CN105500216A - Shot peening strengthening technique of middleware of hub of helicopter rotor system - Google Patents
Shot peening strengthening technique of middleware of hub of helicopter rotor system Download PDFInfo
- Publication number
- CN105500216A CN105500216A CN201610037546.3A CN201610037546A CN105500216A CN 105500216 A CN105500216 A CN 105500216A CN 201610037546 A CN201610037546 A CN 201610037546A CN 105500216 A CN105500216 A CN 105500216A
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- peening
- shot
- center piece
- propeller hub
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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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- Mechanical Engineering (AREA)
- Sampling And Sample Adjustment (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a shot peening strengthening technique of a middleware of a hub of a helicopter rotor system. The technique comprises the following steps: preparation before shot peening, shot peening for a test piece, shot peening for the middleware, inspection of the middleware after shot peening and treatment after shot peening. The shot peening strengthening technique has the advantages that the shot peening strengthening quality and the qualified rate of the middleware are improved, the qualified rate can reach 100%, the production schedule of the hub of a helicopter is ensured, and the cost is saved; in addition, the fatigue strength of the middleware is improved, so that the fatigue life is prolonged.
Description
Technical field
The invention belongs to helicopter and manufacture field, be specifically related to one and be applicable to helicopter rotor system propeller hub same or similar center piece surface shot blasting strengthening process.
Background technology
In existing helicopter rotor system propeller hub same or similar center piece surface shot blasting strengthening technique, shot-peening process adopts manual operations, the method imperfection of shot-peening test piece and center piece Set and Positioning, and technical process is unstable, higher to the skill set requirements of operator, cause fatigue life shorter.
Due to the restriction of helicopter rotor system propeller hub center piece structural complexity, center piece bead blasted surfaces local spray less than or shot peening strength do not reach designing requirement, the qualification rate of center piece shot peening strength and coverage rate is lower, therefore exist center piece bead blasted surfaces quality and fatigue life thereof and have a strong impact on, and then affect the fatigue life of helicopter rotor system, also the maintenance work of helicopter rotor system is brought simultaneously and have a strong impact on.
Summary of the invention
Instant invention overcomes the deficiencies in the prior art, the process of the helicopter rotor system propeller hub center piece surface shot blasting strengthening providing a kind of reliability high, easy and simple to handle, to improve center piece shot peening strengthening qualification rate and its fatigue strength, extend the maintenance cycle of helicopter.
For achieving the above object, helicopter rotor system propeller hub center piece stress peening process method of the present invention, comprises the following steps:
1) selection of compressed air shotblasting machine: selection model is that the compressed air shotblasting machine of MP1500TS carries out shot-peening;
2) selection of pill: the shot-peening pellet diameters of selection is 0.4mm;
3) selection of test piece:
3.1) select for determining that the test piece specification of shot peening strength is: long 76.2 ± 0.2mm, wide 19 ± 0.1mm, thickness 1.30 ± 0.02mm;
3.2) select for the thick test piece Ti10.2.3 of coverage rate confirmation with for the thick test piece of the 15-5PH of stress mornitoring after shot-peening, the thickness of above-mentioned two kinds of thick test pieces is 6mm, long 76.2 ± 0.2mm, wide 19 ± 0.1mm, above-mentioned two kinds of thick test pieces only adopt when stress peening process parameter is determined, do not adopt 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 the requirement of propeller hub center piece project organization;
4.2) structure of center piece shot-peening fixture, consider the operation of shot peening coverage and the protection of non-shot peening coverage, wherein the position of shot peening coverage and the protection of non-shot peening coverage, should meet the status requirement in design drawing; Protector material selection hardness is the corrosion resistant plate of HRc60; Hole protective materials selects adhesive plaster or rubber stopper;
5) shot peening strengthening parameter is determined:
5.1) by step 3.1) in the test piece of selecting carry out cloudburst test, determine shot peening strengthening parameter;
5.2) by step 3.2) in two kinds of thick test pieces of selecting carry out cloudburst test, confirm the shot-peening time required for acquisition 150% coverage rate; This shot-peening time is confirmed again by propeller hub center piece shot-peening;
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:
Nozzle is adopted to carry out shot-peening during center piece outer surface shot-peening;
Rotary spray gun is adopted to carry out shot-peening 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 of selecting carry out shot-peening, test piece shot peening strength and coverage rate detect qualified after, again propeller hub center piece is adopted and step 3.1) in the identical shot-blast process parameter of the test piece of selecting carry out shot-peening processing, detect propeller hub center piece coverage rate, shot peening coverage and protection zone and outward appearance thereof; Its detailed process is:
6.3.1) test piece shot-peening
Shot peening strength is checked: before and after each propeller hub center piece shot-peening, need to carry out test piece shot-peening, and make saturation curve, checks camber value, saturation time Ts and shot-peening time Te parameter;
Shot-peening process: according to test piece status requirement on design drawing, by test piece positioning and clamping on test piece special fixture, after utilizing the parameter specified in technological procedure to carry out shot-peening, detects 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, carries out shot-peening by the region nozzle that design drawing specifies to propeller hub center piece upper surface, protects simultaneously to protection zone;
Then overturn center piece, by the region nozzle that design drawing specifies, shot-peening is carried out to center piece lower surface, protection zone is protected simultaneously;
By the region rotary spray gun that design drawing specifies, shot-peening is carried out to center piece 5 macropore madial walls, protection zone is protected simultaneously;
Propeller hub center piece is unloaded, by clean hairbrush cleaning bead blasted surfaces after shot-peening;
6.3.3) the propeller hub center piece inspection after shot-peening
First carry out visual examination, all surface of visual examination propeller hub center piece: whether the whether all even size of visual examination shot peening coverage outward appearance is qualified; According to the dimensional requirement that design drawing specifies, visual examination zone of protection;
After carry out coverage rate detection: adopt 10 times of magnifying glasses, the coverage rate of visual examination propeller hub center piece;
7) process after shot-peening:
Remove protector, and clear up bead blasted surfaces with hairbrush;
Propeller hub center piece after shot-peening passed examination should be transferred to next procedure rapidly, if the storage period should pack by oil sealing more than 12 hours temporarily;
Propeller hub center piece after shot-peening does not allow mechanical checkout;
Propeller hub center piece after shot-peening is cleaned.
Helicopter rotor system propeller hub center piece stress peening process method of the present invention, improve center piece shot peening strengthening quality and qualification rate, qualification rate reaches 100%, ensure that the manufacturing schedule of helicopter hub, has saved cost.Improve the fatigue strength of center piece in addition, make to reach 10000 hours fatigue life.
Detailed description of the invention
Below in conjunction with embodiment, the present invention is described in further detail, but embodiments of the present invention are not limited thereto.
According to aforesaid method, stress peening process process is carried out to EC175-Z15 helicopter rotor system propeller hub center piece.Through inspection, qualification rate reaches 100%, have passed fatigue test checking requirement, improves center piece fatigue life.The concrete steps of shot peening strengthening are:
1) preparation before shot-peening:
Selection model is that the compressed air shotblasting machine of MP1500TS carries out shot-peening;
The shot-peening pellet diameters selected is 0.4mm;
Select for determining that the test piece specification of shot peening strength is: long 76.2 ± 0.2mm, wide 19 ± 0.1mm, thickness 1.30 ± 0.02mm;
Select for the thick test piece Ti10.2.3 of coverage rate confirmation with for the thick test piece of the 15-5PH of stress mornitoring after shot-peening, the thickness of above-mentioned two kinds of thick test pieces 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 the requirement of propeller hub center piece project organization;
The structure of center piece shot-peening fixture, consider the operation of shot peening coverage and the protection of non-shot peening coverage, wherein the position of shot peening coverage and the protection of non-shot peening coverage, should meet the status requirement in design drawing; Protector material selection hardness is the corrosion resistant plate of HRc60; Hole protective materials selects adhesive plaster or rubber stopper;
Carry out cloudburst test by test piece, determine shot peening strengthening parameter;
Carry out cloudburst test by two kinds of thick test pieces of selecting, confirm the shot-peening time required for acquisition 150% coverage rate; This shot-peening time is confirmed again by propeller hub center piece shot-peening;
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 positioning and clamping on test piece special fixture, after utilizing the parameter specified in technological procedure to carry out shot-peening, detect shot peening strength and coverage rate, and make 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, carries out shot-peening by the region nozzle that design drawing specifies to propeller hub center piece upper surface, protects simultaneously to protection zone;
Then overturn center piece, by the region nozzle that design drawing specifies, shot-peening is carried out to center piece lower surface, protection zone is protected simultaneously;
By the region rotary spray gun that design drawing specifies, shot-peening is carried out to center piece 5 macropore madial walls, protection zone is protected simultaneously;
Propeller hub center piece is unloaded, by clean hairbrush cleaning bead blasted surfaces after shot-peening.
4) center piece inspection after shot-peening:
First carry out visual examination, all surface of visual examination propeller hub center piece: whether the whether all even size of visual examination shot peening coverage outward appearance is qualified; According to the dimensional requirement that design drawing specifies, visual examination zone of protection;
After carry out coverage rate detection: adopt 10 times of magnifying glasses, the shot-peening degree of depth of visual examination propeller hub center piece is 0.25 ~ 0.35mm; Coverage rate is 150% ~ 400%;
5) process after shot-peening:
Remove protector, and clear up bead blasted surfaces with hairbrush; Propeller hub center piece after shot-peening passed examination should be transferred to next procedure rapidly, if the storage period should pack by oil sealing more than 12 hours temporarily; Propeller hub center piece after shot-peening does not allow mechanical checkout; 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: selection model is that the compressed air shotblasting machine of MP1500TS carries out shot-peening;
2) selection of pill: the shot-peening pellet diameters of selection is 0.4mm;
3) selection of test piece:
3.1) select for determining that the test piece specification of shot peening strength is: long 76.2 ± 0.2mm, wide 19 ± 0.1mm, thickness 1.30 ± 0.02mm;
3.2) select for the thick test piece Ti10.2.3 of coverage rate confirmation with for the thick test piece of the 15-5PH of stress mornitoring after shot-peening, the thickness of above-mentioned two kinds of thick test pieces is 6mm, long 76.2 ± 0.2mm, wide 19 ± 0.1mm, above-mentioned two kinds of thick test pieces only adopt when stress peening process parameter is determined, do not adopt 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 the requirement of propeller hub center piece project organization;
4.2) structure of center piece shot-peening fixture, consider the operation of shot peening coverage and the protection of non-shot peening coverage, wherein the position of shot peening coverage and the protection of non-shot peening coverage, should meet the status requirement in design drawing; Protector material selection hardness is the corrosion resistant plate of HRc60; Hole protective materials selects adhesive plaster or rubber stopper;
5) shot peening strengthening parameter is determined:
5.1) by step 3.1) in the test piece of selecting carry out cloudburst test, determine shot peening strengthening parameter;
5.2) by step 3.2) in two kinds of thick test pieces of selecting carry out cloudburst test, confirm the shot-peening time required for acquisition 150% coverage rate; This shot-peening time is confirmed again by propeller hub center piece shot-peening;
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:
Nozzle is adopted to carry out shot-peening during center piece outer surface shot-peening;
Rotary spray gun is adopted to carry out shot-peening 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 of selecting carry out shot-peening, test piece shot peening strength and coverage rate detect qualified after, again propeller hub center piece is adopted and step 3.1) in the identical shot-blast process parameter of the test piece of selecting carry out shot-peening processing, detect propeller hub center piece coverage rate, shot peening coverage and protection zone and outward appearance thereof; Its detailed process is:
6.3.1) test piece shot-peening
Shot peening strength is checked: before and after each propeller hub center piece shot-peening, need to carry out test piece shot-peening, and make saturation curve, checks camber value, saturation time Ts and shot-peening time Te parameter;
Shot-peening process: according to test piece status requirement on design drawing, by test piece positioning and clamping on test piece special fixture, after utilizing the parameter specified in technological procedure to carry out shot-peening, detects 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, carries out shot-peening by the region nozzle that design drawing specifies to propeller hub center piece upper surface, protects simultaneously to protection zone;
Then overturn center piece, by the region nozzle that design drawing specifies, shot-peening is carried out to center piece lower surface, protection zone is protected simultaneously;
By the region rotary spray gun that design drawing specifies, shot-peening is carried out to center piece 5 macropore madial walls, protection zone is protected simultaneously;
Propeller hub center piece is unloaded, by clean hairbrush cleaning bead blasted surfaces after shot-peening;
6.3.3) the propeller hub center piece inspection after shot-peening
First carry out visual examination, all surface of visual examination propeller hub center piece: whether the whether all even size of visual examination shot peening coverage outward appearance is qualified; According to the dimensional requirement that design drawing specifies, visual examination zone of protection;
After carry out coverage rate detection: adopt 10 times of magnifying glasses, the coverage rate of visual examination propeller hub center piece;
7) process after shot-peening:
Remove protector, and clear up bead blasted surfaces with hairbrush;
Propeller hub center piece after shot-peening passed examination should be transferred to next procedure rapidly, if the storage period should pack by oil sealing more than 12 hours temporarily;
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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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN110760658A (en) * | 2019-11-29 | 2020-02-07 | 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 |
| CN112643554A (en) * | 2020-12-22 | 2021-04-13 | 中船重工龙江广瀚燃气轮机有限公司 | Blade liquid shot blasting control method |
| CN113063690A (en) * | 2021-04-12 | 2021-07-02 | 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 |
| 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 |
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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 |
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Cited By (10)
| 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 |
| CN110760658A (en) * | 2019-11-29 | 2020-02-07 | 中国航发中传机械有限公司 | Method for shot peening strengthening of tooth surface of spiral bevel gear |
| 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 |
| CN112643554A (en) * | 2020-12-22 | 2021-04-13 | 中船重工龙江广瀚燃气轮机有限公司 | Blade liquid shot blasting control method |
| 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 |
| CN113063690A (en) * | 2021-04-12 | 2021-07-02 | 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 |
| 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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| CN105500216B (en) | 2017-09-12 |
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