公开(公告)号：US4043841A

公开(公告)日：1977-08-23

申请号：US608346

申请日：1975-08-27

Applicant: Herve Bibring ,  Jean-Pierre Trottier ,  Tasadduq Khan ,  Maurice Rabinovitch ,  Jean-Francois Stohr

Inventor： Herve Bibring ,  Jean-Pierre Trottier ,  Tasadduq Khan ,  Maurice Rabinovitch ,  Jean-Francois Stohr

IPC: F01D5/28 ,  C22C19/05 ,  C22C47/00 ,  C30B21/02

CPC classification number: C22C19/056 ,  C30B21/02 ,  Y10T428/12444

Abstract: A refractory composite material usable in making gas-turbine blades for aviation applications. The composite material comprises a nickel-based superalloy matrix containing cobalt, aluminum in the form of a Ni.sub.3 Al precipitate, and tungsten, and a reinforcing phase of oriented monocrystalline niobium carbide fibers formed in situ during production, by unidirectional solidification. The composition of the composite material by weight expressed in percent is:Co -- 20-30%Cr -- 6-15%W -- 7-10%Al -- 3-6%Nb -- 4-6%C -- 0.4-0.65%Ni balance to 100.

Abstract translation: 可用于制造用于航空应用的燃气涡轮叶片的耐火复合材料。 该复合材料包括含有钴，Ni3Al沉淀形式的铝和钨的镍基超级合金基体，以及通过单向凝固在生产过程中原位形成的取向单晶碳化铌纤维的增强相。 按百分比表示的复合材料的组成为：

公开(公告)号：US5846345A

公开(公告)日：1998-12-08

申请号：US622668

申请日：1996-03-26

Applicant: Shigehisa Naka ,  Marc Thomas ,  Agnes Bachelier-Locq ,  Tasadduq Khan

Inventor： Shigehisa Naka ,  Marc Thomas ,  Agnes Bachelier-Locq ,  Tasadduq Khan

IPC: C22C14/00 ,  C22C21/00

CPC classification number: C22C14/00

Abstract: In an alloy having a Ti/Al ratio close to 52/48, good castability, by virtue of initial solidification in the .beta. phase, together with a sufficiently low density and a good oxidation resistance are obtained by introducing approximately 2 atom. % of rhenium and/or tungsten. These alloys can be used especially for the production of aeronautical turbomachine components.

Abstract translation: 在Ti / Al比接近52/48的合金中，通过引入大约2个原子可获得良好的铸造性，通过β相中的初始凝固以及足够低的密度和良好的抗氧化性。 ％的铼和/或钨。 这些合金可用于航空涡轮机组件的生产。

公开(公告)号：US4639280A

公开(公告)日：1987-01-27

申请号：US679766

申请日：1984-12-10

Applicant: Allan Fredholm ,  James H. Davidson ,  Tasadduq Khan ,  Jean-Mare C. F. Theret

Inventor： Allan Fredholm ,  James H. Davidson ,  Tasadduq Khan ,  Jean-Mare C. F. Theret

IPC: C22C19/05 ,  C22F1/00 ,  C22F1/10 ,  C30B1/02 ,  C30B11/00 ,  C30B29/52 ,  C30B33/00 ,  F01D5/28

CPC classification number: C30B11/00 ,  C30B29/52 ,  C30B33/00

Abstract: A monocrystalline alloy with a high resistance to creep having a nickel base matrix, with a density of the order of 8.5 and having a percentage, by weight, composition as follows: Co 5 to 8%--Cr 6.5 to 10%--Mo 0.5 to 2.5%--W 5 to 9%--Ta 6 to 9%--Al 4.5 to 5.8%--Ti 1 to 2%--Nb 0 to 1.5%--C, Zr, and B each less than 100 ppm--Ni remainder to 100%. Furthermore, the summation Ta+Mo+1/2 W lies between 11.5% and 13.5% by weight, the atomic sum Ti+Al+Ta+Nb lies between 15.5% and 17%, the atomic sum Ta+Nb+Mo+1/2 W lies between 4% and 5.5%, the atomic sum Ti+Al+Ta+Nb+Mo+1/2 W lies between 17.5% and 19% and the atomic sum Ti+Al lies between 12.8% and 14.5%.

Abstract translation: 具有高耐蠕变性的单晶合金，具有镍基体，密度约为8.5，重量百分比含量如下：Co 5〜8％-Cr 6.5〜10％-Mo 0.5〜 2.5％-W 5至9％-T 6至9％-Al 4.5至5.8％-Ti 1至2％-Nb 0至1.5％-C，Zr和B各自小于100ppm-Ni余量至100％ 。 此外，相加Ta + Mo + 1 / 2W在11.5重量％〜13.5重量％之间，原子和Ti + Al + Ta + Nb在15.5％〜17％之间，原子和Ta + Nb + Mo + 1 / 2W在4％和5.5％之间，原子和Ti + Al + Ta + Nb + Mo + 1 / 2W在17.5％和19％之间，原子和Ti + Al在12.8％和14.5％之间。

公开(公告)号：US4406716A

公开(公告)日：1983-09-27

申请号：US235948

申请日：1981-02-19

Applicant: Tasadduq Khan

Inventor： Tasadduq Khan

IPC: C22C47/00 ,  C21D6/00 ,  C22F1/10 ,  C30B33/00 ,  C21D9/00

CPC classification number: C30B33/00 ,  C30B29/52

Abstract: The invention relates to a process for increasing the lifetime of a refrary composite material piece comprising a metallic matrix and a reinforcing phase consisting of aligned monocrystalline fibers made of a metallic carbide, when the piece has suffered a plastic deformation in the direction of said fibers. The invention consists in restoring the initial qualities of the piece by subjecting it to a high temperature, inferior to the melting point of the material, more precisely at the temperature at which the piece resumes its initial length after being cooled at ambient temperature. The invention is particularly applicable to pieces forming turbine blades for aircrafts.

Abstract translation: 本发明涉及一种增加耐火材料复合材料的使用寿命的方法，该材料包括金属基体和由金属碳化物制成的排列的单晶纤维组成的增强相，当该片材在所述纤维的方向上遭受塑性变形时。 本发明的目的在于通过将其温度高于材料熔点的高温，更准确地说是在温度在环境温度下冷却之后其恢复其初始长度的温度来恢复该零件的初始质量。 本发明特别适用于形成用于飞行器的涡轮机叶片的部件。