JPH11271172A - Shock wind tunnel testing device - Google Patents
Shock wind tunnel testing deviceInfo
- Publication number
- JPH11271172A JPH11271172A JP7917898A JP7917898A JPH11271172A JP H11271172 A JPH11271172 A JP H11271172A JP 7917898 A JP7917898 A JP 7917898A JP 7917898 A JP7917898 A JP 7917898A JP H11271172 A JPH11271172 A JP H11271172A
- Authority
- JP
- Japan
- Prior art keywords
- nozzle
- melting
- alloy containing
- wind tunnel
- crack
- 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
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、極超音速流中の供
試体への流れの作用を測定する空力加熱試験等に使用さ
れる衝撃風洞試験装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a shock tunnel test apparatus used for an aerodynamic heating test for measuring the action of a flow on a specimen in a hypersonic flow.
【０００２】[0002]
【従来の技術】従来から使用されている衝撃風洞試験装
置の代表的なものとしては、米国カリフォルニア工科大
学のＴ５，独国ドイツ航空宇宙研究所（ＤＬＲ）のＨＥ
Ｇ等がある。2. Description of the Related Art A typical example of a conventional shock wind tunnel test apparatus is T5 of the California Institute of Technology in the United States, and HE of the German Aerospace Laboratory (DLR) of Germany.
G and the like.
【０００３】このような衝撃風洞試験装置で極超音速流
を発生させるノズルには、百数十ＭＰａにもなる高圧
と、数十ＭＪ／kgにもなる高エンタルピーのよどみ点状
態の気体がノズル内に発生する。このノズルの稼働時間
は、衝撃波管によって得られる気体のよどみ点状態の持
続時間に依存し、風洞によっても異なるが、１〜３msec
と極めて短時間である。[0003] In a nozzle for generating a hypersonic flow in such a shock wind tunnel test apparatus, a gas in a stagnation point state having a high pressure as high as one hundred and several tens of MPa and a high enthalpy as high as several tens MJ / kg is used. Occurs within. The operating time of this nozzle depends on the duration of the stagnation point state of the gas obtained by the shock tube, and varies depending on the wind tunnel.
It is an extremely short time.
【０００４】しかしながら、通過する極超音速流からノ
ズルに伝達される入熱量が極めて大きいため、使用する
材料によってはノズルに溶融や割れを生じ、流路面形状
を保持できなくなることがあった。なお、従来のノズル
において使用されていた材料は、通常、３０％Ｃｕ−
Ｗ，Ｍｏ等であった。However, since the amount of heat input transmitted from the passing hypersonic flow to the nozzle is extremely large, the nozzle may be melted or cracked depending on the material used, and the shape of the flow channel surface may not be maintained. The material used in the conventional nozzle is usually 30% Cu-
W, Mo, etc.
【０００５】[0005]
【発明が解決しようとする課題】従来の衝撃風洞試験装
置においては、前記のように、ノズルの溶融や割れによ
り流路面形状が変形することがあるため、下流側に発生
させる極超音速流が所要のマッハ数に達することができ
ず、風洞試験ができなくなる、あるいは、計測データが
信頼性の低いものとなることがあった。In the conventional shock wind tunnel test apparatus, the flow path surface shape may be deformed due to the melting or cracking of the nozzle as described above. In some cases, the required Mach number could not be reached and the wind tunnel test could not be performed, or the measurement data became unreliable.
【０００６】また、ノズルの溶融や割れに伴い、ノズル
をひんぱんに交換する必要があった。更に、使用されて
いた３０％Ｃｕ−Ｗ，Ｍｏ製のノズルは、素材費が高
く、衝撃風洞試験費の経費アップの要因となっていた。
本発明は上記の課題を解決しようとするものである。In addition, the nozzle has to be frequently replaced due to melting or cracking of the nozzle. In addition, the 30% Cu-W, Mo nozzle used was expensive in material cost, which increased the cost of shock wind tunnel test costs.
The present invention seeks to solve the above problems.
【０００７】[0007]
【課題を解決するための手段】請求項１の発明は、高温
・高圧の気体により超音速流を発生させるノズルを有す
る衝撃風洞試験装置において、ＣｒとＺｒとを含有する
Ｃｕ合金によりノズルを形成したことを特徴としてい
る。According to a first aspect of the present invention, there is provided an impact wind tunnel test apparatus having a nozzle for generating a supersonic flow by a high-temperature and high-pressure gas, wherein the nozzle is formed of a Cu alloy containing Cr and Zr. It is characterized by doing.
【０００８】本発明は、まず、流路面の割れと溶融の発
生を回避するため、延性と耐溶融性に優れた金属材料の
候補を数種類選定した後、この候補材料を用いてノズル
を製作し、製作したノズルを衝撃風洞試験に供すること
により好適な金属材料を見出したものである。According to the present invention, first, in order to avoid cracking and melting of the flow path surface, several types of metal materials having excellent ductility and melting resistance are selected, and then a nozzle is manufactured using the candidate materials. A suitable metal material was found by subjecting the manufactured nozzle to a shock wind tunnel test.
【０００９】本発明に係るノズルの形成に用いるＣｒと
Ｚｒとを含有するＣｕ合金は、純Ｃｕの耐割れ性、耐溶
融性を損なうことなく降伏強度を向上させた材料であ
り、安価な材料である。The Cu alloy containing Cr and Zr used for forming the nozzle according to the present invention is a material having improved yield strength without impairing the cracking resistance and melting resistance of pure Cu, and is a low-cost material. It is.
【００１０】そのため、従来の３０％Ｃｕ−Ｗあるいは
Ｍｏを用いたノズルと比較し、割れに対して格段に強い
上に、流路面の溶融や形状変形も極めて小さく、また、
素材費も非常に安価なノズルの実現が可能となる。Therefore, as compared with the conventional nozzle using 30% Cu-W or Mo, the nozzle is remarkably resistant to cracking, and the melting and shape deformation of the channel surface are extremely small.
It is possible to realize a nozzle with a very low material cost.
【００１１】[0011]
【発明の実施の形態】本発明の実施の一形態に係る衝撃
風洞試験装置について、図１乃至図３により説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A shock wind tunnel test apparatus according to an embodiment of the present invention will be described with reference to FIGS.
【００１２】図１乃至図３により説明する本実施形態に
係る衝撃風洞試験装置においては、０〜１．０重量％の
Ｃｒと、０〜１．０重量％のＺｒとを含有するＣｕ合金
によりノズルを形成している。In the shock tunnel test apparatus according to the present embodiment described with reference to FIGS. 1 to 3, a Cu alloy containing 0 to 1.0% by weight of Cr and 0 to 1.0% by weight of Zr is used. A nozzle is formed.
【００１３】本実施形態において、ノズルの形成用材料
に０〜１．０重量％のＣｒと０〜１．０重量％のＺｒを
含有するＣｕ合金を用いるものとしたのは、候補材料の
選定と試験による材料の絞り込みを行ったことによるも
のであり、以下、その内容を説明する。In this embodiment, the reason why a Cu alloy containing 0 to 1.0% by weight of Cr and 0 to 1.0% by weight of Zr is used as a material for forming a nozzle is to select a candidate material. This is because the materials were narrowed down by the test.
【００１４】まず、候補材料の選定では、従来のノズル
において問題となっていた流路面の割れと溶融の発生を
回避するため、延性と耐溶融性に優れた金属材料を数種
類選定することとした。First, in selecting candidate materials, several types of metal materials having excellent ductility and melting resistance were selected in order to avoid the occurrence of cracks and melting of the flow path surface, which were problems in conventional nozzles. .
【００１５】延性については、伸びを指標とし、耐溶融
性については融点（Ｔｍ），密度（ρ），比熱（ｃ），
熱伝導率（ｋ）で規格化したＴｍ（ρｃｋ）1/2 を指標
として図１を作成し、これらの指標が高い値を示す金属
材料を候補として選定した。For ductility, elongation is used as an index. For melting resistance, melting point (Tm), density (ρ), specific heat (c),
FIG. 1 was created using Tm (ρck) 1/2 normalized by the thermal conductivity (k) as an index, and a metal material having a high value of these indexes was selected as a candidate.
【００１６】この図１をもとに候補として選定された金
属材料は、Ｗ，Ｍｏ，Ｔａ−２．５Ｗ，３０％Ｃｕ−
Ｗ，Ｃｒ及びＺｒを含有するＣｕ合金であった。なお、
図１中のＴｉ，Ｆｅ，Ａｌは、その位置付けを参考とし
て記載したものである。The metal materials selected as candidates based on FIG. 1 are W, Mo, Ta-2.5 W, 30% Cu-
It was a Cu alloy containing W, Cr and Zr. In addition,
Ti, Fe, and Al in FIG. 1 are described with reference to their positioning.
【００１７】この材料選定においては、耐溶融性指標Ｔ
ｍ（ρｃｋ）1/2 を導入することにより、融点だけでな
く、密度，比熱，熱伝導率を加味した材料選定が可能と
なった。In this material selection, the melting resistance index T
By introducing m (ρck) 1/2 , it became possible to select a material in consideration of not only the melting point but also the density, specific heat, and thermal conductivity.
【００１８】次に、試験による材料の絞り込みでは、試
験の実施に先立って、上記候補として選定した金属材料
により図２に示す衝撃風洞用ノズルを製作し、これを衝
撃風洞試験装置に取付け、４５ＭＰａ，２３ＭＪ／kgの
極超音速流を発生させて衝撃風洞試験を実施した。Next, in narrowing down the materials by the test, prior to the test, a nozzle for an impact wind tunnel shown in FIG. 2 is manufactured from the metal material selected as the above candidate, and this nozzle is attached to an impact wind tunnel test device, and is subjected to 45 MPa. , 23 MJ / kg hypersonic flow was generated and a shock wind tunnel test was performed.
【００１９】この試験は、試験前後の重量減少量の測定
を行うとともに、流路面の電子顕微鏡による溶融、欠損
の確認を行うものであり、図３はそれぞれの材料につい
ての重量減少量の測定結果を示している。In this test, the weight loss before and after the test is measured, and melting and loss of the flow path surface are confirmed by an electron microscope. FIG. 3 shows the measurement results of the weight loss of each material. Is shown.
【００２０】図３に示すように、Ｔａ−２．５Ｗ，３０
％Ｃｕ−Ｗは、試験回数を重ねると、重量減少量が大き
くなっていった。特に、３０％Ｃｕ−Ｗでは、Ｃｕ部が
優先的に溶融飛散し、試験回数を重ねると、流路面が粗
くなる傾向のあることが分かった。As shown in FIG. 3, Ta-2.5 W, 30
As for% Cu-W, the weight loss increased as the number of tests increased. In particular, it was found that in the case of 30% Cu-W, the Cu portion was preferentially melted and scattered, and when the number of tests was repeated, the flow path surface tended to be rough.
【００２１】また、耐溶融性の指標であるＴｍ（ρｃ
ｋ）1/2 が大きくても、耐割れ性の指標である伸びが小
さい材料のＷ及びＭｏは、１回の高エネルギー衝撃波に
より割れが発生してしまい、ノズルとしての機能を果た
せないことが分かった。Also, Tm (ρc
k) Even if the value of 1/2 is large, W and Mo, which are materials having small elongation, which are indicators of crack resistance, may not be able to function as a nozzle because cracks are generated by a single high-energy shock wave. Do you get it.
【００２２】一方、図１に示すようにＷ及びＭｏと同様
にＴｍ（ρｃｋ）1/2 の高い純Ｃｕでは、割れや溶融は
発生しなかったが、衝撃波通過時にノズルが変形してし
まい、空力的に狙った形状を維持できないことが分かっ
た。これは降伏強度が不足しているためである。On the other hand, as shown in FIG. 1, in the case of pure Cu having a high Tm (ρck) 1/2 like W and Mo, cracking and melting did not occur, but the nozzle was deformed during the passage of the shock wave. It turned out that the target shape could not be maintained aerodynamically. This is because the yield strength is insufficient.
【００２３】これに対し、ＣｒとＺｒを含有するＣｕ合
金は、重量減少量が最も少なく、かつ１０回の試験を行
った後も割れが発生せず、試験回数を重ねると、表面が
滑らかになる傾向が認められ、候補材料中で最も流路面
形状の変形が小さかった。On the other hand, the Cu alloy containing Cr and Zr has the smallest weight loss, does not crack even after 10 tests, and has a smooth surface when the number of tests is repeated. The deformation of the channel surface shape was the smallest among the candidate materials.
【００２４】以上より、純Ｃｕの耐割れ性、耐溶融性を
損なうことなく、降伏強度を向上させた材料であるＣｒ
及びＺｒを微量添加したＣｕ合金が、衝撃風洞試験装置
に好適であることが分かった。As described above, Cr which is a material having improved yield strength without impairing the crack resistance and melting resistance of pure Cu
It has been found that a Cu alloy containing a small amount of Zr and Zr is suitable for a shock wind tunnel test apparatus.
【００２５】[0025]
【発明の効果】本発明は、高温・高圧の気体により極超
音速流を発生するノズルを有する衝撃風洞試験装置にお
いて、上記ノズルがＣｒとＺｒとを含有するＣｕ合金に
より形成されたものとしたことによって、純Ｃｕの耐割
れ性、耐溶融性を損なうことなく降伏強度を向上させ得
るため、従来の３０％Ｃｕ−ＷあるいはＭｏを用いたノ
ズルと比較し、割れに対して格段に強い上に、流路面の
溶融や形状変形も極めて小さく、また、１／５〜１／１
０と非常に安価なノズルの実現が可能となる。According to the present invention, there is provided an impact wind tunnel test apparatus having a nozzle for generating a hypersonic flow by a high-temperature and high-pressure gas, wherein the nozzle is formed of a Cu alloy containing Cr and Zr. As a result, the yield strength can be improved without impairing the cracking resistance and melting resistance of pure Cu. Therefore, compared to a conventional nozzle using 30% Cu-W or Mo, it is much more resistant to cracking. In addition, melting and shape deformation of the flow channel surface are extremely small, and 1/5 to 1/1.
It is possible to realize a very inexpensive nozzle of 0.
【図１】本発明の実施の一形態に係る衝撃風洞試験装置
に用いるノズルの材料の説明図である。FIG. 1 is an explanatory diagram of a material of a nozzle used in a shock wind tunnel test device according to an embodiment of the present invention.
【図２】上記一実施形態に係る衝撃風洞試験装置に用い
るノズルの形状の説明図で、（ａ）は正面図、（ｂ）は
（ａ）のＡ−Ａ矢視図である。FIGS. 2A and 2B are explanatory views of the shape of a nozzle used in the shock wind tunnel test apparatus according to the embodiment, wherein FIG. 2A is a front view and FIG. 2B is a view taken along the line AA of FIG.
【図３】上記一実施形態に係る衝撃風洞試験における各
材料の重量減少量の説明図である。FIG. 3 is an explanatory diagram of a weight reduction amount of each material in a shock wind tunnel test according to the embodiment.
Claims (1)
させるノズルを有する衝撃風洞試験装置において、Ｃｒ
とＺｒとを含有するＣｕ合金によりノズルを形成したこ
とを特徴とする衝撃風洞試験装置。An impact wind tunnel test apparatus having a nozzle for generating a supersonic flow by a high-temperature and high-pressure gas, comprising:
Wind tunnel testing device, wherein a nozzle is formed of a Cu alloy containing Zr and Zr.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7917898A JPH11271172A (en) | 1998-03-26 | 1998-03-26 | Shock wind tunnel testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7917898A JPH11271172A (en) | 1998-03-26 | 1998-03-26 | Shock wind tunnel testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH11271172A true JPH11271172A (en) | 1999-10-05 |
Family
ID=13682734
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7917898A Pending JPH11271172A (en) | 1998-03-26 | 1998-03-26 | Shock wind tunnel testing device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH11271172A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102507203A (en) * | 2011-11-03 | 2012-06-20 | 中国科学院力学研究所 | Shockwave wind tunnel-based self-starting test device for hypersonic air inlet channel |
| US10120477B2 (en) | 2012-09-28 | 2018-11-06 | Murata Manufacturing Co., Ltd. | Push amount detecting sensor and touch input device |
| CN113624440A (en) * | 2021-08-05 | 2021-11-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for arranging pulsating pressure measuring points of high-speed buffeting test model |
-
1998
- 1998-03-26 JP JP7917898A patent/JPH11271172A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102507203A (en) * | 2011-11-03 | 2012-06-20 | 中国科学院力学研究所 | Shockwave wind tunnel-based self-starting test device for hypersonic air inlet channel |
| US10120477B2 (en) | 2012-09-28 | 2018-11-06 | Murata Manufacturing Co., Ltd. | Push amount detecting sensor and touch input device |
| CN113624440A (en) * | 2021-08-05 | 2021-11-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for arranging pulsating pressure measuring points of high-speed buffeting test model |
| CN113624440B (en) * | 2021-08-05 | 2024-02-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for arranging pulsating pressure measuring points of high-speed buffeting test model |
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