CN202330020U - Throat section of hypersonic-speed engine test bed - Google Patents
Throat section of hypersonic-speed engine test bed Download PDFInfo
- Publication number
- CN202330020U CN202330020U CN2011203490837U CN201120349083U CN202330020U CN 202330020 U CN202330020 U CN 202330020U CN 2011203490837 U CN2011203490837 U CN 2011203490837U CN 201120349083 U CN201120349083 U CN 201120349083U CN 202330020 U CN202330020 U CN 202330020U
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- shell
- venturi section
- throat section
- sound engine
- engine testsand
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Abstract
The utility model discloses a throat section of a hypersonic-speed engine test bed. The throat section comprises a flange, an inner shell, an outer shell and reinforcing rib plates, which are connected into a whole by welding, wherein the two ends of the shell is large and the middle part of the shell is small; and rectangular water grooves are axially distributed on the outer surface of the inner shell. The shell is radially cut into three sections which connect the inner shell and the outer shell into a whole by brazing. After the technical scheme is adopted, the throat section has the advantages that the rectangular water grooves can be connected into a cooling water interlayer by a high-temperature brazing technology, and the bearing capability of brazing seams for a 10MPa pressure test can be ensured; and an inner cavity bears the erosion of high-temperature gas flow, and the technical effect is good.
Description
Technical field
The utility model relates to the similar Rafael nozzle hypersonic speed of a kind of multiple-grooved water-cooled interlayer engine testsand venturi section manufacturing technology, belongs to the machine-building welding technology field.
Background technology
The venturi section is hypersonic speed (Ma7) engine testsand key component; It provides condition for producing hypersonic speed; Self then should satisfy the ability of bearing HTHP; Ma7 velocity of sound hot stream temperature is about 2400 ° of K. except that refractory metal (W, Mo, Ta, Nb), and metal material can't bear high temperature like this.
The deviser at first breaks through from structure, is designed to inner casing and bears high temperature, and externally carrying out the water flowing cooling is the water-cooled interlayer, guarantees that inner casing elevated temperature heat air-flow does not destroy the venturi section.Wherein water-cooled interlayer solder technology is the key of this product.To reach the key of hypersonic speed test run performance for engine run provides thermal current, change or dwindle throat area; All can change gas flow temperature, thus decision engine run performance, therefore; Design and processing technology to the venturi section have proposed harsh requirement, and because hypersonic speed venturi section is passed through hot stream temperature up to about 2400 ° of K, must cool off the venturi material; Need to increase one deck multiple-grooved water-cooled interlayer; Make the material of contact thermal air-flow obtain cooling through current, therefore, increased high difficulty for the manufacturing of venturi section.
The utility model content
The utility model provides a kind of superelevation velocity of sound engine testsand venturi section to the shortcoming of prior art, and said venturi section can be applicable to the requirement of temperature, pressure.
It is following that the utility model solves the problems of the technologies described above the technical scheme that is adopted:
A kind of superelevation velocity of sound engine testsand venturi section comprises:
Flange, inner casing, shell, reinforcement gusset, as a whole through being welded to connect, the two ends of this shell are big, and are middle little; And said shell is cut into three lobes vertically and connects as one through high temperature brazing.
Further, preferred construction is, longitudinally is formed with three weld seams at the outside surface of said shell.
Further, preferred construction is that matching between said inner casing outside surface and the inner surface of outer cover forms the Rectangular Water Trough interlayer.
Further, preferred construction is, is provided with the rectangle panel in the corresponding position of said Rectangular Water Trough, lays foil-shaped brazing material between said panel and the inner casing.
Further, preferred construction is, said inner shell materials is selected chromium zirconium copper, and said sheathing material is chosen as stainless steel.
The utility model has been taked after the technique scheme, can adopt the high temperature brazing technology that Rectangular Water Trough is connected into the water-cooled interlayer, and the brazed seam of water-cooled interlayer can bear the not bulge of 10MPa pressure test, not reveal, and has the good technical effect.
Description of drawings
Below in conjunction with accompanying drawing the utility model is carried out detailed description, so that the above-mentioned advantage of the utility model is clearer and more definite.
Fig. 1 is the synoptic diagram of the utility model superelevation velocity of sound engine testsand venturi section;
Fig. 2 is the partial schematic diagram of the utility model superelevation velocity of sound engine testsand venturi section;
Fig. 3 is the A-A schematic cross-section of superelevation velocity of sound engine testsand venturi section shown in Figure 1.
Embodiment
Come the utility model is carried out detailed description below in conjunction with accompanying drawing and specific embodiment.
Fig. 1 is the synoptic diagram of the utility model superelevation velocity of sound engine testsand venturi section; Fig. 3 is the A-A schematic cross-section of superelevation velocity of sound engine testsand venturi section shown in Figure 1;
As scheme saidly, said superelevation velocity of sound engine testsand venturi section comprises: flange (not shown), inner casing 1, shell 2, strengthen the gusset (not shown), as a whole through being welded to connect, big centre, the two ends of this shell 2 is little; And said shell is cut into three lobes vertically and connects as one through high temperature brazing.
Through above-mentioned design, three lobes with shell after the inside and outside shell soldering are welded to connect to former state integral body through argon arc, only longitudinally can form three weld seams at the casing part outside surface.
And with reference to Fig. 1, matching between said inner casing 1 outside surface and shell 2 inside surfaces forms the Rectangular Water Trough interlayer.In addition, Fig. 2 is the partial schematic diagram of the utility model superelevation velocity of sound engine testsand venturi section.
As shown in Figure 2, be provided with rectangle panel 3 in the corresponding position of said Rectangular Water Trough, lay foil-shaped brazing material between said panel and the inner casing 1; According to above-mentioned design, can be through the effect of said panel, and then reached the technique effect that prevents the solder overflow or form pre-cooled passage, and this panel is the key of technology for this reason, does not establish this panel, and then three argon-arc welding seams can't be implemented.
The utility model has been taked after the technique scheme, can Rectangular Water Trough be connected into the water-cooled interlayer through the high temperature brazing technology, and the brazed seam that forms the water-cooled interlayer can bear the 10MPa pressure test, not bulge, does not reveal, and has the good technical effect.
It should be noted that; Above-mentioned specific embodiment only is exemplary; Under the above-mentioned instruction of the utility model, those skilled in the art can carry out various improvement and distortion on the basis of the foregoing description, and these improve or distortion drops in the protection domain of the utility model.It will be understood by those skilled in the art that top specific descriptions just in order to explain the purpose of the utility model, are not to be used to limit the utility model.The protection domain of the utility model is limited claim and equivalent thereof.
Claims (5)
1. a superelevation velocity of sound engine testsand venturi section is characterized in that, comprising:
Flange, inner casing, shell, reinforcement gusset, as a whole through being welded to connect, the two ends of this shell are big, and are middle little; And said shell radially is cut into three lobes and is connected together through soldering.
2. superelevation velocity of sound engine testsand venturi section according to claim 1 is characterized in that, longitudinally is formed with three weld seams at the outside surface of said shell.
3. superelevation velocity of sound engine testsand venturi section according to claim 1 and 2 is characterized in that, matches between said inner casing outside surface and the inner surface of outer cover to form said Rectangular Water Trough interlayer.
4. superelevation velocity of sound engine testsand venturi section according to claim 3 is characterized in that, is provided with the rectangle panel in the corresponding position of said Rectangular Water Trough, lays foil-shaped brazing material between said panel and the inner casing.
5. superelevation velocity of sound engine testsand venturi section according to claim 1 is characterized in that, said inner shell materials is selected chromium zirconium copper, and said sheathing material is chosen as stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203490837U CN202330020U (en) | 2011-09-16 | 2011-09-16 | Throat section of hypersonic-speed engine test bed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203490837U CN202330020U (en) | 2011-09-16 | 2011-09-16 | Throat section of hypersonic-speed engine test bed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202330020U true CN202330020U (en) | 2012-07-11 |
Family
ID=46441998
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011203490837U Expired - Lifetime CN202330020U (en) | 2011-09-16 | 2011-09-16 | Throat section of hypersonic-speed engine test bed |
Country Status (1)
| Country | Link |
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| CN (1) | CN202330020U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109695784A (en) * | 2018-12-17 | 2019-04-30 | 北京动力机械研究所 | A kind of nozzle throat section of cooling trough insert |
| CN109695783A (en) * | 2018-12-17 | 2019-04-30 | 北京动力机械研究所 | A kind of nozzle throat section with ring stiffener |
| CN109848660A (en) * | 2019-03-11 | 2019-06-07 | 任耀文 | A kind of preparation method of active cooling structure |
| CN109848659A (en) * | 2019-03-08 | 2019-06-07 | 任耀文 | A kind of axisymmetric nozzle integral welding method |
| CN112338447A (en) * | 2020-10-23 | 2021-02-09 | 西安远航真空钎焊技术有限公司 | Machining method of wide-runner throat structural part |
| CN112747886A (en) * | 2020-12-29 | 2021-05-04 | 中国航天空气动力技术研究院 | Thin-wall throat |
-
2011
- 2011-09-16 CN CN2011203490837U patent/CN202330020U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109695784A (en) * | 2018-12-17 | 2019-04-30 | 北京动力机械研究所 | A kind of nozzle throat section of cooling trough insert |
| CN109695783A (en) * | 2018-12-17 | 2019-04-30 | 北京动力机械研究所 | A kind of nozzle throat section with ring stiffener |
| CN109848659A (en) * | 2019-03-08 | 2019-06-07 | 任耀文 | A kind of axisymmetric nozzle integral welding method |
| CN109848660A (en) * | 2019-03-11 | 2019-06-07 | 任耀文 | A kind of preparation method of active cooling structure |
| CN109848660B (en) * | 2019-03-11 | 2022-05-31 | 西安远航真空钎焊技术有限公司 | Preparation method of active cooling structure |
| CN112338447A (en) * | 2020-10-23 | 2021-02-09 | 西安远航真空钎焊技术有限公司 | Machining method of wide-runner throat structural part |
| CN112747886A (en) * | 2020-12-29 | 2021-05-04 | 中国航天空气动力技术研究院 | Thin-wall throat |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120711 |
|
| CX01 | Expiry of patent term |