CN103133413A - Engine blower multilayer receiver structure - Google Patents
Engine blower multilayer receiver structure Download PDFInfo
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- CN103133413A CN103133413A CN2011103798664A CN201110379866A CN103133413A CN 103133413 A CN103133413 A CN 103133413A CN 2011103798664 A CN2011103798664 A CN 2011103798664A CN 201110379866 A CN201110379866 A CN 201110379866A CN 103133413 A CN103133413 A CN 103133413A
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- receiver
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- chamber casing
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- multilayer
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Abstract
The invention provides an engine blower multilayer receiver structure which comprises a front installation side, a rear installation side, a receiver shell body, a stator blade, an inner ring, an interlayer, a receiver shell body inner layer and a receiver shell body outer layer, wherein the front installation side and the rear installation side are connected with receivers at front and rear of a blower receiver, and the inner surface of the receiver shell body and the inner surfaces of the receivers at the front and the rear of the blower receiver commonly form a passageway of an engine. The receiver shell body is composed of 3-6 layers, the receiver shell body outer layer is a common receiver metal matrix, namely titanium alloy or steel, the interlayer is made of single-layer nonmetal materials or multilayer composite materials, and the receiver shell body inner layer is made of aluminum alloy or titanium alloy. By matching and combing of different materials of the multilayer receiver shell body, under the premise that enough containment of an engine blower receiver is ensured, the engine blower multilayer receiver structure reduces weight of the blower receiver, solves the problem that a single-layer receiver is poor in containment and a double-layer receiver is heavy in an existing airplane engine blower receiver, and combines the advantages that the single-layer receiver is light and the double-layer receiver is good in containment.
Description
Technical field
The present invention relates to airplane engine fancase structural design field, particularly a kind of engine blower multilayer case structure.
Background technique
The fancase of some airplane engines adopts the single-layer metal structure, and the outside increases reinforcing rib structure sometimes, and the casing containment of this structure is very poor, and fan blade is larger simultaneously, after the fan blade fracture, easily punches fancase, jeopardizes the safety of aircraft.Other aircrafts are to guarantee that fancase has enough containments, be designed to double layer construction more, wherein one deck is metal, bears the load of motor, another the layer or be light-weight metal, be perhaps nonmetallic material, play the effect of containing blade, in this structure, for guaranteeing enough containments, light-weight metal and nonmetallic material are usually thicker, and weight is larger.
Summary of the invention
The objective of the invention is for realize having higher containment, the target of airplane engine fancase that weight is lighter, the spy provides a kind of engine blower multilayer case structure.
The invention provides a kind of engine blower multilayer case structure, it is characterized in that: described engine blower multilayer case structure comprises front mounting edge 1, rear mounting edge 2, wheel chamber casing 3, stator blade 4, interior ring 5, interlayer 6, wheel chamber casing internal layer 7, wheel chamber casing skin 8;
Wherein: front mounting edge 1, rear mounting edge 2 are connected with casing before and after fancase, casing internal surface before and after wheel chamber casing 3 internal surfaces and fancase forms the runner of motor jointly, wheel chamber casing 3 forms for the 3-6 layer, wheel chamber casing outer 8 is specially titanium alloy or steel for common casing metallic matrix, with bearing load, interlayer 6 is individual layer nonmetallic material or multilayer materials, guarantee that it has higher tensility, and wheel chamber casing internal layer 7 is aluminum alloy or titanium alloy, coordinate different shell constructions, reach the lightest structure purpose.
The multilayer shell of described wheel chamber casing 3 connects by modes such as welding, assemblings, and wherein welding manner is applicable to the situation that wheel chamber casing outer 8 and wheel chamber casing internal layer 7 are all titanium alloy, and this mode connects reliably, and weight is lighter;
The assembling mode is applicable to the situation that internal and external layer is different materials, be specially wheel chamber casing outer 8 and be steel, wheel chamber casing internal layer 7 is titanium alloy or aluminum alloy, or wheel chamber casing outer 8 is titanium alloy, wheel chamber casing internal layer 7 is aluminum alloy, this mode does not have welding deformation, and the different materials collocation can reduce weight, the requirement of the different motors of adaptation equally.
Advantage of the present invention:
The present invention is by different material adapted and the combinations of multilayer wheel chamber casing, can guarantee that the airplane engine fancase has under enough containment prerequisites, reduce the weight of fancase, solve the heavier problem of the poor and double-deck casing of individual layer casing containment in existing airplane engine fancase, had the lighter and good advantage of double-deck casing containment of individual layer casing concurrently.
Description of drawings
The present invention is further detailed explanation below in conjunction with drawings and the embodiments:
Fig. 1 is airplane engine fancase schematic diagram;
Fig. 2 is embodiment's one schematic diagram;
Fig. 3 is embodiment's two schematic diagram.
Embodiment
Embodiment 1
Fancase embodiment 1 of the present invention as shown in Figure 2.
Fancase comprises the front mounting edge 1 of front side, and the rear mounting edge 2 of rear side has welded wheel chamber casing internal layer 7 and wheel chamber casing skin 8 between front mounting edge 1 and rear mounting edge 2, be equipped with interlayer 6 between wheel chamber casing internal layer 7 and wheel chamber casing skin 8.Be fixed with stator blade 4 and interior ring 5 on wheel chamber casing.
The material of fancase consists of: front mounting edge 1, rear mounting edge 2, stator blade 4, interior ring 5, wheel chamber casing internal layer 7 and wheel chamber casing skin 8 are titanium alloy, guarantee that fancase has enough intensity, and weight is lighter simultaneously; Interlayer 6 guarantees that for Kev draws fancase has enough containments.
Fancase comprises the wheel chamber casing skin 10 with front mounting edge and rear mounting edge, assembled the wheel chamber casing internal layer 9 with front mounting edge on the front mounting edge of wheel chamber casing skin 10, be equipped with interlayer 6 between wheel chamber casing internal layer 9 and wheel chamber casing skin 10.Be fixed with stator blade 4 and interior ring 5 on wheel chamber casing skin 10.
The material of fancase consists of: wheel chamber casing skin 10, stator blade 4 and interior ring 5 are titanium alloy, guarantee that fancase has enough intensity, and weight is lighter simultaneously; Interlayer 6 guarantees that for Kev draws fancase has enough containments, and 9 of wheel chamber casing internal layers have been selected aluminum alloy, have further reduced the weight of fancase.
Claims (2)
1. engine blower multilayer case structure, it is characterized in that: described engine blower multilayer case structure comprises front mounting edge (1), rear mounting edge (2), wheel chamber casing (3), stator blade (4), interior ring (5), interlayer (6), wheel chamber casing internal layer (7), wheel chamber casing outer (8);
Wherein: front mounting edge (1), rear mounting edge (2) are connected with casing before and after fancase, casing internal surface before and after wheel chamber casing (3) internal surface and fancase forms the runner of motor jointly, wheel chamber casing (3) forms for the 3-6 layer, wheel chamber casing outer (8) is specially titanium alloy or steel for common casing metallic matrix, interlayer (6) is individual layer nonmetallic material or multilayer materials, and wheel chamber casing internal layer (7) is aluminum alloy or titanium alloy.
2. according to engine blower multilayer case structure claimed in claim 1, it is characterized in that: the multilayer shell of described wheel chamber casing (3) connects by modes such as welding, assemblings, and wherein welding manner is applicable to the situation that wheel chamber casing skin (8) and wheel chamber casing internal layer (7) are all titanium alloy;
The assembling mode is applicable to the situation that internal and external layer is different materials, and being specially wheel chamber casing skin (8) is steel, and wheel chamber casing internal layer (7) is titanium alloy or aluminum alloy, or wheel chamber casing outer (8) is titanium alloy, and wheel chamber casing internal layer (7) is aluminum alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103798664A CN103133413A (en) | 2011-11-25 | 2011-11-25 | Engine blower multilayer receiver structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103798664A CN103133413A (en) | 2011-11-25 | 2011-11-25 | Engine blower multilayer receiver structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103133413A true CN103133413A (en) | 2013-06-05 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011103798664A Pending CN103133413A (en) | 2011-11-25 | 2011-11-25 | Engine blower multilayer receiver structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN103133413A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107762568A (en) * | 2017-09-30 | 2018-03-06 | 中国航发沈阳发动机研究所 | Weld the fancase formed |
| CN108388701A (en) * | 2018-01-30 | 2018-08-10 | 南京理工大学 | A kind of ballistic limit computational methods of gapless double-level-metal casing |
| CN111577463A (en) * | 2020-05-25 | 2020-08-25 | 中国航发沈阳发动机研究所 | Engine air inlet casing structure |
| CN112280328A (en) * | 2019-07-24 | 2021-01-29 | 中国航发商用航空发动机有限责任公司 | Engine fan containing casing and preparation method thereof |
| CN114483306A (en) * | 2020-11-13 | 2022-05-13 | 中国航发商用航空发动机有限责任公司 | Fan containing casing and aircraft engine |
| CN115870702A (en) * | 2022-12-07 | 2023-03-31 | 中国航发动力股份有限公司 | Machining method for ensuring width of flow channel of inner sleeve of casing |
| CN115870702B (en) * | 2022-12-07 | 2024-04-30 | 中国航发动力股份有限公司 | Machining method for guaranteeing width of inner sleeve runner of casing |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5308225A (en) * | 1991-01-30 | 1994-05-03 | United Technologies Corporation | Rotor case treatment |
| GB2361032A (en) * | 2000-04-05 | 2001-10-10 | Rolls Royce Plc | A gas turbine engine blade containment assembly |
| CN1923615A (en) * | 2006-09-27 | 2007-03-07 | 北京航空航天大学 | Fibre-reinforced metal/ceramic sheet-like composite containment casing |
| CN101457771A (en) * | 2007-12-14 | 2009-06-17 | 斯奈克玛 | Abradable support panel in a turbine engine |
| CN202483952U (en) * | 2011-11-25 | 2012-10-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Engine fan multilayer casing structure |
-
2011
- 2011-11-25 CN CN2011103798664A patent/CN103133413A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5308225A (en) * | 1991-01-30 | 1994-05-03 | United Technologies Corporation | Rotor case treatment |
| GB2361032A (en) * | 2000-04-05 | 2001-10-10 | Rolls Royce Plc | A gas turbine engine blade containment assembly |
| CN1923615A (en) * | 2006-09-27 | 2007-03-07 | 北京航空航天大学 | Fibre-reinforced metal/ceramic sheet-like composite containment casing |
| CN101457771A (en) * | 2007-12-14 | 2009-06-17 | 斯奈克玛 | Abradable support panel in a turbine engine |
| CN202483952U (en) * | 2011-11-25 | 2012-10-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Engine fan multilayer casing structure |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107762568A (en) * | 2017-09-30 | 2018-03-06 | 中国航发沈阳发动机研究所 | Weld the fancase formed |
| CN108388701A (en) * | 2018-01-30 | 2018-08-10 | 南京理工大学 | A kind of ballistic limit computational methods of gapless double-level-metal casing |
| CN108388701B (en) * | 2018-01-30 | 2021-09-03 | 南京理工大学 | Ballistic limit calculation method of gapless double-layer metal casing |
| CN112280328A (en) * | 2019-07-24 | 2021-01-29 | 中国航发商用航空发动机有限责任公司 | Engine fan containing casing and preparation method thereof |
| CN112280328B (en) * | 2019-07-24 | 2022-07-12 | 中国航发商用航空发动机有限责任公司 | Engine fan containing casing and preparation method thereof |
| CN111577463A (en) * | 2020-05-25 | 2020-08-25 | 中国航发沈阳发动机研究所 | Engine air inlet casing structure |
| CN111577463B (en) * | 2020-05-25 | 2021-08-17 | 中国航发沈阳发动机研究所 | Engine air inlet casing structure |
| CN114483306A (en) * | 2020-11-13 | 2022-05-13 | 中国航发商用航空发动机有限责任公司 | Fan containing casing and aircraft engine |
| CN114483306B (en) * | 2020-11-13 | 2023-09-01 | 中国航发商用航空发动机有限责任公司 | Fan containing casing and aeroengine |
| CN115870702A (en) * | 2022-12-07 | 2023-03-31 | 中国航发动力股份有限公司 | Machining method for ensuring width of flow channel of inner sleeve of casing |
| CN115870702B (en) * | 2022-12-07 | 2024-04-30 | 中国航发动力股份有限公司 | Machining method for guaranteeing width of inner sleeve runner of casing |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Liu Yongquan Inventor after: Ding Quan Inventor after: Wang Yamou Inventor after: Liang Mingjie Inventor after: Gang Tie Inventor before: Ding Quan Inventor before: Wang Yamou Inventor before: Liang Mingjie Inventor before: Gang Tie |
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| COR | Change of bibliographic data | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20130605 |