JP2002500955A - Casting products, methods for producing castings, and molds - Google Patents
Casting products, methods for producing castings, and moldsInfo
- Publication number
- JP2002500955A JP2002500955A JP2000528386A JP2000528386A JP2002500955A JP 2002500955 A JP2002500955 A JP 2002500955A JP 2000528386 A JP2000528386 A JP 2000528386A JP 2000528386 A JP2000528386 A JP 2000528386A JP 2002500955 A JP2002500955 A JP 2002500955A
- Authority
- JP
- Japan
- Prior art keywords
- casting
- mold
- casting material
- positioning element
- area
- 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.)
- Granted
Links
- 238000005266 casting Methods 0.000 title claims abstract description 148
- 238000000034 method Methods 0.000 title description 2
- 238000004519 manufacturing process Methods 0.000 claims abstract description 9
- 239000000463 material Substances 0.000 claims description 55
- 238000002844 melting Methods 0.000 claims description 4
- 230000008018 melting Effects 0.000 claims description 4
- 230000001681 protective effect Effects 0.000 claims description 2
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 2
- 229910052721 tungsten Inorganic materials 0.000 claims description 2
- 239000010937 tungsten Substances 0.000 claims description 2
- 239000012809 cooling fluid Substances 0.000 description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 229910000601 superalloy Inorganic materials 0.000 description 4
- 229910017052 cobalt Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000005496 eutectics Effects 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C21/00—Flasks; Accessories therefor
- B22C21/12—Accessories
- B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
(57)【要約】 本発明は、少なくとも２つの空洞（１８，１９）を有し、空洞間に、特に消耗鋳型（１）の２つの鋳型範囲を離間させるために使われる位置決め要素（１２〜１６）を備えた中間壁（２１）が配置され、２つの鋳型範囲が鋳造範囲（８）を少なくとも部分的に画成する鋳造品（１７）に関する。位置決め要素（１２〜１６）は中間壁（２１）からの抜け落ちを防止する幾何形状を有している。本発明はさらに鋳型（１）ならびに鋳造品（１７）の製造方法に関する。 SUMMARY OF THE INVENTION The present invention has at least two cavities (18, 19), and positioning elements (12 to 19) used between the cavities, in particular for separating the two mold areas of the consumable mold (1). An intermediate wall (21) with 16) is arranged, wherein the two mold areas relate to a casting (17) at least partially defining a casting area (8). The positioning elements (12-16) have a geometry that prevents them from falling out of the intermediate wall (21). The invention further relates to a method for producing the mold (1) and the casting (17).
Description
【０００１】 本発明は、表面と出発部と終端部とを備え、特に消耗鋳型の２つの鋳型範囲を
離間させるために使われる位置決め要素に関する。その場合、２つの鋳型範囲は
鋳造範囲を少なくとも部分的に画成し、鋳造範囲は鋳造材料を充填される。本発
明はさらに鋳型、鋳造品ならびに鋳造品の製造方法に関する。The present invention relates to a positioning element with a surface, a starting part and a terminal part, used in particular for separating two mold areas of a consumable mold. In that case, the two mold areas at least partially define the casting area, the casting area being filled with casting material. The invention further relates to a mold, a casting and a method for producing a casting.
【０００２】 内部空洞を有する鋳造品を製造するために、ドイツ連邦共和国特許出願公開第
３３１２８６７号明細書により、外殻と鋳造中子とを有する鋳型を使用すること
が知られている。外殻は鋳造品の外形形状を規定する鋳造空間を包囲する。内部
空洞を作成するために、鋳造中子が鋳造空間内に配置され、支持部材によって外
殻から離間させられかつ位置決めされる。これによって、外殻と鋳造中子との間
に鋳造範囲が形成され、これに鋳造材料が充填される。鋳造品が２つの隣接する
内部空洞を有し、これらが鋳造材料から成る中間壁によって互いに分離される場
合、内部空洞を作成するために、鋳造空間内に配置された２つの鋳造中子が使用
される。鋳造中子はそれぞれ鋳型範囲を有し、鋳型範囲は互いに離間させられ、
それゆえ鋳造空間は鋳型範囲の間を中間壁の作成のために延びている。[0002] It is known from DE 33 12 867 A1 to use a mold having an outer shell and a casting core for producing a casting having an internal cavity. The outer shell surrounds a casting space that defines the outer shape of the casting. To create an internal cavity, a casting core is positioned in the casting space, spaced from the outer shell and positioned by a support member. This forms a casting area between the shell and the casting core, which is filled with the casting material. If the casting has two adjacent internal cavities, which are separated from one another by an intermediate wall of casting material, two casting cores arranged in the casting space are used to create the internal cavities. Is done. The casting cores each have a mold area, the mold areas are spaced apart from each other,
The casting space therefore extends between the mold areas for the creation of intermediate walls.
【０００３】 支持部材は外殻に関して鋳造中子を離間させかつ位置決めするために、ならび
に鋳型範囲を離間させかつ位置決めするために形成されている。支持部材は、鋳
型範囲に注入されると溶解し鋳造材料と化合する材料から構成されている。支持
部材は溶解によって鋳型範囲の注入の際に不安定になり、それゆえ支持部材は消
耗鋳型範囲の位置変動をもはや確実に阻止することができない。[0003] Support members are formed for spacing and positioning the casting core with respect to the shell, as well as for spacing and positioning the mold area. The support member is composed of a material that melts and mixes with the casting material when injected into the mold area. The support element becomes unstable during the injection of the mold area due to melting, so that the support element can no longer reliably prevent positional fluctuations of the consumable mold area.
【０００４】 米国特許第３５９６７０３号明細書および米国特許第３６６２８１６号明細書
により、鋳造品を製造するために、鋳造空間内に内部空洞を作成するための鋳造
中子を保持し外殻から離間させる支柱を有する鋳型を使用することが知られてい
る。鋳型及び支柱はセラミック材料から構成されている。鋳造範囲に注入された
後、外殻と鋳造中子とが除かれ、壊される。技術的な理由から支柱は一緒に除か
れる。というのは、支柱は外殻及び鋳造中子と同一材料から構成されているから
である。これによって、鋳型を用いて製造可能な鋳造品は内部空洞への通路を形
成する穴を有することになる。鋳造品の内部空洞が冷却流体を導くために使用さ
れる場合、不所望に冷却流体はその穴を通って内部空洞から外部へ流出すること
ができる。さらに、支柱を金属製円筒状ピンとして形成し、このピンが外殻内へ
突入し、鋳造中子のところで終わるようにすることも知られている。外殻及び鋳
造中子は鋳造品の製造後に除かれて壊されるので、それらは消耗外殻及び消耗鋳
造中子と呼ばれている。According to US Pat. Nos. 3,596,703 and 3,662,816, a casting core for creating an internal cavity in a casting space is held and separated from an outer shell to produce a casting. It is known to use a mold with struts. The mold and the struts are made of a ceramic material. After being injected into the casting area, the shell and the casting core are removed and broken. The struts are removed together for technical reasons. This is because the struts are made of the same material as the shell and the casting core. This results in a casting that can be manufactured using a mold having holes that form a passage to the internal cavity. If the internal cavity of the casting is used to conduct a cooling fluid, the cooling fluid can undesirably flow out of the internal cavity through the holes. It is also known to form the struts as metal cylindrical pins, which project into the outer shell and terminate at the casting core. Because the shell and the casting core are removed and broken after the manufacture of the casting, they are called consumable shells and consumable casting cores.
【０００５】 ドイツの雑誌“ギーセライ−プラクシス”（第１８号、１９６０年発行）に掲
載されたフリッツ・パシュケの論文「中子支えを用いた経験及びその使用」（第
３２７頁〜第３３０頁）には、例えば厚肉の鋳物を製造ずるために重い鋳造中子
を支持するいわゆる二重中子支えが記載されている。この二重中子支えはこの場
合外殻と内部の鋳造中子との間に滑り支持を生ぜしめる。この場合、二重中子支
えの設置目的は、その際に発生する高い圧力に耐えると共に鋳造時に発生する揚
力にも耐えることである。[0005] Fritz Paschke's dissertation, "Experience and Use of Core Support and Its Use", published in the German magazine "Gieserai-Praxis" (No. 18, 1960) (pp. 327-330) Describes, for example, a so-called double core support for supporting a heavy casting core in order to produce a thick casting. This double core support then creates a sliding support between the shell and the inner cast core. In this case, the purpose of installing the double core support is to withstand the high pressure generated at that time and to withstand the lift generated at the time of casting.
【０００６】 本発明の課題は、鋳型範囲、特に消耗鋳型範囲を離間させるために使われる位
置決め要素を備えた鋳型を提供することにある。別の課題は、鋳造品ならびに鋳
造品の製造方法を提供することにある。[0006] It is an object of the present invention to provide a mold with a positioning element which is used for separating a mold area, in particular a consumable mold area. Another object is to provide a casting and a method of manufacturing the casting.
【０００７】 本発明によれば、位置決め要素を備えた鋳型に関する課題は、鋳造範囲に鋳造
材料を注入した後この鋳造材料からの抜け落ちを防止する幾何形状を有する請求
項１の前文に記載の位置決め要素を備えた鋳型によって解決される。[0007] According to the invention, the problem with a mold having a positioning element is that the casting has a geometry which prevents the casting material from falling out of the casting material after it has been poured into the casting area. Solved by a mold with elements.
【０００８】 複数の隣接する内部空洞を備えた又は１つの内部空洞に互いに結合された複数
の内部空洞範囲を備えた鋳造品を製造するために、少なくとも１つの鋳造中子又
は鋳造中子構成体を備えた鋳型が使用される。鋳造中子はそれぞれ内側鋳型範囲
を規定する。外殻は、一部品から成ろうと多分割部品から成ろうと、外側鋳型範
囲を形成する。鋳造品の内部空洞ないしは内部空洞範囲は中間壁によって互いに
分離され、例えば鋳造品を冷却する冷却流体を導くために使われる。以下におい
て、鋳造品を製造するために使用された後に壊されて捨てられる鋳造中子又は鋳
造中子構成体の鋳型範囲は消耗鋳型範囲と呼ばれる。１つの位置決め要素又は複
数の位置決め要素が鋳造中子又は鋳造中子構成体の固定的な位置決め（固定）を
行うために使われ、それによって注入時にこれらの中子部品が相互に移動するの
が回避される。[0008] At least one casting core or casting core arrangement for producing a casting with a plurality of adjacent internal cavities or with a plurality of internal cavity areas coupled to one internal cavity to one another. A mold with is used. Each casting core defines an inner mold area. The shell forms an outer mold area, whether of one piece or of multiple pieces. The internal cavities or areas of the internal cavities of the casting are separated from one another by intermediate walls and are used, for example, for conducting a cooling fluid for cooling the casting. In the following, the mold area of a casting core or casting core structure that is broken and discarded after it has been used to produce a casting is referred to as a consumable mold area. One or more positioning elements are used to perform a fixed positioning (fixation) of the casting core or casting core structure, so that these core parts move relative to each other during injection. Be avoided.
【０００９】 鋳型範囲（特に消耗鋳型範囲）間の鋳造空間は中間壁を作成するために使われ
る。鋳造範囲に鋳造材料を注入した後、位置決め要素はその出発部とその終端部
との間が鋳造材料によって取り囲まれる。位置決め要素の幾何形状によって中間
壁からの抜け落ちが確実に回避され、それにより中間壁には穴が形成されない。
鋳造材料と位置決め要素の表面との間にはせいぜい非常に僅かな隙間しか残され
ない。位置決め要素は優れた幾何形状によって中間壁内に保持され、内部空洞範
囲を通って冷却流体を導く際に冷却流体はひょっとしたら残されているその隙間
を通って僅かしか流出しない。[0009] The casting space between the mold areas (especially the consumable mold areas) is used to create intermediate walls. After pouring the casting material into the casting area, the positioning element is surrounded by the casting material between its start and its end. The geometry of the locating element ensures that dropout from the intermediate wall is avoided, so that no holes are formed in the intermediate wall.
At most very little clearance is left between the casting material and the surface of the positioning element. The locating element is held in the intermediate wall by a good geometry, so that when conducting the cooling fluid through the interior cavity area, the cooling fluid only escapes a small amount through the remaining gaps.
【００１０】 位置決め要素の幾何形状が出発部と終端部との間に少なくとも１つの局部的な
極部を備えた表面輪郭線を有していると好ましい。出発部及び終端部がそれぞれ
径大部を有していると好ましい。他の優れた実施態様においては、位置決め要素
が出発部と終端部との間に追加的に又は代替的に径大部を有する。[0010] Preferably, the geometry of the positioning element has a surface contour with at least one local pole between the start and the end. Preferably, the starting portion and the terminal portion each have a large diameter portion. In another advantageous embodiment, the locating element additionally or alternatively has a larger diameter between the start and the end.
【００１１】 他の優れた実施態様においては、位置決め要素が鋳造材料より高い融点を有す
る母材から形成される。母材として例えばニッケル基超合金又はコバルト基超合
金が使われる。この場合には鋳造材料を鋳造範囲に注入する際に母材の溶解が起
らない。鋳造中子（特に消耗鋳造中子）の位置変化又は鋳造中子（特に消耗鋳造
中子）の形状変化はこれによって回避される。さらに母材が金属、特にタングス
テンであると好ましい。In another preferred embodiment, the positioning element is formed from a base material having a higher melting point than the casting material. For example, a nickel-based superalloy or a cobalt-based superalloy is used as a base material. In this case, the base material does not melt when the casting material is poured into the casting range. A change in the position of the casting core (especially the consumable casting core) or a change in the shape of the casting core (especially the consumable casting core) is thereby avoided. Further, the base material is preferably a metal, particularly tungsten.
【００１２】 位置決め要素の表面に保護膜、特に酸化膜が設けられていると好ましい。これ
によって、特に母材の溶解により及び鋳造材料との混合により鋳造材料が母材と
化合して共晶体を形成することが、完全に回避できない場合でも、少なくとも明
らかに困難になる。Preferably, a protective film, particularly an oxide film, is provided on the surface of the positioning element. This makes it at least clearly difficult, if not completely unavoidable, for the casting material to combine with the matrix to form a eutectic, especially by melting of the matrix and by mixing with the casting material.
【００１３】 位置決め要素がタービン翼の製造に使われる２つの鋳型範囲（特に消耗鋳型範
囲）を離間させるために使用されると好ましい。さらに、鋳型範囲（特に消耗鋳
型範囲）がタービン翼内に少なくとも１つの内部空洞を作成するために使用され
ると好ましい。[0013] Preferably, a positioning element is used to separate the two mold sections (especially the consumable mold section) used in the manufacture of the turbine blade. Furthermore, it is preferred if the mold area, especially the consumable mold area, is used to create at least one internal cavity in the turbine blade.
【００１４】 位置決め要素の出発部及び／又は終端部がそれぞれ鋳型範囲（特に消耗鋳型範
囲）内に突入していると好ましい。これによって位置決め要素が鋳型範囲内に保
持され、ずり落ちを防止される。[0014] Preferably, the starting part and / or the end part of the positioning element each project into the mold area, in particular the consumable mold area. This keeps the positioning element in the mold area and prevents it from slipping off.
【００１５】 鋳造品に関する課題は、中間壁が位置決め要素を有し、この位置決め要素が少
なくとも部分的に鋳造材料によって取り囲まれ、鋳造材料からの抜け落ちを防止
する幾何形状を有している請求項９の前文に記載された鋳造品、特にガスタービ
ン用のタービン翼によって解決される。この場合、鋳造品は鋳型の構成に関する
実施態様によって形成される位置決め要素を有している。A problem with the casting is that the intermediate wall has a positioning element, the positioning element being at least partially surrounded by the casting material and having a geometry that prevents falling out of the casting material. The invention is solved by a casting described in the preamble of the above paragraph, in particular by a turbine blade for a gas turbine. In this case, the casting has locating elements formed by the embodiment relating to the construction of the mold.
【００１６】 鋳造品の製造方法に関する課題は、鋳型範囲（特に消耗鋳型範囲）を用いて注
入可能な鋳造範囲が少なくとも部分的に画成され、鋳造範囲には鋳型範囲を互い
に離間させる位置決め要素が配置される請求項１０の前文に基づく方法によって
解決される。鋳造範囲は鋳造材料を注入され、鋳造材料の硬化後に鋳造材料が位
置決め要素を少なくとも部分的に取り囲む。位置決め要素は鋳造材料からの抜け
落ちを阻止する幾何形状を有している。The problem with the method of manufacturing a casting is that the casting area, in particular the consumable mold area, is at least partially defined by the casting area, and the casting area has positioning elements which separate the casting areas from one another. It is solved by a method according to the preamble of claim 10 to be arranged. The casting area is filled with a casting material, which after curing of the casting material at least partially surrounds the positioning element. The positioning element has a geometry that prevents falling out of the casting material.
【００１７】 図面に示された実施例に基づいて、位置決め要素、鋳型、鋳造品及び鋳造品の
製造方法を詳細に説明する。The positioning element, the mold, the casting and the method of manufacturing the casting are described in detail with reference to the exemplary embodiments shown in the drawings.
【００１８】 図面には説明のために使用されている構造的及び機能的な特徴が概略的に示さ
れ、部分的に縮尺通りではない。 図１はタービン翼用の鋳型の横断面図、 図２は鋳型の横断面図、 図３はガスタービンのタービン翼の断面図、 図４は位置決め要素の一例の縦断面図、 図５は位置決め要素の他の例の縦断面図を示す。 全ての図面における参照符号はそれぞれ同一の意味を有している。The drawings schematically show structural and functional features used for description, and are not necessarily to scale. 1 is a cross-sectional view of a mold for a turbine blade, FIG. 2 is a cross-sectional view of a mold, FIG. 3 is a cross-sectional view of a turbine blade of a gas turbine, FIG. 4 is a vertical cross-sectional view of an example of a positioning element, and FIG. FIG. 4 shows a longitudinal section of another example of the element. The reference numerals in all the drawings have the same meaning.
【００１９】 図１はガスタービン翼を製造するために中心軸線２４に沿って延びている鋳型
１の横断面図を示す。鋳型１は鋳造空間７を包囲する外殻２を有し、鋳造空間７
内には３つの鋳造中子３，４，５が支持要素６によって位置決めされ、外殻２か
ら離間させられている。鋳造中子３，４，５を中心軸線２４に関する鋳造範囲８
の外で例えば適当な懸架装置によって外殻２に対して離間させることも同様に可
能である。この場合、鋳造中子３，４，５は一端部が固定され、他端部が可動に
なっている。これによって、外殻２と鋳造中子３，４，５との間に鋳造範囲８が
形成される。外殻２は外側鋳型範囲を形成している。鋳造中子３，４，５はそれ
ぞれ内側鋳型範囲９．１０，１１を形成し、これらは位置決め要素１２〜１６に
よって互いに離間させられている。位置決め要素１２〜１６は母材３５（図４又
は図５参照）から構成されている。支持要素６はそれぞれ外殻２内に突入し、位
置決め要素１３，１４は鋳型範囲９，１０内に突入し、位置決め要素１６は鋳型
範囲１０，１１内に突入している。FIG. 1 shows a cross-sectional view of a mold 1 extending along a central axis 24 for manufacturing gas turbine blades. The mold 1 has an outer shell 2 surrounding a casting space 7,
Inside, three casting cores 3, 4, 5 are positioned by a support element 6 and are spaced from the shell 2. The casting cores 3, 4, and 5 are cast in a casting range 8 with respect to the central axis 24.
It is likewise possible to separate the outer shell 2 from the outer shell 2 by a suitable suspension, for example. In this case, the casting cores 3, 4, and 5 have one end fixed and the other end movable. As a result, a casting range 8 is formed between the outer shell 2 and the casting cores 3, 4, and 5. The shell 2 forms an outer mold area. The casting cores 3, 4, 5 respectively form inner mold areas 9.10, 11 which are separated from one another by positioning elements 12-16. The positioning elements 12 to 16 are composed of a base material 35 (see FIG. 4 or 5). The support elements 6 each extend into the shell 2, the positioning elements 13, 14 extend into the mold areas 9, 10, and the positioning elements 16 extend into the mold areas 10, 11.
【００２０】 鋳型１を用いて鋳造品１７（図３参照）を製造する際、鋳造範囲８は溶解した
鋳造材料２３、例えばニッケル基超合金又はコバルト基超合金を注入される。鋳
造材料２３は鋳造範囲８内で支持要素６及び位置決め要素１２〜１６を取り囲む
。鋳造材料２３の硬化後、鋳造中子３〜５が取り除かれる。位置決め要素１２〜
１６は、鋳造材料２３が母材３５と溶け合わない場合でも、鋳造材料２３からの
抜け落ちを阻止する幾何形状を有している。When producing the casting 17 (see FIG. 3) using the mold 1, the casting area 8 is filled with a molten casting material 23, for example a nickel-based superalloy or a cobalt-based superalloy. The casting material 23 surrounds the support element 6 and the positioning elements 12 to 16 in the casting area 8. After the casting material 23 has hardened, the casting cores 3 to 5 are removed. Positioning element 12 ~
16 has a geometrical shape that prevents the casting material 23 from falling off from the casting material 23 even when the casting material 23 does not melt with the base material 35.
【００２１】 図２には、外殻２と、その中に配置された鋳造中子３，４，５とを備え、鋳造
品１７、特にタービン翼を製造するための鋳型１が強く簡単化されて概略的に示
されている。隣接する鋳造中子対３，４及び４，５はそれぞれ位置決め要素１３
によって互いに固定されている。外殻２と鋳造中子３，４，５との間には固定ピ
ン又は位置決め要素は設けられていない。寧ろ、鋳造中子３，４，５は固定端部
４２が強固に外殻２に結合され、中心軸線２４に沿って固定端部４２とは反対側
に位置する解放端部４３が少なくとも１つの解放側支持部（すべり支持部）４１
によって移動可能に支持されている。これによって、鋳造材料２３を外殻２と鋳
造中子３，４，５との間に形成された鋳造範囲８内に注ぎ込む際、鋳造中子３，
４，５が互いに横方向にかつ外殻２に向かって移動しないことが保証される。FIG. 2 shows an outer shell 2 and casting cores 3, 4 and 5 arranged therein, with which the casting 1, in particular the mold 1 for producing turbine blades, is strongly simplified. Are shown schematically. Adjacent casting core pairs 3, 4 and 4, 5 each have a positioning element 13
Are fixed to each other. No fixing pins or positioning elements are provided between the shell 2 and the casting cores 3, 4, 5. Rather, the casting cores 3, 4, 5 have a fixed end 42 firmly connected to the shell 2 and at least one open end 43 located opposite the fixed end 42 along the central axis 24. Release side support (slip support) 41
It is movably supported by. Accordingly, when the casting material 23 is poured into the casting area 8 formed between the outer shell 2 and the casting cores 3, 4, and 5, the casting core 3,
It is ensured that the 4, 5 do not move laterally with respect to each other and towards the shell 2.
【００２２】 図３は鋳型１を用いて製造可能な鋳造品１７、特にタービン翼１７の横断面図
を示す。タービン翼１７は３つの空洞１８〜２０を有している。これらは鋳造品
１７を製造する際に鋳造中子３，４，５によって規定される。空洞１８，１９間
並びに空洞１９．２０間にはそれぞれ中間壁２１，２２が存在している。中間壁
２１には位置決め要素１２〜１４が設けられており、これらはその幾何形状に基
づいて鋳造材料２３を用いて形成された中間壁２１から抜け落ちない。中間壁２
２は位置決め要素１５，１６を有し、これらも同様に（折り曲げ部、穴を有する
）その幾何形状に基づいて中間壁２３から抜け落ちない。FIG. 3 shows a cross-sectional view of a casting 17, in particular a turbine blade 17, which can be manufactured using the mold 1. The turbine blade 17 has three cavities 18 to 20. These are defined by the casting cores 3, 4, and 5 when the casting 17 is manufactured. Intermediate walls 21, 22 are present between the cavities 18, 19 and between the cavities 19.20, respectively. The intermediate wall 21 is provided with positioning elements 12 to 14 which do not fall off from the intermediate wall 21 formed with the casting material 23 on the basis of its geometry. Intermediate wall 2
2 has positioning elements 15, 16 which likewise do not fall off the intermediate wall 23 based on their geometry (with folds, holes).
【００２３】 図４には位置決め要素１４が拡大して示されている。この位置決め要素は出発
部２５と、終端部２６と、表面輪郭線２８を有する表面２７とによってほぼ円筒
状に形成されている。表面輪郭線２８は出発部２５と終端部２６との間に局部的
な極部（すなわち出発部２５と終端部２６との間に設けられた径大部３０によっ
て形成された極大部）２９を有している。これによって、位置決め要素１４は出
発部２５と終端部２６との間を鋳造材料２３によって取り囲まれた後には鋳造材
料２３からの抜け落ちを防止される。FIG. 4 shows the positioning element 14 in an enlarged manner. This positioning element is formed substantially cylindrical by a starting part 25, an end part 26 and a surface 27 having a surface contour 28. The surface contour 28 forms a local pole part 29 between the start part 25 and the end part 26 (that is, a maximum part formed by the large diameter part 30 provided between the start part 25 and the end part 26). Have. This prevents the positioning element 14 from falling out of the casting material 23 after being surrounded by the casting material 23 between the starting part 25 and the terminal part 26.
【００２４】 図５には位置決め要素１３が拡大して示されている。この位置決め要素は出発
部２５と終端部２６とにそれぞれ径大部３１，３２を有している。これによって
、出発部２５と終端部２６との間の表面輪郭線２８は局部的な極部（すなわち極
小部）３３を有する。FIG. 5 shows the positioning element 13 in an enlarged manner. This positioning element has large diameter parts 31 and 32 at the start part 25 and the end part 26, respectively. Thereby, the surface contour 28 between the starting part 25 and the terminal part 26 has a local pole part (that is, a minimum part) 33.
【００２５】 本発明は、出発部と終端部とを備え、出発部と終端部との間を鋳造材料によっ
て取り囲まれた後には鋳造材料からの抜け落ちを阻止する幾何形状を有する位置
決め要素を特徴とする。位置決め要素は２つの鋳型範囲（鋳造中子、鋳造中子領
域）相互を固定するのに使われる。The invention features a locating element having a starting portion and a terminating portion, the locating element having a geometry that prevents falling out of the casting material after being surrounded by the casting material between the starting portion and the terminating portion. I do. The positioning element is used to fix the two mold areas (cast core, cast core area) to each other.
【図１】 タービン翼用の鋳型の横断面図FIG. 1 is a cross-sectional view of a mold for a turbine blade.
【図２】 鋳型の横断面図FIG. 2 is a cross-sectional view of a mold.
【図３】 ガスタービンのタービン翼の断面図FIG. 3 is a sectional view of a turbine blade of a gas turbine.
【図４】 位置決め要素の一例の縦断面図FIG. 4 is a longitudinal sectional view of an example of a positioning element.
【図５】 位置決め要素の他の例の縦断面図FIG. 5 is a longitudinal sectional view of another example of a positioning element.
１ 鋳型 ２ 外殻 ３，４，５ 鋳造中子 ６ 支持要素 ７ 鋳造空間 ８ 鋳造範囲 ９，１０，１１ 内部鋳型範囲 １２〜１６ 位置決め要素 １７ 鋳造品 ２３ 鋳造材料 ２４ 中心軸線 ３５ 母材 DESCRIPTION OF SYMBOLS 1 Mold 2 Outer shell 3,4,5 Casting core 6 Supporting element 7 Casting space 8 Casting range 9,10,11 Inner mold range 12-16 Positioning element 17 Casting product 23 Casting material 24 Center axis 35 Base material
Claims (10)
る外側鋳型範囲（４０）を備え、内側鋳型範囲が位置決め要素（１２〜１６）に
よって互いに離間させられそれにより形成された鋳造範囲（８）を少なくとも部
分的に画成し、鋳造範囲（８）が鋳造材料（２３）を注入される、特にタービン
翼（１７）を製造するための鋳型（１）において、位置決め要素（１２〜１６）
が鋳造材料（２３）の注入後にこの鋳造材料によって少なくとも部分的に取り囲
まれ、鋳造材料（２３）からの抜け落ちを防止する幾何形状を有していることを
特徴とする鋳型（１）。1. An outer mold area (40) surrounding at least two inner mold areas (9, 10, 11), the inner mold areas being separated from one another by positioning elements (12-16) and formed thereby. The casting area (8) is at least partially defined and the casting area (8) is filled with the casting material (23), in particular in the mold (1) for producing turbine blades (17). (12-16)
(1) characterized in that it has a geometry which is at least partially surrounded by the casting material (23) after the casting material (23) has been poured and which prevents it from falling out of the casting material (23).
２６）との間に少なくとも１つの局部的な極部（２９）を持つ表面輪郭線（２８
）を備えた幾何形状を有していることを特徴とする請求項１記載の鋳型（１）。2. A positioning element (12-16) comprising a starting part (25) and a terminating part (12).
26) with at least one local pole (29).
The mold (1) according to claim 1, characterized in that it has a geometry with (1).
２６）はそれぞれ径大部（３１，３２）を有していることを特徴とする請求項１
又は２記載の鋳型（１）。3. The start (25) and the end (25) of the positioning elements (12-16).
26) Each of the (26) has a large diameter portion (31, 32).
Or the template (1) according to 2.
６）との間に径大部（３０）を有していることを特徴とする請求項２記載の鋳型
（１）。4. A positioning element (12-16) comprising a starting part (25) and an end part (2).
The mold (1) according to claim 2, characterized in that it has a large-diameter portion (30) between the mold (6).
母材（３５）が鋳造材料（２３）より高い融点を有していることを特徴とする請
求項１乃至４の１つに記載の鋳型（１）。5. The positioning element (12-16) is formed from a base material (35),
The mold (1) according to one of the claims 1 to 4, characterized in that the base material (35) has a higher melting point than the casting material (23).
であることを特徴とする請求項５記載の鋳型（１）。6. The mold (1) according to claim 5, wherein the base material (35) of the positioning elements (12-16) is tungsten.
に酸化膜が設けられていることを特徴とする請求項６記載の鋳型（１）。7. The mold (1) according to claim 6, characterized in that a protective film, in particular an oxide film, is provided on the surface (27) of the positioning element (12-16).
６）とを有し、出発部（２５）及び／又は終端部（２６）がそれぞれの鋳型範囲
（９，１０）内に突入していることを特徴とする請求項１乃至７の１つに記載の
鋳型（１）。8. A positioning element (12-16) comprising a starting part (25) and a terminating part (2).
6), wherein the starting part (25) and / or the end part (26) extend into the respective mold area (9, 10). The described mold (1).
材料（２３）から成る中間壁（２１）が配置され、中間壁（２１）が位置決め要
素（１２〜１６）を有し、この位置決め要素は少なくとも部分的に鋳造材料（２
３）によって取り囲まれ、鋳造材料（２３）からの抜け落ちを防止する幾何形状
を有している鋳造品（１７）、特にタービン翼（１７）。9. An intermediate wall (21) comprising at least two cavities (18, 19) and comprising a casting material (23) arranged between the cavities, the intermediate wall (21) being located by a positioning element (12-16). And the positioning element is at least partially at the casting material (2
A casting (17), in particular a turbine blade (17), which is surrounded by 3) and has a geometry which prevents it from falling out of the casting material (23).
造範囲（８）が少なくとも部分的に画成され、鋳造範囲（８）には２つの内側鋳
型範囲（９，１０，１１）を互いに離間させる位置決め要素（１２〜１６）が配
置され、鋳造範囲（８）が鋳造材料（２３）を注入され、鋳造材料（２３）の硬
化後に鋳造材料（２３）が位置決め要素（１２〜１６）を少なくとも部分的に取
り囲み、位置決め要素（１２〜１６）が鋳造材料（２３）からの抜け落ちを阻止
する幾何形状を有していることを特徴とする鋳造品（１７）、特にタービン翼（
１７）の製造方法。10. An injectable casting zone (8) is at least partially defined by means of a mold zone (9, 10, 11, 40), the casting zone (8) comprising two inner mold zones (9). , 10, 11) are arranged to separate the casting material (23) from the casting area (8), and the casting material (23) is positioned after the casting material (23) has hardened. A casting (17), characterized by at least partially surrounding the element (12-16), wherein the locating element (12-16) has a geometry that prevents it from falling out of the casting material (23); Especially turbine blades (
17) The manufacturing method.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19802573 | 1998-01-23 | ||
| DE19802573.4 | 1998-01-23 | ||
| PCT/DE1999/000121 WO1999037421A1 (en) | 1998-01-23 | 1999-01-19 | Cast part, method for producing a cast part and casting mould |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2002500955A true JP2002500955A (en) | 2002-01-15 |
| JP4327351B2 JP4327351B2 (en) | 2009-09-09 |
Family
ID=7855499
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2000528386A Expired - Fee Related JP4327351B2 (en) | 1998-01-23 | 1999-01-19 | Casting product, casting method and casting mold |
Country Status (4)
| Country | Link |
|---|---|
| EP (1) | EP1049549B1 (en) |
| JP (1) | JP4327351B2 (en) |
| DE (1) | DE59904037D1 (en) |
| WO (1) | WO1999037421A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009297765A (en) * | 2008-06-16 | 2009-12-24 | Mitsubishi Heavy Ind Ltd | Core for producing turbine blade |
| US7673669B2 (en) | 2004-10-29 | 2010-03-09 | United Technologies Corporation | Investment casting cores and methods |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2874187B1 (en) * | 2004-08-16 | 2008-01-25 | Snecma Moteurs Sa | PROCESS FOR PRODUCING A TURBOMACHINE BLADE BY PERFORATED WAX MOLDING |
| EP2460604A1 (en) * | 2010-12-01 | 2012-06-06 | Siemens Aktiengesellschaft | Method and apparatus for casting a hollow component of a turbomachine |
| US9550230B2 (en) * | 2011-09-16 | 2017-01-24 | United Technologies Corporation | Mold for casting a workpiece that includes one or more casting pins |
| US10300526B2 (en) | 2014-02-28 | 2019-05-28 | United Technologies Corporation | Core assembly including studded spacer |
| FR3120807B1 (en) * | 2021-03-16 | 2023-12-01 | Safran Aircraft Engines | Lost wax casting manufacturing process |
| CN116174660B (en) * | 2023-04-25 | 2023-06-30 | 蓬莱三和铸造有限公司 | High-precision casting device for balance shaft of mine car |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1141203A (en) * | 1956-02-08 | 1957-08-28 | Von Roll Ag | Casting process for thin-walled hollow bodies and foundry hollow bodies produced by this process |
| US4487246A (en) * | 1982-04-12 | 1984-12-11 | Howmet Turbine Components Corporation | System for locating cores in casting molds |
| US4596281A (en) * | 1982-09-02 | 1986-06-24 | Trw Inc. | Mold core and method of forming internal passages in an airfoil |
| JPS60121038A (en) * | 1983-12-02 | 1985-06-28 | Mazda Motor Corp | Assembling method of casting mold |
| GB2150875B (en) * | 1983-12-07 | 1986-07-02 | Rolls Royce | Investment casting |
-
1999
- 1999-01-19 EP EP99932439A patent/EP1049549B1/en not_active Expired - Lifetime
- 1999-01-19 JP JP2000528386A patent/JP4327351B2/en not_active Expired - Fee Related
- 1999-01-19 DE DE59904037T patent/DE59904037D1/en not_active Expired - Lifetime
- 1999-01-19 WO PCT/DE1999/000121 patent/WO1999037421A1/en active IP Right Grant
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7673669B2 (en) | 2004-10-29 | 2010-03-09 | United Technologies Corporation | Investment casting cores and methods |
| JP2009297765A (en) * | 2008-06-16 | 2009-12-24 | Mitsubishi Heavy Ind Ltd | Core for producing turbine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| DE59904037D1 (en) | 2003-02-20 |
| EP1049549B1 (en) | 2003-01-15 |
| WO1999037421A1 (en) | 1999-07-29 |
| EP1049549A1 (en) | 2000-11-08 |
| JP4327351B2 (en) | 2009-09-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4637449A (en) | Component casting | |
| US6626230B1 (en) | Multi-wall core and process | |
| EP2777842B1 (en) | Cast-in cooling features especially for turbine airfoils | |
| BR102016022597A2 (en) | casting mold apparatus and method for forming a mold | |
| US5505250A (en) | Investment casting | |
| EP0105602B1 (en) | Mold core and method of forming internal passages in an airfoil | |
| EP0818256A1 (en) | Composite, internal reinforced ceramic cores and related methods | |
| US20090165988A1 (en) | Turbine airfoil casting method | |
| JP4369622B2 (en) | Multi-wall ceramic core assembly, method for manufacturing the same, and method for manufacturing blade casting having a multi-wall defining the shape of the internal cooling passage | |
| JP5511967B2 (en) | Improved method of lost wax production of an annular bladed turbomachine assembly, mold and wax mold for carrying out such a method | |
| UA77277C2 (en) | Foundry system and core made of refractory metal (variants) | |
| JP2008151129A (en) | Turbine engine component and its manufacturing method | |
| JP2003513189A (en) | Cast airfoil structure with openings that do not require plugging | |
| GB2028928A (en) | Aerofoil blade for a gas turbine engine | |
| JP2003340548A (en) | Base core and method for casting working material | |
| US10155265B2 (en) | Method for positioning core by soluble wax in investment casting | |
| GB2102317A (en) | Internally reinforced core for casting | |
| RU2745073C2 (en) | Method for the formation of dust removing holes for the turbine blade and the coupled ceramic core | |
| JP3927628B2 (en) | Turbine nozzle and its investment casting method | |
| JP2002500955A (en) | Casting products, methods for producing castings, and molds | |
| EP1419834B1 (en) | Master mould for precursor and precursor for investment casting | |
| JP2017159362A (en) | Casting with second metal component formed around first metal component using hot isostatic pressing | |
| EP3246108B1 (en) | Methods for fabricating cast components with cooling channels | |
| JPS611446A (en) | Production of piston for internal-combustion engine | |
| JP4087287B2 (en) | Manufacturing method of cylindrical product |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20051213 |
|
| A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20081222 |
|
| A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20090108 |
|
| A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20090331 |
|
| TRDD | Decision of grant or rejection written | ||
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20090512 |
|
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 |
|
| A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20090611 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120619 Year of fee payment: 3 |
|
| R150 | Certificate of patent or registration of utility model |
Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130619 Year of fee payment: 4 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| LAPS | Cancellation because of no payment of annual fees |