CN104723014B - Extension engine turbine air conduit overhauls life-span phase - Google Patents
Extension engine turbine air conduit overhauls life-span phase Download PDFInfo
- Publication number
- CN104723014B CN104723014B CN201510053290.0A CN201510053290A CN104723014B CN 104723014 B CN104723014 B CN 104723014B CN 201510053290 A CN201510053290 A CN 201510053290A CN 104723014 B CN104723014 B CN 104723014B
- Authority
- CN
- China
- Prior art keywords
- air conduit
- life
- overhauls
- engine turbine
- ground
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
Abstract
The method that a kind of extension engine turbine air conduit proposed by the present invention overhauls life-span phase, it is desirable to provide a kind of to extend the method that engine turbine air conduit overhauls life-span phase.The technical scheme is that：The end face and circumference denuded to air conduit fine motion are ground or turning, to ensure that air conduit respectively coordinates periphery relative to the concentricity of reference plane and the depth of parallelism of each counterface, and ensure that each small―gap suture coordinates；The adjusting pad 12 of design air conduit assembling；Solder joint repair welding again at the five road reinforcements arranged in parallel to air conduit surface, and use water logging ultrasonic examination weld seam, increase and chromium plating process is ground at air conduit mounting surface fine motion abrasion, use air conduit front end assembling cushion rubber instead metal o-ring, then shot peening air conduit surface.Air conduit after being repaired using the present invention, examined, the abnormal failure such as flawless by 1.5 times of test runs for overhauling life-span phase for second, it is to avoid the waste that renewal part is brought.
Description
Technical field
The present invention relates to the method that a kind of aviation extension engine turbine air conduit overhauls life-span phase.
Background technology
Engine turbine air conduit occurs many in second endurance test for overhauling the phase and factory test engine
Secondary through wall flaw failure.Because low-pressure turbine shaft is passed through from air conduit inner chamber, if air conduit fracture after with low pressure whirlpool
Wheel shaft is contacted, and will produce the risk of cutoff low turbine wheel shaft.Because air conduit crack fault occurs to overhaul the phase at second, institute
Using generally give the engine air conduit life-span overhauled the phase as one, i.e., it is next overhaul the phase then need replacing new product.In prevention hair
The prior art that motivation air conduit second overhauls the air conduit crack fault occurred in phase lifetime is usually to use end
Face sprayed on material Metco447 technical scheme is repaired, but equally occurs in that crack fault.Air conduit is welded using double-deck
Structure type is connect, middle part between conduit outer cylinder body 10, conduit inner barrel 11 by electron-bombardment welding by being welded.Air is led
Tubular construction figure is shown in Fig. 1.
The content of the invention
The purpose of the present invention is that there is provided a kind of repairing skill of the pre- Anti-cracking of air conduit the problem of presence for prior art
Art, it is to avoid change the waste of material that air conduit is brought, extension engine turbine air conduit is overhauled life-span phase, pre- Anti-cracking
Repair method.
The present invention above-mentioned purpose can be reached by following measures,
It is a kind of to extend the method that engine turbine air conduit overhauls life-span phase, it is characterised in that to comprise the following steps：
1）The end face and circumference denuded to the fine motion of air conduit 1 are ground or turning, to ensure the respectively cooperation of air conduit 1
Periphery is relative to the concentricity of reference plane 3 and the depth of parallelism of each counterface, and ensures that each small―gap suture coordinates；
2）Design ensures the adjusting pad 12 of assembling air conduit axial gap and the small―gap suture radial fit of internal diameter 8 at step 7；
3）Solder joint repair welding again at the five road reinforcements arranged in parallel to the surface of air conduit 1, and use water logging ultrasonic wave
Check and be ground chromium plating process at weld seam, the increase mounting surface fine motion abrasion of air conduit 1, the front end of air conduit 1 assembling cushion rubber is changed
With metal o-ring, the then surface of shot peening air conduit 1.
The present invention has the advantages that compared to prior art.
The present invention uses water logging ultrasonic examination weld seam to solder joint repair welding again at the road reinforcement of air conduit five, protects
Demonstrate,prove welding spot reliability.Air conduit after being repaired using the present invention, the endurance test for overhauling life-span phase for second by 1.5 times
With long examination examination, the abnormal failure such as flawless, state meets air conduit second and overhauls life expectancy phase, extends air
Conduit service life, it is to avoid the waste that renewal part is brought, saves energy consumption.
Brief description of the drawings
Fig. 1 is engine turbine air conduit structural representation profile.
Fig. 2 is Fig. 1 contour structures schematic diagram.
Fig. 3 is Fig. 1 front view.
Fig. 4 is the partial schematic diagram that air conduit is assembled by adjusting pad.
In figure：1 air conduit, 2 reinforcements, 3 reference planes, 4 rear end faces, 5 circumference mating surfaces, 6 metal o-rings, 7 steps,
8 internal diameters, electron beam weld, 10 air conduit outer cylinder bodies, 11 air conduit inner barrels, 12 adjusting pads between cylinder inside and outside 9.
Embodiment
Refering to Fig. 1-Fig. 4.The abrasion condition of engine air conduit is determined first, then processes fine motion abrasive surface, it is ensured that
Surface concentricity, perpendicularity after processing etc., repair method include adjustment concentricity, mill repair chromium plating, electron beam welding, shot-peening with
And dynamic balancing etc..Embodiment is as follows：
Abrasion condition is checked after 1 first time between overhauls of engine air conduit.The end face denuded to air conduit fine motion
It is ground with circumference or turning, to ensure that air conduit respectively coordinates periphery relative to the concentricity and each abutting end of reference plane
The depth of parallelism in face, and ensure that each small―gap suture coordinates；The adjusting pad 12 of design air conduit assembling；It is ground fine motion abrasion base
Quasi- face 3 to fretting wear is eliminated, it is ensured that the perpendicularity of reference plane 3.It is ground the rear end face 4 of fine motion abrasion, it is ensured that rear end face and base
The depth of parallelism in quasi- face 3.Design the fit dimension of axially adjustable section of adjusting pad 12, it is ensured that reference plane 4 is axially engaged.It is ground circumference
Mating surface 5, and the rear axle surface mill of the part coordinated with circumference mating surface 5 is repaiied into chromium plating, it is ensured that small―gap suture radial fit.To sky
The weld seam 9 of solder joint carries out repair welding again at conductance pipe surface five road reinforcements 2 arranged in parallel, and uses water logging ultrasonic examination
Chromium plating process is ground at weld seam, increase air conduit mounting surface fine motion abrasion, air conduit front end assembling cushion rubber is used instead metal
Sealing ring, then shot peening air conduit surface.Step 7 and the Surface Machining of internal diameter 8 are eliminated after polishing scratch, design adjusting pad
Ensure assembling axial gap and the small―gap suture radial fit of internal diameter 8 at step 7.The weight of electron beam weld 9 between cylinder inside and outside air conduit 1
New electron beam soldering weldering, and with water logging ultrasonic examination weld seam 9 without sealing-off.Described shot peening refers to air conduit
（1）The shot-peening that inside and outside barrel is carried out, and to air conduit（1）The shot peening strength that inner tube wall and outer tube wall are carried out is respectively 0.12A
And 0.14A.Enter residual unbalance, at action balance, rear and front end to air conduit 1 to reach within 5 g cm.In front end assembling
Vibration damping metal o-ring 6.
The air conduit repaired by above technical scheme passes through endurance test examination.Product after reparation meets the
Two time between overhauls, flawless failure.
Claims (4)
1. a kind of extend the method that engine turbine air conduit overhauls life-span phase, it is characterised in that comprises the following steps：
1）To air conduit（1）The end face and circumference of fine motion abrasion are ground or turning, to ensure air conduit（1）It is each to coordinate
Periphery is relative to reference plane（3）Concentricity and each counterface the depth of parallelism, and ensure each small―gap suture coordinate；
2）Design ensures step（7）Place's assembling air conduit axial gap and internal diameter（8）The adjusting pad of small―gap suture radial fit
（12）；
3）To air conduit（1）Solder joint repair welding again at the five road reinforcements arranged in parallel of surface, and using the inspection of water logging ultrasonic wave
Weld seam is looked into, increases air conduit（1）Chromium plating process is ground at mounting surface fine motion abrasion, by air conduit（1）Assemble cushion rubber in front end
Use metal o-ring instead, then shot peening air conduit（1）Surface.
2. the method that extension engine turbine air conduit overhauls life-span phase as claimed in claim 1, it is characterised in that：Grinding
Fine motion base level of abrasion（3）Eliminated to fretting wear, it is ensured that reference plane（3）Perpendicularity；It is ground the rear end face of fine motion abrasion
（4）, it is ensured that rear end face and reference plane（3）The depth of parallelism.
3. the method that extension engine turbine air conduit overhauls life-span phase as claimed in claim 1, it is characterised in that：Design
Adjusting pad（12）Axially adjustable section of fit dimension, it is ensured that reference plane（3）Axially engage；It is ground circumference mating surface（5）, and will
With circumference mating surface（5）The surface mill of the rear axle part of cooperation repaiies chromium plating, it is ensured that small―gap suture radial fit.
4. the method that extension engine turbine air conduit overhauls life-span phase as claimed in claim 1, it is characterised in that：Air
Conduit（1）Electron beam weld between inside and outside cylinder（9）Again electron beam soldering is welded, and with water logging ultrasonic examination weld seam（9）Without de-
Weldering.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510053290.0A CN104723014B (en) | 2015-02-02 | 2015-02-02 | Extension engine turbine air conduit overhauls life-span phase |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510053290.0A CN104723014B (en) | 2015-02-02 | 2015-02-02 | Extension engine turbine air conduit overhauls life-span phase |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104723014A CN104723014A (en) | 2015-06-24 |
| CN104723014B true CN104723014B (en) | 2017-07-11 |
Family
ID=53447740
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510053290.0A Expired - Fee Related CN104723014B (en) | 2015-02-02 | 2015-02-02 | Extension engine turbine air conduit overhauls life-span phase |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104723014B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110936099A (en) * | 2019-11-19 | 2020-03-31 | 中国航发沈阳黎明航空发动机有限责任公司 | Process method for maintaining high-pressure turbine guide pipe |
| CN115338594B (en) * | 2022-07-01 | 2024-02-20 | 中国航发南方工业有限公司 | Air tightness repairing method for catheter in combined cavity of rear bearing shell |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1032582A (en) * | 1987-10-15 | 1989-04-26 | 通用电气公司 | The method and apparatus of replacing section of tubing |
| US7140106B1 (en) * | 2003-09-25 | 2006-11-28 | Reynolds Russell B | Process to restore and refurbish an engine turbo charger or exhaust part |
| RU2311998C2 (en) * | 2006-01-30 | 2007-12-10 | Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") | Method for restoring heat pipe of gas turbine engine combustion chamber |
| CN104297342A (en) * | 2014-10-17 | 2015-01-21 | 西安航空动力股份有限公司 | Ultrasonic testing method of engine air conduit electron beam welding line |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7146725B2 (en) * | 2003-05-06 | 2006-12-12 | Siemens Power Generation, Inc. | Repair of combustion turbine components |
-
2015
- 2015-02-02 CN CN201510053290.0A patent/CN104723014B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1032582A (en) * | 1987-10-15 | 1989-04-26 | 通用电气公司 | The method and apparatus of replacing section of tubing |
| US7140106B1 (en) * | 2003-09-25 | 2006-11-28 | Reynolds Russell B | Process to restore and refurbish an engine turbo charger or exhaust part |
| RU2311998C2 (en) * | 2006-01-30 | 2007-12-10 | Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") | Method for restoring heat pipe of gas turbine engine combustion chamber |
| CN104297342A (en) * | 2014-10-17 | 2015-01-21 | 西安航空动力股份有限公司 | Ultrasonic testing method of engine air conduit electron beam welding line |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104723014A (en) | 2015-06-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103212937B (en) | On-line overlaying welding fan journal repairing method | |
| CN104439926B (en) | A kind of rear housing assembly manufacture method that can solve the problem that deformation and crack problem | |
| CN105817832B (en) | Pressure vessel field repair is with remanufacturing technique | |
| CN104723014B (en) | Extension engine turbine air conduit overhauls life-span phase | |
| CN105965203A (en) | Bearing seat repairing technology of vacuum pump shaft | |
| CN107264835A (en) | A kind of gear test load charger | |
| US20110179843A1 (en) | Method for hardening the surface of a component in a wind turbine | |
| CN101890610A (en) | Field repairing method of welding cracks of feeding slip-ring body of large-sized slide mill | |
| KR101315361B1 (en) | Shaft manufacturing method | |
| US20050132569A1 (en) | Method of repairing a part using laser cladding | |
| CN103465062A (en) | Tilting-type bearing bush laser repair device and laser repair method | |
| CN105689857A (en) | Tower drum manufacturing welding process | |
| US20160102554A1 (en) | Inspection and qualification for remanufacturing of compressor wheels | |
| KR20130091512A (en) | Method for remanufacturing of bearing | |
| CN104801920A (en) | Shield tunneling machine hydraulic cylinder piston rod surface repairing re-manufacturing method | |
| CN102762336A (en) | Method for repairing a flange of a housing | |
| CN107971693B (en) | A kind of wheel chamber casing crackle repair method of titanium alloy inlet casing | |
| CN105803453A (en) | Engine crankshaft fatigue crack laser repairing and strengthening device and method | |
| CN105598632B (en) | A kind of diesel locomotive indicator valve mandrel restorative procedure | |
| CN109950986B (en) | Method for improving stability of stator shielding sleeve of shielding motor | |
| JP2019044969A (en) | Pressure reservoir for high-pressure hydrogen gas | |
| RU2009127195A (en) | SHAFT RECOVERY METHOD | |
| CN109454397A (en) | A kind of restorative procedure of drum type vacuum filter filler cylinder | |
| CN103406724B (en) | A kind of process strengthening pressure-resistance structure bearing capacity | |
| CN102554556B (en) | Machining method for eliminating wear of propeller hub and blades of adjustable propeller device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170711 Termination date: 20180202 |