JPH1018911A - Flow passage forming method - Google Patents
Flow passage forming methodInfo
- Publication number
- JPH1018911A JPH1018911A JP8171953A JP17195396A JPH1018911A JP H1018911 A JPH1018911 A JP H1018911A JP 8171953 A JP8171953 A JP 8171953A JP 17195396 A JP17195396 A JP 17195396A JP H1018911 A JPH1018911 A JP H1018911A
- Authority
- JP
- Japan
- Prior art keywords
- base material
- flow passage
- outer layer
- forming method
- layer
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、母材に流体の流通
路を形成する方法に関し、特に、ロケットエンジンやジ
ェットエンジンなどに冷却液などの流通路を形成する際
に適用すると有効である。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method of forming a fluid flow passage in a base material, and is particularly effective when applied to a flow passage for a coolant or the like in a rocket engine or a jet engine.
【０００２】[0002]
【従来の技術】ロケットエンジンやジェットエンジンな
どは、燃焼室を冷却するために、液体水素などの冷却液
を流通させる流通路が形成されている。このような流通
路は、図４に示すように、銅合金などからなる母材１の
表面に凹状の溝１ａを機械加工（図４（ａ））し、当該
溝１ａにワックス２を充填（図４（ｂ））した後、当該
母材１の表面をめっき処理して当該表面に銅の外層３を
形成（図４（ｃ））したら、当該母材１を加熱して上記
ワックス２を溶融させて除去する（図４（ｄ））ことに
より、冷却液の流通方向と直交する方向の断面形状が略
ロ型となるように形成されている。2. Description of the Related Art In a rocket engine, a jet engine, and the like, a flow passage through which a cooling liquid such as liquid hydrogen flows is formed in order to cool a combustion chamber. As shown in FIG. 4, such a flow path is formed by machining a concave groove 1a on the surface of a base material 1 made of a copper alloy or the like (FIG. 4A), and filling the groove 1a with wax 2 (FIG. 4A). 4B), after plating the surface of the base material 1 to form an outer copper layer 3 on the surface (FIG. 4C), the base material 1 is heated to remove the wax 2. By melting and removing (FIG. 4D), the cross-sectional shape in the direction orthogonal to the flowing direction of the coolant is formed to be substantially rectangular.
【０００３】[0003]
【発明が解決しようとする課題】前述したようにして母
材１に流通路１ｂを形成する方法では、比較的肉厚の大
きい（約２ｍｍ）外層３をめっき処理により形成してい
るため、当該外層３の形成に多大な時間がかかってしま
い、製作効率が非常に悪かった。In the method of forming the flow passage 1b in the base material 1 as described above, the outer layer 3 having a relatively large thickness (about 2 mm) is formed by plating. It took a lot of time to form the outer layer 3, and the production efficiency was very poor.
【０００４】[0004]
【課題を解決するための手段】前述した課題を解決する
ための、本発明による流通路形成方法は、母材に凹状の
溝を形成し、当該溝に水溶性の中子を充填した後、当該
母材に外層を高圧・高速フレームによる溶射で形成した
ら、上記中子を水に溶解させて除去することにより、当
該母材に流体の流通路を形成することを特徴とする。According to the present invention, there is provided a method of forming a flow passage, comprising: forming a concave groove in a base material; filling the groove with a water-soluble core; When an outer layer is formed on the base material by thermal spraying using a high-pressure / high-speed frame, the core is dissolved in water and removed to form a fluid flow passage in the base material.
【０００５】上述した流通路形成方法においては、前記
中子の充填を行った後、前記母材にろう材を溶射してか
ら前記外層の形成を行い、加熱処理してから前記中子の
除去を行うようにしたことを特徴とする。[0005] In the above-described flow passage forming method, after the core is filled, the outer layer is formed by spraying a brazing filler metal on the base material, and the core is removed after heat treatment. Is performed.
【０００６】上述した流通路形成方法においては、前記
ろう材の溶射を高圧・高速フレームで行うことを特徴と
する。In the above-described flow passage forming method, the spraying of the brazing material is performed by a high-pressure, high-speed frame.
【０００７】[0007]
【発明の実施の形態】本発明による流通路成形方法の各
実施の形態を各図面を用いて以下に説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of the flow passage forming method according to the present invention will be described below with reference to the drawings.
【０００８】［第一番目の実施の形態］本実施の形態
は、純ニッケルからなる母材にハステロイ合金からなる
外層を設けて流通路を形成する場合であり、ロケットエ
ンジンに適用すると有効である。その手順を図１を用い
て説明する。[First Embodiment] This embodiment is a case where a flow passage is formed by providing an outer layer made of a Hastelloy alloy on a base material made of pure nickel, and is effective when applied to a rocket engine. . The procedure will be described with reference to FIG.
【０００９】純ニッケルからなる母材１１の表面に凹状
の溝１１ａを機械加工（図１（ａ））し、アルミナと燐
酸三カリとを混合した水溶性の中子１２を上記溝１１ａ
に充填（図１（ｂ））した後、当該母材１１の表面にＮ
ｉろう材（ＢＮｉ−１）を高速・高圧フレーム（High P
ressure/High Velocity of Flame :以下、ＨＰ／ＨＶＯ
Ｆと記す）により溶射してろう材層１３を形成（図１
（ｃ））し、次に、ハステロイ（Hastelloy ）合金の粉
末をＨＰ／ＨＶＯＦにより溶射して外層１４（約２ｍ
ｍ）を形成（図１（ｄ））し、続いて、当該母材１１を
加熱処理（１１００℃×５ｈ）して上記外層１４を焼結
して緻密化させると共に上記ろう材層１３により母材１
１と外層１４とをろう付したら、母材１１を水に浸漬し
て前記中子１２を溶解させて除去（図１（ｅ））するこ
とにより、冷却液の流通方向と直交する方向の断面形状
が略ロ型をなす流通路１１ｂを母材１１に形成する。A concave groove 11a is machined on the surface of a base material 11 made of pure nickel (FIG. 1A), and a water-soluble core 12 mixed with alumina and potassium phosphate is inserted into the groove 11a.
After filling (FIG. 1 (b)), N
i brazing material (BNi-1) with high-speed, high-pressure frame (High P
ressure / High Velocity of Flame: HP / HVO
F) to form a brazing material layer 13 (FIG. 1).
(C)) Then, a powder of Hastelloy alloy is thermally sprayed by HP / HVOF to form the outer layer 14 (about 2 m).
m) (FIG. 1 (d)). Subsequently, the base material 11 is subjected to a heat treatment (1100 ° C. × 5 h) to sinter and densify the outer layer 14 and to form the base material by the brazing material layer 13. Lumber 1
1 and the outer layer 14, the base material 11 is immersed in water to dissolve and remove the core 12 (FIG. 1 (e)). A flow passage 11b having a substantially rectangular shape is formed in the base material 11.
【００１０】上記ＨＰ／ＨＶＯＦによる溶射は、粉末の
溶射材料を高速・高圧の燃焼ガスで溶融させながら母材
に噴き付けるため、溶射材料の粒子速度が非常に速く
（約９９０〜１１７０ｍ／ｓ）、溶射被膜を厚く（約５
〜６ｍｍ）形成することができる。[0010] In the thermal spraying using the HP / HVOF, since the powder thermal spray material is sprayed onto the base material while being melted by a high-speed and high-pressure combustion gas, the particle velocity of the thermal spray material is extremely high (about 990 to 1170 m / s). Thicker spray coating (about 5
６6 mm).
【００１１】したがって、このような流通路形成方法に
よれば、次のような効果を得ることができる。 （１）ＨＰ／ＨＶＯＦによる溶射で外層１４を形成する
ので、当該外層１４を短時間で厚肉にすることができ
る。 （２）中子１２が水溶性であるので、除去を簡単に行う
ことができる。 （３）ろう材層１３により母材１１と外層１４とをろう
付するので、母材１１と外層１４との結合力を高めるこ
とができる。 （４）加熱処理により外層１４を焼結して緻密化させる
ので、外層１４の強度を高める（１５〜２０ｋｇ／ｃｍ
2 →６０ｋｇ／ｃｍ2 ）ことができる。Therefore, according to such a flow passage forming method, the following effects can be obtained. (1) Since the outer layer 14 is formed by thermal spraying using HP / HVOF, the outer layer 14 can be made thicker in a short time. (2) Since the core 12 is water-soluble, it can be easily removed. (3) Since the base material 11 and the outer layer 14 are brazed by the brazing material layer 13, the bonding force between the base material 11 and the outer layer 14 can be increased. (4) Since the outer layer 14 is sintered and densified by the heat treatment, the strength of the outer layer 14 is increased (15 to 20 kg / cm).
2 → 60 kg / cm 2 ).
【００１２】［第二番目の実施の形態］本実施の形態
は、銅からなる母材にハステロイ合金からなる外層を設
けて流通路を形成する場合であり、ロケットエンジンに
適用すると有効である。その手順を図２を用いて説明す
る。なお、前述した実施の形態と同様な部分について
は、前述した実施の形態と同様な符号を用いることによ
り、その説明を省略する。[Second Embodiment] This embodiment is a case where a flow passage is formed by providing an outer layer made of a Hastelloy alloy on a base material made of copper, and is effective when applied to a rocket engine. The procedure will be described with reference to FIG. In addition, about the part similar to the above-mentioned embodiment, the description is abbreviate | omitted by using the same code | symbol as the above-mentioned embodiment.
【００１３】銅からなる母材２１の表面に凹状の溝２１
ａを機械加工（図２（ａ））し、アルミナと燐酸三カリ
とを混合した水溶性の中子１２を上記溝２１ａに充填
（図２（ｂ））した後、当該母材２１の表面にＡｇろう
材（ＢＡｇ−８）をＨＰ／ＨＶＯＦにより溶射してろう
材層２３を形成（図２（ｃ））し、次に、ハステロイ合
金の粉末をＨＰ／ＨＶＯＦにより溶射して外層１４（約
２ｍｍ）を形成（図２（ｄ））し、続いて、当該母材２
１を加熱処理（１１００℃×５ｈ）して上記外層１４を
焼結して緻密化させると共に上記ろう材層２３により母
材２１と外層１４とをろう付したら、母材２１を水に浸
漬して前記中子１２を溶解させて除去（図２（ｅ））す
ることにより、冷却液の流通方向と直交する方向の断面
形状が略ロ型をなす流通路２１ｂを母材２１に形成す
る。A concave groove 21 is formed on the surface of a base material 21 made of copper.
a is machined (FIG. 2A), and a water-soluble core 12 in which alumina and triphosphate are mixed is filled in the groove 21a (FIG. 2B). The Ag brazing material (BAg-8) is thermally sprayed by HP / HVOF to form a brazing material layer 23 (FIG. 2C), and then the Hastelloy alloy powder is thermally sprayed by HP / HVOF to form the outer layer 14 (FIG. 2C). (About 2 mm) (FIG. 2 (d)).
1 is heated (1100 ° C. × 5 h) to sinter and densify the outer layer 14, and when the base material 21 and the outer layer 14 are brazed by the brazing material layer 23, the base material 21 is immersed in water. By dissolving and removing the core 12 (FIG. 2 (e)), a flow passage 21b having a substantially B-shaped cross section in a direction orthogonal to the flow direction of the coolant is formed in the base material 21.
【００１４】したがって、本実施の形態では、前述した
実施の形態と同様な効果を得ることができる。Therefore, in the present embodiment, the same effect as in the above-described embodiment can be obtained.
【００１５】［第三番目の実施の形態］本実施の形態
は、ハステロイ合金からなる母材にハステロイ合金から
なる外層を設けて流通路を形成する場合であり、ジェッ
トエンジンに適用すると有効である。その手順を図３を
用いて説明する。なお、前述した実施の形態と同様な部
分については、前述した実施の形態と同様な符号を用い
ることにより、その説明を省略する。[Third Embodiment] This embodiment is a case where a flow passage is formed by providing an outer layer made of a Hastelloy alloy on a base material made of a Hastelloy alloy, and is effective when applied to a jet engine. . The procedure will be described with reference to FIG. In addition, about the part similar to the above-mentioned embodiment, the description is abbreviate | omitted by using the same code | symbol as the above-mentioned embodiment.
【００１６】ハステロイ合金からなる母材３１の表面に
凹状の溝３１ａを機械加工（図３（ａ））し、アルミナ
と燐酸三カリとを混合した水溶性の中子１２を上記溝３
１ａに充填（図３（ｂ））した後、当該母材３１の表面
にＮｉろう材（ＢＮｉ−１）をＨＰ／ＨＶＯＦにより溶
射してろう材層１３を形成（図３（ｃ））し、次に、ハ
ステロイ合金の粉末をＨＰ／ＨＶＯＦにより溶射して外
層１４（約２ｍｍ）を形成（図３（ｄ））し、続いて、
当該母材３１を加熱処理（１１００℃×５ｈ）して上記
外層１４を焼結して緻密化させると共に上記ろう材層１
３により母材３１と外層１４とをろう付したら、母材３
１を水に浸漬して前記中子１２を溶解させて除去（図３
（ｅ））することにより、冷却液の流通方向と直交する
方向の断面形状が略ロ型をなす流通路３１ｂを母材３１
に形成する。A concave groove 31a is machined (FIG. 3 (a)) on the surface of a base material 31 made of a Hastelloy alloy, and a water-soluble core 12 mixed with alumina and potassium phosphate is inserted into the groove 3a.
After filling into 1a (FIG. 3B), a Ni brazing material (BNi-1) is thermally sprayed on the surface of the base material 31 by HP / HVOF to form a brazing material layer 13 (FIG. 3C). Next, the Hastelloy alloy powder is thermally sprayed by HP / HVOF to form an outer layer 14 (about 2 mm) (FIG. 3D).
The base material 31 is subjected to a heat treatment (1100 ° C. × 5 h) to sinter and densify the outer layer 14 and the brazing material layer 1
3, the base material 31 and the outer layer 14 are brazed.
1 is immersed in water to dissolve and remove the core 12 (FIG. 3).
(E)), the flow path 31b having a substantially B-shaped cross section in a direction orthogonal to the flow direction of the coolant is formed into the base material 31.
Formed.
【００１７】したがって、本実施の形態では、前述した
実施の形態と同様な効果を得ることができる。Therefore, in the present embodiment, the same effect as in the above-described embodiment can be obtained.
【００１８】なお、前述した各実施の形態では、ろう材
層１３，２３をＨＰ／ＨＶＯＦによる溶射で形成するよ
うにしたが、一般的な他の溶射方法でろう材層を形成す
るようにしてもよい。しかしながら、ろう材層をＨＰ／
ＨＶＯＦによる溶射で形成するようにすれば、ろう材層
を厚肉に形成することができるので、母材と外層との結
合力を大きく向上させることができるようになる。In the above-described embodiments, the brazing material layers 13 and 23 are formed by thermal spraying using HP / HVOF. However, the brazing material layers are formed by other general thermal spraying methods. Is also good. However, if the brazing material layer is HP /
If the brazing material layer is formed by thermal spraying with HVOF, the brazing material layer can be formed thick, so that the bonding strength between the base material and the outer layer can be greatly improved.
【００１９】[0019]
【発明の効果】本発明の流通路形成方法によれば、母材
に流通路を短時間で形成することができるので、製作効
率を大幅に向上させることができる。According to the flow passage forming method of the present invention, the flow passage can be formed in the base material in a short time, so that the production efficiency can be greatly improved.
【図１】本発明による流通路形成方法の第一番目の実施
の形態の手順説明図である。FIG. 1 is an explanatory view of a procedure of a first embodiment of a flow passage forming method according to the present invention.
【図２】本発明による流通路形成方法の第一番目の実施
の形態の手順説明図である。FIG. 2 is an explanatory diagram of a procedure of a first embodiment of a flow passage forming method according to the present invention.
【図３】本発明による流通路形成方法の第一番目の実施
の形態の手順説明図である。FIG. 3 is an explanatory diagram of a procedure of a first embodiment of a flow passage forming method according to the present invention.
【図４】従来の流通路形成方法の手順説明図である。FIG. 4 is an explanatory view of a procedure of a conventional flow passage forming method.
１１ 母材（純ニッケル） １１ａ 溝 １１ｂ 流通路 １２ 中子 １３ ろう材層（Ｎｉ） １４ 外層 ２１ 母材（銅） ２１ａ 溝 ２１ｂ 流通路 ２３ ろう材層（Ａｇ） ３１ 母材（ハステロイ合金） ３１ａ 溝 ３１ｂ 流通路 Reference Signs List 11 base material (pure nickel) 11a groove 11b flow path 12 core 13 brazing material layer (Ni) 14 outer layer 21 base material (copper) 21a groove 21b flow path 23 brazing material layer (Ag) 31 base material (Hastelloy alloy) 31a Groove 31b Flow passage
───────────────────────────────────────────────────── フロントページの続き (72)発明者 恩田 孝 愛知県名古屋市港区大江町10番地 三菱重 工業株式会社名古屋航空宇宙システム製作 所内 (72)発明者 千田 誠 愛知県名古屋市港区大江町10番地 三菱重 工業株式会社名古屋航空宇宙システム製作 所内 ──────────────────────────────────────────────────続 き Continued on front page (72) Inventor Takashi Onda 10 Nagoya Aerospace System Works, Minato-ku, Nagoya City, Aichi Prefecture Mitsubishi Heavy Industries, Ltd. No. 10 Mitsubishi Heavy Industries, Ltd. Nagoya Aerospace System Works
Claims (3)
性の中子を充填した後、当該母材に外層を高圧・高速フ
レームによる溶射で形成したら、上記中子を水に溶解さ
せて除去することにより、当該母材に流体の流通路を形
成することを特徴とする流通路形成方法。After a concave groove is formed in a base material, and a water-soluble core is filled in the groove, an outer layer is formed on the base material by thermal spraying using a high-pressure, high-speed frame. A flow passage forming method, wherein a fluid flow passage is formed in the base material by dissolving and removing the fluid.
て、前記中子の充填を行った後、前記母材にろう材を溶
射してから前記外層の形成を行い、加熱処理してから前
記中子の除去を行うようにしたことを特徴とする流通路
形成方法。2. The flow passage forming method according to claim 1, wherein after the core is filled, a brazing material is sprayed on the base material, and then the outer layer is formed. A method of forming a flow passage, wherein the core is removed after a while.
て、前記ろう材の溶射を高圧・高速フレームで行うこと
を特徴とする流通路形成方法。3. The flow passage forming method according to claim 2, wherein the thermal spraying of the brazing material is performed by a high-pressure and high-speed frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8171953A JPH1018911A (en) | 1996-07-02 | 1996-07-02 | Flow passage forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8171953A JPH1018911A (en) | 1996-07-02 | 1996-07-02 | Flow passage forming method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH1018911A true JPH1018911A (en) | 1998-01-20 |
Family
ID=15932848
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP8171953A Withdrawn JPH1018911A (en) | 1996-07-02 | 1996-07-02 | Flow passage forming method |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH1018911A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0943795A1 (en) * | 1998-03-20 | 1999-09-22 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Production method for a regenerative heat exchange circuit for high thermal flow, especially for rocket combustion chambers |
| JP2006505691A (en) * | 2002-11-07 | 2006-02-16 | オウトクンプ オサケイティオ ユルキネン | Method for forming good contact surface on cathode support bar and support bar |
| WO2013021976A1 (en) * | 2011-08-09 | 2013-02-14 | 日本発條株式会社 | Member comprising flow path and method for producing same |
| US8999284B2 (en) | 2010-04-01 | 2015-04-07 | Omya International Ag | Process for obtaining precipitated calcium carbonate |
| TWI484557B (en) * | 2012-10-01 | 2015-05-11 | Nhk Spring Co Ltd | Member with flow path and method for manufacturing thereof |
| JP2015168856A (en) * | 2014-03-07 | 2015-09-28 | 三菱重工業株式会社 | Spray coating execution method |
| CN105592961A (en) * | 2013-06-07 | 2016-05-18 | 通用电气公司 | Hollow metal objects and methods for making the same |
| US9776884B2 (en) | 2013-08-20 | 2017-10-03 | Omya International Ag | Process for obtaining precipitated calcium carbonate |
| US20180281048A1 (en) * | 2017-04-04 | 2018-10-04 | Unison Industries, Llc | Methods of forming a heat exchanger |
-
1996
- 1996-07-02 JP JP8171953A patent/JPH1018911A/en not_active Withdrawn
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0943795A1 (en) * | 1998-03-20 | 1999-09-22 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Production method for a regenerative heat exchange circuit for high thermal flow, especially for rocket combustion chambers |
| FR2776215A1 (en) * | 1998-03-20 | 1999-09-24 | Snecma | PROCESS FOR MANUFACTURING A HIGH-THERMAL FLOW REGENERATIVE CIRCUIT, IN PARTICULAR FOR A FIREPLACE COMBUSTION CHAMBER |
| US6209199B1 (en) | 1998-03-20 | 2001-04-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation- S.N.E.C.M.A. | Method of manufacturing a high heat flux regenerative circuit, in particular for the combustion chamber of a rocket engine |
| US6516872B1 (en) | 1998-03-20 | 2003-02-11 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation -S.N.E.C.M.A. | High heat flux regenerative circuit, in particular for the combustion chamber of a rocket engine |
| JP2006505691A (en) * | 2002-11-07 | 2006-02-16 | オウトクンプ オサケイティオ ユルキネン | Method for forming good contact surface on cathode support bar and support bar |
| US8999284B2 (en) | 2010-04-01 | 2015-04-07 | Omya International Ag | Process for obtaining precipitated calcium carbonate |
| US9725329B2 (en) | 2010-04-01 | 2017-08-08 | Omya International Ag | Process for obtaining precipitated calcium carbonate |
| JP2013036101A (en) * | 2011-08-09 | 2013-02-21 | Nhk Spring Co Ltd | Member comprising flow path and method for producing the same |
| CN103717786A (en) * | 2011-08-09 | 2014-04-09 | 日本发条株式会社 | Member comprising flow path and method for producing same |
| WO2013021976A1 (en) * | 2011-08-09 | 2013-02-14 | 日本発條株式会社 | Member comprising flow path and method for producing same |
| US9453596B2 (en) | 2011-08-09 | 2016-09-27 | Nhk Spring Co., Ltd. | Member with flow passage and method for manufacturing the same |
| TWI484557B (en) * | 2012-10-01 | 2015-05-11 | Nhk Spring Co Ltd | Member with flow path and method for manufacturing thereof |
| JP2016526105A (en) * | 2013-06-07 | 2016-09-01 | ゼネラル・エレクトリック・カンパニイ | Hollow metal part and manufacturing method thereof |
| CN105592961A (en) * | 2013-06-07 | 2016-05-18 | 通用电气公司 | Hollow metal objects and methods for making the same |
| US10408083B2 (en) | 2013-06-07 | 2019-09-10 | General Electric Company | Hollow metal objects and methods for making same |
| US9776884B2 (en) | 2013-08-20 | 2017-10-03 | Omya International Ag | Process for obtaining precipitated calcium carbonate |
| US10343929B2 (en) | 2013-08-20 | 2019-07-09 | Omya International Ag | Process for obtaining precipitated calcium carbonate |
| JP2015168856A (en) * | 2014-03-07 | 2015-09-28 | 三菱重工業株式会社 | Spray coating execution method |
| US20180281048A1 (en) * | 2017-04-04 | 2018-10-04 | Unison Industries, Llc | Methods of forming a heat exchanger |
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| A300 | Withdrawal of application because of no request for examination |
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