and less than or equal to 5mm.
Optionally, the outer circle of the eccentric ring is in clearance fit with the mounting hole.
Optionally, the fuel nozzle comprises a connecting pipe, an input part and an output part at two ends of the connecting pipe; the input part is fixedly arranged in the nozzle mounting seat, and the adjusting pad is arranged between the input part and the nozzle mounting seat; the output part is inserted into the horn mouth of the primary cyclone.
Optionally, the cyclone cup atomization performance test structure further comprises an air inlet cavity shell, wherein the air inlet cavity shell is arranged at one axial end of the cyclone mounting seat; the inner side peripheral wall of the air inlet cavity shell surrounds to form an air inlet cavity channel, and the air inlet cavity channel is communicated with the cyclone installation cavity.
Optionally, a static pressure joint is arranged on the outer peripheral wall of the air inlet cavity shell, the static pressure joint is communicated with the air inlet cavity channel, and the static pressure joint is suitable for measuring static pressure in the air inlet cavity channel.
The invention provides a swirl cup atomization performance test device, which comprises: the swirl cup atomization performance test structure is arranged on the base.
The invention also provides a swirl cup atomization performance test system, which comprises:
the swirl cup atomization performance test device is as described above;
the oil outlet of the fuel oil tank is communicated with the fuel inlet of the fuel nozzle;
the air outlet of the air compressor is communicated with the air inlet cavity channel of the swirl cup atomization performance test structure.
The technical scheme of the invention has the following advantages:
1. according to the swirl cup atomization performance test structure provided by the invention, the adjustment pad is arranged between the fuel nozzle and the nozzle mounting seat, and the eccentric sizes of the fuel nozzle, the primary swirler and/or the secondary swirler along the first direction are adjusted by adjusting the thickness of the adjustment pad, so that the aim of researching the influence rule of the eccentric sizes of the fuel nozzle, the primary swirler and/or the secondary swirler along the first direction on the swirl cup atomization performance can be fulfilled through experiments; through set up the eccentric ring between the second grade swirler with the mounting hole, and through the adjustment the eccentric distance of eccentric ring with control the fuel nozzle the one-level swirler and/or the eccentric size of second grade swirler along the second direction, thereby can realize through the experiment that research the fuel nozzle the one-level swirler and/or the eccentric size of second grade swirler along the second direction influences the mesh of law to whirl cup atomizing performance, and then guarantees numerical simulation precision, improves the reliability of analysis result.
2. According to the swirl cup atomization performance test structure provided by the invention, the range of the fit clearance Q between the inner hole of the eccentric ring and the secondary swirler is required to be 0.05mm or more and Q or less than 0.2mm or less, so that on one hand, the tightness between the secondary swirler and the eccentric ring can be ensured, the air leakage phenomenon between the secondary swirler and the eccentric ring is avoided, and on the other hand, the eccentric ring and the secondary swirler are prevented from being stuck in the replacement process, and the secondary swirler can be smoothly taken out from the eccentric ring.
3. According to the swirl cup atomization performance test structure provided by the invention, the value range of the radial movable gap W is required to be 3mm or less and is less than or equal to 5mm, so that on one hand, the first-stage cyclone and the second-stage cyclone can be prevented from being blocked in the first direction and/or the second direction in the assembly process, on the other hand, the structures of the baffle and the second-stage cyclone can be prevented from being increased, the space occupation is reduced, and the structural coordination of the swirl cup atomization performance test structure is ensured.
4. According to the swirl cup atomization performance test device provided by the invention, the plurality of swirl cup atomization performance test structures are simultaneously arranged on the base, so that the swirl cup atomization performance test of a plurality of eccentric size schemes can be simultaneously carried out by respectively adjusting and/or replacing the eccentric rings and the adjusting pads of the swirl cup atomization performance test structures, the numerical simulation precision is further ensured, the reliability of an analysis result is improved, and the aim of exploring the influence rule of the coupling effect of different eccentric sizes on the swirl cup atomization performance test can be achieved.
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 diagram of a top view of a swirl cup atomization performance test structure of the present invention on a base;
FIG. 2 is a schematic cross-sectional view of the swirl cup atomization performance test structure of FIG. 1 at section A-A;
FIG. 3 is an enlarged view at B in FIG. 2;
FIG. 4 is a schematic diagram showing the connection of the swirl cup atomization performance test structure in the swirl cup atomization performance test system.
Reference numerals illustrate:
10. a cyclone mounting base; 101. a cyclone mounting cavity; 102. a mounting hole; 11. a primary cyclone; 110. a horn mouth; 12. a secondary cyclone; 13. an eccentric ring; 14. a baffle;
20. a nozzle mount; 21. a fuel nozzle; 210. a connecting pipe; 211. an input unit; 212. an output unit; 22. an adjustment pad;
30. an air intake chamber housing; 301. an air intake chamber channel; 31. a static pressure joint mouth;
40. a base station;
50. a fuel tank; 51. a first pipeline; 52. a first regulating valve;
60. an air compressor; 61. a second pipeline; 62. a second regulating valve;
70. and a gas storage tank.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. 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.
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 apparatus or elements referred to must have a specific orientation, be constructed 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.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; 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 can be understood by those of ordinary skill in the art according to the specific circumstances.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
Example 1
Referring to fig. 1 to 3, the structure for testing atomization performance of a swirl cup according to the present embodiment includes:
the cyclone installation seat 10, the inner peripheral wall and the bottom wall of which jointly enclose a cyclone installation cavity 101; the bottom wall of the cyclone installation seat 10 is provided with an installation hole 102; a primary cyclone 11 and a secondary cyclone 12 are arranged in the cyclone installation cavity 101, one end of the secondary cyclone 12 is suitable for being connected with the installation hole 102, and the other end is suitable for being connected with the primary cyclone 11;
a nozzle mount 20 fixedly provided on an outer peripheral wall of the cyclone mount 10 in a first direction; a fuel nozzle 21, one end of which is provided on the nozzle mount 20, and the other end of which is connected to the primary cyclone 11;
an adjustment pad 22 provided between the fuel nozzle 21 and the nozzle mount 20, wherein one side of the adjustment pad 22 in the thickness direction thereof is in contact with the nozzle mount 20, and the other side is in contact with the fuel nozzle 21; the adjustment pad 22 is adapted to adjust the eccentric dimensions of the fuel nozzle 21, the primary swirler 11 and/or the secondary swirler 12 in the first direction by varying its own thickness;
the eccentric ring 13 is arranged between the secondary cyclone 12 and the mounting hole 102, an inner hole of the eccentric ring 13 is matched with the secondary cyclone 12, and an outer circle of the eccentric ring 13 is matched with the mounting hole 102; the eccentric ring 13 is adapted to adjust the eccentric dimensions of the fuel nozzle 21, the primary swirler 11 and/or the secondary swirler 12 in the second direction by varying its own eccentricity.
It should be noted that, referring to fig. 2, the inner peripheral wall and the bottom wall of the cyclone installation seat 10 jointly enclose a cyclone installation cavity 101, and the cyclone installation cavity 101 is adapted to accommodate a cyclone; the bottom wall of the cyclone installation seat 10 is provided with an installation hole 102 along a first direction, and the installation hole 102 is suitable for fixing a cyclone; the cyclone installation cavity 101 is internally provided with a primary cyclone 11 and a secondary cyclone 12 along a third direction, the primary cyclone 11 is arranged at one end of the secondary cyclone 12 away from the bottom wall of the cyclone installation seat 10 along the third direction, one end of the secondary cyclone 12 along the third direction is suitable for being inserted into the installation hole 102, the other end is suitable for being connected with the primary cyclone 11, and the primary cyclone 11 and/or the secondary cyclone 12 are suitable for acting together with gas to form a cyclone airflow, so that the fuel at the outlet of the fuel nozzle 21 is sheared and atomized. Still referring to fig. 2, the eccentric ring 13 is disposed between the secondary cyclone 12 and the mounting hole 102, an inner hole of the eccentric ring 13 is matched with the secondary cyclone 12, and an outer circle of the eccentric ring 13 is matched with the mounting hole 102; the eccentricity of the eccentric ring 13 refers to a distance between a central axis of an inner hole of the eccentric ring 13 and a central axis of an outer circle of the eccentric ring 13; in a specific implementation process, the number of the eccentric rings 13 may be set to be multiple, and the eccentricities of any two of the multiple eccentric rings 13 are different; compared with the research mode of developing the influence of the eccentricity of the fuel nozzle and the cyclone on the atomization performance of the cyclone cup by a numerical simulation method before improvement, the structure for testing the atomization performance of the cyclone cup of the invention adjusts the eccentric sizes of the fuel nozzle 21, the primary cyclone 11 and/or the secondary cyclone 12 along the second direction by arranging the eccentric rings 13 with different eccentricities between the secondary cyclone 12 and the mounting hole 102, so that the aim of researching the influence rule of the eccentric sizes of the fuel nozzle 21, the primary cyclone 11 and/or the secondary cyclone 12 along the second direction on the atomization performance of the cyclone cup can be realized through experiments, and the numerical simulation precision is ensured; the size of the eccentricity of each eccentric ring 13 may be adjusted according to the actual use, and is not particularly limited herein.
It should be noted that, referring to fig. 2, an installation opening (not shown in the drawing) corresponding to the nozzle installation seat 20 is formed on the outer peripheral wall of the cyclone installation seat 10, the installation opening is located at a bottom corner position of the cyclone installation seat 10, the nozzle installation seat 20 is disposed at the installation opening, and the nozzle installation seat 20 is fixedly connected with the outer peripheral wall of the cyclone installation seat 10; the fuel nozzle 21 is of a cantilever structure, the fuel nozzle 21 is arranged at an angle to the first direction, one end of the fuel nozzle 21 is fixedly arranged on the nozzle mounting seat 20, and the other end of the fuel nozzle is connected with the primary cyclone 11. Still referring to fig. 2, the adjusting pad 22 is disposed between the fuel nozzle 21 and the nozzle mount 20, and one side of the adjusting pad 22 along its thickness direction is abutted against the nozzle mount 20, and the other side is abutted against the fuel nozzle 21; in a specific implementation process, the plurality of adjustment pads 22 may be provided, and thicknesses of any two of the plurality of adjustment pads 22 are different; compared with the research mode of developing the influence of the eccentricity of the fuel nozzle and the swirler on the atomization performance of the swirl cup by a numerical simulation method before improvement, the swirl cup atomization performance test structure provided by the invention has the advantages that the adjustment pads 22 with different thicknesses are arranged between the fuel nozzle 21 and the nozzle mounting seat 20, so that the eccentric sizes of the fuel nozzle 21, the primary swirler 11 and/or the secondary swirler 12 along the first direction are adjusted, the purpose of researching the influence rule of the eccentric sizes of the fuel nozzle 21, the primary swirler 11 and/or the secondary swirler 12 along the first direction on the atomization performance of the swirl cup can be realized through experiments, and the numerical simulation precision is ensured; the thickness of each of the adjusting pads 22 may be adjusted according to the actual use situation, and is not particularly limited herein.
In this embodiment, by arranging the adjusting pad 22 between the fuel nozzle 21 and the nozzle mount 20 and adjusting the thickness of the adjusting pad 22 to adjust the eccentric sizes of the fuel nozzle 21, the primary cyclone 11 and/or the secondary cyclone 12 along the first direction, the purpose of researching the rule of influencing the atomizing performance of the cyclone cup by the eccentric sizes of the fuel nozzle 21, the primary cyclone 11 and/or the secondary cyclone 12 along the first direction can be achieved through experiments; through set up eccentric ring 13 between second grade swirler 12 with mounting hole 102, through the adjustment eccentric distance of eccentric ring 13 with control fuel nozzle 21 the one-level swirler 11 and/or the eccentric size of second grade swirler 12 along the second direction, thereby can realize through the experiment that research fuel nozzle 21 the one-level swirler 11 and/or the eccentric size of second grade swirler 12 along the second direction influences the mesh of law to swirl cup atomizing performance, and then guarantees numerical simulation precision, improves analysis result's reliability.
Specifically, the inner hole of the eccentric ring 13 is in clearance fit with the secondary cyclone 12; the fit clearance between the inner hole of the eccentric ring 13 and the secondary cyclone 12 is Q, and the value range of Q is more than or equal to 0.05mm and less than or equal to 0.2mm.
It should be noted that, referring to fig. 3, the secondary cyclone 12 is fixed in the inner hole of the eccentric ring 13 in a clearance fit manner, and a fit clearance between the inner hole of the eccentric ring 13 and the secondary cyclone 12 is Q; the fit clearance Q cannot be too large, otherwise, the tightness between the secondary cyclone 12 and the eccentric ring 13 is easily reduced, so that the air leakage phenomenon is generated between the secondary cyclone 12 and the eccentric ring 13, and therefore, the fit clearance Q needs to meet Q less than or equal to 0.2mm; the fit clearance Q cannot be too small, otherwise, the eccentric ring 13 and the secondary cyclone 12 are easily blocked in the replacement process, so that the secondary cyclone 12 is difficult to take out from the eccentric ring 13, and therefore, the fit clearance Q needs to meet Q being more than or equal to 0.05mm; in summary, the range of the fit clearance Q between the inner hole of the eccentric ring 13 and the secondary cyclone 12 needs to satisfy 0.05mm less than or equal to Q less than or equal to 0.2mm, so that on one hand, tightness between the secondary cyclone 12 and the eccentric ring 13 can be ensured, and an air leakage phenomenon between the secondary cyclone 12 and the eccentric ring 13 is avoided, and on the other hand, the eccentric ring 13 and the secondary cyclone 12 can be prevented from being stuck in a replacement process, so that the secondary cyclone 12 can be smoothly taken out from the eccentric ring 13.
Specifically, the primary cyclone 11 and the secondary cyclone 12 are independently arranged, a baffle 14 is arranged at one end of the primary cyclone 11 away from the secondary cyclone 12, and the baffle 14 is suitable for axially fixing the primary cyclone 11 and the secondary cyclone 12.
Specifically, a radial movable gap is formed between the inner peripheral wall of the baffle 14 and the primary cyclone 11, wherein the size of the radial movable gap is W, and the value range of W is more than or equal to 3mm and less than or equal to 5mm.
It should be noted that, referring to fig. 3, the primary cyclone 11 and the secondary cyclone 12 are designed in a split type, the primary cyclone 11 and the secondary cyclone 12 are independently disposed, the secondary cyclone 12 is in clearance fit with the inner hole of the eccentric ring 13, a baffle 14 is disposed at one end of the primary cyclone 11 away from the secondary cyclone 12, and the baffle 14 is disposed so as to fix the primary cyclone 11 and the secondary cyclone 12 axially. Still referring to fig. 3, a radial moving gap W is formed between the inner peripheral wall of the baffle 14 and the primary cyclone 11, where the radial moving gap W cannot be too small, otherwise, the primary cyclone 11 and the secondary cyclone 12 are easily stuck in the first direction and/or the second direction during the assembly and/or the replacement process, so that the radial moving gap W needs to satisfy that W is greater than or equal to 3mm; the radial movable gap W cannot be too large, otherwise, the structures of the baffle 14 and the secondary cyclone 12 are easily increased, the space occupation is increased, and the structural coordination of the cyclone cup atomization performance test structure is affected, so that the radial movable gap W needs to meet the condition that W is less than or equal to 5mm; in summary, the range of the radial clearance W needs to satisfy that W is less than or equal to 3mm and less than or equal to 5mm, so that on one hand, the first-stage cyclone 11 and the second-stage cyclone 12 can be prevented from being blocked in the first direction and/or the second direction during the assembly process, and on the other hand, the structures of the baffle 14 and the second-stage cyclone 12 can be prevented from being increased, the space occupation is reduced, and the structural coordination of the cyclone cup atomization performance test structure is ensured.
Specifically, the outer circumference of the eccentric ring 13 is in clearance fit with the mounting hole 102.
It should be noted that, the outer circle of the eccentric ring 13 is in clearance fit with the mounting hole 102, so as to avoid the eccentric ring 13 from being blocked with the mounting hole 102 during the assembly and/or replacement process; the size of the fit gap between the outer circumference of the eccentric ring 13 and the mounting hole 102 is not particularly limited.
Specifically, the fuel nozzle 21 includes a connection pipe 210, and an input portion 211 and an output portion 212 at both ends of the connection pipe 210; the input part 211 is fixedly arranged in the nozzle mounting seat 20, and the adjusting pad 22 is arranged between the input part 211 and the nozzle mounting seat 20; the output portion 212 is inserted into the flare 110 of the primary cyclone 11.
It should be noted that, as shown in fig. 2, the fuel nozzle 21 of the aero-engine combustion chamber is a cantilever structure, and the fuel nozzle 21 includes a connecting pipe 210, and an input portion 211 and an output portion 212 at two ends of the connecting pipe 210, where the input portion 211 is fixedly disposed in the nozzle mounting seat 20, and the output portion 212 is inserted into the bell mouth 110 of the primary cyclone 11 through clearance fit; the adjusting pad 22 is disposed between the input portion 211 and the nozzle mount 20, and the distance between the input portion 211 and the central axis of the mounting hole 102 along the first direction is adjusted by changing the thickness of the adjusting pad 22, so as to adjust the distance between the output portion 212 and the central axis of the mounting hole 102 along the first direction; the inlet 211 is provided with a fuel inlet (not shown) adapted to communicate with the flare 110 of the primary cyclone 11.
Specifically, the swirl cup atomization performance test structure further comprises an air inlet cavity shell 30, wherein the air inlet cavity shell 30 is arranged at one axial end of the swirler mounting seat 10; the inner peripheral wall of the inlet chamber housing 30 encloses an inlet chamber channel 301, the inlet chamber channel 301 being in communication with the cyclone mounting chamber 101.
Optionally, the air intake housing 30 is bolted to the cyclone mount 10.
Optionally, the air inlet cavity housing 30 is in sealing connection with the cyclone mounting base 10.
Specifically, a static pressure nozzle 31 is provided on the outer peripheral wall of the intake chamber housing 30, the static pressure nozzle 31 communicates with the intake chamber passage 301, and the static pressure nozzle 31 is adapted to measure static pressure in the intake chamber passage 301.
Example two
Referring to fig. 1 to 3, the swirl cup atomization performance test device provided in this embodiment includes: a base 40, and the swirl cup atomization performance test structure provided on the base 40.
It should be noted that, in this embodiment, as shown in fig. 1, a plurality of swirl cup atomization performance test structures are simultaneously provided on the base 40, so that the swirl cup atomization performance test of a plurality of eccentric dimension schemes can be simultaneously performed by respectively adjusting and/or replacing the eccentric rings 13 and the adjusting pads 22 of the swirl cup atomization performance test structures, thereby ensuring numerical simulation precision, improving reliability of analysis results, and simultaneously achieving the purpose of exploring influence rules of coupling actions of different eccentric dimensions on the swirl cup atomization performance test.
Example III
In order to better illustrate and understand the structure of the swirl cup atomization performance test according to the present invention, as shown in fig. 4, the present embodiment provides a swirl cup atomization performance test system, including:
the swirl cup atomization performance test device is as described above;
a fuel tank 50, wherein an oil outlet of the fuel tank 50 is communicated with a fuel inlet of the fuel nozzle 21;
the air compressor 60, the gas outlet of air compressor 60 is linked together with the inlet chamber passageway 301 of whirl cup atomization performance test structure.
In this embodiment, referring to fig. 4, the swirl cup atomization performance test device described above is configured in the swirl cup atomization performance test system, so as to perform an atomization performance test on the swirl cup in the eccentric state of the fuel nozzle 21, the primary swirler 11, and/or the secondary swirler 12. Wherein, the oil outlet of the fuel tank 50 is communicated with the fuel inlet of the fuel nozzle 21 through a first pipeline 51, a first regulating valve 52 is arranged on the first pipeline 51, and the first regulating valve 52 is suitable for regulating the fuel quantity flowing to the fuel inlet of the fuel nozzle 21; the air outlet of the air compressor 60 is communicated with an air inlet cavity channel 301 of the swirl cup atomization performance test structure through a second pipeline 61, a second regulating valve 62 is arranged on the second pipeline 61, and the second regulating valve 62 is suitable for regulating the amount of air flowing to the air inlet cavity channel 301; an air storage tank 70 is further disposed between the air compressor 60 and the second regulating valve 62, and the air storage tank 70 is adapted to store air from the air compressor 60. When the test starts, aviation kerosene enters the fuel nozzle 21 from the fuel oil tank 50 through the first pipeline 51, gas enters the air inlet cavity channel 301 from the air storage tank 70 through the second pipeline 61, and the gas forms a swirl flow under the combined action of the primary cyclone 11 and the secondary cyclone 12 so as to shear and atomize the aviation kerosene at the outlet of the fuel nozzle 21. The specific working principles of the control circuit and the laser detection probe are not described here, and can be adjusted according to actual experimental requirements, which is not limited to the case described in fig. 4 of this embodiment.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (10)
1. The utility model provides a whirl cup atomization performance test structure which characterized in that includes:
a cyclone mounting seat (10), wherein the inner peripheral wall and the bottom wall of the cyclone mounting seat jointly enclose a cyclone mounting cavity (101); a mounting hole (102) is formed in the bottom wall of the cyclone mounting seat (10); a primary cyclone (11) and a secondary cyclone (12) are arranged in the cyclone installation cavity (101), one end of the secondary cyclone (12) is suitable for being connected with the installation hole (102), and the other end is suitable for being connected with the primary cyclone (11);
the nozzle mounting seat (20) is fixedly arranged on the outer peripheral wall of the cyclone mounting seat (10) along the first direction; a fuel nozzle (21) with one end arranged on the nozzle mounting seat (20) and the other end connected with the primary cyclone (11);
an adjustment pad (22) provided between the fuel nozzle (21) and the nozzle mount (20), wherein one side of the adjustment pad (22) in the thickness direction thereof is in contact with the nozzle mount (20), and the other side is in contact with the fuel nozzle (21); -said adjustment pad (22) is adapted to adjust the eccentric dimensions of said fuel nozzle (21), said primary swirler (11) and/or said secondary swirler (12) in a first direction by varying its own thickness;
the eccentric ring (13) is arranged between the secondary cyclone (12) and the mounting hole (102), an inner hole of the eccentric ring (13) is matched with the secondary cyclone (12), and an outer circle of the eccentric ring (13) is matched with the mounting hole (102); the eccentric ring (13) is adapted to adjust the eccentric dimensions of the fuel nozzle (21), the primary swirler (11) and/or the secondary swirler (12) in the second direction by varying its own eccentricity.
2. The swirl cup atomization performance test structure according to claim 1, characterized in that a clearance fit is provided between the inner bore of the eccentric ring (13) and the secondary swirler (12); the fit clearance between the inner hole of the eccentric ring (13) and the secondary cyclone (12) is Q, and the value range of Q is more than or equal to 0.05mm and less than or equal to 0.2mm.
3. The swirl cup atomization performance test structure according to claim 1, wherein the primary swirler (11) and the secondary swirler (12) are mutually independent, a baffle (14) is arranged at one end of the primary swirler (11) away from the secondary swirler (12), and the baffle (14) is suitable for axially fixing the primary swirler (11) and the secondary swirler (12).
4. A swirl cup atomization performance test structure according to claim 3, characterized in that a radial movable gap is formed between the inner side peripheral wall of the baffle (14) and the primary cyclone (11), wherein the size of the radial movable gap is W, and the value range of W is 3 mm-5 mm.
5. The swirl cup atomization performance test structure according to claim 1, characterized in that the outer circle of the eccentric ring (13) is in clearance fit with the mounting hole (102).
6. The swirl cup atomization performance test structure according to claim 1, characterized in that the fuel nozzle (21) comprises a connecting pipe (210) and an input part (211) and an output part (212) at both ends of the connecting pipe (210); the input part (211) is fixedly arranged in the nozzle mounting seat (20), and the adjusting pad (22) is arranged between the input part (211) and the nozzle mounting seat (20); the output part (212) is inserted into the horn mouth (110) of the primary cyclone (11).
7. The swirl cup atomization performance test structure according to any one of claims 1-6, further comprising an air inlet chamber housing (30), the air inlet chamber housing (30) being disposed at an axial end of the swirler mounting base (10); an inner peripheral wall of the air inlet cavity shell (30) surrounds an air inlet cavity channel (301), and the air inlet cavity channel (301) is communicated with the cyclone mounting cavity (101).
8. The swirl cup atomization performance test structure according to claim 7, characterized in that a static pressure nozzle (31) is provided on the outer peripheral wall of the air inlet chamber housing (30), the static pressure nozzle (31) is in communication with the air inlet chamber channel (301), and the static pressure nozzle (31) is adapted to measure static pressure in the air inlet chamber channel (301).
9. The utility model provides a whirl cup atomization performance test device which characterized in that includes: a base (40), and a swirl cup atomization performance test structure according to any of the preceding claims 1-8 provided on the base (40).
10. A swirl cup atomization performance test system, comprising:
the swirl cup atomization performance test device according to claim 9;
a fuel tank (50), wherein an oil outlet of the fuel tank (50) is communicated with a fuel inlet of the fuel nozzle (21);
and an air outlet of the air compressor (60) is communicated with an air inlet cavity channel (301) of the swirl cup atomization performance test structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310728102.4A CN117030212A (en) | 2023-06-19 | 2023-06-19 | Swirl cup atomization performance test structure and swirl cup atomization performance test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310728102.4A CN117030212A (en) | 2023-06-19 | 2023-06-19 | Swirl cup atomization performance test structure and swirl cup atomization performance test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117030212A true CN117030212A (en) | 2023-11-10 |
Family
ID=88621484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310728102.4A Pending CN117030212A (en) | 2023-06-19 | 2023-06-19 | Swirl cup atomization performance test structure and swirl cup atomization performance test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117030212A (en) |
-
2023
- 2023-06-19 CN CN202310728102.4A patent/CN117030212A/en active Pending
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