CN1011984B - Cobalt-base superalloy and cast and welded industrial gas turbine component thereof - Google Patents
Cobalt-base superalloy and cast and welded industrial gas turbine component thereofInfo
- Publication number
- CN1011984B CN1011984B CN85109085A CN85109085A CN1011984B CN 1011984 B CN1011984 B CN 1011984B CN 85109085 A CN85109085 A CN 85109085A CN 85109085 A CN85109085 A CN 85109085A CN 1011984 B CN1011984 B CN 1011984B
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- China
- Prior art keywords
- cobalt
- alloy
- weight
- gas turbine
- tantalum
- Prior art date
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- Expired
Links
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 37
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 27
- 239000010941 cobalt Substances 0.000 claims abstract description 27
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 27
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 22
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 20
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 19
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 18
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 13
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 13
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 13
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 11
- 239000011651 chromium Substances 0.000 claims abstract description 11
- 229910052742 iron Inorganic materials 0.000 claims abstract description 11
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 10
- 239000010703 silicon Substances 0.000 claims abstract description 10
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 10
- 239000010937 tungsten Substances 0.000 claims abstract description 10
- 238000004519 manufacturing process Methods 0.000 claims abstract description 9
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 9
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 9
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 claims abstract description 3
- 238000000034 method Methods 0.000 claims description 12
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 11
- 239000010936 titanium Substances 0.000 claims description 11
- 229910052719 titanium Inorganic materials 0.000 claims description 11
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 9
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 7
- 229910052748 manganese Inorganic materials 0.000 claims description 7
- 239000011572 manganese Substances 0.000 claims description 7
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 claims description 5
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims description 5
- 239000005864 Sulphur Substances 0.000 claims description 5
- 229910052698 phosphorus Inorganic materials 0.000 claims description 5
- 239000011574 phosphorus Substances 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 5
- 239000004615 ingredient Substances 0.000 claims 2
- 239000000126 substance Substances 0.000 claims 2
- 229910045601 alloy Inorganic materials 0.000 abstract description 43
- 239000000956 alloy Substances 0.000 abstract description 43
- 230000007797 corrosion Effects 0.000 abstract description 9
- 238000005260 corrosion Methods 0.000 abstract description 9
- 238000012360 testing method Methods 0.000 description 20
- 229910052758 niobium Inorganic materials 0.000 description 10
- 239000010955 niobium Substances 0.000 description 10
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 10
- 238000003466 welding Methods 0.000 description 10
- 238000005266 casting Methods 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 8
- 239000003963 antioxidant agent Substances 0.000 description 5
- 230000003078 antioxidant effect Effects 0.000 description 5
- 235000006708 antioxidants Nutrition 0.000 description 5
- 230000008901 benefit Effects 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 4
- 229910052796 boron Inorganic materials 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 208000037656 Respiratory Sounds Diseases 0.000 description 3
- 239000002131 composite material Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000002939 deleterious effect Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000007655 standard test method Methods 0.000 description 2
- 229910000521 B alloy Inorganic materials 0.000 description 1
- 229910001339 C alloy Inorganic materials 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000007499 fusion processing Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 230000000266 injurious effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000010309 melting process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 229910000679 solder Inorganic materials 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000009617 vacuum fusion Methods 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/07—Alloys based on nickel or cobalt based on cobalt
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Materials For Medical Uses (AREA)
Abstract
钴基超级合金在生产工业燃气轮机的热气路部件中有特殊的用途。这种合金有独特的综合性能，包括极好的抗热腐蚀稳定性、高温下好的蠕变断裂强度、金相稳定性、拉伸延展性和可焊性。这种超级合金含碳、铬、镍、钨、钽、铪、锆、铁、锰、硅和钴。碳化物形成元素的选择应满足以下等式：Cobalt-based superalloys have particular application in the production of hot gas path components for industrial gas turbines. This alloy has a unique combination of properties including excellent hot corrosion stability, good creep rupture strength at elevated temperatures, metallographic stability, tensile ductility and weldability. This superalloy contains carbon, chromium, nickel, tungsten, tantalum, hafnium, zirconium, iron, manganese, silicon and cobalt. The choice of carbide forming elements should satisfy the following equation:
Description
Cobalt-based super-alloy has special purposes in the hot gas circuit unit of manufacture internal combustion turbine.This alloy has fabulous over-all properties, comprises creep-rupture strength, metallographic stability, stretching ductility and weldability that fabulous hot corrosion resistance, high temperature are good down.Cobalt-based super-alloy contain 0.3～0.6% carbon, 27～35% chromium, 9～16% nickel, 6～9% tungsten, 0.45～2.0% tantalum ,≤3% hafnium ,≤0.7 zirconium, be no more than 2.0% iron, 1.5 manganese and silicon and surplus is a cobalt, the selection of carbide forming element should be satisfied following formula:
(atomic percentage (T
a+ H
f+ T
i+ Z
r))/(atomic percentage C)=0.4 to 0.8
The superalloy branch of relate generally to metallurgical technology of the present invention, more clearly say so and produce foundry goods and welded special purpose about new cobalt-based super-alloy with it with fabulous over-all properties, and with the hot gas circuit unit of the infant industry internal combustion turbine of this class new alloy manufacturing.
Cobalt-based super-alloy open and that propose claim has splendid anti-oxidant and hot corrosion resistance in No. 3383205, United States Patent (USP), therefore is widely used in the nozzle of manufacture internal combustion turbine for a long time.In fact, the internal combustion turbine portion of transferee General Electric Company of this patent has specified the alloy with the present production first step of a kind of conduct nozzle in this class superalloy.But the creep-rupture strength of the sort of alloy and fatigue strength have not had surplus when being used to produce new industry gas turbine nozzle.In order to improve these performances anti-oxidant or hot corrosion resistance of not obvious again reduction superalloy simultaneously, carried out scientific effort.Though reached above-mentioned those purposes because resulting superalloy has than higher carbon content (0.40～0.05%),, so do not dealt with problems because they have bad weldability and stretching ductility.
By our new design and discovery of following detailed description, we have developed the cobalt-based super-alloy series that makes new advances, and they have inaccessible over-all properties in the past.Therefore, we have found with the problems referred to above and have come son explanation for example, avoid, and must sacrifice the method that desired performance exchanges.The present invention specializes our new design and discovery, and in the claim that reaches the product of being made by these alloy composites about alloy composite they has been carried out narration compendiously in addressing the above problem.
Our new design is basis of the present invention, and one of them is: the weldability and the stretching ductility that do not need to reduce cobalt-based super-alloy significantly improve creep strength and fatigue strength very significantly.Specifically, by adding one or more the down monocarbide MC of big powers forming elements: hafnium, tantalum, niobium, zirconium and titanium just can obtain to improve the advantageous effects that carbon content brings and avoid common incident deleterious effect.
We find to add more a spot of above-mentioned element, can reach this purpose, and in certain limit, above-mentioned element can use separately or use together with any needed array mode, to guarantee to reach the new result and the benefit of unanimity of the present invention.
We also find, though active stronger element such as titanium, zirconium and also have H to a certain extent
f, be suitable for vacuum melting technique, still, when carrying out melting process in air, the most handy niobium replaces above element.It is about 1% to should be noted that in addition the quantity that adds niobium surpasses, because it has deleterious effect for the hot corrosion resistance of superalloy.According to same reason, when melting new superalloy of the present invention in a vacuum, preferably without niobium.
In carrying out process of the present invention, we have confirmed that carbon can be owing to carbon is separated out and significantly forfeiture with the form of monocarbide to the beneficial effect of creep strength and fatigue strength on superalloy intragranular and crystal boundary.We have also confirmed, this segregation of carbon and separate out weldability, metallographic stability and stretching extension performance are produced favorable influence.And when usually adopting, all can have injurious effects to all these performances according to carbon content scope of the present invention.
We also further find to have only the tantalum of adding at least 0.45%, could stably obtain new effect of the present invention and advantage; Though and the kind of other monocarbide forming element can be selected by the operator, its total consumption then is vital.Relation between the carbon content of alloy and these element total amounts represents that with the ratio of the atomic percentage of these element atomic percentage sum carbon this numerical value must be in 0.4～0.8 scope.In the superalloy of the present invention, this number preferably is 0.62.
Narrate the composition of alloy below tout court.The present invention is a kind of cobalt-based super-alloy that at high temperature has unique over-all properties, and this alloy has special purposes at the hot gas circuit unit of manufacture internal combustion turbine.Alloy contain 0.3～0.6% carbon, 27～35% chromium, 9～16% nickel, 6～9% tungsten ,≤3% hafnium, 0.45～2.0% tantalum ,≤0.7% zirconium ,≤0.5% titanium, manganese and silicon ,≤2.0% iron, surplus are cobalt.Should be noted that in addition: select carbide forming element should satisfy following formula:
(atomic percentage (Ta+H
f+ T
i+ Z
f))/(atomic percentage C)=0.4 to 0.8
Narrate the goods of this alloy equally simply, the invention provides the industry gas turbine nozzle that a kind of cobalt-based super-alloy is cast, it is made of alloy recited above.The gas turbine combustion chamber that the invention provides transition piece and wheel cap in this respect and be processed into by cobalt-based super-alloy, it includes polylith through rolling and to give the new alloy plate that the setting shape is shaped, and these plates assemblings also weld together into the combustion chamber.
Accompanying drawing is the part of this specification sheets.
Fig. 1 is an industry gas turbine nozzle skeleton view of the present invention.
Fig. 2 is Larsen-Miller (Larson-Miller) graph of merit-disrumpent feelings performance of alloy and a kind of alloy of the present invention of United States Patent (USP) № 3383205.
Fig. 3 is the graphic representation of adjustable restraint welding crack test (varestraint weoding test) test-results of alloy of two kinds of prior aries of five kinds of alloys of the present invention and the alloy that comprises the United States Patent (USP) № 3383205 among Fig. 2.This is a total crack length (one-thousandth of an inch) increases percentage ratio to strain a graphic representation.
Fig. 4 is the skeleton view of industry gas turbine transition piece of the present invention.
Although we recommend preferential select to adopt vacuum fusion and vacuum casting method production new alloy, as a kind of alternative plan, we also plan to adopt air fusing and air casting method. When adopting vacuum process, can add hafnium, titanium, zirconium and tantalum, and when adopting the air fusion process, can add niobium and tantalum, whether add hafnium and then can choose wantonly. Under any circumstance, all to carefully control the quantity of required additive when making alloy of the present invention, have the characteristic of above-mentioned expectation to guarantee the product that gets with these Alloys Castings or machining. Equally, in two kinds of technologies in order to obtain best effect, control the content of these several monocarbide forming elements element in addition, will control on the one hand the content range of key component, also should control on the other hand the maximum level of accessory constituent or impurity element such as iron, manganese, silicon and boron.
The front is mentioned, also will narrate below, and the consequence that loses this control is loss one or more important advantages of the present invention. For example the front has been pointed out and has been listed in the claim, and when the consumption of monocarbide forming element and alloy carbon content were uneven, the good solderability of new alloy will be lost. Equally, easily oxidized unlike titanium, zirconium even hafnium because niobium is not too active, so we more are willing to adopt niobium in air fusing, air casting, but should notice that consumption does not surpass 1%, because niobium can damage the corrosion and heat resistant of alloy. In addition, the content of chromium preferably 28～30% in the alloy, are higher or lower than this scope and all can fall low-alloyed performance. When the content of chromium was lower than about 27%, anti-oxidant and corrosion and heat resistant can reduce, and when being higher than 35%, ductility can degenerate and therefore anti-oxidant and hot corrosion resistance can not improve.
Industrial gas turbine component and aircraft jet as casting of the present invention and workpiece start The parts difference of machine is very big, particularly aspect size and quality. Owing to this reason, the problem that they occur is different with the lighter jet engine parts of weight, for example the easier crackle that occurs when welding. This point has important implication to casting and processing industry gas turbine component, because obvious people more are ready to adopt welding to repair industrial gas turbine nozzle, to save time and to change the expense of parts. Can obtain the loss that this advantage is not brought other side simultaneously, this is important progress technically. Equally, owing to the invention provides a kind of alloy with good solderability, can give with welding the chamber structure of method process industry gas turbine of the sheet material of shaping, this is a New Important Advances of manufacture gas turbine. In welding operation practice, we have adopted the technology and equipment of the gas-tungsten arc welding of industrial general processing iron and nonferrous metal structure (comprising the cobalt-based super-alloy structure).
Industry gas turbine first order nozzle 10 shown in Figure 1 is foundry goods of the alloy composite of preferentially selecting of the present invention, and it is to adopt the technical injection molding that generally uses and model casting technology to produce. The first order nozzle of the shape of nozzle 10, size and concrete structure and present standard is identical. Transition piece 20 with for a long time in industry gas turbine normally used transition piece also be on all four, but important difference is: it is to be made through welding by alloy component of the present invention, thereby provides by flawless assemblies some element integral solder, firm. Like this, support 22 is placed on the main body 23, and the no leakage body closely is fixed together after the welding.
By following explanatory but non-limiting instance, those of ordinary skill in the art will be to the present invention and important new advantage thereof, new result has more and better understand.
Example 1
A kind of commodity cobalt base alloy is cast as specimen, the composition of alloy (weight %) as
Carbon 0.25
Chromium 29.0
Nickel 10.0
Tungsten 7.0
Manganese 0.7
Silicon 0.7
Phosphorus 0.02
Sulphur 0.02
Iron 1.0
Boron 0.015
The cobalt surplus
This superalloy is disclosed and claimed in transferring the US Patent No 3383205 of originally being changeed the people.It once was common to process industry internal combustion turbine thermal level parts for a long time, and particularly nonrotational foundry goods partly is as first step nozzle.
The specimen of casting has been carried out the tension test of standard, wriggle tearing test and the test of adjustable restraint (Varestraint) HOT CRACK FOR WELDING P down.Stretching and creep rupture data are listed in the table 1, and adjustable restraint (Varestraint) thermal crack weldability test data illustrate in Fig. 2.Curve A among Fig. 2 is represented Larsen-Miller (Larson-Miller) data, and the curve A A among Fig. 3 represents adjustable restraint (varestraint) hot crack(ing) test data.
Example 2
A kind of cobalt-based super-alloy of the present invention is tested according to condition and the step identical with example 1, and (weight %) is as follows for the composition of alloy:
Carbon 0.36
Chromium 29
Nickel 11
Tungsten 7.3
Tantalum 0.50
Hafnium 1.0
Zirconium 0.5
Titanium 0.2
Iron＜0.4
Silicon＜0.07
Sulphur 0.01
Phosphorus＜0.01
Manganese＜0.01
The cobalt surplus
The results are shown in table 1 and 2 of test can be done contrast with the data of example 1 and following data.Curve B among Fig. 2 is represented Larsen-Miller data, and the curve B B among Fig. 3 represents adjustable restraint crackle (varestraint) testing data.In addition, this alloy is more more superior than the cobalt base alloy of example 1 aspect anti-oxidant and corrosion and heat resistant characteristic in standard test methods.
Example 3
Other four kinds of superalloys of the present invention have been carried out same test, and (weight %) is as follows for the composition of these four kinds of alloys:
Alloy A alloy B alloy C alloy D
481 482 483 485
Carbon 0.25 0.25 0.35 0.35
Manganese 0.70 0.70 0.70 0.70
Silicon 0.75 0.75 0.75 0.75
Phosphorus＜0.04＜0.04＜0.04＜0.04
Sulphur＜0.04＜0.04＜0.04＜0.04
Chromium 28.0 28.0 29.0 29.0
Nickel 10.0 10.0 10.0 10.0
Tungsten 7.0 7.0 7.0 5.0
Iron＜0.5＜0.5＜0.5＜0.5
Zirconium
Hafnium
Titanium
Niobium 0.5 1.0 1.0 1.25
Tantalum 0.5 0.5 0.5
Boron 0.01
Cobalt surplus surplus surplus surplus
By the performance of measuring these alloys as previously mentioned, resulting testing data is also listed in table 1 and 2.
Example 4
Cobalt-based type superalloy to another kind of prior art has also carried out same test, and the result also lists in two following tables.The composition (weight %) of this special alloy (alloy E) is:
Carbon 0.35
Manganese 0.70
Silicon 0.75
Phosphorus＜0.04
Sulphur＜0.04
Chromium 29.0
Nickel 10.0
Tungsten 7.0
Iron＜0.5
Zirconium 0.20
Hafnium
Titanium 0.15
Niobium 0.25
Tantalum
Boron 0.01
The cobalt surplus
The test of when measuring the performance of above-mentioned various different-alloys, being carried out, all be to carry out under each situation according to the test method of standard, and each alloy adopted to use the same method test several times, so that test-results can directly compare and can reach a conclusion according to reliable test data.The ASTM standard test methods is adopted in tension test and repture test, and transfer restrain crackle (Varestraint) test be according to August nineteen eighty-two Welding Research Council can report for No. 280 in people such as C.D.Ludium carry out in the method described in the article that is entitled as " varestraint test " (the Varestaint Test).
As can be seen from Table 1, the ultimate tensile strength of superalloy of the present invention (example 2 and example 3A-D) is parity with or superiority over the ultimate tensile strength of the commodity superalloy of example 1, and creep-rupture strength is then significantly greater than this commodity superalloy.The data of table 1 show: these new superalloys at room temperature have good extensibility characteristic.The data of table 2 and the curve shows of Fig. 3: the weldability of superalloy of the present invention is better than commodity superalloy A and E, and more surprising be that the superalloy of example 2 of preferred embodiment of the invention described above is especially true.Be also pointed out that the numeral in the bracket among the figure shows: it is in the critical range of stipulating in front 0.4～0.8 that superalloy of the present invention (example 2 and 3) has the percentile ratio of carbide forming element-carbon atom, and example 1 He, this ratio of the alloy of 4 prior art does not then meet this important regulation.
Claims (3)
1, therefore a kind of cobalt-based super-alloy that at high temperature has unique needed over-all properties comprises the special purposes of tool body in the industry gas turbine hot gas circuit unit of nozzle and burner in production, it is characterized in that its chemical ingredients (weight %) is:
0.3-0.6% (weight) carbon
27-35% (weight) chromium
9-16% (weight) nickel
6-9% (weight) tungsten
0.45-2.0% (weight) tantalum
≤ 0.5% (weight) titanium
≤ 3.0% (weight) hafnium
≤ 0.7% (weight) zirconium
≤ 1.0% (weight) manganese
≤ 1.0% (weight) silicon
≤ 2.0% (weight) iron
Surplus is a cobalt, described carbon (C), tantalum (T
a), hafnium (H
f), titanium (T
i) and zirconium (Z
r) selection should satisfy following formula:
(atomic percentage (T
a+ H
f+ T
i+ Z
r))/(atomic percentage C)=0.4 to 0.8
2, according to the cobalt-based super-alloy of claim 1, it is characterized in that its chemical ingredients is: 0.36 carbon, 29% chromium, 11% nickel, 7.3% tungsten, 0.5% zirconium, 0.2% titanium, be lower than 0.01% manganese, be lower than 0.07% silicon, 0.50% tantalum, be lower than 0.4% iron, 1.0% hafnium, 0.01% sulphur, be lower than 0.01% phosphorus, all the other are cobalt.
3, according to the purposes of the cobalt-based super-alloy of claim 1, be used for process industry gas turbine nozzle and transition member.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US67811884A | 1984-12-04 | 1984-12-04 | |
| US678,118 | 1984-12-04 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN85109085A CN85109085A (en) | 1986-08-20 |
| CN1011984B true CN1011984B (en) | 1991-03-13 |
Family
ID=24721479
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN85109085A Expired CN1011984B (en) | 1984-12-04 | 1985-11-14 | Cobalt-base superalloy and cast and welded industrial gas turbine component thereof |
Country Status (6)
| Country | Link |
|---|---|
| EP (1) | EP0186797B1 (en) |
| JP (1) | JPS61149450A (en) |
| CN (1) | CN1011984B (en) |
| DE (1) | DE3571146D1 (en) |
| IN (1) | IN164571B (en) |
| NO (1) | NO166542C (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2769024A1 (en) * | 1997-09-29 | 1999-04-02 | Saint Gobain Isover | COBALT-BASED ALLOY, ARTICLE PRODUCED FROM THE ALLOY AND METHOD FOR MANUFACTURING THE SAME |
| US8252376B2 (en) * | 2001-04-27 | 2012-08-28 | Siemens Aktiengesellschaft | Method for restoring the microstructure of a textured article and for refurbishing a gas turbine blade or vane |
| JP2005158471A (en) * | 2003-11-25 | 2005-06-16 | Kyocera Corp | Ceramic heater and manufacturing method thereof |
| EP1696704B1 (en) | 2003-11-25 | 2009-07-29 | Kyocera Corporation | Ceramic heater and method for manufacture thereof |
| US6983599B2 (en) * | 2004-02-12 | 2006-01-10 | General Electric Company | Combustor member and method for making a combustor assembly |
| US20070017906A1 (en) * | 2005-06-30 | 2007-01-25 | General Electric Company | Shimmed laser beam welding process for joining superalloys for gas turbine applications |
| CN102021558B (en) * | 2009-09-09 | 2012-07-11 | 沈阳大陆激光技术有限公司 | Alloy powder for circulating fluidized bed boiler water wall tube laser cladded coating |
| CN108070742A (en) * | 2016-11-15 | 2018-05-25 | 中国科学院金属研究所 | A kind of gas turbine guide vane cobalt base superalloy and its preparation method and application |
| EP3650138B1 (en) * | 2018-11-06 | 2021-10-20 | Hamilton Sundstrand Corporation | Cold spray forming |
| EP3677697A1 (en) * | 2019-01-07 | 2020-07-08 | Siemens Aktiengesellschaft | Co-alloy for additive manufacturing and method |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB891550A (en) * | 1959-08-28 | 1962-03-14 | Sierra Metals Corp | Metal alloys |
| US3383205A (en) * | 1964-12-14 | 1968-05-14 | Gen Electric | Cobalt base alloys |
| US3549356A (en) * | 1969-01-06 | 1970-12-22 | Gen Electric | High temperature corrosive resistant cobalt-base alloys |
| US3582320A (en) * | 1969-12-22 | 1971-06-01 | Robert B Herchenroeder | Cobalt base alloy |
| US3933484A (en) * | 1974-05-31 | 1976-01-20 | Owens-Corning Fiberglas Corporation | Cobalt-base alloy |
| JPS5582741A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
| JPS5582743A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
| JPS5582744A (en) * | 1978-12-15 | 1980-06-21 | Hitachi Ltd | High-strength high-toughness cobalt alloy |
-
1985
- 1985-11-14 CN CN85109085A patent/CN1011984B/en not_active Expired
- 1985-11-18 IN IN818/CAL/85A patent/IN164571B/en unknown
- 1985-11-28 JP JP60266298A patent/JPS61149450A/en active Granted
- 1985-12-03 EP EP85115301A patent/EP0186797B1/en not_active Expired
- 1985-12-03 NO NO854859A patent/NO166542C/en unknown
- 1985-12-03 DE DE8585115301T patent/DE3571146D1/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| JPS61149450A (en) | 1986-07-08 |
| NO166542C (en) | 1991-08-07 |
| CN85109085A (en) | 1986-08-20 |
| NO854859L (en) | 1986-06-05 |
| DE3571146D1 (en) | 1989-07-27 |
| NO166542B (en) | 1991-04-29 |
| EP0186797A1 (en) | 1986-07-09 |
| JPH0459378B2 (en) | 1992-09-22 |
| IN164571B (en) | 1989-04-15 |
| EP0186797B1 (en) | 1989-06-21 |
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