JPH0323352A - Combustion chamber for rocket engine and manufacture thereof - Google Patents
Combustion chamber for rocket engine and manufacture thereofInfo
- Publication number
- JPH0323352A JPH0323352A JP15469689A JP15469689A JPH0323352A JP H0323352 A JPH0323352 A JP H0323352A JP 15469689 A JP15469689 A JP 15469689A JP 15469689 A JP15469689 A JP 15469689A JP H0323352 A JPH0323352 A JP H0323352A
- Authority
- JP
- Japan
- Prior art keywords
- combustion chamber
- cylinder
- groove
- inner cylinder
- outer cylinder
- 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
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 24
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 15
- 238000001816 cooling Methods 0.000 claims abstract description 25
- 238000000034 method Methods 0.000 claims abstract description 15
- 239000003507 refrigerant Substances 0.000 claims abstract description 6
- 238000009792 diffusion process Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 9
- 229910000601 superalloy Inorganic materials 0.000 claims description 8
- 238000007747 plating Methods 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 3
- 238000010894 electron beam technology Methods 0.000 abstract description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 5
- 238000003466 welding Methods 0.000 abstract description 5
- 238000005323 electroforming Methods 0.000 description 12
- 238000010276 construction Methods 0.000 description 7
- 239000010949 copper Substances 0.000 description 6
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 4
- 229910052802 copper Inorganic materials 0.000 description 4
- 230000007547 defect Effects 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 238000007796 conventional method Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 2
- 239000010953 base metal Substances 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 229910000881 Cu alloy Inorganic materials 0.000 description 1
- 101100136092 Drosophila melanogaster peng gene Proteins 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000012670 alkaline solution Substances 0.000 description 1
- ZTXONRUJVYXVTJ-UHFFFAOYSA-N chromium copper Chemical compound [Cr][Cu][Cr] ZTXONRUJVYXVTJ-UHFFFAOYSA-N 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 229910000816 inconels 718 Inorganic materials 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Landscapes
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明は、冷却通路をもつロケットエンジンの燃焼室及
びその製造方法に関する．
〔従来の技術〕
従来、冷却通路をもつロケットエンジンの燃焼ン燃焼室
の製造に当っては、第４図（ａ）に示すように内ｆｉｌ
ｌに溝加工をし、第４図（ｂ）〜（ｅ）に示すように、
溝にワックスＯｌを充填し、内筒ｌとワックス外面に銀
粉０２を塗布し、その上で銅電鋳を行って電鋳層０３を
形戒し、切削加工を行って溝の両端部を露出させ、ワッ
クスＯｌと銀粉０２を除去することによって、冷却通路
０４をもつ燃焼室を製造している．
〔発明が解決しようとする課題〕
前記従来の電鋳による冷却通路をもつロケットエンジン
の燃焼室の製造方法においては、電鋳に長い期間を要し
、かつ電鋳層の品質バラツキが大きかった．
本発明は、前記従来の技術がもつ以上のような問題点を
解消し、短かい期間でかつ品質が安定した冷却通路をも
つロケットエンジンの燃焼室及びその製造方法を提供す
ることを目的とする．（！ｉｌｌ！を解決するための手
段〕
本発明は、上記課題を解決するために、次の手段を採用
したロケントエンジンの燃焼室及びその製造方法に係る
．
（１）断面が同心円状に設けられた内筒と外筒とを有し
、該内筒及び外筒の接する面の少なくとも一方に溝が設
けられ冷媒の通過する冷却通路としたロケットエンジン
の燃焼室において、溝の側壁であるウェブを通じて外筒
と内筒とが拡散接合されていることを特徴とするロケッ
トエンジンの燃焼室．
（２）内筒と超合金からなる外筒とが接する面の内筒側
に溝が設けられ、前記外筒内面に内筒材と同系のメッキ
層が設けられ、内筒の溝の側壁であるウェブ及び前記メ
ッキ層とを通じて外筒と｛３）断面が同心円状に設けら
れた内筒と外筒とを有し、該内筒と外筒の接する面の少
なくとも一方に溝が設けられ冷媒の通過する冷却通路と
したロケットエンジンの燃焼室の製造方法において、溝
に耐熱可溶性中子を充填し内外筒を着接して内外筒の間
を、真空密閉した後、これらを熱間静水圧加工（Ｈｏｔ
Ｉｓｓｏｓｔａｔｉｃ Ｐｒｅｓｓ． 以下ＨＩＰ
という）することにより内外筒を拡散接合し、前記耐熱
可溶性中子を除去することを特徴とするロケットエンジ
ンの燃焼室の製造方法．〔作 用〕
本発明（１）においては、内筒と外筒のいづれか一方に
設けられた冷媒が通過する冷却通路の溝の側壁であるウ
エプを通じて外筒と内筒とが拡散接合され、外筒と外筒
の接合強度が向上し、かつ従来の電鋳法によるポロシテ
ィ等の欠陥が減少して品質が安定する．従って、強度が
向上した分だけ肉厚を減少させ、ペイロード（積荷）を
大きくできる．また、電鋳を用いないために、工期が著
しく短縮される．
本発明（２）においては、前記の本発明（１）の作用に
加えて、外筒として高強度かつ耐熱性のすぐれる超合金
を用いており、強度が著しく向上し、従来燃焼器の周囲
に別途設けていた超合金製の耐圧ジャケットが不要とな
り、または耐圧ジャケットを設けるにしてもその重量を
軽減させることができる．また、外筒の内面に内筒と同
系の材料をあらかじめメッキしてあるので、拡散接合性
にすぐれ、特に内筒が銅系材である場合冷却通路の外筒
側の面も伝熱効率の良い銅系材料のメッキとなるので、
冷却能を高く保持できる．
本発明（３）においては、内筒と外筒の接する面の一方
に冷却通路として形威する溝に耐熱可熔性中子を充填し
、内外筒を着接して内外筒間を真空密閉した後ＨＩＰ処
理することにより、内外筒は溝の側壁をなすウェブ部分
において拡散接合され、両者の接合強度が向上し、また
従来の電鋳法によるボロシティ等の欠陥が減少する．ま
た、その後耐熱可溶性中子を除去することによって、冷
却通路をもつ燃焼室が製造される。更に、本発明（３）
では電鋳を用いていないため、工期が著しく短縮される
．
〔実施例〕
本発明の第一の実施例を第１図及び第２図によって説明
する．
第２図（ａ）に示すように、断面円形の第１図（ａ）に
示される形状の内筒ｌの外周に軸方向に複数の満３を加
工する．４は溝３の側壁を形成するウェブである．この
溝３に、第２図（ｂ）に示すように、水溶性中子５を充
填する．その上で第２図（ｃ）に示すように、外筒２を
かぶせる．内筒１と外筒２の両端部を電子ビーム溶接に
よって接合することにより内筒ｌと外筒２の間は真空密
閉される．なお外筒１を分割したものを使用する場合に
は、分割部も電子ビーム溶接接合する．この状態にした
ものを、ＨＩＰ処理することにより、第２図（ｄ）に示
すように、前記ウェブ４を通して内筒と外筒は拡散接合
一体化される．その上で外筒側から溝の両端が出てくる
まで第１図（ａ）のＸの部分を機械加工除去し、水溶性
中子５を圧力水等を利用して除去することにより、内筒
と外筒との間に冷却通路３が形威された燃焼室が製造さ
れる．本実施例における内筒と外筒、水溶性中子の材質
及び処理条件の１例を挙げると次の通りである．電子ビ
ーム溶接の条件・・・溶け込み深さ２〜３一／ｓＨＩＰ
の条件・・・５００℃×２時間，陶０気圧なお、上記の
ように内筒，外筒が銅合金で使用されるときには、中子
除去に酸又はアルカリ溶液を使用できないために、水溶
性中子を使用する必要がある．
従来の電鋳法によれば、４５日の工期を必要としたが、
本実施例ではこれが９日（中子充填から中子除去まで）
に短縮された．また、従来の銅電鋳法によるものでは、
ホ゜ロシテイがあり引張強さが低＜ （２０ｋｇ／鵬３
以下）伸びが低い（２０％以下）であったが、本実施例
では内筒と外筒の接合部が、母材と同一組織となり、母
材強度と同じ特性が得られる．また、本実施例ではボロ
シティの発生もない．
なお、本実施例では、水溶性中子を使用しているが、中
子として低融点の金属を使用することもできる．例えば
純アルミニウム（融点６６０℃）の戚形品を溝に充填し
、５００℃前後でＨＩＰ加工し、機械加工した後に、９
００℃程度に加熱して純アルξニウムを溶し出して除去
するようにしてもよい．本発明の第二の実施例を第３図
によって説明する．
第３図は、本発明の第二の実施例に係るロケットエンジ
ンの燃焼器断面を示す．外筒２はＮｉ基超合金であるイ
ンコネル７１８材（商品名）からなり、冷却通路用の溝
３の刻設された内筒ｌは第一の実施例の一例として示し
たＣｕ−０．７Ｃｒ−０．０６Ｚｒのクロム銅を用いた
．外１ｉ１２の冷却通路面にはＣｕメッキ層１０が設け
られており、また、外筒２と内筒１とは拡散接合されて
いる．
本実施例の燃焼器の製造方法について説明する．基本的
には第２図に示される第一の実施例のステップとほぼ同
様であるが、本実施例では、内筒ｌに溝加工を施すとと
もに、外筒２内面に純Ｃｕメッキを施こす．次に内筒ｌ
の溝に第１実施例と同様に水溶性中子を充填し、内筒１
と外筒２の前部及び後部を電子ビーム溶接を行って密封
するとともに内外筒１．２の間を真空引きし密閉する．
その後、これらを、第一の実施例と同じ条件にてＨＩＰ
処理を行って内外１１１１．２を接合し、冷却通路の入
口と出口を切削加工により設け、最後に冷却通路の人口
に高圧水を圧入して、水溶性中子を熔解させて水溶性中
子を除去した．
本実施例においては、従来法（電鋳法）に比し工期が５
分のＩ程度に短縮されるとともに、内外筒１．２の接合
強度が１．５〜２倍程度まで向上した．また、外筒２を
インコネル７１Ｂ材としたので、外筒２の強度が著しく
向上するとともに、外筒２の冷却通路側の面に伝熱効率
の良いＣｕメンチ層が残っているので、十分な冷却能を
確保できる．更に、外筒２の肉厚を大きくすることによ
り従来用いられているＮｉ基超合金製の耐圧ジャケット
を不要とすることが可能となる．
すなわち、本実施例によれば工期の著しい短縮と部材強
度を可能とし、肉厚を大幅に軽減できるので、安価で軽
量の燃焼器とすることができる．この軽量化した分、宇
宙に打ち上げるペイロードを増すこともできる．
〔発明の効果〕
以上説明したように、本発明は次の効果を奏することが
できる．
（１） 内外筒が、冷却通路を形戒する溝のウェブを
通して拡散接合されているために、ボロシティ等の欠陥
が減少し品質が安定する．また、従来のように電鋳を用
いていないために、工期を著しく短縮することができる
．
（２）外筒として高強度かつ耐熱性のすぐれた超合金を
用いているために、強度を著しく向上させることができ
、従来燃焼器の周囲に別途設けていた超合金製の耐熱ジ
ャケットが不要となり、また耐熱ジャケットを設けると
してもその重量を軽減させることができる．また外筒の
内面に内筒と同系の材料をメッキしているために、内外
筒の拡散接合性がすぐれている．
（３）冷却通路としての溝に耐熱可溶性中子を充填した
上内外筒を間を真空密閉した上で｝ＩＩＰ処理すること
によって、内外筒を拡散接合して強固に結合することが
できる．また、ポロシティ等の欠陥が減少して品質が安
定すると共に、工期を著しく短縮することができる．DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a combustion chamber for a rocket engine having a cooling passage and a method for manufacturing the same. [Prior Art] Conventionally, when manufacturing a combustion chamber for a rocket engine having a cooling passage, an inner filtration chamber is used as shown in Fig. 4(a).
As shown in Figure 4(b) to (e),
Fill the groove with wax Ol, apply silver powder 02 to the inner cylinder l and the outer surface of the wax, perform copper electroforming on top of that to shape the electroformed layer 03, and perform cutting to expose both ends of the groove. By removing wax Ol and silver powder 02, a combustion chamber with a cooling passage 04 is manufactured. [Problems to be Solved by the Invention] In the conventional method of manufacturing a rocket engine combustion chamber having a cooling passage by electroforming, the electroforming process required a long period of time and the quality of the electroformed layer varied widely. SUMMARY OF THE INVENTION An object of the present invention is to solve the above-mentioned problems of the conventional technology and provide a combustion chamber for a rocket engine having a cooling passage with stable quality in a short period of time, and a method for manufacturing the same. ．． (Means for Solving! ill!) In order to solve the above problems, the present invention relates to a combustion chamber for a Rokento engine and a method for manufacturing the same, which employ the following means. (1) The cross section is concentric. In the combustion chamber of a rocket engine, the combustion chamber of a rocket engine has an inner cylinder and an outer cylinder, and at least one of the contact surfaces of the inner cylinder and the outer cylinder is provided with a groove to serve as a cooling passage through which a refrigerant passes. A combustion chamber of a rocket engine characterized in that an outer cylinder and an inner cylinder are diffusion-bonded through a web. (2) A groove is provided on the inner cylinder side of the surface where the inner cylinder and the outer cylinder made of superalloy contact. , a plating layer of the same type as the inner cylinder material is provided on the inner surface of the outer cylinder, and the outer cylinder and the inner cylinder having a concentric cross section are formed through the web, which is the side wall of the groove of the inner cylinder, and the plating layer. A method for manufacturing a combustion chamber for a rocket engine, which has an outer cylinder and has a groove on at least one of the contacting surfaces of the inner cylinder and the outer cylinder to form a cooling passage through which a refrigerant passes, wherein the groove is filled with a heat-resistant soluble core. After adhering the inner and outer cylinders and vacuum-sealing the space between the inner and outer cylinders, they are subjected to hot isostatic processing (Hot Isostatic Pressure Processing).
Issostatic Press. Below is HIP
A method for manufacturing a combustion chamber for a rocket engine, characterized in that the inner and outer cylinders are diffusion-bonded by performing the above steps (referred to as "removal of the heat-resistant fusible core"). [Function] In the present invention (1), the outer cylinder and the inner cylinder are diffusion bonded through the weep, which is the side wall of the groove of the cooling passage provided in either the inner cylinder or the outer cylinder, through which the refrigerant passes. The joint strength between the cylinder and outer cylinder is improved, and defects such as porosity caused by conventional electroforming methods are reduced, resulting in stable quality. Therefore, the wall thickness can be reduced to the extent that the strength has been improved, and the payload (cargo) can be increased. Additionally, since electroforming is not used, the construction period is significantly shortened. In the present invention (2), in addition to the effects of the present invention (1), a superalloy with high strength and excellent heat resistance is used for the outer cylinder, and the strength is significantly improved. This eliminates the need for a pressure-resistant jacket made of superalloy, which was previously provided separately, and even if a pressure-resistant jacket is provided, its weight can be reduced. In addition, since the inner surface of the outer cylinder is pre-plated with a material similar to that of the inner cylinder, it has excellent diffusion bonding properties, and especially if the inner cylinder is made of copper-based material, the surface of the cooling passage on the outer cylinder side also has good heat transfer efficiency. Since it is plated with copper-based material,
Able to maintain high cooling capacity. In the present invention (3), a heat-resistant fusible core is filled in a groove serving as a cooling passage on one of the contact surfaces of the inner cylinder and the outer cylinder, and the inner and outer cylinders are adhered to form a vacuum seal between the inner and outer cylinders. By post-HIPing, the inner and outer cylinders are diffusion bonded at the web portions that form the side walls of the groove, improving the bonding strength between the two and reducing defects such as borosity caused by conventional electroforming. Furthermore, by subsequently removing the heat-resistant soluble core, a combustion chamber with cooling passages is manufactured. Furthermore, the present invention (3)
Because it does not use electroforming, the construction period is significantly shortened. [Example] A first example of the present invention will be explained with reference to FIGS. 1 and 2. As shown in FIG. 2(a), a plurality of holes are machined in the axial direction on the outer circumference of an inner cylinder l having a circular cross section and the shape shown in FIG. 1(a). 4 is a web forming the side wall of the groove 3. This groove 3 is filled with a water-soluble core 5 as shown in FIG. 2(b). Then, as shown in Fig. 2(c), cover the outer cylinder 2. By joining both ends of the inner cylinder 1 and outer cylinder 2 by electron beam welding, the space between the inner cylinder 1 and the outer cylinder 2 is vacuum-sealed. In addition, when using a divided outer cylinder 1, the divided parts are also joined by electron beam welding. By subjecting this state to HIP processing, the inner tube and the outer tube are integrated by diffusion bonding through the web 4, as shown in FIG. 2(d). Then, the part marked X in Fig. 1(a) is removed by machining until both ends of the groove come out from the outer cylinder side, and the water-soluble core 5 is removed using pressurized water, etc. A combustion chamber with a cooling passage 3 formed between the cylinder and the outer cylinder is manufactured. An example of the materials and processing conditions for the inner cylinder, outer cylinder, and water-soluble core in this example is as follows. Electron beam welding conditions...Penetration depth 2-31/sHIP
Conditions: 500°C x 2 hours, 0 atm pressure When the inner cylinder and outer cylinder are made of copper alloy as mentioned above, acid or alkaline solution cannot be used to remove the core, so water-soluble It is necessary to use a core. According to the conventional electroforming method, it required a construction period of 45 days, but
In this example, this is 9 days (from core filling to core removal)
It was shortened to . In addition, with the conventional copper electroforming method,
There is a hole and the tensile strength is low (20kg/Peng 3
(below) The elongation was low (20% or less), but in this example, the joint between the inner cylinder and the outer cylinder has the same structure as the base metal, and the same properties as the base metal strength can be obtained. Further, in this example, no volocity occurs. Although a water-soluble core is used in this example, a metal with a low melting point can also be used as the core. For example, after filling a groove with a shaped product of pure aluminum (melting point 660°C), HIPing it at around 500°C, and machining it,
Alternatively, pure aluminum may be removed by heating to about 00°C to elute pure aluminum. A second embodiment of the present invention will be explained with reference to FIG. FIG. 3 shows a cross section of a combustor of a rocket engine according to a second embodiment of the present invention. The outer cylinder 2 is made of Inconel 718 material (trade name), which is a Ni-based superalloy, and the inner cylinder 1 with grooves 3 for cooling passages is made of Cu-0.7Cr shown as an example of the first embodiment. -0.06Zr chromium copper was used. A Cu plating layer 10 is provided on the cooling passage surface of the outer cylinder 1i12, and the outer cylinder 2 and the inner cylinder 1 are diffusion bonded. The method for manufacturing the combustor of this example will be explained. Basically, the steps are almost the same as those of the first embodiment shown in FIG. ．． Next, the inner cylinder l
A water-soluble core is filled in the groove of the inner cylinder 1 in the same manner as in the first embodiment.
The front and rear parts of outer cylinder 2 are sealed by electron beam welding, and the space between inner and outer cylinders 1.2 is evacuated and sealed.
Thereafter, these were subjected to HIP under the same conditions as in the first example.
After processing, the inner and outer parts 1111.2 are joined together, the inlet and outlet of the cooling passage are provided by cutting, and finally, high-pressure water is injected into the cooling passage to melt the water-soluble core and form a water-soluble core. has been removed. In this example, the construction period is 55% compared to the conventional method (electroforming method).
It has been shortened to about 1/2, and the joint strength of the inner and outer cylinders 1.2 has been improved by about 1.5 to 2 times. In addition, since the outer cylinder 2 is made of Inconel 71B material, the strength of the outer cylinder 2 is significantly improved, and since a Cu minced layer with good heat transfer efficiency remains on the surface of the outer cylinder 2 on the cooling passage side, sufficient cooling is achieved. ability can be secured. Furthermore, by increasing the wall thickness of the outer cylinder 2, it becomes possible to eliminate the need for a pressure-resistant jacket made of a conventionally used Ni-based superalloy. In other words, according to this embodiment, the construction period can be significantly shortened, the strength of the members can be increased, and the wall thickness can be significantly reduced, making it possible to create an inexpensive and lightweight combustor. This weight reduction also allows for an increase in the payload that can be launched into space. [Effects of the Invention] As explained above, the present invention can have the following effects. (1) Since the inner and outer cylinders are diffusion bonded through the web of grooves that form the cooling passages, defects such as volocity are reduced and quality is stabilized. In addition, because it does not use electroforming like conventional methods, the construction period can be significantly shortened. (2) Since a superalloy with high strength and excellent heat resistance is used for the outer cylinder, the strength can be significantly improved, eliminating the need for a separate superalloy heat-resistant jacket that was conventionally installed around the combustor. Therefore, even if a heat-resistant jacket is provided, its weight can be reduced. In addition, because the inner surface of the outer cylinder is plated with the same material as the inner cylinder, the diffusion bonding between the inner and outer cylinders is excellent. (3) By vacuum-sealing the upper and outer cylinders whose grooves serving as cooling passages are filled with a heat-resistant soluble core and performing IIP treatment, the inner and outer cylinders can be firmly joined by diffusion bonding. In addition, defects such as porosity are reduced, quality is stabilized, and the construction period can be significantly shortened.
第１図（ａ）は本発明の第一の実施例の燃焼室の縦断面
図、第１図（ｂ）は第１図（ａ）のＡ−Ａ断面図、第２
図（ａ）〜（ａ）は前記第一の実施例の製造工程の説明
図、第３図は本発明の第二の実施例の燃焼室の横断面図
、第４図（ａ）〜（ｅ）は従来の電鋳法による製造工程
の説明図である．FIG. 1(a) is a vertical cross-sectional view of a combustion chamber according to the first embodiment of the present invention, FIG. 1(b) is a cross-sectional view taken along line AA in FIG. 1(a), and FIG.
Figures (a) to (a) are explanatory diagrams of the manufacturing process of the first embodiment, Figure 3 is a cross-sectional view of the combustion chamber of the second embodiment of the present invention, and Figures 4 (a) to ( e) is an explanatory diagram of the manufacturing process using the conventional electroforming method.
Claims (1)
該内筒及び外筒の接する面の少なくとも一方に溝が設け
られ冷媒の通過する冷却通路としたロケットエンジンの
燃焼室において、溝の側壁であるウェブを通じて外筒と
内筒とが拡散接合されていることを特徴とするロケット
エンジンの燃焼室。 ２、内筒と超合金からなる外筒とが接する面の内筒側に
溝が設けられ、前記外筒内面に内筒材と同系のメッキ層
が設けられ、内筒の溝の側壁であるウェブ及び前記メッ
キ層とを通じて外筒と内筒とが拡散接合されていること
を特徴とする請求項１に記載のロケットエンジンの燃焼
室。 ３、断面が同心円状に設けられた内筒と外筒とを有し、
該内筒と外筒の接する面の少なくとも一方に溝が設けら
れ冷媒の通過する冷却通路としたロケットエンジンの燃
焼室の製造方法において、溝に耐熱可溶性中子を充填し
内外筒を着接して内外筒の間を、真空密閉した後、これ
らを熱間静水圧加工することにより内外筒を拡散接合し
、前記耐熱可溶性中子を除去することを特徴とするロケ
ットエンジンの燃焼室の製造方法。[Claims] 1. It has an inner cylinder and an outer cylinder whose cross sections are concentric,
In the combustion chamber of a rocket engine, a groove is provided in at least one of the contacting surfaces of the inner cylinder and the outer cylinder to serve as a cooling passage through which a refrigerant passes, and the outer cylinder and the inner cylinder are diffusion bonded through webs that are side walls of the groove. The combustion chamber of a rocket engine. 2. A groove is provided on the inner cylinder side of the surface where the inner cylinder and the outer cylinder made of superalloy contact, and a plating layer of the same type as the inner cylinder material is provided on the inner surface of the outer cylinder, and the side wall of the groove of the inner cylinder is provided. The combustion chamber for a rocket engine according to claim 1, wherein the outer cylinder and the inner cylinder are diffusion-bonded through the web and the plating layer. 3. It has an inner cylinder and an outer cylinder whose cross sections are concentric,
In the method for manufacturing a combustion chamber of a rocket engine, a groove is provided on at least one of the contact surfaces of the inner cylinder and the outer cylinder to form a cooling passage through which a refrigerant passes. A method for manufacturing a combustion chamber for a rocket engine, which comprises vacuum-sealing the space between the inner and outer cylinders, then subjecting them to hot isostatic pressure processing to diffusion-bond the inner and outer cylinders, and removing the heat-resistant soluble core.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP15469689A JPH0323352A (en) | 1989-06-19 | 1989-06-19 | Combustion chamber for rocket engine and manufacture thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP15469689A JPH0323352A (en) | 1989-06-19 | 1989-06-19 | Combustion chamber for rocket engine and manufacture thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0323352A true JPH0323352A (en) | 1991-01-31 |
Family
ID=15589948
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP15469689A Pending JPH0323352A (en) | 1989-06-19 | 1989-06-19 | Combustion chamber for rocket engine and manufacture thereof |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0323352A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008128816A (en) * | 2006-11-21 | 2008-06-05 | Tohoku Univ | Non-destructive inspection device by potential difference method, and measurement method of non-destructive inspection using it |
| CN113172265A (en) * | 2021-04-15 | 2021-07-27 | 西安航天动力试验技术研究所 | Anti-cavity-crossing high-temperature gas generation device body and machining method thereof |
| CN114439652A (en) * | 2021-12-29 | 2022-05-06 | 北京航天动力研究所 | Thermal protection enhancement mode 3D prints spray tube extension |
-
1989
- 1989-06-19 JP JP15469689A patent/JPH0323352A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008128816A (en) * | 2006-11-21 | 2008-06-05 | Tohoku Univ | Non-destructive inspection device by potential difference method, and measurement method of non-destructive inspection using it |
| CN113172265A (en) * | 2021-04-15 | 2021-07-27 | 西安航天动力试验技术研究所 | Anti-cavity-crossing high-temperature gas generation device body and machining method thereof |
| CN114439652A (en) * | 2021-12-29 | 2022-05-06 | 北京航天动力研究所 | Thermal protection enhancement mode 3D prints spray tube extension |
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