CN106134320B - A kind of pottery of soft graphite+soldering combined sealing structure and metal method of attachment - Google Patents
A kind of pottery of soft graphite+soldering combined sealing structure and metal method of attachmentInfo
- Publication number
- CN106134320B CN106134320B CN201010048544.7A CN201010048544A CN106134320B CN 106134320 B CN106134320 B CN 106134320B CN 201010048544 A CN201010048544 A CN 201010048544A CN 106134320 B CN106134320 B CN 106134320B
- Authority
- CN
- China
- Prior art keywords
- ring
- titanium alloy
- ceramic
- adopts
- pottery
- 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
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Abstract
The present invention discloses a kind of pottery and metal method of attachment of soft graphite+soldering combined sealing structure, adopt soft graphite+soldering combination sealing form, using niobium alloy as transition metal, be connected with Ceramic brazing, be connected with the melting welding of titanium alloy head, realize the reliable bonding strength between thrust chamber titanium alloy head and ceramic material body portion; Pottery end face and titanium alloy head interface adopt flexible graphite sealing structure, ensure that interface at high temperature possesses reliable sealing property; Thereby both ensured enough bonding strengths, realized again sealing reliably. The present invention also can be applied to other need to realize the field that pottery is connected with metal.
Description
Technical field
The present invention relates to a kind of pottery and metal method of attachment, for thrust chamber, realizeThe connection of thrust chamber metal head and ceramic matric composite body portion. Thrust chamber head body connecting portion high temperaturePlace, adopts pottery and the metal method of attachment of soft graphite+soldering combined sealing structure, can ensureEnough bonding strengths, can realize again reliable sealing. The present invention also can be applied to other needsRealize the field that pottery is connected with metal.
Background technology
Ceramic matric composite has advantages of that quality is light, mechanical behavior under high temperature good, and has goodHeat resistanceheat resistant shake, antiscour, ablation resistance, be applied gradually in thrust chamber. RootAccording to the difference of user demand, conventionally adopt Ceramic Matrix Composites Reinforced by Carbon Fibers (C/SiC),Silicon carbide fiber reinforced silicon carbide ceramic matric composite (SiC/SiC) or carbon-fiber reinforced carbon potteryBased composites (C/C), as thrust chamber body portion material.
Thrust chamber adopts titanium alloy material head conventionally, if adopt ceramic material body portion, must solve itConnectivity problem with metal head. Metal current and common knot with bolts of being connected of ceramic materialThe structure being connected with titanium alloy melting welding after structure, soldering or chemical vapour deposition (CVD) transition metal. Adopt boltSyndeton heaviness, soldering or chemical vapour deposition (CVD) metal are owing to ceramic molecular structure, thermal expansion beingNumber waits physical function parameter difference large, is difficult to form effective combination, can not ensure existing enough knotsMake a concerted effort, can realize again the reliable sealing property of connecting portion.
Summary of the invention
The technical problem to be solved in the present invention is: for current metal head and pottery at rocket thrust chamberThe existing weak point of ceramic material body portion method of attachment, provides a kind of soft graphite+soldering group that adoptsClose pottery and the metal method of attachment of hermetically-sealed construction, can ensure existing enough adhesions, again can be realNow reliable sealing function.
Technical solution of the present invention is:
With niobium alloy ring as transition metal, with Ceramic Matrix Composites Reinforced by Carbon Fibers " C/SiC "Ring brazing, is connected with the melting welding of titanium alloy ring head, realizes rocket thrust chamber titanium alloy head and C/SiCReliable bonding strength between ceramic material body portion; C/SiC ceramic ring end face docks with titanium alloy ring headFace adopts soft graphite ring hermetically-sealed construction, ensures that interface at high temperature possesses reliable sealing property; DescribedThe soldering interface of niobium alloy ring and C/SiC ceramic ring is cone structure, avoids brazing interface at high temperatureBear tension and ftracture; Described C/SiC ceramic ring and titanium alloy ring interface are tenon groove structure, and guarantee canBy connecting and sealing.
Operation principle of the present invention is: according to niobium alloy and the approaching feature of ceramic thermal coefficient of expansion, useNiobium alloy, as transition metal, with pottery and the welding of titanium alloy head, has ensured connecting portion tool respectivelyThere is certain bond strength, reduced the thermal stress at brazing interface, avoid at hot operation stateLower or the heat brazing face under state that shakes ftractures. Adopt at ceramic end face and titanium alloy head interfaceUse flexible graphite sealing structure, ensured that interface at high temperature possesses reliable sealing property. Niobium closesGold adopts the conical surface to be conducive in the time of high temperature brazing with Ceramic brazing butt joint interface, and ceramic material relies on deadweightCan relatively move with niobium alloy, ensure that niobium alloy and ceramic linkage interface have less prickerWeldering gap, less joint clearance of brazing has been the precondition of soldering; As long as operating temperature is lower than solderingTemperature, the niobium alloy of cone structure and ceramic linkage interface bear compression all the time, avoid thrust chamber manyWhen task, cause connecting portion temperature to raise, niobium alloy and Ceramic brazing linkage interface are drawn because bearingStress and ftractureing.
The present invention's advantage is compared with prior art: compared with bolt connection, and the present invention's knotStructure is simple, volume is little, quality is light; Compared with soldering or chemical gaseous phase depositing process, adopt and potteryThe approaching niobium alloy of thermal coefficient of expansion is made transition metal by the effective combination of the head of thrust chamber and body portion.Increased flexible graphite sealing structure, sealing property is better. The existing enough combinations of thrust chamber are ensuredPower, can realize reliable sealing function again.
Brief description of the drawings
Fig. 1 is metal of the present invention and ceramic syndeton schematic diagram
Detailed description of the invention
Figure 1 shows that and adopt the metal that metal of the present invention and ceramic method of attachment obtain to connect with potteryConnecting structure schematic diagram. Described syndeton by ceramic ring 1, titanium alloy ring 2, soft graphite ring 3,Niobium alloy ring 4 forms. Niobium alloy ring 4 adopts brazing with ceramic ring 1, and soldering interface adoptsCone structure, fit clearance is generally 0.02mm～0.10mm. Conical surface angle and length are according to prickerWeldering connection interface structure size is selected, and physical dimension hour, is chosen less conical surface angle and length.The conical surface length of choosing of the present invention is 5mm～25mm, and choosing conical surface angle [alpha] is 5 °～15 °,Brazing temperature is generally 800 DEG C～1200 DEG C. Niobium alloy ring 4 is connected with 2 melting welding of titanium alloy ring, logicalThe normal vacuum electron beam welding that adopts. Ceramic ring 1 adopts flexible graphite sealing with titanium alloy ring 2 interfaces,Interface is tenon groove structure.
2000N thrust chamber adopts titanium alloy head, Ceramic Matrix Composites Reinforced by Carbon Fibers(C/SiC) body portion, head, body connect soft graphite+soldering combination sealing method that adopts. This thrustA component parts for assembly of a machine heat run has been participated in chamber, and in commissioning process, thrust chamber is working properly, and constant pressure is stable, connects boundaryFace sealing is reliable. By test run result, effect of the present invention is verified.
The foregoing description of the present embodiment and accompanying drawing have represented preferred version of the present invention, art technology peopleMember can define not departing from the claims in the present invention according to different designing requirements and design parameterScope in carry out various supplements, improvement and replacing, therefore, the present invention is widely.
Claims (1)
1. the pottery of soft graphite+soldering combined sealing structure and a metal method of attachment, is characterized in that:Rocket thrust chamber adopts titanium alloy head, Ceramic Matrix Composites Reinforced by Carbon Fibers body portion, head andBody portion connects soft graphite+soldering combination sealing method that adopts, the metal being obtained by this method of attachment and potterySyndeton is by ceramic ring (1), titanium alloy ring (2), soft graphite ring (3) and niobium alloy ring (4) groupBecome, niobium alloy ring (4) adopts brazing with ceramic ring (1), and soldering interface adopts cone structure,Fit clearance is 0.02mm～0.10mm, and conical surface length is 5mm～25mm, and conical surface angle [alpha] is5 °～15 °, brazing temperature is 800 DEG C～1200 DEG C; Niobium alloy ring (4) is molten with titanium alloy ring (2)Soldered connecing, adopts vacuum electron beam welding, and ceramic ring (1) is tongue-and-groove knot with titanium alloy ring (2) interfaceStructure, adopts soft graphite ring (3) sealing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010048544.7A CN106134320B (en) | 2010-04-27 | 2010-04-27 | A kind of pottery of soft graphite+soldering combined sealing structure and metal method of attachment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010048544.7A CN106134320B (en) | 2010-04-27 | 2010-04-27 | A kind of pottery of soft graphite+soldering combined sealing structure and metal method of attachment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106134320B true CN106134320B (en) | 2013-10-30 |
Family
ID=57251410
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010048544.7A Expired - Fee Related CN106134320B (en) | 2010-04-27 | 2010-04-27 | A kind of pottery of soft graphite+soldering combined sealing structure and metal method of attachment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106134320B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107917125A (en) * | 2016-10-11 | 2018-04-17 | 张跃 | A kind of jointing of non-metal board |
| CN107956602A (en) * | 2017-11-23 | 2018-04-24 | 北京航天动力研究所 | A kind of new Joining Structure of composite thrust room |
| CN112338309A (en) * | 2020-10-23 | 2021-02-09 | 西安远航真空钎焊技术有限公司 | Workpiece joint vacuum brazing method based on strength compensation |
| CN115073200A (en) * | 2022-05-19 | 2022-09-20 | 北京控制工程研究所 | Butt-joint sealing structure and method for ceramic reaction chamber and high-temperature alloy injector |
-
2010
- 2010-04-27 CN CN201010048544.7A patent/CN106134320B/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107917125A (en) * | 2016-10-11 | 2018-04-17 | 张跃 | A kind of jointing of non-metal board |
| CN107956602A (en) * | 2017-11-23 | 2018-04-24 | 北京航天动力研究所 | A kind of new Joining Structure of composite thrust room |
| CN107956602B (en) * | 2017-11-23 | 2019-12-31 | 北京航天动力研究所 | Connecting structure of composite material thrust chamber |
| CN112338309A (en) * | 2020-10-23 | 2021-02-09 | 西安远航真空钎焊技术有限公司 | Workpiece joint vacuum brazing method based on strength compensation |
| CN112338309B (en) * | 2020-10-23 | 2022-03-11 | 西安远航真空钎焊技术有限公司 | Workpiece joint vacuum brazing method based on strength compensation |
| CN115073200A (en) * | 2022-05-19 | 2022-09-20 | 北京控制工程研究所 | Butt-joint sealing structure and method for ceramic reaction chamber and high-temperature alloy injector |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| GRSP | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131030 Termination date: 20180427 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |