CN104696261A - Resin matrix composite material bush - Google Patents

Resin matrix composite material bush Download PDF

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Publication number
CN104696261A
CN104696261A CN201310710613.XA CN201310710613A CN104696261A CN 104696261 A CN104696261 A CN 104696261A CN 201310710613 A CN201310710613 A CN 201310710613A CN 104696261 A CN104696261 A CN 104696261A
Authority
CN
China
Prior art keywords
lining
composite material
bush
bmp316
sre
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.)
Pending
Application number
CN201310710613.XA
Other languages
Chinese (zh)
Inventor
林筠
孙瑛聪
潘世海
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GUIZHOU AERONAUTICAL ENGINE INSTITUTE
Original Assignee
GUIZHOU AERONAUTICAL ENGINE INSTITUTE
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by GUIZHOU AERONAUTICAL ENGINE INSTITUTE filed Critical GUIZHOU AERONAUTICAL ENGINE INSTITUTE
Priority to CN201310710613.XA priority Critical patent/CN104696261A/en
Publication of CN104696261A publication Critical patent/CN104696261A/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • F04D29/054—Arrangements for joining or assembling shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/80—Application in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/24—Manufacture essentially without removing material by extrusion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/48—Organic materials other organic materials

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses a resin matrix composite material bush. An adjustable straightening vane is generally used for a modern high-performance aero-engine compressor to ensure the main working parameters and necessary stability margin of the compressor; the bush for the adjustable straightening vane is arranged between a straightening vane journal and a casing hole; the bush is required to be sealed, durable and flexibly rotated in functions, and is required to be small and thin in structure, and high in dimensional accuracy, and further is required to work at a high temperature of 300 DEG C. The high-temperature resin matrix composite material bush for the adjustable straightening vane of the aero-engine compressor is designed; a KL-SRE glass fiber sleeve and BMP316 polyimide resin are selected to form a KL-SRE/BMP316 composite material; the KL-SRE/BMP316 composite material is used for replacing the current graphite-filled polyimide resin plastic material and the titanium alloy material adopting a surface oxygen permeation technology; the highest using temperature is 300 DEG C, so that the resin matrix composite material bush can meet the requirements on the bush for the adjustable straightening vane of the aero-engine compressor.

Description

A kind of polymer matrix composites lining
Technical field
The present invention relates to a kind of polymer matrix composites lining, refer more particularly to a kind of high-temperature resin based composites lining of engine variable straightener(stator) blade.
Background technique
Modern high performance aero-engine compressor generally uses adjustable straightener(stator) blade, to ensure the main working parameters of gas compressor and required engine sta bility margin.The lining that adjustable straightener(stator) blade uses is assemblied between straightener(stator) blade axle journal and casing hole, and functionally require sealing, wear-resisting, flexible rotating, structure requires little and thin, dimensional accuracy is high, and requirement can work at high temperature 300 DEG C.State's intrinsic motivation is used herein is graphite-filled polyimide resin plastic materials and the titanium alloy material adopting Surface Oxygen Diffusion technique, but working life is short, and complex process, cost is high.The polymer matrix composites lining of external development, its technology is maintained secrecy to us.Because polymer matrix composites have the advantage of lightweight, antifriction, high-strength, high-ductility, the functional requirement of lining can be met.But it is generally used for manufacturing large-scale part at aviation field, and as casing, thumbpiece etc., part is large and thick and heavy; And 20 millimeters are less than for diameter, required precision is high, and (diameter of bore is 7 0 + 0.2millimeter), how the lining part of wall thin (0.6 millimeter), carry out careful design, grasps the key technology in bushing design, manufacture, design, produce qualified composite material lining, becoming development high-performance enginer at present needs the problem of urgent solution.
Summary of the invention
The object of the invention is for solving above-mentioned deficiency, meet the requirement that High Performance Aeroengine gas compressor generally uses adjustable straightener(stator) blade lining, and design a kind of high-temperature resin based composites lining meeting the adjustable straightener(stator) blade of aero-engine compressor.
(1) technical problem that will solve
The present invention needs to solve and had both ensured that composite material lining and casing hole seals, ensures that straightener(stator) blade can the problem of flexible rotating in lining again, the manufacturing process that the material require that lining is selected simultaneously has certain intensity and is suitable for.
(2) technological scheme
In order to solve the problems of the technologies described above, the present invention is achieved through the following technical solutions:
A kind of polymer matrix composites lining, structure is divided into lining cylindrical section, lining dish section and lining knuckle radius R, an adjustable straightener(stator) blade installs one or two lining; Lining cylindrical section is sleeved on the axle journal of adjustable straightener(stator) blade.The KL-SRE/BMP316 composite material that lagging material selects KL-SRE glass fibre sleeve and BMP316 polyimide resin to form, maximum operation (service) temperature is 300 DEG C, can meet aero-engine compressor adjustable straightener(stator) blade lining function.
The manufacturing process of lining goes out composite material lining for using a kind of steel mold integral die, has complete structural characteristics, makes intensity and toughness reach perfect combination.
Strengthen as far as possible the knuckle radius R place thickness of lining, to ensure sufficient intensity, but size can not interfere, and when the thickness at the lining knuckle radius R place of design is about 1.0 ~ 1.9 times of wall thickness, can meet the function requirement of lining.
Compared with prior art, the invention has the beneficial effects as follows:
Draw through checking: composite material lining need adopt the preparation process of glass fibre sleeve and high temperature polyimide resin integral die, thus played the carrying effect of continuous fiber, make lining have characteristic that is high-strength, high-ductility; Mechanical property at 300 DEG C compares with room-temperature mechanical property, and conservation rate still has about 80%.Through 300 DEG C, after the heat ageing of 1000h, the Tg of composite material has been elevated to 389 DEG C from 354 DEG C, and weight-loss ratio is 13.35%, and composite material laminated board still maintains original shape, and the conservation rate of its longitudinal compressive strength still has about 80%.When the thickness at lining knuckle radius R place is 1.0 ~ 1.9 times of wall thickness, intensity and the matching requirements of lining can be met.Composite material lining and blade axle journal, lining and the fit up gap of casing radial hole and the expansion gap of working state, meet " Aeroengine Design handbook " requirement, the accessory size of each cooperation, without interference, solves the lining of design in early stage easily from the problem of packing fracture.
Accompanying drawing explanation
Fig. 1 is the schematic diagram that 2 linings are contained on a straightener(stator) blade,
1-lining 2-blade axle journal 3-straightener(stator) blade
Fig. 2 is lining front view.
4-lining cylindrical section 5-lining knuckle radius R 6-lining dish section
Embodiment
Below by embodiment, the present invention is further described.Below implement just descriptive, be not determinate, protection scope of the present invention can not be limited with this.
From Fig. 1 and Fig. 2, a kind of polymer matrix composites lining, lining 1 is made up of lining cylindrical section 4, lining knuckle radius R5 and lining dish section 6, and 1 adjustable straightener(stator) blade 3 is provided with one or two lining, and lining cylindrical section 4 is sleeved on blade axle journal 2; The KL-SRE/BMP316 composite material that lagging material selects KL-SRE glass fibre sleeve and BMP316 polyimide resin to form, maximum operation (service) temperature is 300 DEG C, can meet the functional requirement of aero-engine compressor adjustable straightener(stator) blade lining.
The manufacturing process of lining 1 goes out composite material lining for using a kind of steel mold integral die, has higher intensity and toughness.
The knuckle radius R5 place thickness of lining 1 is strengthened as far as possible, to ensure sufficient intensity, but dimensional interference can not occur.When the thickness at the lining knuckle radius R5 place of design is about 1.0 ~ 1.9 times of wall thickness, the function requirement of lining 1 can be met.

Claims (2)

1. a polymer matrix composites lining, lining (1) is made up of lining cylindrical section (4), lining knuckle radius R (5) and lining dish section (6), adjustable straightener(stator) blade (3) is upper installs one or two lining, and lining cylindrical section (4) is sleeved on blade axle journal (2); It is characterized in that: the KL-SRE/BMP316 composite material that lagging material selects KL-SRE glass fibre sleeve and BMP316 polyimide resin to form; The manufacturing process of lining goes out composite material lining for using a kind of steel mold integral die.
2. a kind of polymer matrix composites lining according to claim 1, is characterized in that: to lining knuckle radius R (5) place Thickness Design be: its thickness is 1.0 ~ 1.9 times of wall thickness.
CN201310710613.XA 2013-12-04 2013-12-04 Resin matrix composite material bush Pending CN104696261A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201310710613.XA CN104696261A (en) 2013-12-04 2013-12-04 Resin matrix composite material bush

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201310710613.XA CN104696261A (en) 2013-12-04 2013-12-04 Resin matrix composite material bush

Publications (1)

Publication Number Publication Date
CN104696261A true CN104696261A (en) 2015-06-10

Family

ID=53343706

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201310710613.XA Pending CN104696261A (en) 2013-12-04 2013-12-04 Resin matrix composite material bush

Country Status (1)

Country Link
CN (1) CN104696261A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109099012A (en) * 2018-09-05 2018-12-28 中国航发动力股份有限公司 It is a kind of for improving the guide vane structure and design method of compressor surge nargin
CN112343854A (en) * 2020-11-05 2021-02-09 中国科学院工程热物理研究所 Adjustable blade sealing structure

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020073840A1 (en) * 1999-06-11 2002-06-20 Pippert Frederick B. Pump liner
CN101126418A (en) * 2007-09-11 2008-02-20 嘉兴中达自润轴承工业有限公司 Polymer self-lubricating thin layer composite axle sleeve and its preparation method
WO2009063723A1 (en) * 2007-11-13 2009-05-22 Bridgestone Corporation Tire
CN102741556A (en) * 2009-12-11 2012-10-17 诺沃皮尼奥内有限公司 Composite rings for impeller-shaft fitting

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020073840A1 (en) * 1999-06-11 2002-06-20 Pippert Frederick B. Pump liner
CN101126418A (en) * 2007-09-11 2008-02-20 嘉兴中达自润轴承工业有限公司 Polymer self-lubricating thin layer composite axle sleeve and its preparation method
WO2009063723A1 (en) * 2007-11-13 2009-05-22 Bridgestone Corporation Tire
CN102741556A (en) * 2009-12-11 2012-10-17 诺沃皮尼奥内有限公司 Composite rings for impeller-shaft fitting

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
宋旻键 等: "小尺寸薄壁耐高温玻璃钢衬套的制备及其轴向压缩性能", 《航空制造技术》 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109099012A (en) * 2018-09-05 2018-12-28 中国航发动力股份有限公司 It is a kind of for improving the guide vane structure and design method of compressor surge nargin
CN112343854A (en) * 2020-11-05 2021-02-09 中国科学院工程热物理研究所 Adjustable blade sealing structure

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C10 Entry into substantive examination
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WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20150610

WD01 Invention patent application deemed withdrawn after publication