CN203702263U - Composite stator blade of engine - Google Patents
Composite stator blade of engine Download PDFInfo
- Publication number
- CN203702263U CN203702263U CN201320805917.XU CN201320805917U CN203702263U CN 203702263 U CN203702263 U CN 203702263U CN 201320805917 U CN201320805917 U CN 201320805917U CN 203702263 U CN203702263 U CN 203702263U
- Authority
- CN
- China
- Prior art keywords
- blade
- engine
- stator blade
- edge plate
- blade body
- 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
Abstract
The utility model discloses a composite stator blade of an engine. The composite stator blade comprises a blade body, an upper edge plate, a lower edge plate, a skin, a nickel front edge covered edge and metal linings, wherein the blade body is made of pre-impregnated carbon cloth, the upper edge plate is provided with installation holes which are connected with an engine crankcase, the skin which is made of pre-impregnated glass cloth is coated out of the blade body, the upper edge plate, the lower edge plate and the installation holes, the nickel front edge covered edge is fixedly arranged at the front edge part of the blade body in a cementing way, and the metal linings are embedded in the installation holes of the upper edge plate. The composite stator blade disclosed by the utility model has the advantages that the specific strength is high, the rigidity is high, the high temperature resisting capacity is strong, the weight is light, the impact resistance and the crushing resistance are strong, the performance requirement of the stator blade is met, the service life is long, the efficiency of the engine is greatly increased, and the oil consumption of the engine is reduced.
Description
Technical field
The utility model relates to a kind of stator blade of motor.
Background technique
The stator blade of existing motor is to be all made up of metallic material, adopts stainless steel 1Cr11Ni2W2MoV, nickel alloy and titanium alloy, adopts that milling, die-cut, roughing, heat treatment, throwing are repaiied, finish rolling, the technique such as heat treatment and cut-out completes again.Although stainless steel 1Cr11Ni2W2MoV, nickel alloy and titanium alloy still have the leeway of its intensity of further raising, rigidity and resistant to elevated temperatures performance, its development potentiality is limited, is difficult to meet the harsher temperature of following aeroengine and weight requirement.Along with improving constantly of aero-engine performance, particularly weight constantly alleviates, to more and more depend on high specific strength, low density, the advanced material that high rigidity and heat-resisting ability are strong, as the composite material of preimpregnation carbon cloth and preimpregnation glass cloth, but little due to the impact resistance nickel alloy relative to crushing resistance of preimpregnation carbon cloth and the composite material of preimpregnation glass cloth and titanium alloy material, so, as the stator blade that adopts the composite material of preimpregnation carbon cloth and preimpregnation glass cloth to make, it easily causes blade breakage under airflow scouring, especially blade inlet edge part, easily wear and tear in blades installation hole place, it is large that position, hole becomes, installation stationarity is poor.
Summary of the invention
The purpose of this utility model solves the above-mentioned problems in the prior art exactly, provides a kind of specific strength high, and specific stiffness is high, and heat-resisting ability is strong, lightweight, and impact resistance and the also composite material stator blade of very strong motor of crushing resistance.
For achieving the above object, technical solution of the present utility model is: a kind of composite material stator blade of motor, and it comprises the blade of being made up of preimpregnation carbon cloth, upper and lower listrium, covering, nickel leading edge bound edge and metal lining; On supramarginal plate, have the mounting hole being connected with engine crankcase, the covering of being made up of preimpregnation glass cloth is wrapped in outside blade, upper and lower listrium and mounting hole; Nickel leading edge bound edge glueds joint the leading edge portion that is fixed on blade, and metal lining is embedded in the mounting hole of supramarginal plate.
The utility model adopts specific strength and specific stiffness composite material high, high temperature resistant, that density is low and structure stability is high to make, it has high strength, high rigidity, lightweight and resistant to elevated temperatures feature, so, it meets the performance requirement of stator blade, be applicable in the comparatively severe air dielectric of the working environment of long-term work in-55 ℃～120 ℃ temperature ranges, its dimensional stability is high, long service life.Its covering adopts preimpregnation glass cloth to make, and its appearance surfaces quality is good, and its leading edge portion is gluedd joint the nickel leading edge bound edge that has resistance to erosion, makes its anti-airflow scouring ability strong, and impact resistance is strong; The metal lining of installing in the mounting hole of supramarginal plate improves the anti-pressure ability at its position, hole place greatly.These have all extended the working life of stator blade greatly.The utility model improves the efficiency of motor greatly, meets the low oil consumption designing requirement of motor, improves the market competitiveness of motor.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Embodiment
Below in conjunction with the drawings and specific embodiments, the utility model is further described.
As shown in Figure 1, the present embodiment comprises the blade 1 of being made up of preimpregnation carbon cloth, upper and lower listrium 2,5, covering 6, nickel leading edge bound edge 4 and metal lining 3.On supramarginal plate 2, have the mounting hole being connected with engine crankcase, the covering 6 of being made up of preimpregnation glass cloth is wrapped in blade 1, upper and lower listrium 2,5, and outside mounting hole.Nickel leading edge bound edge 4 glueds joint the leading edge portion that is fixed on blade 1, and metal lining 3 is embedded in the mounting hole of supramarginal plate 2.Preimpregnation carbon cloth in the present embodiment and preimpregnation glass cloth adopt respectively preimpregnation carbon cloth 5224C/F3052 and the preimpregnation glass cloth 5224/EW110C of Beijing Research Inst. of Aeronautic Material's development.Wherein, 5224 resin systems are that intensity is high, good toughness, impact-resistant hot setting epoxy.
Above-described embodiment is only preferred and exemplary, and those skilled in the art can do equivalent technologies according to the spirit of this patent and improve, and these are all covered by the protection domain of this patent.
Claims (1)
1. a composite material stator blade for motor, is characterized in that: it comprises the blade of being made up of preimpregnation carbon cloth, upper and lower listrium, covering, nickel leading edge bound edge and metal lining; On supramarginal plate, have the mounting hole being connected with engine crankcase, the covering of being made up of preimpregnation glass cloth is wrapped in outside blade, upper and lower listrium and mounting hole; Nickel leading edge bound edge glueds joint the leading edge portion that is fixed on blade, and metal lining is embedded in the mounting hole of supramarginal plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320805917.XU CN203702263U (en) | 2013-12-10 | 2013-12-10 | Composite stator blade of engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320805917.XU CN203702263U (en) | 2013-12-10 | 2013-12-10 | Composite stator blade of engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203702263U true CN203702263U (en) | 2014-07-09 |
Family
ID=51052718
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320805917.XU Expired - Fee Related CN203702263U (en) | 2013-12-10 | 2013-12-10 | Composite stator blade of engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203702263U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104626726A (en) * | 2015-02-06 | 2015-05-20 | 中国商用飞机有限责任公司 | Cold extrusion strengthening method for assembling hole of CFRP composite material laminate |
| CN104690982A (en) * | 2013-12-10 | 2015-06-10 | 惠阳航空螺旋桨有限责任公司 | Composite stator blade of engine and preparation method of composite stator blade |
| CN105150441A (en) * | 2015-09-17 | 2015-12-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Runner-plate and rubber-strip assembly and molding method thereof |
| CN105697070A (en) * | 2014-11-27 | 2016-06-22 | 中国航空工业集团公司沈阳发动机设计研究所 | Composite stator blade of combination structure |
-
2013
- 2013-12-10 CN CN201320805917.XU patent/CN203702263U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104690982A (en) * | 2013-12-10 | 2015-06-10 | 惠阳航空螺旋桨有限责任公司 | Composite stator blade of engine and preparation method of composite stator blade |
| CN105697070A (en) * | 2014-11-27 | 2016-06-22 | 中国航空工业集团公司沈阳发动机设计研究所 | Composite stator blade of combination structure |
| CN104626726A (en) * | 2015-02-06 | 2015-05-20 | 中国商用飞机有限责任公司 | Cold extrusion strengthening method for assembling hole of CFRP composite material laminate |
| CN105150441A (en) * | 2015-09-17 | 2015-12-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Runner-plate and rubber-strip assembly and molding method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| 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: 20140709 Termination date: 20171210 |