CN105606290A - High-performance aero-engine pressure sensitive element and test method thereof - Google Patents
High-performance aero-engine pressure sensitive element and test method thereof Download PDFInfo
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- CN105606290A CN105606290A CN201510978113.3A CN201510978113A CN105606290A CN 105606290 A CN105606290 A CN 105606290A CN 201510978113 A CN201510978113 A CN 201510978113A CN 105606290 A CN105606290 A CN 105606290A
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- pressure
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- bellows
- base plate
- sensing device
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L7/00—Measuring the steady or quasi-steady pressure of a fluid or a fluent solid material by mechanical or fluid pressure-sensitive elements
- G01L7/02—Measuring the steady or quasi-steady pressure of a fluid or a fluent solid material by mechanical or fluid pressure-sensitive elements in the form of elastically-deformable gauges
- G01L7/06—Measuring the steady or quasi-steady pressure of a fluid or a fluent solid material by mechanical or fluid pressure-sensitive elements in the form of elastically-deformable gauges of the bellows type
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L23/00—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
- G01L23/22—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid for detecting or indicating knocks in internal-combustion engines; Units comprising pressure-sensitive members combined with ignitors for firing internal-combustion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L23/00—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
- G01L23/24—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid specially adapted for measuring pressure in inlet or exhaust ducts of internal-combustion engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
- G01N3/36—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by pneumatic or hydraulic means
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention belongs to a field of aero-engine pressure sensitive element technology, especially relates to a high-performance aero-engine pressure sensitive element and a test method thereof, and can solve problems that a pressure-sensitive corrugate pipe assembly matched with a turbofan engine fuel regulator has fault phenomena including corrugate pipe inner cavity paint film peeling off and corrugated pipe fracture failure. The element comprises a corrugate pipe and a base plate, wherein the corrugate pipe is made from a spinning and drawing GH4169 high-temperature alloy tube blank, a polyimide coating is omitted, and parts of the pressure sensitive element assembly are combinedly welded by adopting a vacuum electron beam welding method. According to the invention, the element has advantages of corrosion resistance, high-temperature resistance, long service time, high reliability and relatively easy of manufacture, a ground service life test scheme of the element is made, the working condition and load of the corrugate pipe assembly after being mounted a motor are simulated, the corrugate pipe assembly is individually performed a service life test for simulating the load during total service life period, the corrugate pipe assembly is fully verified in original stage, so that the product with hidden troubles leaving factory and delivering are avoided.
Description
Technical field
The invention belongs to the technical field of aero-engine pressure-sensing device, be specifically related to a kind of high-performance aviation and startMachine pressure-sensing device and test method thereof.
Background technology
Fanjet fuel regulator supporting to pressure-sensitive combined bellows part, be matched in fanjetMain fuel flow regulator, in P3 limiter. When work, experience engine high pressure compressor delivery pressure P3, bellows groupThe component effect of connecting with compression spring, is no more than given numerical value, unit by regulating fuel delivery to carry out limiting engine P3 pressure1 of supporting quantity. Its working environment is: 300 DEG C of temperature, the highest 350 DEG C, pressure 2.38MPa, the highest 2.69MPa, inner chamber mediumFor air, displacement stroke is compression 0.38 ㎜. Protocol requirement product useful life is: initial lifetime 400 engine hour/4 year(examining with RT-18), target life objective 1500 engine hour/8 year (examining with RT-18). This bellows in 2007Sub-assembly successively occurs 3 times and causes fuel regulator fuel delivery low because bellows bursts lost efficacy in line using, causes and startsMachine rotating speed is 80% fault not rising, and also occurs that No. 3 bellows sub-assemblies had leaked but uncracked fault simultaneously. Lost efficacyThe front product work time by 50 hours to 400 hours not etc., bring adverse effect to normal flight. According to statistics, total fault rateBe 2.86%. Meanwhile, the existence of this fault cause combined bellows part cannot meet engine production sizing to become the annex life-span by400 engine hours put the requirement of engine hour in longevity to 600.
Through accident analysis, think that the mechanism of bellows bursts fault is that bellows inside surface is in operating pressure, temperature and containUnder the comprehensive function of sulphur medium, the polyimides paint film of product surface coating progressively comes off, PH15-7Mo half Ovshinsky exposingBody precipitation-hardening stainless steel material matrix produces grain boundary corrosion under the effect of sulfur-containing medium, forms hole on body, and byStep develops into crackle, causes combined bellows part air leakage failure. The production domesticization product of delivered installation all has similar potential faults,The import original product phenomenon of the failure that equally also ubiquity bellows inner chamber paint film spalling and a small amount of bellows bursts lost efficacy.
Summary of the invention
The present invention for solve existing fanjet fuel regulator supporting to pressure-sensitive combined bellows partThe problem that has the phenomenon of the failure of bellows inner chamber paint film spalling and the inefficacy of amount bellows bursts, provides a kind of high-performance aviationEngine pressure sensing element, that is for a kind of combined bellows part of the P3 limiter of aeroengine control system.
The present invention adopts following technical scheme to realize:
A kind of High Performance Aeroengine pressure-sensing device, comprises bellows and base plate, it is characterized in that bellows adoptsThe GH4169 high temperature alloy pipe of spinning drawing is manufactured, and has deleted polyimide coating, and the each sub-assembly of pressure-sensing device adoptsVacuum electron beam welding method Combination Welding.
Between base plate and bellows, connect by base plate nipple, base plate nipple has bigger diameter end and bellows-welding, hasMiner diameter end is inserted in base plate welding. By increasing base plate nipple part, two mounting ear butt welding on base plate part are avoidedThe obstruction connecing, has improved the access for welding of weld seam, has realized the electron beam welding of base plate and bellows.
The step of GH4169 high temperature alloy pipe spinning drawing is,
1), 1mm plate blanking punching bowl is to Φ 35mm;
2), Jing Si road vertical pulling is to Φ 17mm, wall thickness 0.55mm, average drawing coefficient 0.75;
3), through one spinning drawing, wall thickness is to 0.1mm.
The test method of High Performance Aeroengine pressure-sensing device, step is as follows,
1), High Performance Aeroengine pressure-sensing device sample is carried out to air-tightness and visual examination, record check feelings one by oneCondition;
2), sample is loaded in test fixture, adjusts compression travel and be about after 0.38mm and seal and fix, sample is connected to fixtureTogether be placed in well formula heat-treatment furnace; Connect source of the gas, connecting pipeline, passes into compressed air to sample inner chamber, by external rippleLine pipe automatic stabilization equipment, controls absolute pressure and carries out repeat from 0.1MPa～2.1MPa, and frequency is 4 times/hour;
3), first well formula heat-treatment furnace furnace temperature is remained on to 300 DEG C ± 10 DEG C, inner chamber absolute pressure is become by 0.1MPa～2.1MPaChange, carry out the line pressure shift Alternating Test of 134h15min, then carry out absolute chamber pressure by 0.1MPa～2.62MPa, carry outThe line pressure shift Alternating Test of 45min; Furnace temperature is risen to 350 DEG C ± 10 DEG C, inner chamber absolute pressure is by 0.1MPa～2.1MPa againChange, carry out the line pressure shift repeat test of 15h;
4), often carried out 150h, recorded the parameter such as test temperature, test pressure, dismounting product according to step 1) requirement carry outAir-tightness and visual examination;
5), repeat 3), 4), until 1500 × 1.5=2250 hour.
The present invention selects GH4169 high temperature alloy to replace PH15-7Mo semiaustenitic precipitation-hardening stainless steel for bellowsManufacture, the corresponding sub-assembly Welding Structure of having improved, changes electron-bombardment welding into by original high frequency solder brazing simultaneously, has deleted poly-Acid imide coating. By analytic demonstration and contrast test, the combined bellows part after improvement has compared with previous status to be installed mutuallyTranssexual, main fuel flow regulator can be docked in this combined bellows part after improvement without any change. Tool of the present inventionThere is corrosion-resistant, high temperature resistant, long-life, highly reliable and be relatively easy to the feature of manufacturing.
The relative prior art of the present invention has following beneficial effect: (please the principle to test portion and effect are also dividedAnalyse)
1, after improvement, the corrosion resistance of this combined bellows part, reliability improve, and the product export life-span is by original at present400 engine hour/4 year are extended down to 650 engine hour/6 year, and test in 1100 hours is passed through; 2008 to 2014, accumulative total1533 of delivered product, none leakage failure feedback of outfield;
2, improve after bellows and sub-assembly fabrication technology, substitute or deleted that inefficiency, procedure quality are unsettledHigh frequency solder brazing operation and polyimides painting process, production quality improvement, production efficiency improve, bellows and sub-assemblyProduction qualification rate is by average 49% 2007,2014 the production qualification rates that rise to 72%(statistical comparison);
3, delete polyimide coating technique, exempted the use of polyimide varnish and diluent, avoided operating personnelThe employment injuries of breathing, central nervous system, has improved production environment condition;
4, formulated first the ground life assessment test scheme of High Performance Aeroengine pressure-sensing device, simulation bellowsOperating loading after sub-assembly assembling engine, carries out separately the life-span examination of simulation total life cycle load to combined bellows partTest, fully verify in original paper level, avoided paying with the product export of hidden danger.
Brief description of the drawings
Fig. 1 is the structural representation of existing bellows component
Fig. 2 is the structural representation of bellows component of the present invention
Fig. 3 is fatique testing at elevated temperature parametric plot
In figure: 1-end cap, 2-solder sheet, 3-bellows, 4-base plate, 5-base plate nipple.
Detailed description of the invention
By reference to the accompanying drawings the specific embodiment of the present invention is described further.
A kind of High Performance Aeroengine pressure-sensing device, comprises bellows, bellows employing spinning drawingGH4169 high temperature alloy pipe is manufactured, and has deleted polyimide coating, and sub-assembly adopts vacuum electron beam welding method Combination Welding.On the basis of material intercrystalline corrosion contrast test, the present invention uses the GH4169 high-temperature alloy material that corrosion resistance is good to substitute firstPH15-7Mo semiaustenitic precipitation-hardening stainless steel material is for the manufacture of P3 pressure restrictor bellows.
Bellows pipe conventionally adopts seamless pipe or is manufactured by plate punching bowl reducing, ironing. Need according to designing requirementThe pipe that is 0.1mm with thickness, domestic without thin-wall seamless pipe supply, the manufacture that can only stretch voluntarily, the present invention has realized firstThe spinning drawing of GH4169 high temperature alloy pipe. Through repetition test, the invention provides a set of complete process and skillArt parameter, has successfully realized the spinning drawing of GH4169 high temperature alloy bellows pipe first, has certain process innovationAnd application value. Drawing scheme is:
1), 1mm plate blanking punching bowl Φ 35mm;
2), Jing Si road vertical pulling is to Φ 17mm, wall thickness 0.55mm, average drawing coefficient 0.75;
3), through one spinning drawing, wall thickness is to 0.1mm.
Change for adapting to bellows material, the corresponding change of sub-assembly Welding Structure of the present invention, is changed into by vacuum induction solderingVacuum electron beam welding structure; Increase in addition base plate nipple, with bellows and base plate Combination Welding, avoided base plate peace respectivelyThe impact of dress ear on circular weld welding;
The present invention has proposed under the hot environment for P3 pressure restrictor combined bellows part ground certification test first in additionPressures cycle fatigue test method, simultaneously the method can be used for this product follow-uply lengthens the life, determine the longevity and work, and similar to formulatingProduct testing scheme has reference. Test method is as follows:
A) sample is carried out to air-tightness and visual examination one by one, record check situation.
B) sample is loaded in Special test fixture, adjusts compression travel and be about after 0.38mm and seal and fix, will trySample connects fixture and is together placed in well formula heat-treatment furnace; Connect source of the gas, connecting pipeline, passes into local compression sky to sample inner chamberGas, by external bellows automatic stabilization equipment, controlled pressure is absolute from 0.1MPa～2.1MPa() carry out repeat, frequentlyRate is 4 times/hour.
C) first furnace temperature is remained on to 300 DEG C ± 10 DEG C, chamber pressure is absolute by 0.1MPa～2.1MPa() change, carry outThe line pressure shift Alternating Test of 134h15min, then it is absolute by 0.1MPa～2.62MPa(to carry out chamber pressure), the pressure of 45minDisplacement Alternating Test; Furnace temperature is risen to 350 DEG C ± 10 DEG C, chamber pressure is absolute by 0.1MPa～2.1MPa(again) change, carry outThe line pressure shift repeat test of 15h;
D) often carried out 150h, recorded the parameter such as test temperature, test pressure, dismounting product carries out airtight according to requirement a)Property and visual examination;
E) repeat c), d), until 1500 × 1.5=2250 hour.
Gained Apparatus for Pressure at high-temp parameter curve is as Fig. 3.
Claims (4)
1. a High Performance Aeroengine pressure-sensing device, comprises bellows and base plate, it is characterized in that bellows adoptsManufacture with the GH4169 high temperature alloy pipe of spinning drawing, deleted polyimide coating, the each sub-assembly of pressure-sensing device is adoptedBy vacuum electron beam welding method Combination Welding.
2. High Performance Aeroengine pressure-sensing device according to claim 1 and 2, is characterized in that base plate and rippleBetween pipe, connect by base plate nipple, base plate nipple has bigger diameter end and bellows-welding, has miner diameter end to be inserted in base plate alsoWelding.
3. High Performance Aeroengine pressure-sensing device according to claim 1 and 2, is characterized in that: GH4169 is highThe step of temperature alloy pipe spinning drawing is,
1), 1mm plate blanking punching bowl is to Φ 35mm;
2), Jing Si road vertical pulling is to Φ 17mm, wall thickness 0.55mm, average drawing coefficient 0.75;
3), through one spinning drawing, wall thickness is to 0.1mm.
4. the life test method of High Performance Aeroengine pressure-sensing device according to claim 3, its feature existsIn: step is as follows,
1), High Performance Aeroengine pressure-sensing device sample is carried out to air-tightness and visual examination, record check feelings one by oneCondition;
2), sample is loaded in test fixture, adjusts compression travel and be about after 0.38mm and seal and fix, sample is connected to fixtureTogether be placed in well formula heat-treatment furnace; Connect source of the gas, connecting pipeline, passes into compressed air to sample inner chamber, by external rippleLine pipe automatic stabilization equipment, controls absolute pressure and carries out repeat from 0.1MPa～2.1MPa, and frequency is 4 times/hour;
3), first well formula heat-treatment furnace furnace temperature is remained on to 300 DEG C ± 10 DEG C, inner chamber absolute pressure is become by 0.1MPa～2.1MPaChange, carry out the line pressure shift Alternating Test of 134h15min, then carry out absolute chamber pressure by 0.1MPa～2.62MPa, carry outThe line pressure shift Alternating Test of 45min; Furnace temperature is risen to 350 DEG C ± 10 DEG C, inner chamber absolute pressure is by 0.1MPa～2.1MPa againChange, carry out the line pressure shift repeat test of 15h;
4), often carried out 150h, recorded the parameter such as test temperature, test pressure, dismounting product according to step 1) requirement carry outAir-tightness and visual examination;
5), repeat 3), 4), until 1500 × 1.5=2250 hour.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510978113.3A CN105606290B (en) | 2015-12-23 | 2015-12-23 | High Performance Aeroengine pressure-sensing device and its test method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510978113.3A CN105606290B (en) | 2015-12-23 | 2015-12-23 | High Performance Aeroengine pressure-sensing device and its test method |
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| CN105606290A true CN105606290A (en) | 2016-05-25 |
| CN105606290B CN105606290B (en) | 2018-09-21 |
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| CN201510978113.3A Active CN105606290B (en) | 2015-12-23 | 2015-12-23 | High Performance Aeroengine pressure-sensing device and its test method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107907761A (en) * | 2017-11-03 | 2018-04-13 | 北京空间技术研制试验中心 | Test method for the component of spacecraft |
| CN111413027A (en) * | 2020-04-22 | 2020-07-14 | 太原航空仪表有限公司 | Accelerated degradation test method for pressure annunciator |
| CN114382957A (en) * | 2022-01-14 | 2022-04-22 | 中海石油气电集团有限责任公司 | LNG low-temperature hose body forming method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107907761A (en) * | 2017-11-03 | 2018-04-13 | 北京空间技术研制试验中心 | Test method for the component of spacecraft |
| CN111413027A (en) * | 2020-04-22 | 2020-07-14 | 太原航空仪表有限公司 | Accelerated degradation test method for pressure annunciator |
| CN114382957A (en) * | 2022-01-14 | 2022-04-22 | 中海石油气电集团有限责任公司 | LNG low-temperature hose body forming method |
| CN114382957B (en) * | 2022-01-14 | 2023-12-01 | 中海石油气电集团有限责任公司 | LNG low-temperature hose body forming method |
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| CN105606290B (en) | 2018-09-21 |
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