CN114354203B - Swirler and nozzle integration performance test device - Google Patents
Swirler and nozzle integration performance test device Download PDFInfo
- Publication number
- CN114354203B CN114354203B CN202210268302.1A CN202210268302A CN114354203B CN 114354203 B CN114354203 B CN 114354203B CN 202210268302 A CN202210268302 A CN 202210268302A CN 114354203 B CN114354203 B CN 114354203B
- Authority
- CN
- China
- Prior art keywords
- nozzle
- swirler
- test
- performance
- tool
- 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
Images
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
- G01M13/00—Testing of machine parts
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The invention belongs to the technical field of gas turbines, and particularly relates to a vortex device and nozzle integrated performance test device, which comprises: the device comprises a tool which is vertically arranged and provided with a nozzle and a swirler, wherein the tool is provided with an air supply pipe so as to test the performance of the nozzle or the swirler independently or test the matching performance of the nozzle and the swirler in a combined manner; the upper end of the testing section is connected with the tool, and the lower end of the testing section is provided with an outlet pipeline; and the detection equipment is arranged in or outside the test section. The integrated performance test device for the swirler and the nozzle combines the separated test beds in the prior art, can test the performance of the nozzle or the swirler independently, can test the matching performance of the nozzle and the swirler, obtains all performance parameters of the nozzle and the swirler, and promotes the research and development of parts of a combustion chamber.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a device for testing the integrated performance of a swirler and a nozzle.
Background
The swirler and the nozzle are important parts of the combustion chamber of the gas turbine and are core parts for realizing the functions of the combustion chamber parts, and the working performance of the swirler and the nozzle has the most direct influence on the performance of the combustion chamber, so that the stable operation of the whole gas turbine is influenced.
The swirler has the function that after air subjected to speed reduction and diffusion by the diffuser flows through the swirler and enters the head of the flame tube, the air rotates under the flow guiding action of the swirler vanes to form annular rotating air flow with radial, axial and circumferential velocity components, and in the process, the axial momentum of the air flow is reduced, and the radial and circumferential momentum is increased. Meanwhile, because the air has viscosity, the airflow expanded by rotation takes away the airflow near the center of the flame tube, so that the pressure of the airflow in the central area is reduced, a counter pressure gradient is formed in the axial direction, and a part of the airflow generates counter flow due to the fact that the axial momentum is not enough to overcome the counter pressure gradient, and a stable backflow area is formed. The backflow gas is continuously mixed with the gas flow flowing into the swirler in the process, and then flows out from a downstream area at the outer edge of the backflow area to the outlet of the flame tube. The continuous process provides an indispensable flow field structure for the combustion organization of the fuel in the flame tube, and becomes a means for flame stable combustion.
The nozzle has the function that fuel oil is supplied into the flame tube from the fuel oil main pipe in a macroscopic view, the oil-gas ratio of the combustion chamber is directly determined by the oil supply amount, the temperature rise level of the combustion chamber is determined by the oil-gas ratio, and the performance parameters of the whole gas turbine, such as thrust or power, are directly influenced. In the process, the fuel oil is crushed and atomized under the action of the oil supply pressure and the air pneumatic force in the flame tube, and then is mixed with the air in the flame tube to form combustible mixed air, and the atomizing performance of the nozzle determines the particle size of the fuel oil and the spatial distribution of the fuel oil in the flame tube, so that the combustion efficiency, the outlet temperature distribution of a combustion chamber and the like are influenced, and further, the integral operation and the service life of a gas turbine are greatly influenced.
Because the swirler and the nozzle have a significant role in the operation and performance of the gas turbine, a great deal of manpower and material resources are required to complete the design, production and testing of the swirler and the nozzle in the process of developing the combustor component. During the development of swirlers and nozzles, great attention is paid to: the method comprises the following steps of designing a swirler, wherein the swirler comprises the effective flow area (ACd) of the swirler, the swirl strength (Sn) of the swirler, the flow field structural characteristics in a three-dimensional space at the downstream of the swirler, a nozzle flow coefficient (Cd), a nozzle atomization cone angle, nozzle circumferential distribution unevenness, fuel particle Size (SMD) and fuel spatial distribution.
For the above parameter study, due to the limitation of the current numerical simulation technology, a lot of experiments are still required to verify the design target value. However, the testing device currently put into use has the following defects: the nozzle test bed and the swirler test bed are separated from each other, the auxiliary atomization effect of the swirler and the distribution of fuel in an actual air flow field cannot be evaluated, various measuring devices cannot be integrated on one test bed, and the test system is complicated, long in test period, high in cost and low in test resource utilization rate.
Disclosure of Invention
The invention aims to provide a swirler and nozzle integrated performance test device, which solves the problem that the existing test device can only carry out nozzle or swirler performance test independently.
In order to achieve the purpose, the invention adopts the following technical scheme:
a swirler and nozzle integration performance test device comprises:
the device comprises a tool which is vertically arranged and provided with a nozzle and a swirler, wherein the tool is provided with an air supply pipe so as to test the performance of the nozzle or the swirler independently or test the matching performance of the nozzle and the swirler in a combined manner;
the upper end of the testing section is connected with the tool, and the lower end of the testing section is provided with an outlet pipeline; and the detection equipment is arranged in or outside the test section.
In one possible design, the tool comprises a cylindrical shell and a rectifying tube inserted in the shell, wherein a plurality of rectifying holes are formed in the rectifying tube; correspondingly, the nozzle is positioned at the upper end of the shell, the swirler is positioned at the lower end of the shell, and the nozzle and the swirler are respectively partially inserted into the rectifying pipe.
In one possible design, the rectification holes are provided in a plurality of rows, and the rectification holes between adjacent rows are arranged in a staggered manner.
In one possible design, the nozzle is connected to a fuel supply line via a fuel inlet nipple, and the fuel supply line is secured to the housing and communicates with the rectifier tube.
In one possible design, the nozzle is provided with a mounting edge, and the mounting edge is fixed at the upper end of the shell through a plurality of bolts; the inboard of shell lower extreme is equipped with the apron, and the swirler compresses tightly the apron through a plurality of bolt, and all is equipped with the gasket of sealed usefulness on all bolts.
In one possible design, the testing section is a transparent square cylinder, and two ends of the square cylinder are respectively provided with a mounting hole.
In one possible design, the detection device includes a high-speed camera, a particle velocimeter and a laser particle sizer, which are respectively placed outside the test segment, and at least one of the high-speed camera, the particle velocimeter and the laser particle sizer is selected.
In a possible design, the check out test set includes the liquid trap of placing in the test section, and the liquid trap includes collecting tank, plectane and support, and the both sides of plectane are equipped with collecting tank and support respectively, and the collecting tank is equipped with a plurality of and uses the axis of plectane as the central equipartition on the intermediate lamella, is equipped with the weeping hole on every collecting tank respectively, is equipped with on the weeping hole to wear to establish the weeping pipe outside the test section.
In one possible design, the liquid collecting groove is obliquely arranged, the high end of the liquid collecting groove is intersected at the axis of the circular plate, the low end of the liquid collecting groove is connected with the edge of the circular plate, and the liquid leakage hole is formed in the bottom of the liquid collecting groove.
In one possible design, there are 10-20 sumps.
Has the advantages that:
this swirler and nozzle integration performance test device combines together the test bench of separation among the prior art, both can test the performance of nozzle or swirler alone, can test the matching performance of nozzle and swirler again, obtains all performance parameters of nozzle and swirler, promotes the part research and development of combustion chamber, expands and richened this swirler and nozzle integration performance test device's function and application range, greatly improved the practicality.
In addition, the integrated performance test device of the swirler and the nozzle has the advantages of simple structure, low requirement on materials, short construction period and low cost; when the test is carried out, the operation is quick, the safety is high, the test period is short, and the test cost can be effectively reduced.
Drawings
To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, and it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope.
FIG. 1 is a schematic structural diagram of a vortex device and nozzle integrated performance testing device.
Fig. 2 is a partially enlarged schematic view of a portion a in fig. 1.
Fig. 3 is a perspective view of fig. 1.
Fig. 4 is a schematic sectional structure view of the tool.
FIG. 5 is a schematic view of the liquid trap from a first perspective.
FIG. 6 is a schematic view of the liquid trap from a second perspective.
In the figure:
1. assembling; 11. a housing; 12. a rectifier tube; 101. a flow rectifying hole; 102. a cover plate; 2. a testing section; 3. a detection device; 31. a liquid collector; 311. a liquid collecting tank; 312. a circular plate; 313. a support; 301. a liquid leakage pipe; 41. a nozzle; 42. a swirler; 401. an oil inlet joint; 402. a bolt; 403. a static pressure nozzle; 5. a gas supply pipe; 6. an outlet line.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some, but not all embodiments of the present invention.
Example 1:
as shown in fig. 1 to 6, a swirler and nozzle integrated performance testing apparatus includes: the tool 1 is vertically arranged and provided with a nozzle 41 and a swirler 42, and the tool 1 is provided with an air supply pipe 5 so as to test the performance of the nozzle 41 or the swirler 42 independently or test the matching performance of the nozzle 41 and the swirler 42 in a combined manner; the upper end of the testing section 2 is connected with the tool 1, and the lower end of the testing section is provided with an outlet pipeline 6; and a detection device 3 arranged inside or outside the test section 2.
The swirler and nozzle integrated performance testing device is provided with two mounting positions, the nozzle 41 and the swirler 42 are respectively arranged on the mounting positions, and the mounting sequence and the connection relation of the nozzle 41 and the swirler 42 are connected according to actual work so as to simulate the actual work. The nozzle 41 is connected with an oil supply pipe, the fluid for testing flows into the tool 1 through the oil supply pipe and the air supply pipe 5 respectively, at least one of the nozzle 41 and the swirler 42 is used for testing, and the fluid flows through the component for testing, is sprayed into the testing section 2, and flows out through the outlet pipeline 6. When the fluid flows through the test section 2, the fluid is observed through the detection device 3, and according to the measurement result and the relevant parameters of air supply and oil supply, all performance parameters of the nozzle 41 and the swirler 42 are obtained, that is, the performance parameters of the nozzle 41 and the swirler 42 and the matching performance of the nozzle 41 and the swirler 42 are obtained.
Based on the design, this swirler and nozzle integration performance test device combines together the test bench of separation among the prior art, both can test nozzle 41 or swirler 42's performance alone, can test nozzle 41 and swirler 42's matching performance again, obtain nozzle 41 and swirler 42's whole performance parameter, promote the part research and development of combustion chamber, expand and richen this swirler and nozzle integration performance test device's function and application range, greatly improved the practicality.
In addition, the integrated performance test device of the swirler and the nozzle has the advantages of simple structure, low requirement on materials, short construction period and low cost; when the test is carried out, the operation is quick, the safety is high, the test period is short, and the test cost can be effectively reduced.
In operation, the nozzle 41 and the swirler 42 are fixed to the mounting locations and connected to each other. After the installation is finished, testing is carried out, and the testing mode comprises an individual testing mode and a combined testing mode, wherein the individual testing mode supplies fluid to the element to be tested through the oil supply pipe or the air supply pipe 5; in the combined test mode, the oil supply pipe or the gas supply pipe 5 supplies the fluid at the same time. The fluid is sprayed into the test section 2 after flowing through the component to be tested, and then flows out of the test section 2 through the outlet pipeline 6. Finally, the fluid is observed and measurements are obtained with the detection device 3 as it flows through the test section 2. And (5) testing for multiple times, and adjusting gas supply and oil supply parameters simultaneously, thereby obtaining multiple groups of data.
The following describes the test process with reference to the specific structure of the swirler and nozzle integrated performance test device:
in this embodiment, the structure of the tool 1 includes, but is not limited to: the tool 1 comprises a cylindrical shell 11 and a rectifying tube 12 inserted in the shell 11, wherein the rectifying tube 12 is provided with a plurality of rectifying holes 101; accordingly, the nozzle 41 is located at the upper end of the housing 11, the swirler 42 is located at the lower end of the housing 11, and the nozzle 41 and the swirler 42 are each partially inserted into the rectifying tube 12.
The fuel supply pipe supplies fuel to the nozzle 41, the gas supply pipe injects gas into the tool 1, and the two fluids are injected into the test section 2 after flowing through the component to be tested. Specifically, the flow paths of the two fluids are not identical, with fuel entering directly into the nozzle 41 and flowing sequentially through the nozzle 41 and the swirler 42; the gas flows into the rectifying tube 12 through the housing 11 and further flows into the swirler 42, and the gas is rectified by the rectifying hole 101 when flowing through the rectifying tube 12, so that the gas flow performance is improved.
In this case, the structure of the tool 1 is simpler, the design and manufacturing costs are low, no additional component is provided, and the rectifying effect of the rectifying tube 12 is better.
Therefore, the tool 1 is constructed into a double-layer cylindrical structure, wherein the shell 11 not only provides an installation space, but also plays a role in sealing, and liquid is prevented from evaporating to a test environment; the rectifying tube 12 improves the gas performance through the arrangement of the rectifying hole 101, so as to achieve better experimental effect.
Preferably, the nozzle 41 and swirler 42 are generally distributed along the axis of the housing 11, so that the amount of shielding within the housing 11 is reduced and the straightening effect of the tube 12 is maximized.
Alternatively, the rectifying holes 101 are provided in several rows, and the rectifying holes 101 between adjacent rows are staggered with each other. In addition, according to different actual test equipment, parameters such as the aperture of the rectifying hole 101 and the distance between the adjacent rectifying holes 101 are adjusted to achieve the best test effect. In one possible implementation, as shown in fig. 3-4, there are four rows of the fairing holes.
In one possible implementation, the nozzle 41 is connected to a fuel supply pipe through a fuel inlet connector 401, and the fuel supply pipe 5 is fixed to the housing 11 and communicates with the rectifying pipe 12. Therefore, the device meets the requirement of actual test, in addition, the liquid supply pipe can be used for conveying clear water or any other suitable liquid, the air supply pipe can be used for supplying air or any other suitable gas, and the device has the advantages of flexibility, convenience and good practicability in the actual use process.
Taking fuel delivery as an example, the existing test bed is open, part of fuel will evaporate to the surrounding environment during the test, air pollution occurs in the test environment, and the physical health of workers can be affected. Frock 1 is double-deck tubular structure, and the enclosure of shell 11 has effectively reduced the scope of fuel evaporation back loss, avoids appearing air pollution phenomenon, has ensured staff's health.
The casing 11 is provided with a nozzle 41 and a swirler 42, so that a gap influencing the sealing performance of the casing 11 inevitably exists between the component for testing and the casing, and the connection form of the two is described here: the nozzle 41 is provided with a mounting edge which is fixed on the exposed end of the shell 11 through a plurality of bolts 402; the cover plate 102 is arranged on the inner side of the connecting end of the housing 11, the swirler 42 compresses the cover plate 102 through a plurality of bolts 402, and gaskets for sealing are arranged on all the bolts 402.
Based on the design, the structure is simplified and the cost is reduced on the basis of achieving a good sealing effect; and bolt 402 and gasket are the standard part, can select the product of looks adaptation specification according to the size of work body, and the practicality is good.
The detection device 3 can be divided into two types, that is, a device located inside the test section 2 and a device located outside the test section 2, according to different setting positions. Then, during testing, the equipment in the testing section 2 can be in direct contact with the fluid, so that the observation is more direct, and the obtained data volume is larger; the equipment located outside the test section 2 cannot be in direct contact with the fluid but only allows the fluid to be observed through the test section 2, and therefore the test section 2 is preferably provided to be transparent.
Optionally, the equipment located outside the test section 2 includes, but is not limited to, a high-speed camera, a particle velocimeter and a laser particle sizer, wherein the high-speed camera is only required to photograph the fluid; the particle velocimeter can obtain the velocity of the fluid at different cross sections and the distribution of the flow field by shooting the trace particles; the laser particle analyzer needs to inject laser for testing into the testing section 2 so as to obtain particle size data of liquid, and the shape of the testing section 2 influences the testing result of the laser particle analyzer, so the testing section 2 is preferably set to be a square cylinder so as to ensure that the laser particle analyzer achieves an ideal testing effect. It is easily understood that at least one of the high-speed camera, the particle velocimeter and the laser particle sizer is selected, i.e., an appropriate device is selected according to the purpose of the test.
Preferably, the test section 2 is a transparent square cylinder, and two ends of the square cylinder are respectively provided with a mounting hole.
In this embodiment, the detection device 3 comprises a liquid trap 31 placed in the test section 2. Specifically, the liquid trap 31 is used for liquid, and the amount of liquid collected by the liquid trap 31 can be used to determine the circumferential distribution uniformity of the liquid, and further, the flow rate characteristics and the circumferential distribution non-uniformity of the flow rate of the nozzle 41 can be obtained.
The structure of the liquid trap 31 includes, but is not limited to: the liquid collector 31 comprises a liquid collecting groove 311, a circular plate 312 and a support 313, wherein the liquid collecting groove 311 and the support 313 are respectively arranged on two sides of the circular plate 312, the liquid collecting groove 311 is provided with a plurality of liquid collecting grooves and uniformly distributed on the middle plate by taking the axis of the circular plate 312 as the center, each liquid collecting groove 311 is respectively provided with a liquid leakage hole, and a liquid leakage pipe 301 penetrating to the outside of the test section 2 is arranged on each liquid leakage hole.
Meanwhile, the liquid in the liquid collecting tank 311 is discharged in time through the matching of the liquid leakage holes and the liquid leakage pipes 301, so that the liquid overflow phenomenon of the liquid collecting tank 311 is avoided; and the liquid collected by the liquid collecting tank 311 can be obtained without taking out the liquid collector 31, so that the frequency of disassembling and assembling the liquid collector 31 in the test process is reduced, and the test steps are simplified.
Further, the structure of the sump 311 is limited in that the sump 311 is disposed to be inclined, the high end of the sump 311 intersects the axis of the circular plate 312, the low end of the sump 311 is connected to the edge of the circular plate 312, and the drain hole is formed at the bottom of the sump 311. Therefore, the liquid can flow to the bottom of the liquid collecting tank 311 under the action of gravity and flow out through the liquid leakage holes, so that the arrangement of liquid drainage equipment is avoided, and the cost is effectively reduced.
Furthermore, in one possible embodiment, the circular plate 312 is provided with 10-20 sumps 311. Specifically, the number of sumps 311 may be any one of 10, 12, 14, 16, 18, or 20.
Example 2:
on the basis of embodiment 1, the present embodiment describes the use and achieved technical effects of the integrated performance test apparatus of the swirler and the nozzle in embodiment 1 by combining with an actual test scenario:
referring to fig. 1-6, when the swirler and nozzle integration performance testing device is used for a nozzle and a swirler of a gas turbine, the swirler and nozzle integration performance testing device is vertically placed, a nozzle 41 and a swirler 42 are installed on a tool 1 through installation positions, as shown in fig. 4, the nozzle is located at the upper end of a casing 11, the swirler is located at the lower end of the casing 11, and the nozzle is communicated with the swirler. Meanwhile, a static pressure nozzle 403 is arranged around the nozzle, and the static pressure of the air flow in the housing 11 is measured through the static pressure nozzle 403.
Accordingly, the oil supply pipe communicates with the nozzle 41 through the oil feed nipple 401, and the air supply pipe 5 is fixed to the housing 11 and communicates with the rectifying pipe 12, alternatively, referring to fig. 2, the oil feed nipples 401 are provided in two. The fluid injected into the test section 2 is then fuel, air or a mixture of fuel and air.
The test section 2 and the detection device 3 have already been described in example 1 and will not be described in detail here. Alternatively, 20 liquid collecting grooves 311 are provided on the liquid trap 31.
The integrated performance test device for the swirler and the nozzle has the following test modes:
1. swirler 42 performance testing
At this point, the oil supply pipe is closed and the gas supply pipe is open, the outlet pipe 6 is connected to the exhaust system, and the liquid trap 31 need not be placed in the test section 2. The air supply system supplies air to the tool 1 through the air supply pipe, and obtains air inlet flow, temperature and pressure. The static pressure of the airflow within the housing 11 is measured by the static pressure nipple 403 and the effective flow area of the swirler 42 is obtained from the intake airflow, temperature and pressure (ACd).
Adding tracer particles into air provided by an air supply system, erecting a particle velocimeter outside the test section 2, starting the particle velocimeter when the tracer particles flow through the test section 2 to shoot an air flow field in the test section 2, further obtaining the velocity and flow field distribution of different positions of a section at the outlet of the swirler 42, and finally obtaining the rotational flow intensity (Sn) of the swirler 42.
2. Nozzle 41 Performance test
At this time, the oil supply pipe is opened and the gas supply pipe is closed, the outlet pipe 6 is connected to the air pump and the oil-gas separator, and the liquid trap 31 is placed in the test section 2. The oil supply system supplies oil to the nozzle 41 through the oil supply pipe, the fuel oil enters the testing section 2, the liquid collector 31 can measure the flow rate of the fuel oil passing through the nozzle 41 within a certain time, and a nozzle flow characteristic curve and a flow coefficient (Cd) can be obtained by fitting the total flow rate and the oil supply pressure; and respectively collecting the flow values of all the oil leakage holes, and comparing the deviation with the average value to obtain the circumferential distribution unevenness of the nozzle flow.
Meanwhile, a high-speed camera is erected outside the test section 2, the atomizing cone angle of the nozzle 41 under different oil pressures can be shot in the test section 2 by utilizing the high-speed camera, and the fuel particle Size (SMD) in the test section 2 under different oil supply pressures is measured by utilizing a laser particle sizer.
3. Nozzle 41 and swirler 42 match test
At this time, the oil supply pipe and the air supply pipe are both opened, that is, the oil supply system supplies oil to the nozzle 41 through the oil supply pipe, the air supply system supplies air to the tool 1 through the air supply pipe, the outlet pipeline 6 is connected with the air suction pump and the oil-gas separator, and the liquid trap 31 does not need to be placed. A high-speed camera, a particle velocimeter and a laser particle sizer are erected outside the test section 2, the high-speed camera shoots the atomization cone angle in the test section 2, the particle velocimeter shoots the flow field in the test section 2, and the laser particle sizer measures the fuel particle Size (SMD) of the test section 2. Furthermore, the inlet parameters of air and fuel oil are changed to obtain the influence rule of different air inflow conditions on the atomizing performance of the nozzle 41 and the concentration distribution and speed distribution conditions of the fuel oil in the whole flow field.
It is easy to understand that any suitable commercially available model is selected for the auxiliary equipment such as the air supply system, the oil supply system, the air pump, the oil-gas separator and the like, and the details are not repeated herein.
When the device is applied to the swirler 42 and the nozzle 41 of the gas turbine, only a single test can be carried out in the existing test device, and further, the auxiliary atomization effect of the swirler 42 on the nozzle 41 and the distribution of fuel in an actual air flow field cannot be evaluated. In addition to this, the following drawbacks exist:
1. the swirler 42 has no special test bed, and the existing swirler 42 performance test method is as follows: the method is used for optically measuring in a single-head test of a combustion chamber (gas turbine) to obtain the swirl strength (Sn) of the swirler 42 and the flow field structure characteristics in the downstream three-dimensional space of the swirler 42, and has the problems of high test cost, high test difficulty and the like.
2. The nozzle test bed has single function, only the flow characteristic of the nozzle 41 is measured, the flow coefficient (Cd) of the nozzle 41 is obtained, the measurement of the circumferential distribution unevenness of the nozzle 41 is neglected, the test precision is low, and the reliability of the test result is poor.
3. The measurement of the spray cone angle of the nozzle 41, the fuel particle Size (SMD) and the spatial distribution of the fuel cannot be accomplished without high-precision optical measuring equipment.
4. The nozzle test bed is arranged in an open space, so that fuel oil is evaporated to pollute air, and the health of test operators is influenced.
The vortex device and nozzle integrated performance test device effectively solves the technical problems and achieves the following technical effects:
1. through reasonable structural design, the performance test of the swirler 42 and the performance test of the nozzle 41 can be independently carried out on the same test device to obtain the performance parameters of the nozzle 41 and the swirler 42, the tests of the swirler 42 and the nozzle 41 can also be simultaneously carried out, the inlet parameters of air and fuel oil are changed, and the influence rule of different air inflow conditions on the atomizing performance of the nozzle 41 and the concentration distribution and speed distribution conditions of the fuel oil in the whole flow field are obtained.
2. When the performance test of the swirler 42 is carried out, the effective flow area of the swirler is obtained through a blowing test (ACd); meanwhile, a tracer particle velocimeter can be used for flow visualization test to obtain the flow field structure characteristics and the velocity field distribution of the axial section and the circumferential section at different positions downstream of the swirler 42, so as to obtain the swirl strength (Sn).
3. The weight of the fuel oil collected by the liquid collecting tank 311 can be obtained by weighing, then the flow coefficient (Cd) of the nozzle 41 is obtained by using a weighing method test, and in addition, the circumferential distribution unevenness of the nozzle 41 is measured by using the liquid collector 31 in consideration of the circumferential uneven distribution condition of the fuel oil; meanwhile, a high-speed camera and a laser particle analyzer can be adopted to measure the atomizing cone angle, the fuel particle Size (SMD) and the fuel velocity distribution of various types of nozzles.
4. The method is used for detecting the performance of the swirler 42 and the nozzle 41 in the mass production process, and qualified products are screened out according to the performance parameters of the nozzle 41 and the swirler 42 obtained through the combined test of the swirler 42 and the nozzle 41.
Finally, it should be noted that: the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The utility model provides a swirler and nozzle integration performance test device which characterized in that includes:
the device comprises a tool (1), a nozzle (41) and a swirler (42) are vertically arranged on the tool, and an air supply pipe (5) is arranged on the tool (1) so as to test the performance of the nozzle (41) or the swirler (42) independently or test the matching performance of the nozzle (41) and the swirler (42) in a combined manner;
the upper end of the testing section (2) is connected with the tool (1), and the lower end of the testing section is provided with an outlet pipeline (6); and a detection device (3) arranged inside or outside the test section (2);
the tool (1) comprises a cylindrical shell (11) and a rectifying tube (12) inserted in the shell (11), wherein the rectifying tube (12) is provided with a plurality of rectifying holes (101); correspondingly, the nozzle (41) is positioned at the upper end of the shell (11), the swirler (42) is positioned at the lower end of the shell (11), and the nozzle (41) and the swirler (42) are respectively partially inserted into the rectifying tube (12).
2. The swirler and nozzle integration performance testing device as claimed in claim 1, characterized in that the rectifying holes (101) are provided with a plurality of rows, and the rectifying holes (101) between adjacent rows are arranged in a staggered manner.
3. The swirler and nozzle integration performance testing device as claimed in claim 1 or 2, characterized in that the nozzle (41) is connected with a fuel supply pipe through a fuel inlet connector (401), and the gas supply pipe (5) is fixed on the housing (11) and communicated with the rectifier tube (12).
4. The swirler and nozzle integrated performance testing device as claimed in claim 3, wherein a mounting edge is arranged on the nozzle (41), and the mounting edge is fixed at the upper end of the housing (11) through a plurality of bolts (402); the inner side of the lower end of the shell (11) is provided with a cover plate (102), the swirler (42) compresses the cover plate (102) through a plurality of bolts (402), and gaskets for sealing are arranged on all the bolts (402).
5. The swirler and nozzle integration performance testing device as claimed in claim 1, wherein the testing section (2) is a transparent square cylinder, and two ends of the square cylinder are respectively provided with a mounting hole.
6. The swirler and nozzle integration performance testing device as claimed in claim 1, wherein the detection device (3) comprises a high-speed camera, a particle velocimeter and a laser particle sizer, which are respectively placed outside the testing section (2), and at least one of the high-speed camera, the particle velocimeter and the laser particle sizer is selected.
7. The swirler and nozzle integrated performance test device as claimed in claim 1, wherein the detection device (3) comprises a liquid trap (31) disposed in the test section (2), the liquid trap (31) comprises a liquid trap (311), a circular plate (312) and a bracket (313), the liquid trap (311) and the bracket (313) are disposed on two sides of the circular plate (312), the liquid trap (311) is disposed in a plurality and uniformly distributed on the middle plate around the axis of the circular plate (312), each liquid trap (311) is disposed with a liquid leakage hole, and a liquid leakage pipe (301) penetrating to the outside of the test section (2) is disposed on each liquid leakage hole.
8. The swirler and nozzle integration performance testing device as claimed in claim 7, wherein the catch basin (311) is arranged obliquely, the high end of the catch basin (311) intersects at the axis of the circular plate (312), the low end of the catch basin (311) is connected with the edge of the circular plate (312), and the weep hole is located at the bottom of the catch basin (311).
9. The swirler and nozzle integrated performance testing device as claimed in claim 7 or 8, wherein there are 10-20 catch basins (311).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210268302.1A CN114354203B (en) | 2022-03-18 | 2022-03-18 | Swirler and nozzle integration performance test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210268302.1A CN114354203B (en) | 2022-03-18 | 2022-03-18 | Swirler and nozzle integration performance test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114354203A CN114354203A (en) | 2022-04-15 |
| CN114354203B true CN114354203B (en) | 2022-06-03 |
Family
ID=81094884
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210268302.1A Active CN114354203B (en) | 2022-03-18 | 2022-03-18 | Swirler and nozzle integration performance test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114354203B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103007724A (en) * | 2012-12-08 | 2013-04-03 | 中国航天科技集团公司第六研究院第十一研究所 | Swirl type denitration ejector of circulating fluidized bed |
| CN103592132A (en) * | 2013-10-31 | 2014-02-19 | 哈尔滨汽轮机厂有限责任公司 | Pressurization visual combustion test device of combustor of gas turbine |
| CN212807589U (en) * | 2020-09-16 | 2021-03-26 | 中国航发商用航空发动机有限责任公司 | Nozzle performance testing device and nozzle tool thereof |
| CN114018346A (en) * | 2021-10-12 | 2022-02-08 | 苏州泽志流体技术有限公司 | Tool for measuring air flow of swirler of combustion chamber of gas turbine |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7195042B1 (en) * | 2006-04-28 | 2007-03-27 | Pratt & Whitney Canada Corp. | Testing rig and method for a fuel nozzle assembly |
| CN102507206B (en) * | 2011-10-20 | 2015-07-15 | 中国航空动力机械研究所 | Device for measuring distribution unevenness of fuel nozzles |
| CN102901126B (en) * | 2012-10-26 | 2015-01-14 | 中国航空动力机械研究所 | Combustion organizational structure |
| CN202993265U (en) * | 2012-12-27 | 2013-06-12 | 中国燃气涡轮研究院 | Lean partial pre-mixing and pre-evaporation combustion chamber |
| CN103411769B (en) * | 2013-08-23 | 2016-03-23 | 中国航空动力机械研究所 | For the air inlet stable-pressure device of gas-turbine unit swirler performance test |
| GB2547393B (en) * | 2014-12-05 | 2021-07-07 | Nuovo Pignone Srl | Method and system for predicting residual useful life of an air filter |
| CN107219066B (en) * | 2017-04-28 | 2019-04-26 | 中国航发湖南动力机械研究所 | For measuring the experimental rig of swirler air mass flow |
| CN107560836A (en) * | 2017-05-24 | 2018-01-09 | 天津成立航空技术有限公司 | A kind of fuel oil single injector circumferentially distributed experimental rig and its test method |
| CN207795422U (en) * | 2017-12-25 | 2018-08-31 | 深圳光启空间技术有限公司 | Nozzle arrangements, injection apparatus and engine |
| US10962345B2 (en) * | 2018-05-23 | 2021-03-30 | General Electric Company | Tool and method for inspecting an annular space of an engine |
| CN111426485B (en) * | 2020-04-27 | 2021-11-12 | 中国航发湖南动力机械研究所 | Flow measuring device, measuring system and measuring method for batch vortex generators |
| CN212539630U (en) * | 2020-08-20 | 2021-02-12 | 贵州亚亨自动化技术有限公司 | Fuel distribution measuring device between spray bars |
| CN113074927B (en) * | 2021-04-01 | 2022-10-04 | 中国科学院工程热物理研究所 | Comprehensive basic test device and test method for fuel nozzle atomization characteristics |
| CN114034489B (en) * | 2022-01-10 | 2022-03-25 | 成都中科翼能科技有限公司 | Gas turbine engine ground starting acceleration time calculation method |
-
2022
- 2022-03-18 CN CN202210268302.1A patent/CN114354203B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103007724A (en) * | 2012-12-08 | 2013-04-03 | 中国航天科技集团公司第六研究院第十一研究所 | Swirl type denitration ejector of circulating fluidized bed |
| CN103592132A (en) * | 2013-10-31 | 2014-02-19 | 哈尔滨汽轮机厂有限责任公司 | Pressurization visual combustion test device of combustor of gas turbine |
| CN212807589U (en) * | 2020-09-16 | 2021-03-26 | 中国航发商用航空发动机有限责任公司 | Nozzle performance testing device and nozzle tool thereof |
| CN114018346A (en) * | 2021-10-12 | 2022-02-08 | 苏州泽志流体技术有限公司 | Tool for measuring air flow of swirler of combustion chamber of gas turbine |
Non-Patent Citations (2)
| Title |
|---|
| Lie Jasa."Effects of Pressure and Nozzle Angle on RPM: New".《2017 International Conference on Broadband Communication, Wireless Sensors and Powering (BCWSP)》.2017,第1-4页. * |
| 黄强飞."空气雾化燃油喷嘴高效加工工艺研究".《科技创新导报》.2015,第12卷(第19期),第112-113页. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114354203A (en) | 2022-04-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104236917B (en) | Full-ring micro-size backflow combustor tester | |
| CN208333872U (en) | Modular trial device for swirl flow combustion thermal acoustic oscillation characteristic research | |
| CN113074927B (en) | Comprehensive basic test device and test method for fuel nozzle atomization characteristics | |
| CN106089492A (en) | A kind of ejector filler performance testing device | |
| CN115127790A (en) | Fuel manifold flow comprehensive test device with nozzle | |
| CN114354203B (en) | Swirler and nozzle integration performance test device | |
| CN207556859U (en) | A kind of combustor test equipment and system | |
| CN111413102B (en) | Model test piece and measuring device for head flow field test of annular combustion chamber | |
| CN107505137A (en) | A kind of combustor test equipment and system | |
| CN109632316B (en) | Water spraying device and system for water swallowing test of sub-combustion ramjet engine | |
| CN110361182A (en) | The equal bulk-breaking performance testing device of coolant liquid jet stream and method | |
| CN104353376B (en) | A kind of oil gas mixing machine being applied in oil system experiment porch | |
| CN207526535U (en) | A kind of steam turbine axial exhaust cylinder | |
| CN116398905A (en) | Backflow combustion chamber adopting visible optical observation structure | |
| CN106525159A (en) | Air flow measurement device | |
| Corber et al. | Experimental and analytical characterization of alternative aviation fuel sprays under realistic operating conditions | |
| KR102565126B1 (en) | Compressor circumferential fluid distribution system | |
| CN110487558A (en) | A kind of high temperature and pressure test system for gas-turbine combustion chamber | |
| CN111829787B (en) | Visual combustion experiment platform capable of realizing multiple mixing | |
| CN113959700B (en) | Device and method for testing performance of cooling liquid jet flow equally-dividing component of multi-strand grouping jet flow | |
| Gadgil et al. | Mass distribution studies in effervescent sprays | |
| CN1028969C (en) | Generating method and apparatus of large-flow microminiature single particle | |
| CN109186889A (en) | A kind of diesel engine automated watch-keeping facility | |
| CN206847929U (en) | A kind of frock for detecting the circumferentially distributed unevenness of port fuel | |
| CN108204603A (en) | Burner assembly, the gas turbine equipment including it and the method that operates this equipment |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |