WO1996030551A1 - Castable gamma titanium-aluminide alloy containing niobium, chromium and silicon and turbocharger wheels made thereof - Google Patents
Castable gamma titanium-aluminide alloy containing niobium, chromium and silicon and turbocharger wheels made thereof Download PDFInfo
- Publication number
- WO1996030551A1 WO1996030551A1 PCT/US1996/001688 US9601688W WO9630551A1 WO 1996030551 A1 WO1996030551 A1 WO 1996030551A1 US 9601688 W US9601688 W US 9601688W WO 9630551 A1 WO9630551 A1 WO 9630551A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- alloy
- ranges
- tial
- gamma
- cast
- Prior art date
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
Definitions
- the present invention relates generally to turbocharger wheels cast from alloys of titanium and aluminum. More particularly, it relates to cast turbocharger wheels made of gamma alloys of titanium and aluminum which have been modified both with respect to stoichiometric ratio and with respect to chromium, niobium and silicon.
- the stoichiometric ratio of gamma TiAl can vary over a range without varying its crystal stru ⁇ ure. Between about 50 and 60 atom percent, the compound can exist as a single phase material having the LI o, known as the gamma phase. Between 0 approximately 35 and 50 atom percent, the material will consist of a two phase mixture containing both the Ll 0 face centered tetragonal gamma phase and the hexagonal DO, 9
- alpha-two ( ⁇ 2 ) phase consisting of the formula TijAl.
- Current gamma alloys are, in
- Turbocharger rotors cast from ⁇ -TiAl alloys are advantageous compared with
- the present invention provides a TiAl turbocharger rotor composed of a gamma titanium aluminide alloy consisting essentially of the formula Ti-A_.CrbNb c Su, where "a” , “b”, “c” and “d” are in atomic percent, “a” ranges from about 44 to about 48, “b” ranges from about 2 to about 6.
- the invention provides a process for producing a turbocharger rotor composed of a gamma titanium aluminide alloy, comprising the steps of: (a) forming a melt of a gamma titanium aluminide alloy consisting essentially of the formula Ti-Al,Cr b Nb c Sia, where "a” , “b", “c” and “d” are in atomic percent, “a” ranges from about 44 to about 48, “b” ranges from about 2 to about 6, "c” ranges from
- Levels of aluminum above 48 at% range result in reduced yield strength and the ⁇ - tendency to form only single phase gamma microstr ⁇ ctures.
- Aluminum levels below 44 at% tend to result in low plastic elongation during tensile deformation.
- Levels of Cr at about the 2 at% range tend to boost tensile ductility; but higher levels tend to
- Niobium is generally beneficial to creep strength and oxidation but is prone to segregation at levels above about 6 at%.
- niobium levels above about 6 at% increase alloy density and cost, while niobium levels below about 2 at % are generally insufficient to produce the improved oxidation and creep properties 25 exhibited by alloys of the invention.
- Si levels above about 1 at% tend result in reduced oxidation resistance.
- the melt can be formed using standard titanium alloy melt practice, including that of inductive melting in an inert atmosphere or vacuum Adequate clean melt practice must be observed to limit contamination of impurities such as oxygen, - > c nitrogen, and carbon to levels of less than about 2000 ppm oxygen, 500 ppm nitrogen, and 1000 ppm carbon which can embrittle the alloy.
- Cast TiAl turbocharger rotors made from the above alloy have the advantage of having excellent mechanical properties in the as-cast condition. These as-cast properties are so good that the rotors require no additional thermal processing, such as HIPing or heat treatment. A substantial advantage in reduced part cost is thereby obtained. Further, the addition of Si to the alloy results in improved fill of thin
- FIG. 1 is a graph depicting the ultimate tensile strength and tensile elongation
- FIG. 2 is a photograph of a cast ⁇ -TiAl rotor composed of an alloy of the
- the present invention provides a cast ⁇ -TiAl turbocharger rotor composed of an alloy consisting essentially of the formula Ti-Al.Cr b Nb c S , where "a” , "b", V and “d” are in atomic percent, "a” ranges from about 44 to about 48, “b” ranges from about 2 to about 6; “c” ranges from about 2 to about 6 and “d” ranges from about 0.5 to about 1.0.
- the ⁇ -TiAl turbocharger rotor of the invention can be cast by a process comprising the
- steps of forming a melt of the alloy and casting it into a mold cavity having the shape of the rotor steps of forming a melt of the alloy and casting it into a mold cavity having the shape of the rotor. Castings containing fine details and sharp angle are readily filled by the molten alloy, and the ultimate strength and tensile elongation of the alloy is increased.
- Levels of aluminum above 48 at% range result in reduced yield strength and the tendency to form only single phase gamma microstructures.
- Aluminum levels below 44 at% tend to result in low plastic elongation during tensile deformation.
- Levels of Cr at about the 2 at% range tend to boost tensile ductility; but higher levels tend to embrittle the material.
- Niobium is generally beneficial to creep strength and oxidation but is prone to segregation at levels above about 6 at%.
- niobium levels above about 6 at% increase alloy density and cost, while niobium levels below about 2 at % are generally insufficient to produce the improved oxidation and creep properties exhibited by alloys of the invention.
- Si levels above about 1 at% tend result in reduced oxidation resistance.
- the melt can be formed using standard titanium alloy melt practice, including that of inductive melting in an inert atmosphere or vacuum. Adequate clean melt practice must be observed to limit contamination of impurities such as oxygen. nitrogen, and carbon to levels of less than about 2000 ppm oxygen, 500 ppm nitrogen , and 1000 ppm carbon which can embrittle the alloy
- Cast TiAl turbocharger rotors made from the above alloy have the advantage of having excellent mechanical properties in the as-cast condition. These as-cast properties are so good that the rotors require no additional thermal processing, such as HIPing or heat treatment. A substantial advantage in reduced part cost is thereby obtained. Further, the addition of Si to the alloy results in improved fill of thin regions, for example rotor blades.
- the improvement in properties and castability of the gamma titanium aluminide alloy of the invention is illustrated by the following examples, which are presented to provide a more complete understanding of the invention. The specific techniques, conditions, materials, proponions and reported data set forth to illustrate the principles and practice of the invention are exemplary and shall not be construed as limiting the scope of the invention.
- Figure 2 there is shown a photograph of a cast ⁇ -TiAl turbocharger rotor composed of an alloy having the composition Ti-46Al-2Cr-2Nb-0.5Si. This rotor has been subjected to burst tests and functioned successfully to 187,000 ⁇ m in the as-cast condition.
Abstract
A gamma titanium aluminide rotor is produced from an alloy consisting essentially of the formula Ti-AlaCrbNbcSid, where 'a', 'b', 'c' and 'd' are in atomic percent, 'a' ranges from about 44 to about 48, 'b' ranges from about 2 to about 6, 'c' ranges from about 2 to about 6 and 'd' ranges from about 0.5 to about 1.0. The alloy is castable into a mold to thereby form the rotor. Advantageously, the mold can contain fine detail and sharp angle. Molded rotors composed of the alloy exhibit excellent strength and toughness.
Description
CASTABLE GAMMA TITANIUM-ALUMINIDE ALLOY
CONTAINING NIOBIUM, CHROMIUM AND SILICON AND
TURBOCHARGER WHEELS MADE THEREOF
BACKGROUND OF THE INVENTION
1. Field Of The Invention
10
The present invention relates generally to turbocharger wheels cast from alloys of titanium and aluminum. More particularly, it relates to cast turbocharger wheels made of gamma alloys of titanium and aluminum which have been modified both with respect to stoichiometric ratio and with respect to chromium, niobium and silicon.
2. Description Of The Prior Art
The alloy of titanium and aluminum having a tetragonal Ll0 crystal structure
20 has a stoichiometric ratio of approximately one. It is an intermetallic compound having low density, high modulus, good elevated temperature tensile properties and good creep resistance. With respect to all aforementioned properties, gamma TiAl is
- 5 superior to all other conventional titanium alloys and, on a specific basis, is frequently superior to nickel alloys. For this reason, gamma TiAl alloys have been the subject of intense research as a replacement for nickel alloys in various aerospace applications,
30 for example turbine blades.
Several characteristics of gamma TiAl have thus far prevented its utilization in the aerospace industry These include poor room temperature ductility, low fracture toughness, and low oxidation resistance when compared with nickel base superalloys The goal of most recent research has been to tmprove these properties to the degree
which would allow for the successful substitution of relatively dense nickel superallovs with low density gamma TiAl alloys.
The stoichiometric ratio of gamma TiAl can vary over a range without varying its crystal struαure. Between about 50 and 60 atom percent, the compound can exist as a single phase material having the LI o, known as the gamma phase. Between 0 approximately 35 and 50 atom percent, the material will consist of a two phase mixture containing both the Ll0 face centered tetragonal gamma phase and the hexagonal DO,9
alpha-two (α2) phase, consisting of the formula TijAl. Current gamma alloys are, in
- fart, two phase mixtures consisting of α2 and γ which have been found to have a more
desirable combination of strength and ductility than true single phase γ alloys Heat
treatment of these alloys can result in a substantial change in the morphology and distribution of the two phases, resulting in a considerable range in mechanical 0 properties. Additional alloying with other elements can further modify the mechanical properties.
c There has been considerable research devoted to improving the mechanical
properties of γ TiAl alloys. Publications describing such research include a review paper Young- Won Kim, Intermetallic Alloys Based on Gamma Titanium-Aluminide JOM, (1989), pg. 24. A second review paper has been published by Shih-Chin Huang 0 and Donald S Shih, Microstructure-Property Correlation in TiAl-B se Alloys, in Microstructure-Property Relationships in Titanium Alumintdes and Alloys, ed Y W Kim and R.R. Boyer, TMS. (1991) Additionally, there exists a number of patents 5 describing alloy development of γ TiAl alloys U S Patents 5,213,635 to Huang.
5,045.406 to Huang, 4,879.092 to Huang, 5.080.860 to Huang, 4,836,983 to Huang
and Gigliotti, and U.S. Patent 4,983,357 to Mitao et. al are representative of recent patents in which ternary and quaternary additions have been added to TiAl for the purpose of improving mechanical properties.
Turbocharger rotors cast from γ-TiAl alloys are advantageous compared with
conventional nickel based superalloy turbocharger rotors in that they have half the density of their nickel based counterparts while maintaining comparable or even bener specific mechanical properties. Due to their reduced density, rotational inertia is significantly reduced, resulting in improved efficiency and the reduction of turbo-lag, which is often present in nickel alloy turbocharger rotors. A detailed discussion of TiAl turbocharger rotors is provided by, Nishiyama et al., "Development of Titanium Aluminide Turbocharger Rotors", High Temperature Aluminides and Intermetallics, Ed. S.H. Whang, C.T. Liu, D P. Pope and J O. Stiegler, The Minerals, Metals & Materials Society, 1990, the subject matter of which is incorporated herein by
reference thereto.
SUMMARY OF THE INVENTION
The present invention provides a TiAl turbocharger rotor composed of a gamma titanium aluminide alloy consisting essentially of the formula Ti-A_.CrbNbcSu, where "a" , "b", "c" and "d" are in atomic percent, "a" ranges from about 44 to about 48, "b" ranges from about 2 to about 6. "c" ranges from about 2 to about 6 and "d" ranees from about 0 5 to about 1 0
In addition, the invention provides a process for producing a turbocharger rotor composed of a gamma titanium aluminide alloy, comprising the steps of: (a) forming a melt of a gamma titanium aluminide alloy consisting essentially of the formula Ti-Al,CrbNbcSia, where "a" , "b", "c" and "d" are in atomic percent, "a" ranges from about 44 to about 48, "b" ranges from about 2 to about 6, "c" ranges from
10 about 2 to about 6 and "d" ranges from about 0.5 to about 1.0; and (b) casting the melt into a mold cavity having the form of the rotor.
Levels of aluminum above 48 at% range result in reduced yield strength and the ~ - tendency to form only single phase gamma microstrυctures. Aluminum levels below 44 at% tend to result in low plastic elongation during tensile deformation. Levels of Cr at about the 2 at% range tend to boost tensile ductility; but higher levels tend to
2 o embrittle the material. Niobium is generally beneficial to creep strength and oxidation but is prone to segregation at levels above about 6 at%. In addition, niobium levels above about 6 at% increase alloy density and cost, while niobium levels below about 2 at % are generally insufficient to produce the improved oxidation and creep properties 25 exhibited by alloys of the invention. Si levels above about 1 at% tend result in reduced oxidation resistance.
30 The melt can be formed using standard titanium alloy melt practice, including that of inductive melting in an inert atmosphere or vacuum Adequate clean melt practice must be observed to limit contamination of impurities such as oxygen, -> c nitrogen, and carbon to levels of less than about 2000 ppm oxygen, 500 ppm nitrogen, and 1000 ppm carbon which can embrittle the alloy.
Cast TiAl turbocharger rotors made from the above alloy have the advantage of having excellent mechanical properties in the as-cast condition. These as-cast properties are so good that the rotors require no additional thermal processing, such as HIPing or heat treatment. A substantial advantage in reduced part cost is thereby obtained. Further, the addition of Si to the alloy results in improved fill of thin
10 regions, for example rotor blades.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will be more fully understood and further advantages will - - become apparent when reference is had to the following detailed description and the accompanying drawings, in which:
FIG. 1 is a graph depicting the ultimate tensile strength and tensile elongation
2 Q measured at 760°C for alloys cast in accordance with the invention; and
FIG. 2 is a photograph of a cast γ-TiAl rotor composed of an alloy of the
present invention.
25
DESCRIPTION OF THE PREFERRED EMBODIMENTS
It is known that, except for its brinleness, the intermetallic compound gamma 0 TiAl would have many uses in industry, owing to its light weight, high strength at high temperatures and relatively low cost. It has also been recognized that cast gamma TiAl suffers from a number of problems, including brinleness and low strength of the castings. Another problem with cast gamma TiAl is low fluidity in the molten state 5 thereof This condition prevents adequate filling in castings, such as automobile turbocharger compressor wheels, which contain fine detail and sharp angle
The present invention provides a cast γ-TiAl turbocharger rotor composed of an alloy consisting essentially of the formula Ti-Al.CrbNbcS , where "a" , "b", V and "d" are in atomic percent, "a" ranges from about 44 to about 48, "b" ranges from about 2 to about 6; "c" ranges from about 2 to about 6 and "d" ranges from about 0.5 to about 1.0.
The γ-TiAl turbocharger rotor of the invention can be cast by a process comprising the
steps of forming a melt of the alloy and casting it into a mold cavity having the shape of the rotor. Castings containing fine details and sharp angle are readily filled by the molten alloy, and the ultimate strength and tensile elongation of the alloy is increased.
Levels of aluminum above 48 at% range result in reduced yield strength and the tendency to form only single phase gamma microstructures. Aluminum levels below 44 at% tend to result in low plastic elongation during tensile deformation. Levels of Cr at about the 2 at% range tend to boost tensile ductility; but higher levels tend to embrittle the material. Niobium is generally beneficial to creep strength and oxidation but is prone to segregation at levels above about 6 at%. In addition, niobium levels above about 6 at% increase alloy density and cost, while niobium levels below about 2 at % are generally insufficient to produce the improved oxidation and creep properties exhibited by alloys of the invention. Si levels above about 1 at% tend result in reduced oxidation resistance.
The melt can be formed using standard titanium alloy melt practice, including that of inductive melting in an inert atmosphere or vacuum. Adequate clean melt practice must be observed to limit contamination of impurities such as oxygen.
nitrogen, and carbon to levels of less than about 2000 ppm oxygen, 500 ppm nitrogen, and 1000 ppm carbon which can embrittle the alloy
Cast TiAl turbocharger rotors made from the above alloy have the advantage of having excellent mechanical properties in the as-cast condition. These as-cast properties are so good that the rotors require no additional thermal processing, such as HIPing or heat treatment. A substantial advantage in reduced part cost is thereby obtained. Further, the addition of Si to the alloy results in improved fill of thin regions, for example rotor blades. The improvement in properties and castability of the gamma titanium aluminide alloy of the invention is illustrated by the following examples, which are presented to provide a more complete understanding of the invention. The specific techniques, conditions, materials, proponions and reported data set forth to illustrate the principles and practice of the invention are exemplary and shall not be construed as limiting the scope of the invention.
EXAMPLES 1-9
Individual melts were prepared to contain titanium and aluminum in various binary stoichiometric rations approximating TiAl with various additions All compositions are listed in atomic percent. Variations of Cr and Nb were performed between 2 and 6 % while holding silicon constant at 0.5 % Variations in silicon of between 0 and 1.0 % were made holding aluminum, chromium, and niobium constant at 46Al-2Cr-2Nb. Samples were cast into graphite test bar molds and were HIPed for
8 hrs at 30 ksi pressure at 1250°C, followed by a furnace cool from the HIP unit Button head tensile bars were then machined from the HIP test bar blanks and yield
strength, ultimate strength and tensile elongation were measured at 760βC test
temperature.
- From the test date included in Table I, it is evident that the 46Al-2Cr-2Nb alloy containing l.OSi evidenced a superior combination of ultimate strength and tensile elongation, as compared with the alloys containing no silicon or 0 5 Si. This improved
I o combination of strength and elongation is further evidenced by Figure 1 which plots
the ultimate tensile strength and tensile elongation measured at 760°C. In this figure,
properties increase along the diagonal away from the origin. It is clear from the plot that the 46Al-2Cr-Nb- l.OSi alloy evidenced a superior combination of strength and
15 toughness.
20
25
0
5
Table I
Example Nominal YS(ksi) UTSOαi) El(%) Number Composition (At%)
1 46Al-2Cr-4Nb-0.5Si 46Al-2Cr-4Nb-0.5Si 2 46Al-2Cr-6Nb-0.5Si 46Al-2Cr-6Nl>-0.5Si 3 46Al-4Cr-2Nb-0.5Si 46Al-4Cr-2Nb-0.5Si 4 46AU6Cr-2Nb-0.5Si
5 48Ai-2Cr-2Nb-0.5Si
6 48Al-2Cr-4Nb-0.5Si 48Al-2Cr-4Nb-0.SSi
7 44Al-2Cr-2Nb-0.5Si 8 46 AI-2Cr-2Nb- l.OSi 46Al-2Cr-2Nb-1.0Si 9 4 A.-2Cr-2Nb-0.5Si 46Al-2Cr-2Nl>-0.5Si 10 46Al-2Cr-2 b 46Al-2Cr-2Nb
In Figure 2 there is shown a photograph of a cast γ-TiAl turbocharger rotor composed of an alloy having the composition Ti-46Al-2Cr-2Nb-0.5Si. This rotor has been subjected to burst tests and functioned successfully to 187,000 φm in the as-cast condition.
Having thus described the invention in rather full detail, it will be understood that such detail need not be strictly adhered to but that various changes and modifications may suggest themselves to one skilled in the art, all falling within the scope of the present invention as defined by the subjoined claims.
Claims
What is claimed is: 5 1. A γ-TiAl turbocharger rotor cast from a composition consisting essentially of the formula Ti-Al.CrbNb.Si4, where "a" , "b", "c" and "d" are in atomic percent, "a" ranges from about 44 to about 48, "b" ranges from about 2 to about 6; "c" ranges
I o from about 2 to about 6 and "d" ranges from about 0 5 to about 1.0.
2. A cast γ-TiAl turbocharger rotor having the composition as recited by claim 1, wherein "a" is 46.
15
3. A cast γ-TiAl turbocharger rotor having the composition as recited by claim 1 , wherein "a" is 48, "b" is 2 and "c" is 2.
4. A cast γ-TiAl turbocharger rotor having the composition, as recited by claim 1, wherein "a" is 48, "b" is 2 and "c" is 4.
20
25
30
35
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US41247595A | 1995-03-28 | 1995-03-28 | |
| US08/412,475 | 1995-03-28 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO1996030551A1 true WO1996030551A1 (en) | 1996-10-03 |
Family
ID=23633149
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/US1996/001688 WO1996030551A1 (en) | 1995-03-28 | 1996-03-28 | Castable gamma titanium-aluminide alloy containing niobium, chromium and silicon and turbocharger wheels made thereof |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO1996030551A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1127949A2 (en) * | 2000-02-23 | 2001-08-29 | Mitsubishi Heavy Industries, Ltd. | TiA1 based alloy, production process therefor, and rotor blade using same |
| US6294132B1 (en) * | 1996-10-28 | 2001-09-25 | Mitsubishi Heavy Industries Ltd. | TiAl intermetallic compound-based alloy |
| EP1897966A3 (en) * | 2006-09-08 | 2008-07-16 | General Electric Company | Method for applying a high temperature anti-fretting wear coating |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0521516A1 (en) * | 1991-07-05 | 1993-01-07 | Nippon Steel Corporation | TiAl-based intermetallic compound alloys and processes for preparing the same |
| US5196162A (en) * | 1990-08-28 | 1993-03-23 | Nissan Motor Co., Ltd. | Ti-Al type lightweight heat-resistant materials containing Nb, Cr and Si |
| EP0545614A1 (en) * | 1991-12-02 | 1993-06-09 | General Electric Company | Gamma titanium alloys modified by chromium, niobium, and silicon |
| EP0549181A1 (en) * | 1991-12-23 | 1993-06-30 | General Electric Company | Gamma titanium aluminide |
| EP0568951A2 (en) * | 1992-05-08 | 1993-11-10 | ABBPATENT GmbH | High-temperature resistant material |
-
1996
- 1996-03-28 WO PCT/US1996/001688 patent/WO1996030551A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5196162A (en) * | 1990-08-28 | 1993-03-23 | Nissan Motor Co., Ltd. | Ti-Al type lightweight heat-resistant materials containing Nb, Cr and Si |
| EP0521516A1 (en) * | 1991-07-05 | 1993-01-07 | Nippon Steel Corporation | TiAl-based intermetallic compound alloys and processes for preparing the same |
| EP0545614A1 (en) * | 1991-12-02 | 1993-06-09 | General Electric Company | Gamma titanium alloys modified by chromium, niobium, and silicon |
| EP0549181A1 (en) * | 1991-12-23 | 1993-06-30 | General Electric Company | Gamma titanium aluminide |
| EP0568951A2 (en) * | 1992-05-08 | 1993-11-10 | ABBPATENT GmbH | High-temperature resistant material |
Non-Patent Citations (1)
| Title |
|---|
| NISHIYAMA ET AL.: "Development of Titanium Aluminide Turbocharger Rotors", HIGH TEMPERATURE ALUMINIDES AND INTERMETALLICS, THE MINERALS, METALS AND MATERIALS SOCIETY, 1990, pages 557 - 584, XP000564857 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6294132B1 (en) * | 1996-10-28 | 2001-09-25 | Mitsubishi Heavy Industries Ltd. | TiAl intermetallic compound-based alloy |
| EP1127949A2 (en) * | 2000-02-23 | 2001-08-29 | Mitsubishi Heavy Industries, Ltd. | TiA1 based alloy, production process therefor, and rotor blade using same |
| EP1127949A3 (en) * | 2000-02-23 | 2002-09-18 | Mitsubishi Heavy Industries, Ltd. | TiA1 based alloy, production process therefor, and rotor blade using same |
| US6669791B2 (en) | 2000-02-23 | 2003-12-30 | Mitsubishi Heavy Industries, Ltd. | TiAl based alloy, production process therefor, and rotor blade using same |
| US7618504B2 (en) | 2000-02-23 | 2009-11-17 | Mitsubishi Heavy Industries, Ltd. | TiA1 based alloy, production process therefor, and rotor blade using same |
| EP1897966A3 (en) * | 2006-09-08 | 2008-07-16 | General Electric Company | Method for applying a high temperature anti-fretting wear coating |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1390167B1 (en) | Casting of alloys with isotropic graphite molds | |
| JP2881626B2 (en) | Single crystal nickel-based superalloy | |
| EP1795621B1 (en) | High-strength and high-ductility ni-base superalloys, parts using them, and method of producing the same | |
| JP4653388B2 (en) | Yttrium modified amorphous alloy | |
| EP0275391B1 (en) | Titanium-aluminium alloy | |
| EP0502654B1 (en) | Improved ductility microalloyed NiAL intermetallic compounds | |
| EP0693567A2 (en) | High-strength, high-ductility cast aluminum alloy and process for producing the same | |
| JPH0323613B2 (en) | ||
| JP4204650B2 (en) | High strength heat-resistant zinc alloy and molded product | |
| JP4719583B2 (en) | Unidirectional solidification nickel-base superalloy excellent in strength, corrosion resistance and oxidation resistance and method for producing unidirectional solidification nickel-base superalloy | |
| US6174387B1 (en) | Creep resistant gamma titanium aluminide alloy | |
| JP4266196B2 (en) | Nickel-base superalloy with excellent strength, corrosion resistance and oxidation resistance | |
| JPS6249342B2 (en) | ||
| EP0477559B1 (en) | Process of forming niobium and boron containing titanium aluminide | |
| WO1996030552A1 (en) | Castable gamma titanium-aluminide alloy containing niobium, chromium and silicon | |
| JP3006120B2 (en) | Ti-Al alloy and method for producing the same | |
| JPH0776399B2 (en) | Niobium-containing titanium aluminide rendered castable by boron inoculation | |
| US7306682B2 (en) | Single-crystal Ni-based superalloy with high temperature strength, oxidation resistance and hot corrosion resistance | |
| EP3725901A1 (en) | Cobalt-based alloy powder, cobalt-based alloy sintered body, and method for manufacturing cobalt-based alloy sintered body | |
| WO1996030551A1 (en) | Castable gamma titanium-aluminide alloy containing niobium, chromium and silicon and turbocharger wheels made thereof | |
| EP0387976A2 (en) | New superalloys and the methods for improving the properties of superalloys | |
| JP4184648B2 (en) | Ni-based single crystal alloy excellent in strength and corrosion resistance and its manufacturing method | |
| EP1052298A1 (en) | Creep resistant gamma titanium aluminide | |
| JP2579316B2 (en) | Single crystal Ni-base superalloy with excellent strength and corrosion resistance | |
| US8241560B2 (en) | Nickel base superalloy and single crystal castings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| AK | Designated states |
Kind code of ref document: A1 Designated state(s): JP |
|
| AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): AT BE CH DE DK ES FI FR GB GR IE IT LU MC NL PT SE |
|
| DFPE | Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101) | ||
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
| 122 | Ep: pct application non-entry in european phase |