CN219798708U - Fuel nozzle flow measuring device of turbojet engine - Google Patents
Fuel nozzle flow measuring device of turbojet engine Download PDFInfo
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- CN219798708U CN219798708U CN202320209837.1U CN202320209837U CN219798708U CN 219798708 U CN219798708 U CN 219798708U CN 202320209837 U CN202320209837 U CN 202320209837U CN 219798708 U CN219798708 U CN 219798708U
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- ignition
- main combustion
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- 239000000446 fuel Substances 0.000 title claims abstract description 111
- 238000002485 combustion reaction Methods 0.000 claims abstract description 22
- 239000000295 fuel oil Substances 0.000 claims abstract description 15
- 239000003921 oil Substances 0.000 claims abstract description 8
- 238000005259 measurement Methods 0.000 claims description 10
- 239000002828 fuel tank Substances 0.000 claims description 8
- 239000007788 liquid Substances 0.000 claims description 4
- 238000012360 testing method Methods 0.000 abstract description 26
- 238000000889 atomisation Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 3
- 230000003993 interaction Effects 0.000 description 2
- 230000005856 abnormality Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000003749 cleanliness Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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- Testing Of Engines (AREA)
Abstract
The utility model discloses a fuel nozzle flow measuring device of a turbojet engine, which comprises an oil supply main path, an ignition nozzle branch path and a main combustion nozzle branch path. The oil supply main path comprises a fuel oil tank, a pressure transmitter, a fuel pump, a first flowmeter, a first electromagnetic valve, a first one-way valve and a second one-way valve; the ignition nozzle branch comprises a third electromagnetic valve, a second flowmeter, a third filter, a pressure transmitter, an ignition nozzle and a second fuel collecting container; the main combustion nozzle branch comprises a second electromagnetic valve, a second filter, a pressure transmitter, a main combustion nozzle and a first fuel collecting container. The utility model meets the test item test conditions of the nozzle flow technical requirement, has higher reliability and accuracy, and can finish the flow test of the main combustion nozzle and the ignition nozzle in one oil supply pipeline.
Description
Technical Field
The utility model relates to a flow measuring device of a fuel nozzle of a turbojet engine, and belongs to the technical field of fluid testing.
Background
The fuel nozzle of the turbojet engine is divided into an ignition nozzle and a main fuel nozzle, and the fuel atomization characteristic of the ignition nozzle and the flow uniformity of the main fuel nozzle play a vital role in the running process of the turbojet engine. The ignition nozzle has good fuel atomization effect, so that the turbojet engine can be easily successfully ignited at low rotation speed; when the main combustion nozzle ring pipe has better flow uniformity, a more uniform temperature field can be formed in the combustion chamber, so that the turbine can be prevented from being damaged due to local high temperature. The fuel system can be tested before the whole turbojet engine is tested, and the reliability of the system and the performance of the fuel nozzle are verified. Because the performance of the fuel nozzle is inconvenient to measure during the thermal state test of the turbojet engine, the performance of the fuel nozzle is required to be measured at normal temperature and normal pressure, and then the fuel parameters required during the thermal state operation of the turbojet engine are calculated through numerical simulation calculation.
For the reasons, a fuel nozzle flow measuring device of the turbojet engine needs to be designed, various performance parameters of the fuel nozzle at normal temperature and normal pressure are measured, and a sufficient test data basis is provided for simulating and calculating parameters such as fuel flow, fuel pressure and the like required by the thermal state operation of the turbojet engine.
Disclosure of Invention
The utility model aims to provide a fuel nozzle flow measuring device of a turbojet engine, so as to meet the performance test requirements of various existing fuel nozzles of the turbojet engine, and particularly can realize the flow test of a main fuel nozzle and an ignition nozzle at the same time.
The utility model is realized by the following scheme:
the fuel nozzle flow measuring device of the turbojet engine comprises,
the oil supply main circuit is sequentially connected with a fuel tank, a first filter, a first pressure transmitter, a fuel pump, a second pressure transmitter, a first flowmeter, a first electromagnetic valve, a third pressure transmitter, a first check valve, a fourth pressure transmitter and a second check valve;
the ignition nozzle branch is sequentially connected with a third electromagnetic valve, a second flowmeter, a third filter, a pressure transmitter, an ignition nozzle and a fuel oil collecting container, wherein the inlet end of the third electromagnetic valve is connected between the outlet end of the first one-way valve and the inlet end of the second one-way valve;
and the main combustion nozzle branch is sequentially connected with a second electromagnetic valve, a second filter, a fifth pressure transmitter, a main combustion nozzle and a fuel oil collecting container, wherein the inlet end of the second electromagnetic valve is connected with the outlet end of the second one-way valve.
Alternatively, the fuel tank is provided with a blow-down valve and a level gauge.
Alternatively, the ignition nozzle branch comprises a plurality of ignition nozzles, the inlet end of each ignition nozzle is connected with the outlet end of the third filter, the outlet end of each ignition nozzle is connected with an independent fuel collecting container, and a pressure transmitter is arranged between the inlet end of each ignition nozzle and the outlet end of the third filter.
Alternatively, the main fuel nozzle branch comprises a plurality of main fuel nozzles, the inlet end of each main fuel nozzle is connected with the outlet end of the second filter, the outlet end of each main fuel nozzle is connected with a separate fuel oil collecting container, and the inlet ends of the main fuel nozzles share a pressure transmitter.
The measuring principle of the utility model is as follows: the fuel pump transmits the fuel in the fuel tank to the ignition nozzle branch, and the fuel is atomized and diffused into the fuel collecting container after passing through the ignition nozzle, and then the flow of the ignition nozzle and the angle of an atomized cone are measured; and continuously increasing the fuel oil supply flow, opening a second one-way valve corresponding to the branch of the main combustion nozzle, allowing the fuel oil to enter the fuel oil collecting container after passing through the main combustion nozzle, and measuring the flow of the main combustion nozzle and the angle of the atomization cone.
Compared with the prior art, the utility model has the following characteristics:
(1) The flow measurement of the ignition nozzle and the main combustion nozzle is combined in one set of oil supply main path through two one-way valves, so that the complexity of the flow test device is reduced;
(2) The fuel flow in the fuel supply main path is respectively switched to the test of the ignition nozzle and the main combustion nozzle, so that independent measurement of the ignition nozzle in the ignition nozzle branch path and the main combustion nozzle in the main combustion nozzle branch path is realized, and the independent measurement is not influenced;
(3) The control mode is simple, the adjustment of flow and the switching of pipelines can be realized only by controlling the fuel pump and the electromagnetic valve, the control of test parameters is stable, the safety is strong, the sealing of the pipelines is easy to realize, and the operation is simple.
Drawings
FIG. 1 is a diagram showing the construction and connection of a measuring device according to the present utility model;
in the figure: 1-first filter, 2-first pressure transmitter, 3-fuel pump, 4-second pressure transmitter, 5-first flow meter, 6-first solenoid valve, 7-third pressure transmitter, 8-first check valve, 9-fourth pressure transmitter, 10-second check valve, 11-second solenoid valve, 12-second filter, 13-fifth pressure transmitter, 14-main fuel nozzle, 15-first fuel collection container, 16-third solenoid valve, 17-second flow meter, 18-third filter, 19-sixth pressure transmitter, 20-ignition nozzle, 21-second fuel collection container, 22-seventh pressure transmitter, 23-fuel tank.
Detailed Description
The present utility model will be further described with reference to the drawings and the specific embodiments, but it should not be construed that the scope of the subject matter of the present utility model is limited to the following embodiments, and various modifications, substitutions and alterations made according to the ordinary skill and familiar means of the art to which this utility model pertains are included within the scope of the present utility model without departing from the above technical idea of the utility model.
As shown in fig. 1, the device for measuring (calibrating) the flow rate of the fuel nozzle of the turbojet engine mainly comprises a first filter 1, a first pressure transmitter 2, a fuel pump 3, a first flowmeter 5, a first electromagnetic valve 6, a first one-way valve 8, a second filter 12, a main fuel nozzle 14, a first fuel collecting container 15, an ignition nozzle 20, a fuel tank 23, an electric control console and the like. The device can easily realize the regulation and control of the fuel pump 3 and the electromagnetic valves (the first electromagnetic valve 6, the second electromagnetic valve 11 and the third electromagnetic valve 16), such as the flow regulation of the fuel pump 3 and the start and stop of the electromagnetic valves. Each test data can be stored and printed, and the method is convenient and quick. The testing device has reasonable layout and easy operation. The fuel pump 3 pumps the fuel in the fuel tank 23 into the fuel supply main path, when the fuel pressure in the fuel supply main path exceeds the set pressure of the first one-way valve 8, the fuel enters the ignition nozzle branch and starts to be atomized and spread, and enters the fuel collecting container, and the matching relation between the fuel flow and the fuel pressure of the ignition nozzle 20 and the physical characteristic of fuel atomization at the ignition nozzle 20 can be obtained through test data; and continuously increasing the flow rate of the main fuel supply path, when the fuel pressure of the main fuel supply path exceeds the set pressure of the second one-way valve, closing the third electromagnetic valve 16 of the ignition nozzle branch, and enabling the fuel to enter the main fuel nozzle branch, pass through the main fuel nozzle 14 and enter each fuel collection container, so that the matching relation between the fuel flow rate and the fuel pressure of the main fuel nozzle can be obtained through test data.
After the testing device is started, the numerical value of each electric instrument is displayed in a human-computer operation interface, and whether the data abnormality exists or not is checked. The first electromagnetic valve 6, the third electromagnetic valve 16 and the second electromagnetic valve 11 are firstly opened, the fuel pump 3 is started, the flow rate of the fuel supply main path is gradually increased, when the fuel pressure of the fuel supply main path is larger than the set pressure of the first one-way valve 8, fuel enters the ignition nozzle branch (comprising 2 ignition nozzles 20, 2 second fuel collecting containers 21, a sixth pressure transmitter 19 and a seventh pressure transmitter 22), and then is atomized and diffused from the two ignition nozzles 20, enters the second fuel collecting containers 21, and flow measurement and the size of the fuel atomization cone angle of the ignition nozzles can be carried out. When the fuel pressure of the fuel supply main path is larger than the set pressure of the second check valve 10, the second check valve 10 is opened, the third electromagnetic valve 16 is automatically closed, fuel enters the main fuel branch path and is ejected out through the main fuel nozzles 14 into the first fuel collecting containers 15 (7 main fuel nozzles 14 and 7 first fuel collecting containers 15 in the main fuel branch path), and flow measurement of each main fuel nozzle 14 can be performed.
After the test is finished, the oil supply main path automatically stops running when the electric control console stop button is pressed, and the fuel pump 3, the first electromagnetic valve 6 and the second electromagnetic valve 11 are immediately closed.
The fuel oil tank 23 is provided with a remote magnetic transfer plate-turning liquid level meter, the control console man-machine interaction interface can display the current liquid level height of the fuel oil tank 23 in real time, and when the liquid level of the fuel oil is lower than the set fuel oil height, the control system sends out an alarm signal to prompt that the fuel oil tank 23 should be filled with fuel oil.
The method for using the fuel nozzle flow measuring device of the turbojet engine in the embodiment is as follows:
step one, turning on a power supply of an electric control console, turning on a man-machine interaction interface, and checking whether various electric instrument parameters are normal.
Step two, the first electromagnetic valve 6 of the oil supply main path and the third electromagnetic valve 16 of the ignition nozzle branch are opened, the fuel pump 3 is started, after the fuel pressure is larger than that of the first one-way valve 8, the first one-way valve 8 is opened, the fuel enters the ignition nozzle branch, and the flow of each ignition nozzle 20 and the angle of the fuel atomization cone are measured.
And thirdly, adjusting the rotation speed of the fuel pump 3, increasing the fuel flow, closing the third electromagnetic valve 16 of the ignition nozzle branch when the fuel pressure is greater than the pressure of the second one-way valve 10 of the main fuel nozzle branch, enabling fuel to enter the main fuel nozzle branch, enabling the fuel to jet into the first fuel collecting container 15 through the main fuel nozzles 14, and measuring the flow of each main fuel nozzle 14.
And step four, pressing a control console stop button, and closing the fuel pump 3 and each electromagnetic valve.
And fifthly, finishing the test bed, printing test data, and closing the power supply of the test bed.
The test equipment in the embodiment is accurate in flow control, and each item of test data has a real-time acquisition function and can be printed at any time. The utility model has the advantages of stable test parameter, high test measurement precision, good pipeline tightness, high cleanliness, simple test operation, strong safety and the like, and perfectly meets the test requirements of the test.
Claims (4)
1. The utility model provides a turbojet engine fuel nozzle flow measurement device which characterized in that: comprising the steps of (a) a step of,
the oil supply main circuit is sequentially connected with a fuel tank (23), a first filter (1), a first pressure transmitter (2), a fuel pump (3), a second pressure transmitter (4), a first flowmeter (5), a first electromagnetic valve (6), a third pressure transmitter (7), a first check valve (8), a fourth pressure transmitter (9) and a second check valve (10);
the ignition nozzle branch is sequentially connected with a third electromagnetic valve (16), a second flowmeter (17), a third filter (18), a pressure transmitter, an ignition nozzle (20) and a fuel collection container, wherein the inlet end of the third electromagnetic valve (16) is connected between the outlet end of the first one-way valve (8) and the inlet end of the second one-way valve (10);
and the main combustion nozzle branch is sequentially connected with a second electromagnetic valve (11), a second filter (12), a fifth pressure transmitter (13), a main combustion nozzle (14) and a fuel oil collecting container (15), wherein the inlet end of the second electromagnetic valve (11) is connected with the outlet end of the second one-way valve (10).
2. The turbojet engine fuel nozzle flow measurement device of claim 1, wherein: the fuel tank (23) is provided with a drain valve and a liquid level meter.
3. The turbojet engine fuel nozzle flow measurement device of claim 1, wherein: the ignition nozzle branch comprises a plurality of ignition nozzles (20), the inlet end of each ignition nozzle (20) is connected with the outlet end of the third filter (18), the outlet end of each ignition nozzle (20) is connected with an independent fuel collecting container, and a pressure transmitter is arranged between the inlet end of each ignition nozzle (20) and the outlet end of the third filter (18).
4. The turbojet engine fuel nozzle flow measurement device of claim 1, wherein: the main combustion nozzle branch comprises a plurality of main combustion nozzles (14), wherein the inlet end of each main combustion nozzle (14) is connected with the outlet end of the second filter (12), the outlet end of each main combustion nozzle (14) is connected with an independent fuel oil collecting container, and the inlet ends of the main combustion nozzles (14) share a pressure transmitter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320209837.1U CN219798708U (en) | 2023-02-14 | 2023-02-14 | Fuel nozzle flow measuring device of turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320209837.1U CN219798708U (en) | 2023-02-14 | 2023-02-14 | Fuel nozzle flow measuring device of turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219798708U true CN219798708U (en) | 2023-10-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320209837.1U Active CN219798708U (en) | 2023-02-14 | 2023-02-14 | Fuel nozzle flow measuring device of turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219798708U (en) |
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2023
- 2023-02-14 CN CN202320209837.1U patent/CN219798708U/en active Active
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