CN103639101A - Method for coating abradable coating of composite containing ring of aircraft engine - Google Patents
Method for coating abradable coating of composite containing ring of aircraft engine Download PDFInfo
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- CN103639101A CN103639101A CN201310575013.7A CN201310575013A CN103639101A CN 103639101 A CN103639101 A CN 103639101A CN 201310575013 A CN201310575013 A CN 201310575013A CN 103639101 A CN103639101 A CN 103639101A
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Abstract
The invention belongs to a surface processing technology and relates to a method for coating an abradable coating of a composite containing ring of an aircraft engine. The method for coating the abradable coating (3) is characterized by including the following steps that a surface is cleaned; prime paint of the abradable coating is prepared; surface course paint of the abradable coating is prepared; the abradable coating is coated with the prime paint; the abradable coating is coated with the surface course paint; solidification is performed; turning is performed. According to the method for coating the abradable coating of the composite contaiing ring of the aircraft engine, the manufacturing cost of a fan casing assembly is greatly reduced.
Description
Technical field
The invention belongs to process for treating surface, relate to the painting method that a kind of aero-engine composite contains ring abradable coating.
Background technology
The structure of certain novel aerial engine fan casing assembly, referring to Fig. 1, has increased composite and has contained ring 2 in aerial engine fan casing assembly, and it is connected to integral body by bonding with casing 1.The sealing of obturaging between casing 1 and fan blade always is the key technology of engine design and manufacture, because this material should play the effect of the sealing of obturaging, can't cause damage to fan blade simultaneously.At military aero-engine fancase inner surface, conventionally adopt hot-spraying coating to realize the manufacture of this seal coating of obturaging, but hot-spraying coating cost is high, needs large-scale professional thermal spraying apparatus and expensive dusty spray material.Meanwhile, encircle high-temperature resistant and be not more than 120 ℃, and hot-spraying technique generally all can reach thousands of degrees Celsius because composite contains, therefore, hot-spraying technique also cannot be realized the coating that composite contains ring abradable coating.
Summary of the invention
The object of the invention is: propose the painting method that a kind of aero-engine composite contains ring abradable coating, propose first and realized the coating that aero-engine composite contains ring abradable coating, having avoided abradable coating coating composite to be contained to the impact of ring material; Also significantly reduced economically the manufacturing cost of fancase assembly.
Technical scheme of the present invention is: aero-engine composite contains the painting method of ring abradable coating, composite in fancase assembly contains the surperficial abradable coating 3 that applies of obturaging of ring 2, and composite contains ring 2 and is connected to integral body by bonding with casing 1; It is characterized in that, the step that applies abradable coating 3 is as follows:
1, removing surface: fancase component level is placed on rotary tooling, the front port that in fancase assembly, casing 1 internal diameter is larger is towards operator, then, ring 2 surfaces are contained with the cloth wiping composite that is moistened with alcohol or acetone in the surface of obturaging of containing ring 2 at composite, remove surperficial grease;
2, preparation abradable coating subbing: the formula of abradable coating subbing is: many amine curing agents account for 10%～20% of abradable coating subbing weight, and surplus is rubber modified epoxy resin; The compound method of abradable coating subbing is: after two kinds of raw materials of abradable coating subbing are weighed in proportion, put into container, use mechanical agitator to stir 10min～20min; Many amine curing agents are: diethylenetriamine or triethylene tetramine.
3, preparation abradable coating investment precoat: the formula of abradable coating investment precoat is: many amine curing agents account for 5%～15% of abradable coating investment precoat weight, talcum powder accounts for 50%～58% of abradable coating investment precoat weight, and surplus is the epoxy resin below epoxide equivalent 4000g/mol; Abradable coating investment precoat compound method be: after three kinds of raw materials of abradable coating investment precoat are weighed in proportion, put into container, use mechanical agitator to stir 10min～20min;
4, coating abradable coating subbing: contain the surface coating abradable coating subbing of obturaging of ring 2 with scraper to composite, the coating thickness of abradable coating subbing is 0.2mm～0.4mm, and the time interval that abradable coating subbing is accomplished to coating from preparation is not more than 30min;
5, coating abradable coating investment precoat: divide coating abradable coating investment precoat three times with the surface that scraper contains the abradable coating subbing of obturaging surperficial of ring 2 to composite, the coating thickness of ground floor abradable coating investment precoat is 0.5mm～1mm, the coating thickness of second layer abradable coating investment precoat is 1mm～1.5mm, and the gross thickness of abradable coating investment precoat is 3mm～3.5mm; From abradable coating investment precoat preparation, being accomplished to three layers of abradable coating investment precoat applies the complete time and is not more than 40min;
6, solidifying of abradable coating: by fancase assembly natural drying 24h～48h at room temperature;
7, Vehicle Processing composite contains the ring 2 surperficial abradable coating 3 of obturaging: adopt lathe machining composite material to contain the ring 2 surperficial abradable coating 3 of obturaging, machined parameters is: rotating speed (30～50) r/min, the amount of feeding (0.3～0.8) mm/r, until meet the size of drawing regulation.
Advantage of the present invention is: proposed the painting method that a kind of aero-engine composite contains ring abradable coating, realized and met the coating that aero-engine composite contains the tight surperficial room temperature curing type abradable coating of ring seal, avoided abradable coating to apply the impact of composite being contained to ring material; Also significantly reduced economically the manufacturing cost of fancase assembly.
Accompanying drawing explanation
Fig. 1 is the structural representation of certain novel aerial engine fan casing assembly.
The specific embodiment
Below the present invention is described in further details.Referring to Fig. 1, aero-engine composite contains the painting method of ring abradable coating, and the composite in fancase assembly contains the surperficial abradable coating 3 that applies of obturaging of ring 2, and composite contains ring 2 and is connected to integral body by bonding with casing 1; It is characterized in that, the step that applies abradable coating 3 is as follows:
1, removing surface: fancase component level is placed on rotary tooling, the front port that in fancase assembly, casing 1 internal diameter is larger is towards operator, then, ring 2 surfaces are contained with the cloth wiping composite that is moistened with alcohol or acetone in the surface of obturaging of containing ring 2 at composite, remove surperficial grease;
2, preparation abradable coating subbing: the formula of abradable coating subbing is: many amine curing agents account for 10%～20% of abradable coating subbing weight, and surplus is rubber modified epoxy resin; The compound method of abradable coating subbing is: after two kinds of raw materials of abradable coating subbing are weighed in proportion, put into container, use mechanical agitator to stir 10min～20min; Many amine curing agents are: diethylenetriamine or triethylene tetramine.
3, preparation abradable coating investment precoat: the formula of abradable coating investment precoat is: many amine curing agents account for 5%～15% of abradable coating investment precoat weight, talcum powder accounts for 50%～58% of abradable coating investment precoat weight, and surplus is the epoxy resin below epoxide equivalent 4000g/mol; Abradable coating investment precoat compound method be: after three kinds of raw materials of abradable coating investment precoat are weighed in proportion, put into container, use mechanical agitator to stir 10min～20min;
4, coating abradable coating subbing: contain the surface coating abradable coating subbing of obturaging of ring 2 with scraper to composite, the coating thickness of abradable coating subbing is 0.2mm～0.4mm, and the time interval that abradable coating subbing is accomplished to coating from preparation is not more than 30min;
5, coating abradable coating investment precoat: divide coating abradable coating investment precoat three times with the surface that scraper contains the abradable coating subbing of obturaging surperficial of ring 2 to composite, the coating thickness of ground floor abradable coating investment precoat is 0.5mm～1mm, the coating thickness of second layer abradable coating investment precoat is 1mm～1.5mm, and the gross thickness of abradable coating investment precoat is 3mm～3.5mm; From abradable coating investment precoat preparation, being accomplished to three layers of abradable coating investment precoat applies the complete time and is not more than 40min;
6, solidifying of abradable coating: by fancase assembly natural drying 24h～48h at room temperature;
7, Vehicle Processing composite contains the ring 2 surperficial abradable coating 3 of obturaging: adopt lathe machining composite material to contain the ring 2 surperficial abradable coating 3 of obturaging, machined parameters is: rotating speed (30～50) r/min, the amount of feeding (0.3～0.8) mm/r, until meet the size of drawing regulation.
Operation principle of the present invention is: composite contains ring and is bonded in fancase inner surface, because not possessing, this containing ring can not wear away function, therefore, at composite, contain ring and to mill region, must apply one deck abradable coating with fan blade and just can play the effect of sealing of obturaging, and fan blade is extended and the composite of injuring contains ring while preventing aero-engine work.
1, removing surface: fancase component level is placed on rotary tooling, the front port that in fancase assembly, casing 1 internal diameter is larger is towards operator, then, ring 2 surfaces are contained with dipping in spirituous cloth wiping composite in the surface of obturaging of containing ring 2 at composite, remove surperficial grease;
2, preparation abradable coating subbing: the formula of abradable coating subbing is: many amine curing agents account for 10% of abradable coating subbing weight, and surplus is rubber modified epoxy resin; The compound method of abradable coating subbing is: after two kinds of raw materials of abradable coating subbing are weighed in proportion, put into container, use mechanical agitator to stir 10min; Many amine curing agents are: diethylenetriamine.
3, preparation abradable coating investment precoat: the formula of abradable coating investment precoat is: many amine curing agents account for 5% of abradable coating investment precoat weight, talcum powder accounts for 50% of abradable coating investment precoat weight, and surplus is the epoxy resin below epoxide equivalent 4000g/mol; Abradable coating investment precoat compound method be: after three kinds of raw materials of abradable coating investment precoat are weighed in proportion, put into container, use mechanical agitator to stir 10min;
4, coating abradable coating subbing: contain the surface coating abradable coating subbing of obturaging of ring 2 with scraper to composite, the coating thickness of abradable coating subbing is 0.2mm, and abradable coating subbing is accomplished to the time interval 20min of coating from preparation;
5, coating abradable coating investment precoat: divide coating abradable coating investment precoat three times with the surface that scraper contains the abradable coating subbing of obturaging surperficial of ring 2 to composite, the coating thickness of ground floor abradable coating investment precoat is 0.5mm, the coating thickness of second layer abradable coating investment precoat is 1mm, and the gross thickness of abradable coating investment precoat is 3mm; From abradable coating investment precoat preparation, being accomplished to three layers of abradable coating investment precoat, to apply the complete time be 30min;
6, solidifying of abradable coating: by fancase assembly natural drying 24h at room temperature;
7, Vehicle Processing composite contains the ring 2 surperficial abradable coating 3 of obturaging: adopt lathe machining composite material to contain the ring 2 surperficial abradable coating 3 of obturaging, machined parameters is: rotating speed 30r/min, amount of feeding 0.3mm/r, until meet the size of drawing regulation.
1, removing surface: fancase component level is placed on rotary tooling, the front port that in fancase assembly, casing 1 internal diameter is larger is towards operator, then, ring 2 surfaces are contained with the cloth wiping composite that is moistened with acetone in the surface of obturaging of containing ring 2 at composite, remove surperficial grease;
2, preparation abradable coating subbing: the formula of abradable coating subbing is: many amine curing agents account for 15% of abradable coating subbing weight, and surplus is rubber modified epoxy resin; The compound method of abradable coating subbing is: after two kinds of raw materials of abradable coating subbing are weighed in proportion, put into container, use mechanical agitator to stir 15min; Many amine curing agents are: diethylenetriamine.
3, preparation abradable coating investment precoat: the formula of abradable coating investment precoat is: many amine curing agents account for 10% of abradable coating investment precoat weight, talcum powder accounts for 54% of abradable coating investment precoat weight, and surplus is the epoxy resin below epoxide equivalent 4000g/mol; Abradable coating investment precoat compound method be: after three kinds of raw materials of abradable coating investment precoat are weighed in proportion, put into container, use mechanical agitator to stir 15min;
4, coating abradable coating subbing: contain the surface coating abradable coating subbing of obturaging of ring 2 with scraper to composite, the coating thickness of abradable coating subbing is 0.3mm, and the time interval that abradable coating subbing is accomplished to coating from preparation is 25min;
5, coating abradable coating investment precoat: divide coating abradable coating investment precoat three times with the surface that scraper contains the abradable coating subbing of obturaging surperficial of ring 2 to composite, the coating thickness of ground floor abradable coating investment precoat is 0.75mm, the coating thickness of second layer abradable coating investment precoat is 1.25mm, and the gross thickness of abradable coating investment precoat is 3.25mm; From abradable coating investment precoat preparation, being accomplished to three layers of abradable coating investment precoat, to apply the complete time be 35min;
6, solidifying of abradable coating: by fancase assembly natural drying 36h at room temperature;
7, Vehicle Processing composite contains the ring 2 surperficial abradable coating 3 of obturaging: adopt lathe machining composite material to contain the ring 2 surperficial abradable coating 3 of obturaging, machined parameters is: rotating speed 40r/min, amount of feeding 0.5mm/r, until meet the size of drawing regulation.
1, removing surface: fancase component level is placed on rotary tooling, the front port that in fancase assembly, casing 1 internal diameter is larger is towards operator, then, ring 2 surfaces are contained with the cloth wiping composite that is moistened with alcohol or acetone in the surface of obturaging of containing ring 2 at composite, remove surperficial grease;
2, preparation abradable coating subbing: the formula of abradable coating subbing is: many amine curing agents account for 20% of abradable coating subbing weight, and surplus is rubber modified epoxy resin; The compound method of abradable coating subbing is: after two kinds of raw materials of abradable coating subbing are weighed in proportion, put into container, use mechanical agitator to stir 20min; Many amine curing agents are: triethylene tetramine.
3, preparation abradable coating investment precoat: the formula of abradable coating investment precoat is: many amine curing agents account for 15% of abradable coating investment precoat weight, talcum powder accounts for 58% of abradable coating investment precoat weight, and surplus is the epoxy resin below epoxide equivalent 4000g/mol; Abradable coating investment precoat compound method be: after three kinds of raw materials of abradable coating investment precoat are weighed in proportion, put into container, use mechanical agitator to stir 20min;
4, coating abradable coating subbing: contain the surface coating abradable coating subbing of obturaging of ring 2 with scraper to composite, the coating thickness of abradable coating subbing is 0.4mm, and the time interval that abradable coating subbing is accomplished to coating from preparation is 30min;
5, coating abradable coating investment precoat: divide coating abradable coating investment precoat three times with the surface that scraper contains the abradable coating subbing of obturaging surperficial of ring 2 to composite, the coating thickness of ground floor abradable coating investment precoat is 1mm, the coating thickness of second layer abradable coating investment precoat is 1.5mm, and the gross thickness of abradable coating investment precoat is 3.5mm; From abradable coating investment precoat preparation, being accomplished to three layers of abradable coating investment precoat, to apply the complete time be 40min;
6, solidifying of abradable coating: by fancase assembly natural drying 48h at room temperature;
7, Vehicle Processing composite contains the ring 2 surperficial abradable coating 3 of obturaging: adopt lathe machining composite material to contain the ring 2 surperficial abradable coating 3 of obturaging, machined parameters is: rotating speed 50r/min, amount of feeding 0.8mm/r, until meet the size of drawing regulation.
Claims (1)
1. aero-engine composite contains the painting method of ring abradable coating, composite in fancase assembly contains the surperficial abradable coating (3) that applies of obturaging of ring (2), and composite contains ring (2) and is connected to integral body by bonding with casing (1); It is characterized in that, the step that applies abradable coating (3) is as follows:
1.1, removing surface: fancase component level is placed on rotary tooling, the larger front port of casing in fancase assembly (1) internal diameter is towards operator, then, ring (2) surface is contained with the cloth wiping composite that is moistened with alcohol or acetone in the surface of obturaging of containing ring (2) at composite, removes surperficial grease;
1.2, preparation abradable coating subbing: the formula of abradable coating subbing is: many amine curing agents account for 10%～20% of abradable coating subbing weight, and surplus is rubber modified epoxy resin; The compound method of abradable coating subbing is: after two kinds of raw materials of abradable coating subbing are weighed in proportion, put into container, use mechanical agitator to stir 10min～20min; Many amine curing agents are:
1.3, preparation abradable coating investment precoat: the formula of abradable coating investment precoat is: many amine curing agents account for 5%～15% of abradable coating investment precoat weight, talcum powder accounts for 40%～50% of abradable coating investment precoat weight, and surplus is the epoxy resin below epoxide equivalent 4000g/mol; Abradable coating investment precoat compound method be: after three kinds of raw materials of abradable coating investment precoat are weighed in proportion, put into container, use mechanical agitator to stir 10min～20min;
1.4, coating abradable coating subbing: contain the surface coating abradable coating subbing of obturaging of ring (2) with scraper to composite, the coating thickness of abradable coating subbing is 0.2mm～0.4mm, and the time interval that abradable coating subbing is accomplished to coating from preparation is not more than 30min;
1.5, coating abradable coating investment precoat: divide coating abradable coating investment precoat three times with the surface that scraper contains the abradable coating subbing of obturaging surperficial of ring (2) to composite, the coating thickness of ground floor abradable coating investment precoat is 0.5mm～1mm, the coating thickness of second layer abradable coating investment precoat is 1mm～1.5mm, and the gross thickness of abradable coating investment precoat is 3mm～3.5mm; From abradable coating investment precoat preparation, being accomplished to three layers of abradable coating investment precoat applies the complete time and is not more than 40min;
1.6, solidifying of abradable coating: by fancase assembly natural drying 24h～48h at room temperature;
1.7, Vehicle Processing composite contains ring (2) the surperficial abradable coating (3) of obturaging: adopt lathe machining composite material to contain ring (2) the surperficial abradable coating (3) of obturaging, machined parameters is: rotating speed (30～50) r/min, the amount of feeding (0.3～0.8) mm/r, until meet the size of drawing regulation.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104327754A (en) * | 2014-10-28 | 2015-02-04 | 西安航空动力股份有限公司 | Glued joint process of glass bead filled silicon rubber abrasive material |
| CN106497334A (en) * | 2016-11-17 | 2017-03-15 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN106497335A (en) * | 2016-11-17 | 2017-03-15 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN106513288A (en) * | 2016-11-17 | 2017-03-22 | 无锡明盛纺织机械有限公司 | Anti-corrosion and anti-abrasion method of hydraulic turbine blade organic coating |
| CN106752224A (en) * | 2016-11-17 | 2017-05-31 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN106752675A (en) * | 2016-11-17 | 2017-05-31 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN106752674A (en) * | 2016-11-17 | 2017-05-31 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN108150650A (en) * | 2017-12-06 | 2018-06-12 | 中国航发动力股份有限公司 | A kind of abnormity window suppresses encapsulating method |
| CN110982388A (en) * | 2020-01-02 | 2020-04-10 | 中国科学院兰州化学物理研究所 | Room-temperature curing coating with abradable sealing function and preparation method thereof |
| CN113803162A (en) * | 2020-06-16 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Fan containing casing and aircraft engine |
| CN114100999A (en) * | 2021-11-12 | 2022-03-01 | 西安交通大学 | Wearable sealing coating with complete closed pore structure and preparation method thereof |
| CN115352102A (en) * | 2022-07-29 | 2022-11-18 | 中国航发沈阳发动机研究所 | Manufacturing method of composite material containing ring for engine case and engine case |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1803953A (en) * | 2005-12-26 | 2006-07-19 | 中国化工建设总公司常州涂料化工研究院 | Matched coating for aluminium alloy base material |
| DE102006009345A1 (en) * | 2006-03-01 | 2007-09-06 | Man Nutzfahrzeuge Ag | Production of joint between fiber-reinforced synthetic cladding component and cladding support for interior area of motor vehicle, involves intermeshing joint surface of component with joint surface of support during pultrusion of component |
| CN101723086A (en) * | 2009-11-16 | 2010-06-09 | 浙江大学 | Containing ring of aircraft engine fan made of fiber-reinforced composite material |
| CN102224208A (en) * | 2008-11-26 | 2011-10-19 | 迈图特种化工有限公司 | Coated reinforcement and method for producing same |
| CN102627901A (en) * | 2012-03-20 | 2012-08-08 | 中国科学院金属研究所 | Chromium-free nanocomposite epoxy aircraft paint and preparation method thereof |
-
2013
- 2013-11-15 CN CN201310575013.7A patent/CN103639101B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1803953A (en) * | 2005-12-26 | 2006-07-19 | 中国化工建设总公司常州涂料化工研究院 | Matched coating for aluminium alloy base material |
| DE102006009345A1 (en) * | 2006-03-01 | 2007-09-06 | Man Nutzfahrzeuge Ag | Production of joint between fiber-reinforced synthetic cladding component and cladding support for interior area of motor vehicle, involves intermeshing joint surface of component with joint surface of support during pultrusion of component |
| CN102224208A (en) * | 2008-11-26 | 2011-10-19 | 迈图特种化工有限公司 | Coated reinforcement and method for producing same |
| CN101723086A (en) * | 2009-11-16 | 2010-06-09 | 浙江大学 | Containing ring of aircraft engine fan made of fiber-reinforced composite material |
| CN102627901A (en) * | 2012-03-20 | 2012-08-08 | 中国科学院金属研究所 | Chromium-free nanocomposite epoxy aircraft paint and preparation method thereof |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104327754A (en) * | 2014-10-28 | 2015-02-04 | 西安航空动力股份有限公司 | Glued joint process of glass bead filled silicon rubber abrasive material |
| CN106752674A (en) * | 2016-11-17 | 2017-05-31 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN106497335A (en) * | 2016-11-17 | 2017-03-15 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN106513288A (en) * | 2016-11-17 | 2017-03-22 | 无锡明盛纺织机械有限公司 | Anti-corrosion and anti-abrasion method of hydraulic turbine blade organic coating |
| CN106752224A (en) * | 2016-11-17 | 2017-05-31 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN106752675A (en) * | 2016-11-17 | 2017-05-31 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN106497334A (en) * | 2016-11-17 | 2017-03-15 | 无锡明盛纺织机械有限公司 | A kind of turbine blade modified epoxy multicoat anticorrosion abrasionproof etching method |
| CN108150650A (en) * | 2017-12-06 | 2018-06-12 | 中国航发动力股份有限公司 | A kind of abnormity window suppresses encapsulating method |
| CN110982388A (en) * | 2020-01-02 | 2020-04-10 | 中国科学院兰州化学物理研究所 | Room-temperature curing coating with abradable sealing function and preparation method thereof |
| CN110982388B (en) * | 2020-01-02 | 2021-06-01 | 中国科学院兰州化学物理研究所 | Room-temperature curing coating with abradable sealing function and preparation method thereof |
| CN113803162A (en) * | 2020-06-16 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Fan containing casing and aircraft engine |
| CN113803162B (en) * | 2020-06-16 | 2023-02-28 | 中国航发商用航空发动机有限责任公司 | Fan containing casing and aircraft engine |
| CN114100999A (en) * | 2021-11-12 | 2022-03-01 | 西安交通大学 | Wearable sealing coating with complete closed pore structure and preparation method thereof |
| CN115352102A (en) * | 2022-07-29 | 2022-11-18 | 中国航发沈阳发动机研究所 | Manufacturing method of composite material containing ring for engine case and engine case |
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| CN103639101B (en) | 2014-12-10 |
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