CN105500216B - Helicopter rotor system propeller hub center piece stress peening process method - Google Patents
Helicopter rotor system propeller hub center piece stress peening process method Download PDFInfo
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- CN105500216B CN105500216B CN201610037546.3A CN201610037546A CN105500216B CN 105500216 B CN105500216 B CN 105500216B CN 201610037546 A CN201610037546 A CN 201610037546A CN 105500216 B CN105500216 B CN 105500216B
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- peening
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- center piece
- propeller hub
- piece
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Sampling And Sample Adjustment (AREA)
Abstract
The invention discloses helicopter rotor system propeller hub center piece stress peening process method, including preparation before shot-peening, carry out test piece shot-peening, carry out center piece after center piece shot-peening, shot-peening examine and shot-peening after the several steps of processing.The helicopter rotor system propeller hub center piece stress peening process method of the present invention, improves center piece shot peening strengthening quality and qualification rate, qualification rate reaches 100%, it ensure that the manufacturing schedule of helicopter hub, cost has been saved, the fatigue strength of center piece is also improved in addition, increases fatigue life.
Description
Technical field
The invention belongs to helicopter manufacture field, and in particular to one kind is applied to that helicopter rotor system propeller hub is identical or phase
Like center piece surface shot blasting strengthening process.
Background technology
In the existing same or similar center piece surface shot blasting strengthening technique of helicopter rotor system propeller hub, shot-peening process is adopted
Operate by hand, the method imperfection of shot-peening test piece and center piece Set and Positioning, technical process is unstable, to the technical ability of operator
It is required that it is higher, cause fatigue life shorter.
Due to the limitation of helicopter rotor system propeller hub center piece structural complexity, center piece bead blasted surfaces locally spray less than
Or shot peening strength does not reach design requirement, the qualification rate ratio of center piece shot peening strength and coverage rate is relatively low, therefore center piece is sprayed
Ball surface quality and its fatigue life, which exist, to be had a strong impact on, and then influences the fatigue life of helicopter rotor system, while also right
The maintenance work of helicopter rotor system, which is brought, to be had a strong impact on.
The content of the invention
Instant invention overcomes the deficiencies in the prior art, there is provided a kind of reliability is high, helicopter rotor system easy to operate
The process of propeller hub center piece surface shot blasting strengthening, to improve center piece shot peening strengthening qualification rate and its fatigue strength, extension
The maintenance cycle of helicopter.
To achieve the above object, helicopter rotor system propeller hub center piece stress peening process method of the invention, including
Following steps：
1) selection of compressed air shotblasting machine：Model MP1500TS compressed air shotblasting machine is selected to carry out shot-peening；
2) selection of pill：The shot-peening pellet diameters of selection are 0.4mm；
3) selection of test piece：
3.1) select be for the test piece specification for determining shot peening strength：Long 76.2 ± 0.2mm, wide 19 ± 0.1mm, thickness
1.30±0.02mm；
3.2) select the thick test piece Ti 10.2.3 for coverage rate confirmation and the 15-5PH for stress mornitoring after shot-peening thick
Test piece, the thickness of above two thickness test piece is 6mm, long 76.2 ± 0.2mm, wide 19 ± 0.1mm, and the test piece of above two thickness is only in spray
Ball reinforcement process parameter is used when determining, is not used when fatigue test piece and installation part shot peening strengthening；
4) selection of fixture：
4.1) test piece fixture selects the structure similar to propeller hub center piece, and test piece position should meet propeller hub center piece design knot
The requirement of structure；
4.2) structure of center piece shot-peening fixture, it is considered to the operation and the protection of non-shot peening coverage of shot peening coverage, wherein spraying
The position in ball region and the protection of non-shot peening coverage, should meet the status requirement in design drawing；Protector material selection is hard
Spend the stainless steel plate for HRc60；Adhesive plaster or rubber stopper are selected in hole with protective materials；
5) shot peening strengthening parameter is determined：
5.1) by step 3.1) the middle test piece progress cloudburst test selected, determine shot peening strengthening parameter；
5.2) by step 3.2) the middle thick test pieces progress cloudburst tests of two kinds selected, confirm 150% coverage rate institute of acquisition
The shot-peening time needed；The shot-peening time is confirmed by propeller hub center piece shot-peening again；
6) stress peening process process is carried out：
6.1) the propeller hub center piece needed for shot-peening process is prepared；
6.2) propeller hub center piece shot-peening type is determined：
Shot-peening is carried out using nozzle during the shot-peening of center piece outer surface；
Shot-peening is carried out using rotary spray gun when center member bore and surface of internal cavity shot-peening；
6.3) center piece shot-blast process process and examination requirements
First to step 3.1) in the test piece selected carry out shot-peening, test piece shot peening strength and coverage rate detection it is qualified after, it is then right
Propeller hub center piece is used and step 3.1) the middle test piece identical shot-blast process parameter progress shot-peening processing selected, is detected in propeller hub
Central member coverage rate, shot peening coverage and protection zone and its outward appearance；Its detailed process is：
6.3.1) test piece shot-peening
Shot peening strength is examined：, it is necessary to carry out test piece shot-peening before and after each propeller hub center piece shot-peening, and make saturation curve,
Check camber value, saturation time Ts and shot-peening time Te parameters；
Shot-peening process：According to test piece status requirement on design drawing, by test piece on test piece special fixture positioning and clamping, profit
Carried out with parameter specified in technological procedure after shot-peening, detection shot peening strength and coverage rate, and make shot-peening saturation curve；
6.3.2) propeller hub center piece shot-peening
Propeller hub center piece positioning and clamping on special fixture, by defined region nozzle on design drawing to propeller hub center
Part upper surface carries out shot-peening, while being protected to protection zone；
Center piece is afterwards turned over, shot-peening is carried out to center piece lower surface with nozzle by defined region on design drawing, together
When protection zone is protected；
Shot-peening is carried out to 5 macropore madial walls of center piece with rotary spray gun by defined region on design drawing, while right
Protected protection zone；
Propeller hub center piece is unloaded after shot-peening, bead blasted surfaces are cleared up with clean hairbrush；
6.3.3) the propeller hub center piece after shot-peening is examined
Visual examination is first carried out, all surface of propeller hub center piece is visually inspected：Whether visually inspect shot peening coverage outward appearance
Whether uniform size is qualified；Required according to size as defined in design drawing, visually inspect zone of protection；
Coverage rate detection is carried out afterwards：Using 10 times of magnifying glasses, the coverage rate of propeller hub center piece is visually inspected；
7) processing after shot-peening：
Remove protector, and bead blasted surfaces are cleared up with hairbrush；
Propeller hub center piece after shot-peening passed examination should be transferred to next procedure rapidly, if the storage period should more than 12 hours
Interim oil sealing packaging；
Propeller hub center piece after shot-peening does not allow mechanical checkout；
Propeller hub center piece after shot-peening is cleaned.
The helicopter rotor system propeller hub center piece stress peening process method of the present invention, improves center piece shot peening strengthening
Quality and qualification rate, qualification rate reach 100%, it is ensured that the manufacturing schedule of helicopter hub, have saved cost.Additionally improve
The fatigue strength of center piece, makes the fatigue life reach 10000 hours.
Embodiment
The present invention is described in further detail with reference to embodiment, but the implementation of the present invention is not limited to this.
As the method previously described, stress peening process has been carried out to EC175-Z15 helicopter rotor system propeller hub center pieces
Processing.Through examining, qualification rate reaches 100%, has passed through fatigue test checking requirement, has improved center piece fatigue life.Shot-peening
That strengthens concretely comprises the following steps：
1) preparation before shot-peening：
Model MP1500TS compressed air shotblasting machine is selected to carry out shot-peening；
The shot-peening pellet diameters of selection are 0.4mm；
Select be for the test piece specification for determining shot peening strength：Long 76.2 ± 0.2mm, wide 19 ± 0.1mm, thickness 1.30 ±
0.02mm；
Select the 15-5PH thickness examinations for the thick test piece Ti 10.2.3 of coverage rate confirmation and for stress mornitoring after shot-peening
Piece, the thickness of above two thickness test piece is 6mm, long 76.2 ± 0.2mm, wide 19 ± 0.1mm；
Test piece fixture selects the structure similar to propeller hub center piece, and test piece position should meet propeller hub center piece design structure
It is required that；
The structure of center piece shot-peening fixture, it is considered to the operation and the protection of non-shot peening coverage of shot peening coverage, wherein shot-peening area
The position in domain and the protection of non-shot peening coverage, should meet the status requirement in design drawing；Protector material selection hardness is
HRc60 stainless steel plate；Adhesive plaster or rubber stopper are selected in hole with protective materials；
Cloudburst test is carried out by test piece, shot peening strengthening parameter is determined；
Cloudburst test is carried out by the two kinds thick test piece of selection, confirms to obtain the shot-peening time required for 150% coverage rate；
The shot-peening time is confirmed by propeller hub center piece shot-peening again；
2) test piece shot-peening is carried out：Test piece shot-peening fixture number：S7900M622G1200602.
According to test piece status requirement on design drawing, by test piece on test piece special fixture positioning and clamping, utilize Process Planning
Parameter specified in journey is carried out after shot-peening, detection shot peening strength and coverage rate, and makes shot-peening saturation curve
3) center piece shot-peening is carried out：Center piece shot-peening fixture number：S7901M622G2100602.
Propeller hub center piece positioning and clamping on special fixture, by defined region nozzle on design drawing to propeller hub center
Part upper surface carries out shot-peening, while being protected to protection zone；
Center piece is afterwards turned over, shot-peening is carried out to center piece lower surface with nozzle by defined region on design drawing, together
When protection zone is protected；
Shot-peening is carried out to 5 macropore madial walls of center piece with rotary spray gun by defined region on design drawing, while right
Protected protection zone；
Propeller hub center piece is unloaded after shot-peening, bead blasted surfaces are cleared up with clean hairbrush.
4) center piece is examined after shot-peening：
Visual examination is first carried out, all surface of propeller hub center piece is visually inspected：Whether visually inspect shot peening coverage outward appearance
Whether uniform size is qualified；Required according to size as defined in design drawing, visually inspect zone of protection；
Coverage rate detection is carried out afterwards：Using 10 times of magnifying glasses, the shot-peening depth of visual inspection propeller hub center piece for 0.25~
0.35mm；Coverage rate is 150%~400%；
5) processing after shot-peening：
Remove protector, and bead blasted surfaces are cleared up with hairbrush；Propeller hub center piece after shot-peening passed examination should turn rapidly
Enter to next procedure, if the storage period answered interim oil sealing to pack more than 12 hours；Propeller hub center piece after shot-peening does not allow machinery
Correction；Propeller hub center piece after shot-peening is cleaned.
Claims (1)
1. helicopter rotor system propeller hub center piece stress peening process method, comprises the following steps：
1) selection of compressed air shotblasting machine：Model MP1500TS compressed air shotblasting machine is selected to carry out shot-peening；
2) selection of pill：The shot-peening pellet diameters of selection are 0.4mm；
3) selection of test piece：
3.1) select be for the test piece specification for determining shot peening strength：Long 76.2 ± 0.2mm, wide 19 ± 0.1mm, thickness 1.30 ±
0.02mm；
3.2) the 15-5PH thickness examinations for the thick test piece Ti 10.2.3 of coverage rate confirmation and for stress mornitoring after shot-peening are selected
Piece, the thickness of above two thickness test piece is 6mm, long 76.2 ± 0.2mm, wide 19 ± 0.1mm, and above two thickness test piece is only in shot-peening
Reinforcement process parameter is used when determining, is not used when fatigue test piece and installation part shot peening strengthening；
4) selection of fixture：
4.1) test piece fixture selects the structure similar to propeller hub center piece, and test piece position should meet propeller hub center piece design structure
It is required that；
4.2) structure of center piece shot-peening fixture, it is considered to the operation and the protection of non-shot peening coverage of shot peening coverage, wherein shot-peening area
The position in domain and the protection of non-shot peening coverage, should meet the status requirement in design drawing；Protector material selection hardness is
HRc60 stainless steel plate；Adhesive plaster or rubber stopper are selected in hole with protective materials；
5) shot peening strengthening parameter is determined：
5.1) by step 3.1) the middle test piece progress cloudburst test selected, determine shot peening strengthening parameter；
5.2) by step 3.2) in the two kinds thick test pieces selected carry out cloudburst tests, required for confirming to obtain 150% coverage rate
The shot-peening time；The shot-peening time is confirmed by propeller hub center piece shot-peening again；
6) stress peening process process is carried out：
6.1) the propeller hub center piece needed for shot-peening process is prepared；
6.2) propeller hub center piece shot-peening type is determined：
Shot-peening is carried out using nozzle during the shot-peening of center piece outer surface；
Shot-peening is carried out using rotary spray gun when center member bore and surface of internal cavity shot-peening；
6.3) center piece shot-blast process process and examination requirements
First to step 3.1) in the test piece selected carry out shot-peening, test piece shot peening strength and coverage rate detection it is qualified after, then to propeller hub
Center piece is used and step 3.1) the middle test piece identical shot-blast process parameter progress shot-peening processing selected, detects propeller hub center piece
Coverage rate, shot peening coverage and protection zone and its outward appearance；Its detailed process is：
6.3.1) test piece shot-peening
Shot peening strength is examined：, it is necessary to carry out test piece shot-peening before and after each propeller hub center piece shot-peening, and saturation curve is made, checked
Camber value, saturation time Ts and shot-peening time Te parameters；
Shot-peening process：According to test piece status requirement on design drawing, by test piece on test piece special fixture positioning and clamping, utilize work
Parameter specified in skill code is carried out after shot-peening, detection shot peening strength and coverage rate, and makes shot-peening saturation curve；
6.3.2) propeller hub center piece shot-peening
Propeller hub center piece positioning and clamping on special fixture, by defined region nozzle on design drawing in propeller hub center piece
Surface carries out shot-peening, while being protected to protection zone；
Center piece is afterwards turned over, shot-peening is carried out to center piece lower surface with nozzle by defined region on design drawing, while right
Protected protection zone；
Shot-peening is carried out to 5 macropore madial walls of center piece with rotary spray gun by defined region on design drawing, while to protection
Protected in region；
Propeller hub center piece is unloaded after shot-peening, bead blasted surfaces are cleared up with clean hairbrush；
6.3.3) the propeller hub center piece after shot-peening is examined
Visual examination is first carried out, all surface of propeller hub center piece is visually inspected：Whether uniform visually inspect shot peening coverage outward appearance
It is whether qualified with size；Required according to size as defined in design drawing, visually inspect zone of protection；
Coverage rate detection is carried out afterwards：Using 10 times of magnifying glasses, the coverage rate of propeller hub center piece is visually inspected；
7) processing after shot-peening：
Remove protector, and bead blasted surfaces are cleared up with hairbrush；
Propeller hub center piece after shot-peening passed examination should be transferred to next procedure rapidly, if the storage period should be interim more than 12 hours
Oil sealing is packed；
Propeller hub center piece after shot-peening does not allow mechanical checkout；
Propeller hub center piece after shot-peening is cleaned.
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| CN201610037546.3A CN105500216B (en) | 2016-01-20 | 2016-01-20 | Helicopter rotor system propeller hub center piece stress peening process method |
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| CN201610037546.3A CN105500216B (en) | 2016-01-20 | 2016-01-20 | Helicopter rotor system propeller hub center piece stress peening process method |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108977640A (en) * | 2018-09-10 | 2018-12-11 | 中石化四机石油机械有限公司 | A kind of stress peening process method of fracturing pump valve chamber |
| CN109551376B (en) * | 2018-11-21 | 2021-09-10 | 中国航发哈尔滨东安发动机有限公司 | Method for accurately acquiring shot blasting strength of centrifugal impeller |
| CN110760658B (en) * | 2019-11-29 | 2021-09-17 | 中国航发中传机械有限公司 | Method for shot peening strengthening of tooth surface of spiral bevel gear |
| CN110951954A (en) * | 2019-12-25 | 2020-04-03 | 哈尔滨电气动力装备有限公司 | Surface shot blasting strengthening process method for guide vane blade of main pump of nuclear power station |
| CN111002229A (en) * | 2019-12-26 | 2020-04-14 | 中船重工龙江广瀚燃气轮机有限公司 | Processing method for strengthening surface of liquid shot blasting |
| CN112643554B (en) * | 2020-12-22 | 2022-07-05 | 中船重工龙江广瀚燃气轮机有限公司 | Blade liquid shot blasting control method |
| CN113063690B (en) * | 2021-04-12 | 2021-11-16 | 湖南南方宇航高精传动有限公司 | Method for calculating process parameters of cylindrical gear strengthening shot blasting |
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|---|---|---|---|---|
| CN101358271A (en) * | 2008-09-26 | 2009-02-04 | 无锡透平叶片有限公司 | Blade root surface strengthening method |
| CN101363075A (en) * | 2008-09-26 | 2009-02-11 | 无锡透平叶片有限公司 | Processing method for concentrated peening to blade |
| CN104625967A (en) * | 2014-12-24 | 2015-05-20 | 上海振华重工集团(南通)传动机械有限公司 | Shot blasting treatment method for increasing stress of gear workpiece |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2014092867A (en) * | 2012-11-01 | 2014-05-19 | Mitsubishi Heavy Ind Ltd | Processing work schedule creating system and work schedule creating program |
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2016
- 2016-01-20 CN CN201610037546.3A patent/CN105500216B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101358271A (en) * | 2008-09-26 | 2009-02-04 | 无锡透平叶片有限公司 | Blade root surface strengthening method |
| CN101363075A (en) * | 2008-09-26 | 2009-02-11 | 无锡透平叶片有限公司 | Processing method for concentrated peening to blade |
| CN104625967A (en) * | 2014-12-24 | 2015-05-20 | 上海振华重工集团(南通)传动机械有限公司 | Shot blasting treatment method for increasing stress of gear workpiece |
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