CN105784376A - Fault eliminating method for performance decay of aero-engine fuel regulator - Google Patents
Fault eliminating method for performance decay of aero-engine fuel regulator Download PDFInfo
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- CN105784376A CN105784376A CN201610115559.8A CN201610115559A CN105784376A CN 105784376 A CN105784376 A CN 105784376A CN 201610115559 A CN201610115559 A CN 201610115559A CN 105784376 A CN105784376 A CN 105784376A
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- fuel regulator
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- controller
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- 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
- G01M15/04—Testing internal-combustion engines
Abstract
Provided is a fault eliminating method for performance decay of an aero-engine fuel regulator. If the performance of the fuel regulator decays, whether mould hole areas of a rotary speed controller and a differential pressure controller diminish is firstly detected. The mould hole area of the rotary speed controller diminishes because the performance of air system elements decays and the spring force of the controller declines. The decay of the performance of the air system elements is classified into decay of sylphon performance, failure of bellows, air leakage of an air sealing ring, a large motion drag of a sylphon supporting frame in a rail. The failure of the bellows is due to poor corrosion resistance of materials. The air leakage of the air sealing ring is caused by that the materials vary as an influence of environment. The large motion drag of the sylphon supporting frame in the rail is caused by that relevant component indexing does not meet demands. The decline of the spring force of the controller is due to decay of spring performance of the controller and clamping stagnation of a temperature compensation mechanism. The mould hole area of the differential pressure controller diminishes due to clamping stagnation of a fly weight and abnormal wearing of matched parts. According to the invention, the decay reasons can be found out in time through layer-by-layer checking and are rectified, and the service life of accessories is prolonged.
Description
Technical field
The invention belongs to engine failure and get rid of field, be specifically related to a kind of troubleshooting method of aero-engine fuel regulator performance degradation, for reducing the rate of decay of aircraft engine accessory performance, improve the adnexa life-span.
Background technology
Aero-engine fuel regulator performance degradation needs to carry out performance repetition measurement, and the flow being generally fuel regulator exists decay.The adjustment point flow not revising state with sea level is vertical coordinate, and the product work time is abscissa, then graphical representation different operating time and product do not revise the adjustment point flux depression trend of state.Being expressed as through returning factory's the performance test results, adjusted to specified limits at maximum (top) speed adjustment nail, flow still can not meet the specification regulation requirement.Fuel regulator performance degradation derives from the change of electromotor input parameter and the decay of product self spare part performance, therefore a kind of troubleshooting method of aircraft engine accessory performance degradation is provided, for reducing aircraft engine accessory performance degradation speed, improve the adnexa life-span significant.
Summary of the invention
Present invention aims to above-mentioned defect of the prior art, it is provided that a kind of troubleshooting method of aero-engine fuel regulator performance degradation, it is possible to the monitoring of system goes out whether electromotor performance degradation meets instructions for use, thus rectifying and improving in time.
To achieve these goals, the technical scheme that troubleshooting method of the present invention adopts comprises the following steps:
If step one fuel regulator performance degradation, whether the type hole area of detection rotational speed governor and differential pressure controller diminishes；
If the type hole area of step 2 rotational speed governor diminishes, then whether detection air system element function occurs whether the elastic force of decay and controller spring occurs declining；Whether described air system element function occurs decaying includes whether bellows performance decays, whether corrugated tube lost efficacy, whether aeroseal circle leaks gas and whether the bellows bearing support resistance of motion in track increases；If declining occurs in the elastic force of controller spring, then detection controller spring performance whether decay, temperature compensation mechanism whether clamping stagnation；
Step 3, corrugated tube lost efficacy and checked whether material corrosion performance is deteriorated, and whether aeroseal circle leak test material is affected by environment changes, and the resistance of motion increase in track of the bellows bearing support then checks that whether spare part calibration is undesirable；
If the type hole area of step 4 differential pressure controller diminishes, then detection fly weight whether clamping stagnation, couple whether inordinate wear；
Step 5, formulation measures to rectify and reform the result of appraisal, whether checking fuel regulator performance degradation reason is investigated correctly.
The couple model of described differential pressure controller is RT18-0511-000.
Described fuel regulator use time≤head turns over the phase.
Described step 5 measures to rectify and reform include: 1) by changing the problem that corrugated tube material solves corrugated tube inefficacy；2) stability of controller spring performance is improved by adjusting Technology for Heating Processing；3) compensation effect of temperature compensation mechanism is required to ensure by increasing the form tolerance of temperature compensation mechanism spare part；4) dimensional stability after the processing of aeroseal circle is improved by Optimizing Process Parameters.
The attenuation degree of fuel regulator performance is verified in described examination by engine test.
The fuel flow relation that during described engine test, checking input Parameters variation adapts with duty.
The described engine test proving time is 500 hours.
Described fly weight is aluminum fly weight.
When described fuel regulator detects, maximum (top) speed stop nail is adjusted to extreme position.
Compared with prior art, the present invention has following beneficial effect: fuel regulator fuel delivery depends on flow area and the pressure reduction of product, theory analysis thinks that its performance degradation is mainly derived from air pressure and controls passage and rotating speed control passage, and two kinds of reasons of performance degradation are that rotational speed governor type hole area diminishes and differential pressure controller type hole area diminishes.Two kinds of reasons that rotational speed governor type hole area diminishes are the decay of air system element function and the decline of controller spring force, the decay of air system element function is divided into four kinds of bellows performance degradations, corrugated tube lost efficacy, aeroseal circle leaks gas, bellows bearing support resistance of motion in track is big, it is owing to the corrosion resistance of material is poor that corrugated tube lost efficacy, and the gas leakage of aeroseal circle is because material from environmental impact change, and bellows bearing support resistance of motion in track is big because relevant spare part calibration is undesirable.Controller spring force declines and is because controller spring performance degradation and temperature compensation mechanism clamping stagnation.Differential pressure controller type hole area diminishes and is because fly weight clamping stagnation and couple inordinate wear.The present invention, according to problem Producing reason, successively investigates, and final measures to rectify and reform the result of appraisal formulated, whether checking investigation is correct, it is ensured that the reason of aero-engine fuel regulator performance degradation can be found out in time and effectively be solved, and improves the adnexa life-span.
Accompanying drawing explanation
Fig. 1 Fuel Flow Regulator of the present invention performance degradation malfunction elimination figure；
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Referring to Fig. 1, the troubleshooting method of aero-engine fuel regulator performance degradation of the present invention, comprise the following steps:
Step one, fuel regulator is as the core adnexa of electromotor main fuel system, with the fuel regulation system that electromotor constitutes a closed loop, by experiencing 10 input parameters of electromotor, the fuel flow that output and engine behavior adapt, therefore fuel regulator performance degradation derives from the performance degradation of electromotor input Parameters variation and product self spare part, the present invention use time≤head turns over the fuel regulator of phase as object, when fuel regulator adjusts to specified limits at maximum (top) speed stop nail, the product that performance can not reach to specify is considered as performance degradation and is unsatisfactory for instructions for use, fuel regulator fuel delivery depends on flow area and the pressure reduction of product, theory analysis thinks that its performance degradation is mainly derived from air pressure and controls passage and rotating speed control passage.
Step 2, analysis reason draw fault tree.Two kinds of reasons of aero-engine fuel regulator performance degradation are that rotational speed governor type hole area diminishes and differential pressure controller type hole area diminishes.
Two kinds of reasons that rotational speed governor type hole area diminishes are the decay of air system element function and the decline of controller spring force.
The performance degradation of air system related elements is divided into four kinds of bellows performance degradations, and corrugated tube lost efficacy, and aeroseal circle leaks gas, and bellows bearing support resistance of motion in track is big.
Corrugated tube lost efficacy owing to the corrosion resistance of material is poor.The gas leakage of aeroseal circle is because the impact change of material from environmental.It is undesirable that bellows bearing support resistance of motion in track is because greatly relevant spare part calibration.
Controller spring force declines and is because controller spring performance degradation and temperature compensation mechanism clamping stagnation.
Differential pressure controller type hole area diminishes and is because aluminum fly weight clamping stagnation and couple inordinate wear.
Step 3, formulation measures to rectify and reform:
1) Problem of Failure of secondary auxiliary equipment combined bellows part is solved by changing corrugated tube material.Corrugated tube material is changed to GH4169 high temperature alloy by PH15-7Mo.
2) stability of controller spring performance is improved by improving Technology for Heating Processing.
3) by increasing the form tolerance requirement guarantee temperature compensation mechanism compensation effect of temperature compensation mechanism spare part.
4) dimensional stability after the processing of aeroseal circle is improved by Optimizing Process Parameters.
Step 3,500 hours result of appraisal of engine test:
After the fuel regulator that corrective measure is implemented is carried out engine test examination, the attenuation degree of checking fuel regulator performance, the analysis of causes of checking performance degradation is correct.
The present invention, according to problem Producing reason, successively investigates, and formulates measures to rectify and reform the result of appraisal, and whether checking investigation is correct, it is ensured that the reason of aero-engine fuel regulator performance degradation can be found out in time and effectively be solved, and improves the adnexa life-span.
Above content is the further description present invention done in conjunction with detailed description of the invention, it is impossible to assert that specific embodiment of the invention is confined to these explanations.For person of an ordinary skill in the technical field, without departing from the inventive concept of the premise, it may also be made that some simple reckonings or replacement, all should be considered as belonging to protection scope of the present invention.
Claims (9)
1. the troubleshooting method of an aero-engine fuel regulator performance degradation, it is characterised in that comprise the following steps:
If step one fuel regulator performance degradation, whether the type hole area of detection rotational speed governor and differential pressure controller diminishes；
If the type hole area of step 2 rotational speed governor diminishes, then whether detection air system element function occurs whether the elastic force of decay and controller spring occurs declining；Whether described air system element function occurs decaying includes whether bellows performance decays, whether corrugated tube lost efficacy, whether aeroseal circle leaks gas and whether the bellows bearing support resistance of motion in track increases；If declining occurs in the elastic force of controller spring, then detection controller spring performance whether decay, temperature compensation mechanism whether clamping stagnation；
Step 3, corrugated tube lost efficacy and checked whether material corrosion performance is deteriorated, and whether aeroseal circle leak test material is affected by environment changes, and the resistance of motion increase in track of the bellows bearing support then checks that whether spare part calibration is undesirable；
If the type hole area of step 4 differential pressure controller diminishes, then detection fly weight whether clamping stagnation, couple whether inordinate wear；
Step 5, formulation measures to rectify and reform the result of appraisal, whether checking fuel regulator performance degradation reason is investigated correctly.
2. the troubleshooting method of aero-engine fuel regulator performance degradation according to claim 1, it is characterised in that: the couple model of described differential pressure controller is RT18-0511-000.
3. the troubleshooting method of aero-engine fuel regulator performance degradation according to claim 1, it is characterised in that: the use of described fuel regulator time≤head turns over the phase.
4. the troubleshooting method of aero-engine fuel regulator performance degradation according to claim 1, it is characterised in that the measures to rectify and reform of described step 5 include: 1) by changing the problem that corrugated tube material solves corrugated tube inefficacy；2) stability of controller spring performance is improved by adjusting Technology for Heating Processing；3) compensation effect of temperature compensation mechanism is required to ensure by increasing the form tolerance of temperature compensation mechanism spare part；4) dimensional stability after the processing of aeroseal circle is improved by Optimizing Process Parameters.
5. the troubleshooting method of aero-engine fuel regulator performance degradation according to claim 1, it is characterised in that: the attenuation degree of fuel regulator performance is verified in described examination by engine test.
6. the troubleshooting method of aero-engine fuel regulator performance degradation according to claim 5, it is characterised in that: the fuel flow relation that during described engine test, checking input Parameters variation adapts with duty.
7. the troubleshooting method of aero-engine fuel regulator performance degradation according to claim 5, it is characterised in that: the described engine test proving time is 500 hours.
8. the troubleshooting method of aero-engine fuel regulator performance degradation according to claim 1, it is characterised in that: described fly weight is aluminum fly weight.
9. the troubleshooting method of aero-engine fuel regulator performance degradation according to claim 1, it is characterised in that: when described fuel regulator detects, maximum (top) speed stop nail is adjusted to extreme position.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109946083A (en) * | 2019-03-29 | 2019-06-28 | 吉林化工学院 | A kind of aero-engine fuel regulator failure diagnosis apparatus |
| CN112758315A (en) * | 2019-10-21 | 2021-05-07 | 北京京东乾石科技有限公司 | Propeller blade angle adjusting method and device |
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| CN112758315A (en) * | 2019-10-21 | 2021-05-07 | 北京京东乾石科技有限公司 | Propeller blade angle adjusting method and device |
| CN112758315B (en) * | 2019-10-21 | 2023-12-05 | 北京京东乾石科技有限公司 | Propeller blade angle adjusting method and device |
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Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC |
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Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |