Method for determining performance indexes of pressure atomizing nozzle

A determination method and technology of atomizing nozzles, applied in the direction of fuel injection device, engine test, machine/structural component test, etc., can solve the problems of poor combustion performance and large loss, achieve good combustion performance, reduce repetition and loss , the effect of shortening the R&D cycle

Active Publication Date: 2017-01-04
TIANJIN CHENGLI AVIATION TECH CO LTD
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Problems solved by technology

[0003] In the past, in the design of combustion chambers and fuel nozzles, there was no clear method for determining nozzle performance indicators, and there was obvious arbitrariness and blindness. As a result, in the process of combustor re

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  • Method for determining performance indexes of pressure atomizing nozzle

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[0010] In order to further understand the content, features, and effects of the present invention, the following examples are given to illustrate in detail as follows:

[0011] The present invention includes the following steps:

[0012] a. Determination of the auxiliary spray cone angle of the fuel nozzle: The auxiliary spray cone angle mainly affects the lean flameout and ignition performance of the combustion chamber. A small auxiliary spray angle is beneficial to the flameout and ignition performance of the combustion chamber, generally less than 80°. Select several nozzles with different angles in the range of 50°~80°, conduct flameout test under idle state on the ground, and select the best value through test screening.

[0013] b. Determination of the auxiliary spray cone angle of the fuel nozzle: It mainly affects the combustion efficiency of the combustion chamber and the outlet temperature field, so its size depends on the size of the return zone of the combustion chamber a...

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Abstract

The invention belongs to the technical field of aero-engine fuel nozzle design and especially relates to a method for determining the performance indexes of a pressure atomizing nozzle. The method includes the steps of a, determining an auxiliary spray cone angle, to be more specific, selecting a plurality of nozzles of different angles in a range of 50-80 degrees, and performing a flameout experiment under a ground idle state to select an optimal value; b, determining a main spray cone angle, to be more specific, calculating the main spray cone angle according to the size and position of a recirculation zone in a flame cylinder; c, determining auxiliary nozzle flow; d, determining main nozzle flow according to the principle that Fn/delta P of an engine in the maximum state is smaller than 2.5 and the Fn/delta P of the engine in a cruising state is smaller than 13; e, determining nozzle atomizing quality; f, determining flow distribution nonuniformity, which is smaller than 1.5-2.0%, of a master fuel pipe. The method has the advantages that the performance indexes are determined step by step by reasonable experiments and calculating methods, repetition and loss during research and development are reduced, and research and development cycle is shortened.

Description

technical field [0001] The invention belongs to the technical field of aero-engine fuel nozzle design, in particular to a method for determining the performance index of a pressure atomization nozzle. Background technique [0002] The performance index of the pressure atomizing nozzle refers to the auxiliary spray cone angle, the main spray cone angle, the flow rate of the auxiliary nozzle, the flow rate of the main nozzle, and the spray quality standard. These indicators have a direct impact on the comprehensive performance of the combustion chamber, including ignition performance, flameout performance, combustion efficiency, outlet temperature field, carbon deposition, smoke and exhaust pollution. Therefore, in the design stage of the combustion chamber, the determination of the performance index of the fuel nozzle is an important link that cannot be ignored. If the index is not selected properly, it will not only affect the combustion performance, but also affect the deve...

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Application Information

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IPC IPC(8): F02M65/00
CPCF02M65/00
Inventor 尚明智陈立郝晓波樊淼海李晓宁
Owner TIANJIN CHENGLI AVIATION TECH CO LTD
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