CN108216650A - A kind of gradient-structure air intake duct - Google Patents
A kind of gradient-structure air intake duct Download PDFInfo
- Publication number
- CN108216650A CN108216650A CN201711376910.XA CN201711376910A CN108216650A CN 108216650 A CN108216650 A CN 108216650A CN 201711376910 A CN201711376910 A CN 201711376910A CN 108216650 A CN108216650 A CN 108216650A
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- China
- Prior art keywords
- air intake
- intake duct
- operating temperature
- gradient
- relatively low
- Prior art date
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- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 20
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 20
- 239000000956 alloy Substances 0.000 claims abstract description 20
- 239000000463 material Substances 0.000 claims abstract description 18
- 239000010936 titanium Substances 0.000 claims abstract description 17
- 229910000765 intermetallic Inorganic materials 0.000 claims abstract description 5
- 238000005516 engineering process Methods 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 238000002360 preparation method Methods 0.000 claims description 2
- 230000007704 transition Effects 0.000 abstract description 6
- 239000002994 raw material Substances 0.000 abstract description 3
- 230000008021 deposition Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 229910001040 Beta-titanium Inorganic materials 0.000 description 1
- 229910004349 Ti-Al Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910004692 Ti—Al Inorganic materials 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/10—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
- B22F5/106—Tube or ring forms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Composite Materials (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention relates to aerospace field, more particularly to a kind of admission line of aircraft, specifically a kind of xenogenesis titanium alloy gradient-structure air intake duct.The air intake duct can integrally be divided into higher three, the position part of the relatively low position of operating temperature, intermediate location, operating temperature；Wherein, the higher position of operating temperature uses intermetallic compound Ti2Prepared by AlNb based alloys, the relatively low position of operating temperature is prepared using the TA15 titanium alloys of high-strength light, and intermediate location is using TA15, Ti that mass fraction is 50%2AlNb material transitions.The application of xenogenesis titanium alloy also saves raw material, alleviates weight, while can give full play to the characteristic of respective alloy, there is increasing application prospect in fields such as Aeronautics and Astronautics, weapons in addition to that can meet air intake duct aerodynamic performance requirements.
Description
Technical field
The present invention relates to aerospace field, more particularly to a kind of admission line of aircraft is specifically a kind of different
Kind titanium alloy gradient-structure air intake duct.
Background technology
Awing, air intake duct will realize the deceleration supercharging of high-speed flow to aircraft, and the kinetic energy of air-flow is changed into pressure
Energy.With the increase of flying speed, the pressurization of air intake duct is increasing, and the pressurization in supersonic flight can be significantly
More than compressor, so supersonic vehicle air intake duct has important role to improving flying quality.
Titanium alloy is widely used in the fields such as aerospace with the advantages of its high-strength light, heat-proof corrosion-resistant.Ti2AlNb alloys
Belong to Ti-Al series intermetallic compound materials, compared with traditional high-temperature titanium alloy, there is high intensity, high creep resistance, high
The outstanding features such as high temperature specific strength and high antioxidant.Ti2AlNb alloys can be for a long time in 650~750 DEG C of work, short time
800~900 DEG C are can be applied to, is ideal lightweight high-temperature structural material；TA15 alloys had both had the good heat of alpha titanium alloy by force
Property and solderability and the process plastic close to alpha and beta titanium alloy, and be a kind of with medium room temperature and high high-temp stability
The titanium alloy of high comprehensive performance, available for less than 500 DEG C aircrafts to work long hours, engine components.
But many titanium alloy structure parts can encounter the service condition of various complexity, traditional homogenous material zero in the application
Part has been difficult to meet air intake duct requirement, needs the dissimilar material overall structure of Development of Novel, makes structural member different parts
Performance meets different actual demands, to increase the adaptability of structural member and practicability.The integration system of xenogenesis titanium alloy structure
Standby and forming technique considers the difference of different parts operating temperatures, and the titanium for selecting different model in part different parts closes
Gold so as to both save raw material, alleviates weight, and can give full play to the characteristic of respective titanium alloy.Dissimilar material structure is led to
It is often used as mitigating the heat resistance mechanical part of thermal stress, there is increasing answer in fields such as Aeronautics and Astronautics, machinery, weapons
Use prospect.
Invention content
While air intake duct aerodynamic characteristic is met, to give full play to the performance of different materials, the present invention proposes a kind of ladder
Spend structure air intake duct technical solution.
A kind of gradient-structure air intake duct is whole higher by the relatively low position 1 of operating temperature, intermediate location 2, operating temperature
Position 3 forms；Wherein, the higher position 3 of operating temperature is using intermetallic compound Ti2Prepared by AlNb based alloys, operating temperature
Relatively low position 1 is prepared using the TA15 titanium alloys of high-strength light.
Intermediate location 2 between the higher position 3 of operating temperature and the relatively low position 1 of operating temperature is equal using mass fraction
For 50% TA15, Ti2AlNb material transitions, length 5mm.
The wall thickness at the higher position 3 of operating temperature and the relatively low position 1 of operating temperature is consistent, is 3mm.
The air intake duct preparation method is integrally formed using laser gain material manufacturing technology.
Beneficial effects of the present invention are as follows：
Xenogenesis titanium alloy gradient-structure considers the difference of different parts operating temperatures, is used in air intake duct high temperature position
Inter-metallic compound material, low temperature position uses near αtitanium alloy, integrally formed using laser gain material manufacturing technology, avoids biography
System is mechanically connected the problems such as number of parts generated, architecture quality increase, so as to meet the same of air intake duct aerodynamic performance requirements
When, raw material are both saved, construction weight are alleviated, and the characteristic of respective alloy can be given full play to, in Aeronautics and Astronautics, weapons
There is increasing application prospect in the fields of grade.
Description of the drawings
Fig. 1 is gradient-structure inlet structure schematic diagram.
In figure, the relatively low position of 1- operating temperatures, 2- intermediate locations, the higher position of 3- operating temperatures.
Specific embodiment
The present invention provides a kind of gradient-structure air intake duct, specifically a kind of xenogenesis titanium alloy gradient-structure air intake duct.
The present invention is described in further detail in the following with reference to the drawings and specific embodiments.
Embodiment 1
A kind of high-speed aircraft gradient-structure air intake duct, as shown in Figure 1, air intake duct total length be 600mm, diameter from
300mm to 500mm transition.
To mitigate Ti2Structural stress between AlNb based alloys and TA15 titanium alloys, Ti2AlNb based alloys and TA15 alloys
Between using 50% TA15+50% Ti2AlNb (being mass fraction) material transition, length 5mm.
Thermo parameters method when simulating its work by ANSYS softwares, the long 320mm in position of operating temperature≤600 DEG C, wherein
2.5mm is transition material, i.e. 1 long 317.5mm of TA15 titanium alloys part；The long 280mm in position that 600 DEG C of operating temperature ＞, wherein
2.5mm is transition material, i.e. Ti23 long 277.5mm of AlNb based alloys part.
In the present embodiment, Ti2The wall thickness of AlNb based alloys and TA15 titanium alloys part is consistent, is 3mm.
Air intake duct is integrally formed using laser gain material manufacturing technology, is deposited on forging state TA15 titanium alloy substrates first
The TA15 titanium alloys section 1 of 317.5mm, then using TA15 alloys as the Ti of the TA15+50% of matrix deposition 5mm50%2AlNb is (
For mass fraction) material segment 2, finally with alloy section 2 be matrix deposition 277.5mm Ti2AlNb based alloys section 3.Deposition terminates
Afterwards, 550 DEG C of heat preservation 2h annealings are carried out to air intake duct, are then cut air intake duct from substrate using wire cutting.
When the present embodiment is used for the aircraft of high-speed flight, close to the Ti of engine side2AlNb based alloys can be born
Higher temperature, the TA15 alloys far from engine side have higher intensity at a lower temperature, while reduce air inlet
The weight in road increases the mobility of aircraft.
Claims (4)
1. a kind of gradient-structure air intake duct, which is characterized in that it is whole by the relatively low position of operating temperature (1), intermediate location (2),
The higher position of operating temperature (3) forms；Wherein, the higher position of operating temperature (3) are using intermetallic compound Ti2AlNb bases
Prepared by alloy, the relatively low position of operating temperature (1) is prepared using the TA15 titanium alloys of high-strength light.
2. a kind of gradient-structure air intake duct as described in claim 1, which is characterized in that the higher position of operating temperature (3) and work
Make TA15, Ti that the intermediate location (2) between the relatively low position of temperature (1) is 50% using mass fraction2AlNb material mistakes
It crosses, length 5mm.
3. a kind of gradient-structure air intake duct as described in claim 1, which is characterized in that the higher position of operating temperature (3) and
The wall thickness at the relatively low position of operating temperature (1) is consistent, is 3mm.
4. a kind of gradient-structure air intake duct as described in claim 1, which is characterized in that the air intake duct preparation method using
Laser gain material manufacturing technology is integrally formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711376910.XA CN108216650A (en) | 2017-12-19 | 2017-12-19 | A kind of gradient-structure air intake duct |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711376910.XA CN108216650A (en) | 2017-12-19 | 2017-12-19 | A kind of gradient-structure air intake duct |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108216650A true CN108216650A (en) | 2018-06-29 |
Family
ID=62649888
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711376910.XA Pending CN108216650A (en) | 2017-12-19 | 2017-12-19 | A kind of gradient-structure air intake duct |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108216650A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030201366A1 (en) * | 2002-04-30 | 2003-10-30 | Connelly Thomas J. | Hybrid exhaust heat shield for pylon mounted gas turbine engines |
| CN105154872A (en) * | 2015-09-06 | 2015-12-16 | 中国航空工业集团公司北京航空材料研究院 | Laser manufacturing method for preparing Ni base alloy gradient materials on titanium alloy |
| CN105772718A (en) * | 2014-12-18 | 2016-07-20 | 北京有色金属研究总院 | Double-alloy whole blade disc and preparation method thereof |
| CN106637013A (en) * | 2016-10-28 | 2017-05-10 | 机械科学研究总院先进制造技术研究中心 | Thermal treatment method capable of enhancing high temperature strength of Ti2AlNb-based alloy |
| CN107138924A (en) * | 2017-06-27 | 2017-09-08 | 中国航发北京航空材料研究院 | A kind of bimetallic dual-property titanium alloy blisk manufacture method |
-
2017
- 2017-12-19 CN CN201711376910.XA patent/CN108216650A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030201366A1 (en) * | 2002-04-30 | 2003-10-30 | Connelly Thomas J. | Hybrid exhaust heat shield for pylon mounted gas turbine engines |
| CN105772718A (en) * | 2014-12-18 | 2016-07-20 | 北京有色金属研究总院 | Double-alloy whole blade disc and preparation method thereof |
| CN105154872A (en) * | 2015-09-06 | 2015-12-16 | 中国航空工业集团公司北京航空材料研究院 | Laser manufacturing method for preparing Ni base alloy gradient materials on titanium alloy |
| CN106637013A (en) * | 2016-10-28 | 2017-05-10 | 机械科学研究总院先进制造技术研究中心 | Thermal treatment method capable of enhancing high temperature strength of Ti2AlNb-based alloy |
| CN107138924A (en) * | 2017-06-27 | 2017-09-08 | 中国航发北京航空材料研究院 | A kind of bimetallic dual-property titanium alloy blisk manufacture method |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180629 |
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| RJ01 | Rejection of invention patent application after publication |