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Designing method of fuel nozzle reticular fuel filter

A technology of fuel nozzle and design method, which is applied to fuel injection devices, mechanical equipment, liquid fuel feeders, etc., and can solve the problems of insufficient flow area, large pressure loss, and reduced fuel supply pressure, etc.

Active Publication Date: 2020-05-19
TIANJIN CHENGLI AVIATION TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Sometimes due to the insufficient flow area of ​​the oil filter, the pressure loss on the oil filter is too large, causing the oil supply pressure in front of the sprayer to drop, affecting the flow rate of the sprayer and the size of the spray cone angle, and bringing great trouble to the debugging of the nozzle

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] (1) Filter size calculation:

[0032] ① Calculate the total flow area according to the maximum flow through the oil filter and the pressure difference between the inlet and outlet of the oil filter (0.5 ~ 1.0kpa), and the flow coefficient is 0.6,

[0033] ②According to the minimum slit size of the sprayer, take the single hole diameter size of the oil filter, which is 1 / 10 of the minimum slit size, and then obtain the mesh number of the oil filter,

[0034] ③Choose the model of the oil filter according to the mesh number of the oil filter, and according to the size given by the filter model, we can get the outline size of the filter we need,

[0035] ④ Calculate the pressure drop of the oil filter according to the resistance coefficient of the filter screen recommended in the "Hydraulic Friction Handbook".

[0036] ⑤ If it exceeds this range, return to step 1, assume the flow coefficient again, and repeat the calculation of steps 1 to 4 until it is reasonable;

[0037...

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Abstract

The invention provides a designing method of a fuel nozzle reticular fuel filter. The designing method comprises the following steps: 1, controlling the flow resistance loss of the fuel filter, and controlling the pressure drop generated on the fuel filter within the range of 0.5-1.0 kpa; 2, reasonably selecting the size of the fuel filter screen mesh; and 3, designing the reticular fuel filter structure: (1) rigidity of the fuel filter avoids deformation during the working process, (2) the fit clearance between the fuel filter and a nozzle shell is less than the screen mesh size, and (3), thefuel filter screen is made of nickle and stainless steel wires or is a metal foil screen formed through laser boring of metal foil. According to the designing method, the reasonable control range offuel filter pressure drop, the selecting principle of the screen mesh diameter and the designing key points of the fuel filter structure are given to ensure that the designed reticular fuel filter meets the nozzle working requirements.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a design method for a fuel nozzle mesh oil filter. Background technique [0002] The role of the oil filter in the fuel nozzle is to filter out the solid impurities in the fuel and avoid the small gaps in the sprayer from being blocked. The setting of the oil filter is a necessary measure to ensure the reliability of the fuel nozzle. However, the size of the flow area of ​​the oil filter will produce different pressure losses on the fuel oil filter, which will affect the fuel supply pressure before the sprayer, and the result will directly affect the nozzle flow rate, spray cone angle and spray quality. In addition, improper selection of the hole size of the oil filter will also cause coking of the fuel, which will not only block the filter and cause premature failure of the oil filter, but also damage the performance of the nozzle. Therefore, the design quality of the oil ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02M61/18F02M61/16F02M37/34
CPCF02M61/18F02M61/16F02M37/34
Inventor 尚明智陈立任金茹
Owner TIANJIN CHENGLI AVIATION TECH CO LTD
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