CN112809310B - Method for discriminating and repairing manufacturing defects of anti-surge system of aircraft engine - Google Patents
Method for discriminating and repairing manufacturing defects of anti-surge system of aircraft engine Download PDFInfo
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- CN112809310B CN112809310B CN202011615237.2A CN202011615237A CN112809310B CN 112809310 B CN112809310 B CN 112809310B CN 202011615237 A CN202011615237 A CN 202011615237A CN 112809310 B CN112809310 B CN 112809310B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a method for screening and repairing manufacturing defects of an anti-surge system of an aircraft engine. The invention determines a fault discrimination method which mainly judges the angle of a high-pressure compressor blade of an engine and the position of a nozzle, designs an oil pressure distribution simulation test to realize accurate positioning of the defective position of a product, and adopts a rapid assembly technology under high-temperature and low-temperature states to ensure effective fitting and assembly correctness of a parking valve bush and a guider shell. The invention realizes the identification, detection and repair of the manufacturing and processing defects of the anti-surge system, thoroughly avoids the failure of the anti-surge system, saves the military cost of spare part purchase for the country and has obvious military and economic benefits.
Description
Technical Field
The invention relates to the technical field of maintenance of aero-engines, in particular to a method for discriminating and repairing manufacturing defects of an anti-surge system of an aero-engine.
Background
When the lead-in equipment is subjected to large-scale overhaul after the lead-in equipment is turned over first and is expired, the applicant finds that the lead mechanism of the alpha 2 adjustable stator blade of the main fuel regulator does not work in the surge elimination performance test, the further check is carried out, the fact is confirmed that the manufacturing and processing defects exist in the oil way controlled by the guider, the applicant immediately counts the six-digit numbered main fuel regulator similar to the one which is not subjected to domestic overhaul, the failure rate of the manufacturing and processing defects of the surge elimination system is found to be as high as 50%, the manufacturing and processing defects can cause that the surge of the engine cannot be effectively eliminated when the surge occurs, serious quality hidden dangers exist, and the flight safety is endangered.
Due to the limitation of the current repair standard, no special screening means aiming at the manufacturing and processing defects of the asthma system exists in China at present, the manufacturing and processing defects can be found only by comparison when performance tests are carried out, omission possibly exists greatly, and the screening accuracy cannot be guaranteed. In addition, according to the existing repair means, the repair workload of the manufacturing and processing defects is large, the repair success rate is low, the introduced equipment is subject to foreign technical blockade, spare parts are expensive and difficult to purchase, and the requirements of troops on combat training cannot be met.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method for discriminating and repairing the manufacturing defects of the anti-surge system of the aircraft engine is provided, the positions of the defects can be accurately positioned, and the repairing difficulty is reduced.
In order to solve the technical problems, the invention adopts the technical scheme that: a method for discriminating and repairing the defect of the antiasthmatic system of aircraft engine features that the main fuel regulator with defect is determined by analyzing the angle variation of the guider when the antiasthmatic instruction is switched on, the oil pressure distribution simulation test is used to locate the position of defect, and the liner of stop valve is detached and installed at high and low temp.
Further, the method comprises the following steps: the method comprises the following steps:
a. performing a performance recording test on the main fuel regulator which is not overhauled, and judging that the surge eliminating system manufacturing defect exists if a test detection result is unqualified;
b. carrying out an oil pressure distribution simulation test on a main fuel regulator with the defect of the surge elimination system manufacture, inputting three constant oil sources in different states, and comparing the deviation condition of the distribution oil pressure of the tested system and a standard oil pressure value, wherein the oil way with the maximum oil pressure deviation and the pressure drop less than 0.05MPa is judged as the oil way with the defect;
c. heating the guide machine shell with the defective oil path, and pulling out the parking valve bush;
d. polishing the non-conducted oil way of the guider shell to open the oil way, cleaning the guider shell and washing the connected oil ways;
e. selecting a new parking valve bush, heating the guider shell, cooling the new parking valve bush, and installing the new parking valve bush at the stop position of the guider shell;
f. and cleaning the repaired guider shell, performing the oil pressure distribution simulation test again, and repairing according to the standard repairing operation flow after the oil pressure distribution simulation test is qualified.
Further, the method comprises the following steps: in step a, when a performance recording test is carried out, the electromagnet is switched on three times, the rotation of the alpha 2 feedback small shaft in the direction of reducing the angle is checked, and the oil pressure P of the connecting nozzle P31 is checkedKOMIn three examinations PKOMIf the pressure is less than 0.4MPa, the pressure is judged to be unqualified, and the defect of the anti-surge system is caused.
Further, the method comprises the following steps: and c, heating the guider shell with the defective oil path to 100-120 ℃ in a high-low temperature test box, keeping the temperature for 20min, taking out the guider shell, and pulling out the parking valve bush by adopting a decomposition tool within 1 min.
Further, the method comprises the following steps: and d, using a pneumatic polishing head to polish the non-conducted oil way of the guider shell, wherein the polishing depth is consistent with the annular groove of the guider shell.
Further, the method comprises the following steps: and d, cleaning the outer surface of the guide device shell by using gasoline, flushing each oil path connected in the parking valve bush by using an oil source single hole of 0.3MPa, and then performing pulse flushing on the guide device shell until a hole detector detects that no communication oil path exists in the hole of the parking valve bush and no impurity exists in the oil path.
Further, the method comprises the following steps: and e, measuring the diameter, the taper and the ovality of the parking valve bushing hole, and selecting a new parking valve bushing according to the interference tightness of 0.02-0.035 mm.
Further, the method comprises the following steps: step e, heating the guider shell to 100-120 ℃ in a high-low temperature test box, preserving heat for 20min, taking out, cooling a new parking valve bush in liquid nitrogen, taking out, installing the new parking valve bush to the stop position of the guider shell within 1min by adopting an assembly fixture, and checking that the distance between the end face of the parking valve bush and the end face of the guider shell is equal to
Further, the method comprises the following steps: and cleaning the repaired guider shell by sequentially adopting modes of gasoline cleaning, single-hole flushing and pulse flushing.
The invention has the beneficial effects that: the invention researches the surge-eliminating fault mechanism of the introduced aero-engine, determines a fault discrimination method which mainly judges the angle of a high-pressure compressor blade of the engine and the position of a nozzle, designs an oil pressure distribution simulation test to realize accurate positioning of the defect position of a product, implements positioning and quantitative supplementary processing to communicate with a defect oil way, and adopts a rapid assembly technology under high-temperature and low-temperature states to ensure the effective attachment and assembly correctness of a parking valve bush and a guider shell. The invention realizes the identification, detection and repair of the manufacturing and processing defects of the introduced aeroengine anti-surge system, thoroughly avoids the failure of the anti-surge system, can save the military cost of spare part purchase for the country, and has obvious military and economic benefits.
Detailed Description
In order to facilitate understanding of the present invention, the present invention will be further described with reference to the following examples.
The invention discloses a method for screening and repairing manufacturing defects of an aircraft engine anti-surge system, which is used for tracing the anti-surge performance inspection condition of a fault piece which is found in repair and has the manufacturing defects of the anti-surge system according to history information, performing data statistical analysis and researching a monitoring means. And carrying out data statistical analysis on the repair test condition of the main fuel regulator to be repaired, and researching corresponding monitoring measures. The method is improved aiming at the qualitative inspection mode of the current ground trial run anti-surge performance, the simulation test grasps the fault data, and the quantitative control standard of the defect diagnosis and repair measures in the repair operation and the trial run anti-surge performance inspection is formulated. The method for discriminating the manufacturing defects of the anti-surge system of the aero-engine, the three-dimensional positioning and processing technology of the guider shell and the high-low temperature rapid assembly technology are established by taking the angle of the blade of the high-pressure compressor of the aero-engine and the position of the nozzle as main judgment bases, so that the original manufacturing defects of the anti-surge system of the aero-engine are effectively discriminated and accurately positioned, and the aero-engine with the repaired manufacturing defects can be restored to the original design standard state.
Judging the anti-surge performance characteristic curve of the aeroengine outfield flight parameter recorded data, statistically analyzing the change condition of the feedback angles of the high-pressure compressor guider and the low-pressure compressor guider when the aeroengine is connected with an anti-surge instruction, and determining a main fuel regulator which possibly has original manufacturing and processing defects; and then, designing an oil pressure distribution simulation test method by the aid of an oil path trend principle of an inner cavity of the guider housing and characteristic analysis of related elements, and accurately positioning the manufacturing and processing defect positions of the aircraft engine.
The invention extracts the parking valve bush of the main fuel regulator with manufacturing and processing defects by researching a process method except for hard extraction of the parking valve bush so as to reduce the probability of damage to the shell of the guide device; the special positioning and guiding tool is designed and manufactured, so that the guider shell and the replaced new parking valve bushing are rapidly assembled at high temperature and low temperature respectively, other adjacent bushings in the guider shell are prevented from unnecessarily falling off or loosening, and the effective fitting and assembling correctness of the parking valve bushing and the guider shell are ensured.
The invention calculates the minimum flow area of the output readjustment control pressure under the normal condition by developing the readjustment control pressure characteristic research of the anti-surge control system under the normal condition and utilizing mathematical modeling; the precise positioning tool is designed and manufactured, so that in the oil way repairing process, other machine bodies except the repaired part are not damaged, the minimum repairing amount is limited, and the engine is ensured to be restored to the original design standard state after the defects are repaired.
The invention further formulates the ground test of the main fuel regulator and the acceptance check quantification standard of the surge elimination characteristic of the engine test based on the research of the defect detection and identification technology of the surge elimination system of the aircraft engine and the statistical analysis of the surge elimination characteristic of the normal aircraft engine.
Examples
The applicant conducts performance recording tests on a plurality of main fuel oil regulators of the introduced aero-engine without domestic overhaul, and when conducting the performance recording tests, the electromagnetic is switched onIron three times, checking the alpha 2 feedback small shaft to rotate in the direction of reducing angle, and checking the oil pressure P of the nozzle P31KOMIn three examinations PKOMIf the pressure is less than 0.4MPa, the pressure is judged to be unqualified, and the defect of the anti-surge system is caused.
And positioning the defect position by adopting an oil pressure distribution simulation test, inputting three constant oil sources in different states, and comparing the deviation condition of the distributed oil pressure of the tested system and the standard oil pressure value, wherein the oil way with the maximum oil pressure deviation and the pressure drop less than 0.05MPa is judged as the oil way with the defect.
Heating the guider shell with the defective oil path to 100-120 ℃ in a high-low temperature test box, keeping the temperature for 20min, taking out the guider shell, and pulling out the parking valve bush by adopting a decomposition tool within 1 min.
The method comprises the steps of using a pneumatic polishing head with a positioning function to polish non-conducted oil ways of the guider shell, enabling the polishing depth to be consistent with that of an annular groove of the guider shell, using gasoline to clean the outer surface of the guider shell, using a 0.3MPa oil source single hole to flush all oil ways connected in a parking valve bush, and then carrying out pulse flushing on the guider shell until a hole detector detects that no oil way is communicated in the hole of the parking valve bush and no impurities exist in the oil ways.
Measuring the diameter, taper and ovality of a parking valve bushing hole, selecting a new parking valve bushing according to the interference tightness of 0.02-0.035 mm, heating a guider shell to 100-120 ℃ in a high-low temperature test box, keeping the temperature for 20min, taking out the guider shell, cooling the new parking valve bushing in liquid nitrogen, taking out the guider shell, installing the new parking valve bushing at the stop position of the guider shell within 1min by adopting an assembling fixture, and checking that the distance between the end face of the parking valve bushing and the end face of the guider shell is equal to
And cleaning the repaired guider shell by sequentially adopting modes of gasoline cleaning, single-hole flushing and pulse flushing, performing an oil pressure distribution simulation test again after cleaning, and repairing according to a standard repairing operation flow after inspection is qualified. And continuously searching reasons for the unqualified inspection according to the steps and performing supplementary processing until the inspection is qualified.
Through the repair work, the applicant completes the repair of the manufacturing defects of all the introduced aero-engines, thoroughly avoids the failure of the anti-surge system, and saves 3059.9 ten thousand yuan of spare part procurement for the country at present.
Claims (8)
1. The method for discriminating and repairing the manufacturing defects of the anti-surge system of the aircraft engine is characterized by comprising the following steps of: determining a main fuel regulator possibly having defects by analyzing the change condition of a guider feedback angle when an engine is connected with an anti-surge instruction, positioning the defect position by adopting an oil pressure distribution simulation test, and respectively disassembling and assembling a parking valve bush in a high-temperature state and a low-temperature state;
the method comprises the following steps:
a. performing a performance recording test on the main fuel regulator which is not overhauled, and judging that the surge eliminating system manufacturing defect exists if a test detection result is unqualified;
b. carrying out an oil pressure distribution simulation test on a main fuel regulator with the defect of the surge elimination system manufacture, inputting three constant oil sources in different states, and comparing the deviation condition of the distribution oil pressure of the tested system and a standard oil pressure value, wherein the oil way with the maximum oil pressure deviation and the pressure drop less than 0.05MPa is judged as the oil way with the defect;
c. heating the guide machine shell with the defective oil path, and pulling out the parking valve bush;
d. polishing the non-conducted oil way of the guider shell to open the oil way, cleaning the guider shell and washing the connected oil ways;
e. selecting a new parking valve bush, heating the guider shell, cooling the new parking valve bush, and installing the new parking valve bush at the stop position of the guider shell;
f. and cleaning the repaired guider shell, performing the oil pressure distribution simulation test again, and repairing according to the standard repairing operation flow after the oil pressure distribution simulation test is qualified.
2. The method of claim 1The method for discriminating and repairing the manufacturing defects of the anti-surge system of the aircraft engine is characterized by comprising the following steps of: in step a, when a performance recording test is carried out, the electromagnet is switched on three times, the rotation of the alpha 2 feedback small shaft in the direction of reducing the angle is checked, and the oil pressure P of the connecting nozzle P31 is checkedKOMIn three examinations PKOMIf the pressure is less than 0.4MPa, the pressure is judged to be unqualified, and the defect of the anti-surge system is caused.
3. The method for screening and repairing manufacturing defects of an aircraft engine anti-surge system according to claim 1, wherein: and c, heating the guider shell with the defective oil path to 100-120 ℃ in a high-low temperature test box, keeping the temperature for 20min, taking out the guider shell, and pulling out the parking valve bush by adopting a decomposition tool within 1 min.
4. The method for screening and repairing manufacturing defects of an aircraft engine anti-surge system according to claim 1, wherein: and d, using a pneumatic polishing head to polish the non-conducted oil way of the guider shell, wherein the polishing depth is consistent with the annular groove of the guider shell.
5. The method for screening and repairing manufacturing defects of an aircraft engine anti-surge system according to claim 1, wherein: and d, cleaning the outer surface of the guide device shell by using gasoline, flushing each oil path connected in the parking valve bush by using an oil source single hole of 0.3MPa, and then performing pulse flushing on the guide device shell until a hole detector detects that no communication oil path exists in the hole of the parking valve bush and no impurity exists in the oil path.
6. The method for screening and repairing manufacturing defects of an aircraft engine anti-surge system according to claim 1, wherein: and e, measuring the diameter, the taper and the ovality of the parking valve bushing hole, and selecting a new parking valve bushing according to the interference tightness of 0.02-0.035 mm.
7. The method of screening for and repairing manufacturing defects in an aircraft engine anti-surge system of claim 1, wherein the method comprisesIs characterized in that: step e, heating the guider shell to 100-120 ℃ in a high-low temperature test box, preserving heat for 20min, taking out, cooling a new parking valve bush in liquid nitrogen, taking out, installing the new parking valve bush to the stop position of the guider shell within 1min by adopting an assembly fixture, and checking that the distance between the end face of the parking valve bush and the end face of the guider shell is equal to
8. The method for screening and repairing manufacturing defects of an aircraft engine anti-surge system according to claim 1, wherein: and cleaning the repaired guider shell by sequentially adopting modes of gasoline cleaning, single-hole flushing and pulse flushing.
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| CN202011615237.2A CN112809310B (en) | 2020-12-30 | 2020-12-30 | Method for discriminating and repairing manufacturing defects of anti-surge system of aircraft engine |
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| CN202011615237.2A CN112809310B (en) | 2020-12-30 | 2020-12-30 | Method for discriminating and repairing manufacturing defects of anti-surge system of aircraft engine |
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| CN112809310B true CN112809310B (en) | 2022-01-25 |
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Citations (3)
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| CN104551528A (en) * | 2013-10-21 | 2015-04-29 | 哈尔滨飞机工业集团有限责任公司 | Thermoelectric assembly method of composite blade embedded bushing |
| CN110362065A (en) * | 2019-07-17 | 2019-10-22 | 东北大学 | A kind of method for diagnosing status of aero-engine anti-asthma control system |
| CN111735633A (en) * | 2020-06-10 | 2020-10-02 | 中国航发北京航科发动机控制系统科技有限公司 | Pressure load loading and strain online test system for fuel oil electric control regulator |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104551528A (en) * | 2013-10-21 | 2015-04-29 | 哈尔滨飞机工业集团有限责任公司 | Thermoelectric assembly method of composite blade embedded bushing |
| CN110362065A (en) * | 2019-07-17 | 2019-10-22 | 东北大学 | A kind of method for diagnosing status of aero-engine anti-asthma control system |
| CN111735633A (en) * | 2020-06-10 | 2020-10-02 | 中国航发北京航科发动机控制系统科技有限公司 | Pressure load loading and strain online test system for fuel oil electric control regulator |
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