CN103593501A - Design method of aeroengine lubricating oil system - Google Patents
Design method of aeroengine lubricating oil system Download PDFInfo
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- CN103593501A CN103593501A CN201310474180.2A CN201310474180A CN103593501A CN 103593501 A CN103593501 A CN 103593501A CN 201310474180 A CN201310474180 A CN 201310474180A CN 103593501 A CN103593501 A CN 103593501A
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Abstract
A design method of an aeroengine lubricating oil system includes: assuming steady-state calculation analysis for a system; ignoring gravity effect of the system; ignoring elbows with an angle of smaller than 10 degrees and bend elements; disregarding the heat exchange process between a flow path and the outside; for the positive cycle lubricating oil system, ignoring the temperature influence upon resistance loss of a pipeline in the front of a radiator; providing a lubricating oil system design, performing feedback iteration on bearing chamber nozzle flow tests, interpolating an oil supply pressure difference, performing iterative repetitive calculation, and outputting results if the design requirements are met. Through the application of the method, distribution of parameters such as lubricating oil system pressure, flow, Reynolds number and flow speed is provided for various types of engine lubricating oil systems, and parameters such as system pressure and flow are provided for lubricating oil system parts. The method has the advantages that the method is directly applicable to the design of lubricating systems in active engines and engines under research, and high-reliability high-precision technical design support is provided for the design of advanced engine lubricating oil systems.
Description
Technical field
The present invention relates to Aero-Engine Lubrication System design and analysis and computing method, particularly a kind of Aero-Engine Lubrication System method for designing.
Background technology
At present, only in oil feed pump outlet, measure the fuel feeding pressure reduction of a charge oil pressure or some nozzles.Firing test data shows, traditional nominal pressure and system charge oil pressure test run value differ larger.Thus, be that test or calculate all can not obtain comprehensively, parameter result is in order to describe the work of oil system exactly.
Formerly set out in Motivation Research, it has higher requirement to the performance of mechanical system, life and reliability etc., and this,, with regard to requiring oil system at different conditions, main fuel feeding cooling, lubricating component to be divided and mixed, reaches the requirement of accurate design.But before oil system is applied to engine, domestic also do not have a system-level lubricating system exerciser, to oil system design verification and correction.The pressure of oil system and flow are most important parameters.And owing to restricted by objective condition, the parameter that can test is few, affected the carrying out of design requirement of the miniaturization of advanced engine requirement oil system volume, lightweightization and high reliability.
Therefore, oil system design is badly in need of breaking through traditional design method, sets up a kind ofly to improve oil system design accuracy, can expand and grasp each site pressure of oil system and data on flows, and can improve towards each model the novel simulated method for designing of design efficiency.
Summary of the invention
The object of the invention is for improving the Aero-Engine Lubrication System designed capacity that becomes more meticulous, spy provides a kind of Aero-Engine Lubrication System method for designing.
The invention provides a kind of Aero-Engine Lubrication System method for designing, it is characterized in that: described Aero-Engine Lubrication System method for designing, is specially:
Supposing the system is stable state computational analysis, ignore its gravity effect, ignored elbow and broken pipe element that angle of bend is less than 10 degree, do not consider stream and extraneous heat transfer process, for the oil system of forward circulation, ignore the impact of the resistance loss of pipeline of temperature before on heating radiator;
Proposing oil system design iterates with each bearing bore nozzle flow test feedback, detailed process is: initialization system fuel feeding pressure reduction initial value △ P=△ Pi first, the exterior line numerical model of analog computation based on engine UG model, obtain exterior line drag losses △ Pw, △ P-△ Pw is as nozzle flow Experimental Calibration pressure reduction △ Pb, simulate again the nozzle flow test model based on physical arrangement, can obtain each nozzle and meet the structured value that design discharge requires, the oil system numerical model of foundation based on the rear structure of nozzle flow test, obtain flow system flow pressure distribution, obtain new fuel feeding pressure reduction △ P=△ Pi+1 simultaneously, with the comparison of design initial value, when △ Pi+1-△ Pi is greater than δ, wherein δ is system permissible variation, to fuel feeding pressure reduction interpolation, iterate and repeat above-mentioned computation process, until △ Pi+1-△ Pi≤δ, Output rusults meets design requirement,
Proposition is based on physical arrangement and be applicable to each parts numerical simulation model of oil system of oil system operating characteristic, is less than 6.1% with test firing test data comparison relative error;
By application the design method, for each model engine oil system provides the distribution of oil system pressure, flow, reynolds number Re and flow parameters, and test nozzle arrangements design initial value is provided for each bearing bore nozzle flow of each model engine oil system, and be oil system parts, comprise the parameter that system pressure and flow are provided for dump pump, oil filter, heating radiator, oil tank, pressure regulation, poor valve design and verification experimental verification; By application the design method, for revising oil system fuel feeding pressure reduction and changing certain bearing bore fuel supply flow rate, provide the structural design value of oil system pipeline or throttle orifice or nozzle.
Advantage of the present invention:
Improve the Aero-Engine Lubrication System designed capacity that becomes more meticulous, propose the method for designing that oil system design and each bearing bore nozzle flow test feedback iterate; Proposition is based on physical arrangement and be applicable to each parts numerical simulation model of oil system of oil system operating characteristic, with test relatively relative error be less than 15%; By application the design method, for each model engine oil system provides the distribution of oil system pressure, flow, Re and flow parameters, and test nozzle arrangements design initial value is provided for each bearing bore nozzle flow of each model engine oil system; By application the design method, for revising oil system fuel feeding pressure reduction and changing certain bearing bore fuel supply flow rate, provide the structural design value of oil system pipeline or throttle orifice or nozzle.Can directly apply to active service engine, in the oil system design of R&D motives, for advanced engine oil system design provides high reliability and the support of high-precision refinement designing technique.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is oil system numbered analog simulation method for designing block diagram.
Embodiment
Embodiment 1
The present embodiment provides a kind of Aero-Engine Lubrication System method for designing, it is characterized in that: described Aero-Engine Lubrication System method for designing, is specially:
Supposing the system is stable state computational analysis, ignore its gravity effect, ignored elbow and broken pipe element that angle of bend is less than 10 degree, do not consider stream and extraneous heat transfer process, for the oil system of forward circulation, ignore the impact of the resistance loss of pipeline of temperature before on heating radiator;
Proposing oil system design iterates with each bearing bore nozzle flow test feedback, detailed process is: initialization system fuel feeding pressure reduction initial value △ P=△ Pi first, the exterior line numerical model of analog computation based on engine UG model, obtain exterior line drag losses △ Pw, △ P-△ Pw is as nozzle flow Experimental Calibration pressure reduction △ Pb, simulate again the nozzle flow test model based on physical arrangement, can obtain each nozzle and meet the structured value that design discharge requires, the oil system numerical model of foundation based on the rear structure of nozzle flow test, obtain flow system flow pressure distribution, obtain new fuel feeding pressure reduction △ P=△ Pi+1 simultaneously, with the comparison of design initial value, when △ Pi+1-△ Pi is greater than δ, wherein δ is system permissible variation, to fuel feeding pressure reduction interpolation, iterate and repeat above-mentioned computation process, until △ Pi+1-△ Pi≤δ, Output rusults meets design requirement,
Proposition is based on physical arrangement and be applicable to each parts numerical simulation model of oil system of oil system operating characteristic, is less than 6.1% with test firing test data comparison relative error;
By application the design method, for each model engine oil system provides the distribution of oil system pressure, flow, reynolds number Re and flow parameters, and test nozzle arrangements design initial value is provided for each bearing bore nozzle flow of each model engine oil system, and be oil system parts, comprise the parameter that system pressure and flow are provided for dump pump, oil filter, heating radiator, oil tank, pressure regulation, poor valve design and verification experimental verification; By application the design method, for revising oil system fuel feeding pressure reduction and changing certain bearing bore fuel supply flow rate, provide the structural design value of oil system pipeline or throttle orifice or nozzle.
Claims (1)
1. an Aero-Engine Lubrication System method for designing, is characterized in that: described Aero-Engine Lubrication System method for designing, is specially:
Supposing the system is stable state computational analysis, ignore its gravity effect, ignored elbow and broken pipe element that angle of bend is less than 10 degree, do not consider stream and extraneous heat transfer process, for the oil system of forward circulation, ignore the impact of the resistance loss of pipeline of temperature before on heating radiator;
Proposing oil system design iterates with each bearing bore nozzle flow test feedback, detailed process is: initialization system fuel feeding pressure reduction initial value △ P=△ Pi first, the exterior line numerical model of analog computation based on engine UG model, obtain exterior line drag losses △ Pw, △ P-△ Pw is as nozzle flow Experimental Calibration pressure reduction △ Pb, simulate again the nozzle flow test model based on physical arrangement, can obtain each nozzle and meet the structured value that design discharge requires, the oil system numerical model of foundation based on the rear structure of nozzle flow test, obtain flow system flow pressure distribution, obtain new fuel feeding pressure reduction △ P=△ Pi+1 simultaneously, with the comparison of design initial value, when △ Pi+1-△ Pi is greater than δ, wherein δ is system permissible variation, to fuel feeding pressure reduction interpolation, iterate and repeat above-mentioned computation process, until △ Pi+1-△ Pi≤δ, Output rusults meets design requirement,
Proposition is based on physical arrangement and be applicable to each parts numerical simulation model of oil system of oil system operating characteristic, is less than 6.1% with test firing test data comparison relative error;
By application the design method, for each model engine oil system provides the distribution of oil system pressure, flow, reynolds number Re and flow parameters, and test nozzle arrangements design initial value is provided for each bearing bore nozzle flow of each model engine oil system, and be oil system parts, comprise the parameter that system pressure and flow are provided for dump pump, oil filter, heating radiator, oil tank, pressure regulation, poor valve design and verification experimental verification.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104408243A (en) * | 2014-11-19 | 2015-03-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for correcting installation thrust of engine model |
| CN106124219A (en) * | 2016-05-31 | 2016-11-16 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of assay device verifying oil pump function of having no progeny in lubricating oil and verification method |
| CN106709173A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Method for correcting wind resistance characteristic of oil cooler |
| CN109213004A (en) * | 2018-11-15 | 2019-01-15 | 中国直升机设计研究所 | A method of building the engine Real-Time Model of Helicopter Simulator |
| CN109269398A (en) * | 2018-10-16 | 2019-01-25 | 北京动力机械研究所 | A kind of digitlization angular displacement sensor signal conditioning circuit design method |
| CN118036343A (en) * | 2024-04-11 | 2024-05-14 | 中国航发四川燃气涡轮研究院 | Design method and system for oil supply flow path of accessory case of aero-engine |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104408243A (en) * | 2014-11-19 | 2015-03-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for correcting installation thrust of engine model |
| CN104408243B (en) * | 2014-11-19 | 2019-02-12 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of engine mockup installed thrust modification method |
| CN106124219A (en) * | 2016-05-31 | 2016-11-16 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of assay device verifying oil pump function of having no progeny in lubricating oil and verification method |
| CN106124219B (en) * | 2016-05-31 | 2018-12-11 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of experimental rig and verification method for verifying lubricating oil pumping function after lubricating oil interrupts |
| CN106709173A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Method for correcting wind resistance characteristic of oil cooler |
| CN106709173B (en) * | 2016-12-15 | 2019-11-15 | 中国航空工业集团公司西安飞机设计研究所 | A method of amendment oil cooler windage characteristic |
| CN109269398A (en) * | 2018-10-16 | 2019-01-25 | 北京动力机械研究所 | A kind of digitlization angular displacement sensor signal conditioning circuit design method |
| CN109269398B (en) * | 2018-10-16 | 2020-08-04 | 北京动力机械研究所 | Design method of signal conditioning circuit of digital angular displacement sensor |
| CN109213004A (en) * | 2018-11-15 | 2019-01-15 | 中国直升机设计研究所 | A method of building the engine Real-Time Model of Helicopter Simulator |
| CN118036343A (en) * | 2024-04-11 | 2024-05-14 | 中国航发四川燃气涡轮研究院 | Design method and system for oil supply flow path of accessory case of aero-engine |
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