CN104313397A - Nickel base superalloy compositions being substantially free of rhenium and superalloy articles - Google Patents
Nickel base superalloy compositions being substantially free of rhenium and superalloy articles Download PDFInfo
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- CN104313397A CN104313397A CN201410525776.5A CN201410525776A CN104313397A CN 104313397 A CN104313397 A CN 104313397A CN 201410525776 A CN201410525776 A CN 201410525776A CN 104313397 A CN104313397 A CN 104313397A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- 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
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A nickel base superalloy composition substantially free of rhenium includes, in percentages by weight: about 5-8 Cr; about 7-8 Co; about 1.3-2.2 Mo; about 4.75-6.75 W; about 6.0-7.0 Ta; if present, up to about 0.5 Ti; about 6.0-6.4 Al; about 0.15-0.6 Hf; if present, from about 0.03-0.06 C; if present, up to about 0.004 B; if present, one or more rare earths selected from Y, La, and Ce up to about 0.03 total, the balance including nickel and incidental impurities. The superalloy composition is able to provide sustained-peak low cycle fatigue and/or oxidation resistance properties comparable to second generation superalloy compositions including at least about 3 wt% rhenium. Superalloy articles incorporating the compositions include nozzles, shrouds, and splash plates for gas turbine engines.
Description
The application is the divisional application of following application: the applying date: on August 25th, 2008; Application number: 200880105530.5 (PCT/US2008/074171); Denomination of invention: " nickel base superalloy compositions of substantially free of rhenium and superalloy articles ".
The cross reference of related application
This application claims the right of priority of the U.S. Provisional Application sequence number 60/969,360 that on August 31st, 2007 submits to, described provisional application is incorporated herein by reference.
Invention field
Embodiment disclosed herein relates generally to nickel based super alloy and comprises the goods of nickel based super alloy.Disclosed embodiment can be used for being arranged in the parts in gas turbine engine hot arc, more particularly, for non-creep restricted type application as in turbine nozzle and housing.
Background of invention
The efficiency of gas turbine engine depends on the working temperature of various engine parts to a great extent, and working temperature increases, and efficiency increases.Along with to increasing the seeking of efficiency, people have developed and can bear more and more higher temperature and the superalloy that keeps its structural integrity.
Nickel based super alloy is widely used in whole aircraft engine, comprises in the application of turbine blade, nozzle and housing.For improving motor performance, Aeroengine Design needs the alloy that can bear more and more higher temperature.Although housing and nozzle application are without the need for the high temperature creep-resisting level identical with blade applications, it needs similar heat resistanceheat resistant mechanical failure performance and environment resistant degraded performance really.To keep its intensity due to it under the temperature of fusion of height to 90% and there is excellent environmental resistance, therefore superalloy is applied in the application of these high requests.
Monocrystalline (SC) superalloy can be divided into " four generations " based on the composition of alloy and performance similarity.The restriction feature of so-called " first-generation " SC superalloy there is not alloying element rhenium (Re).Such as, United States Patent (USP) 5,154,884,5,399,313,4,582,548 and 4,209,348 respectively disclose substantially without the superalloy compositions of Re.
Representational SC nickel based super alloy is famous with Rene N4 in the art, and the nominal of Rene N4 consists of: 6.0-7.0%Co, 9.5-10.0%Cr, 1.5%Mo, 6.0%W, 4.8%Ta, 4.2%Al, 3.5%Ti, 0.5%Nb, the B of maximum 0.01%, the Hf of maximum 0.2%, surplus is Ni and C substantially, and wherein C is defined as maximum 0.01% (100ppm).Object for comparing in accompanying drawing provides Rene N4 superalloy and the mach one speed loop oxidation test data of AM1 superalloy under 2150 °F.
It is found that the Re adding about 3% weight in superalloy compositions will make creep resistance fracture energy improve about 50 °F (28 DEG C) with antifatigue benefit.Alloy product is if CMSX-4, PWA-1484 and Rene N5 is all containing the Re of about 3% weight.These " s-generation " alloys, at such as United States Patent (USP) 4,719,080,4,643,782,6,074,602 and 6,444, have open in 057.
United States Patent (USP) 4,719,080 provides the relation between the component being called " P-value ", and P is defined as=-200Cr+80Mo-20Mo
2-250Ti
2-50 (Ti x Ta)+15Cb+200W-14W
2+ 30Ta-1.5Ta
2+ 2.5Co+1200Al-100Al
2+ 100Re+1000Hf-2000Hf
2+ 700Hf
3-2000V-500C-15000B-500Zr.This patent is emphasized, higher " P-value " is relevant to the corrosive combination of high strength, stability, heat-treatability and resistance to oxidation.Especially, superalloy compositions disclosed in this patent is confined to " P-value " higher than 3360.
United States Patent (USP) 6,074,602 relate to the nickel based super alloy being suitable for manufacturing single crystal casting.Superalloy disclosed in it is containing the Al of Ti, 5-7% weight of Ta, 0-2% weight of W, 3-8% weight of Mo, 3-8% weight of Co, 0-2% weight of Cr, 5-10% weight of 5-10% weight, the high Y to B, 0.0-0.04% weight of C, 0.003-0.006% weight of Hf, 0.03-0.07% weight of Re, 0.08-0.2% weight of 6% weight, and surplus is nickel and adjoint impurity.Compared with first-generation nickel based super alloy, based on stress breaking strength and low, high cycle fatigue, these superalloy have the temperature capability of raising.In addition, described superalloy has better anti-cyclic oxidation degenerative and corrosion and heat resistant than first-generation superalloy.
United States Patent (USP) 5,151,249,5,366,695,6,007,645 and 6,966,956 relate to third and fourth generation superalloy.Generally speaking, the feature of third generation superalloy is the introduction of the Re of about 6% weight; Forth generation superalloy contains Re and the alloying element Ru of about 6% weight.These superalloy compositions show the value of the add-on increasing Re from mechanical property angle.
First-generation SC superalloy does not provide heat resistanceheat resistant mechanical fatigue (TMF) performance of many heating section components required by turbine nozzle and housing or environmental resistance.In addition, first-generation SC superalloy can not provide acceptable high temperature oxidation resistance for these parts.
At present, aircraft engine main superalloy using s-generation type in increasing hot arc application.Alloying element Re is the most effective sosoloid reinforcer that this kind of superalloy is known, and therefore it has been widely used as the alloy Addition ofelements that SC and cylindricality crystal grain orienting solidify (DS) superalloy.S-generation superalloy has remarkable oxidation-resistance property and the balance of gratifying mechanical property.
The known superalloy compositions with lower Re content can not provide the performance that can obtain from s-generation superalloy.Especially, at United States Patent (USP) 4,719, in 080, Re goes out with the first-generation namely without the performance that the superalloy of Re is comparable lower than the data presentation of a kind of alloy (i.e. B1) of 2.9%.Therefore, in the exploitation of superalloy compositions, trend has been use the Re of at least 3% weight to obtain the balance of gratifying antioxidant property and hot strength.
But the whole world of raw-material cost and particularly Re shortage to exploitation with low, preferably 0% Re level but the mechanical property of improvement that s-generation superalloy can be provided to represent and the superalloy compositions of antioxidant property propose challenge.
Therefore the nickel base superalloy compositions that the substantially free of rhenium that can provide required mechanical behavior under high temperature and antioxidant property is provided is needed.
Summary of the invention
Needs above-mentioned can not provide the exemplary of the nickel base superalloy compositions of required thermomechanical property, creep strength and antioxidant property to be met containing Re by providing substantially.
An exemplary provides a kind of nickel base superalloy compositions, and it contains: the Cr of about 5-8% weight; The Co of about 7-8% weight; The Mo of about 1.3-2.2% weight; The W of about 4.75-6.75% weight; The Ta of about 6.0-7.0% weight; The high Ti to about 0.5% weight, if present; The Al of about 6.0-6.4% weight; The high Re to about 1.3% weight, if present; The Hf of about 0.15-0.6% weight; The C of about 0.03-0.06% weight, if present; The high B to about 0.004% weight, if present; High one or more to about 0.03% weight are selected from the rare earth element of Y, La and Ce altogether, if present; Surplus is nickel and adjoint impurity.
An exemplary provides a kind of nickel-based monocrystal goods comprising superalloy, and described superalloy contains: the Cr of about 5-8% weight; The Co of about 7-8% weight; The Mo of about 1.3-2.2% weight; The W of about 4.75-6.75% weight; The Ta of about 6.0-7.0% weight; The high Ti to about 0.5% weight, if present; The Al of about 6.0-6.4% weight; The high Re to about 1.3% weight, if present; The Hf of about 0.15-0.6% weight; The C of about 0.03-0.06% weight, if present; The high B to about 0.004% weight, if present; High one or more to about 0.03% weight are selected from the rare earth element of Y, La and Ce altogether, if present; Surplus is nickel and adjoint impurity.
An exemplary provides a kind of combustion turbine engine components from nickel base superalloy compositions casting, and described nickel base superalloy compositions comprises: the Cr of about 5-8; The Co of about 7-8; The Mo of about 1.3-2.2; The W of about 4.75-6.75; The Ta of about 6.0-7.0; The Ti of height to about 0.5, if present; The Al of about 6.0-6.4; The Re of height to about 1.3, if present; The Hf of about 0.15-0.6; The C of about 0.03-0.06, if present; The B of height to about 0.004, if present; Altogether high to about 0.03 one or more be selected from the rare earth element of Y, La and Ce, if present; Surplus is nickel and adjoint impurity.
Accompanying drawing is sketched
Theme of the present invention to particularly point out and claimed clearly at the end part of specification sheets.But the present invention can be understood better with reference to the description below in conjunction with accompanying drawing, in the accompanying drawings:
Fig. 1 is the contrast diagram of anti-sustained peak low cycle fatigue (SPLCF) performance.
Fig. 2 is the contrast diagram of 2150 °F of lower mach one speed loop oxidation test data.
Fig. 3 is the contrast diagram of 2000 °F of lower mach one speed loop oxidation test data.
Fig. 4 is the contrast diagram of 2150 °F of lower mach one speed loop oxidation test data.
Fig. 5 is the diagram of the creep rupture data normalization under 2100 °F/10ksi to the s-generation nickel based super alloy of the Re containing about 3% weight.
Fig. 6 is the diagram of the creep rupture data normalization under 1600 °F, 1800 °F, 2000 °F and 2100 °F to the s-generation nickel based super alloy of the Re containing about 3% weight.
Fig. 7 is the diagram of the SPLCF data normalization under 2000 °F and 1600 °F to the s-generation nickel based super alloy of the Re containing about 3% weight.
Fig. 8 is the diagram of the SPLCF data normalization under 2000 °F to the s-generation nickel based super alloy of the Re containing about 3% weight.
Fig. 9 is the schematic diagram of exemplary gas turbine engine turbine blade.
Detailed Description Of The Invention
See accompanying drawing (label identical in each accompanying drawing represents identical element), Fig. 9 shows parts goods 20 of gas turbine engine, illustrates with gas-turbine blade 22.Gas-turbine blade 22 contains the middle lateral extension platform 28 of aerofoil profile 24, the joint gas-turbine blade 22 of swallow tail form and the annex 26 of turbine disk (not shown) and aerofoil profile 24 and annex 26.In an exemplary embodiment, parts goods 20 are monocrystalline substantially.That is, parts goods 20 at least about 80% volume, be more preferably the single die of single crystalline orientation at least about 95% volume.The region that may have other crystalline orientations of smaller size smaller mark and be separated by low angle boundary.Described single crystal structure is prepared by method directional freeze well known to those skilled in the art by alloy composite.In another exemplary, parts goods 20 are the polycrystalline of directional orientation, wherein have at least some crystal grain with general orientation preferred growth direction.
The alloy composite discussed herein can be used on other combustion turbine engine components as in nozzle, housing and splash plate.
Embodiment disclosed herein balances various alloying element, to the contribution of composition thermomechanical property, creep strength and antioxidant property, deleterious effect is reduced to minimum.Unless otherwise noted, otherwise all values are all in weight percent.
Such as, some embodiment disclosed herein contains the chromium (Cr) at least about 5%.Amount lower than about 5% may reduce corrosion and heat resistant.Amount higher than about 8% may cause the anti-cyclic oxidation performance of topological Mi Dui (TCP) phase instability and difference.
Some embodiment disclosed herein contains the Co at least about 7% to about 8%.Lower cobalt amount may reduce alloy stability.Higher amount may reduce γ ' solid solubility temperature, thus affects hot strength and antioxidant property.
Some embodiment disclosed herein contains the molybdenum (Mo) of the amount of about 1.3% to 2.2%.Namely minimum value is enough to Intensive intervention body.The amount exceeding maximum value may cause surface instability.Higher Mo amount adversely may affect corrosion and heat resistant and antioxidant property simultaneously.
Some embodiment disclosed herein contains the tungsten (W) of the amount of about 4.75% to about 6.75%.Lower W amount may reduce intensity.With regard to TCP phase is formed, higher amount may produce unstable.Higher amount also may reduce oxidation capacity.
Some embodiment disclosed herein can contain the tantalum (Ta) of the amount of about 6.0% to about 7.0%.Other embodiments can contain the Ta of the amount of about 6.25% to about 6.5%.
Some embodiment disclosed herein can contain the aluminium (Al) of the amount of about 6.0% to about 6.5%.Other embodiments can containing the Al of about 6.2% to about 6.5%.
Some embodiment disclosed herein is optionally containing the titanium (Ti) of height to about 0.5%.Titanium is effective γ ' stiffening agent.Adding of optional Ti can strengthen γ ' phase, thus improves creep resisting ability.But antioxidant property may affect adversely because of adding of Ti, especially higher than about 0.5% level.
In an exemplary embodiment, superalloy compositions is not substantially containing Re." substantially not containing Re " refers to that being added in exemplary composition of Re is not that nominal requires.But can predict, compatible revert alloy (alloy namely used, surplus or excess alloy or secondary alloy) can be utilized to provide exemplary superalloy compositions.In such embodiments, Re can be as high as the amount existence of about 1.3%.
Some embodiment disclosed herein contains the hafnium (Hf) of the amount of about 0.15% to about 0.6%.Hafnium is used for improving the antioxidant property of coating alloy and corrosion and heat resistant and can improves the life-span of the heat insulating coat of applying.The hafnium adding about 0.7% can be satisfactory, but will adversely affect resistant to stress cracking and onset melting temperature when being added beyond about 1%.
Some embodiment disclosed herein can containing the boron (B) of height to about 0.004%.B provides strain for low angle boundary and provides the tolerance interval of increase for the component with low angle boundary.
The content of carbon (C) can be about 0.03% to about 0.06%, if present.Lower limit provides enough C and realizes more clean molten alloy and contribute to improving erosion resistance.
Can optionally add in some embodiment high to about 0.03% the rare earth element of amount and yttrium (Y), lanthanum (La) and (Ce).These additives improve antioxidant property by improving the confining force of protectiveness alumina scale.Higher amount may promote the mould/metal reaction at casting surface place, increases component and introduces content.
An exemplary embodiment is containing nickel based super alloy, the nominal composition of described nickel based super alloy comprises: Ti, the Al of 6.2% weight of the W of Mo, 6.0-6.5% weight of the Cr of 6.0% weight, Co, 1.5-2.0% weight of 7.5% weight, the Ta of 6.5% weight, 0% weight, the C of Hf, 0.03-0.06% weight of Re, 0.15-0.6% weight of 0% weight, the B of 0.004% weight, surplus is nickel and adjoint impurity.Some exemplary also have P-value lower than 3360 feature, wherein said P-value is determined by the relation provided above.In exemplary embodiment, described P-value is lower than 3250.
Following table 1 gives the serial and relevant Re ratio of exemplary composition and P-value.The % weight of % weight to W that " Re ratio " is defined as Re in this article adds the ratio of the summation of the % weight of Mo.For the exemplary substantially not comprising Re, Re ratio is zero (such as alloy 1-4,15 and 16) substantially.The value of each composition all provides with % weight, and surplus is nickel and adjoint impurity.For comparing object, give the nominal composition of Rene N5, Re ratio and P value.
Following table 2 gives another exemplary composition series, relevant Re ratio and normalizes to creep rupture (CR) data of the s-generation (namely containing the Re of 3%) nickel based super alloy.Exemplary composition in table 2 provides the composition of the Re containing about 1% weight that can provide required creep-rupture strength.The contrast of data from table 2 and s-generation alloy (Re containing 3% weight) and first-generation alloy (Re containing 0% weight) has been shown in Fig. 8.
Table 1
Table 2
Fig. 1 shows some embodiment disclosed herein and is improved and anti-sustained peak low cycle fatigue (SPLCF) performance more comparable with s-generation superalloy than first-generation superalloy.First-generation SC superalloy does not provide heat resistanceheat resistant mechanical failure (TMF) performance required in many heating section components.SPLCF is brought by the combining properties of uniqueness, and one of described performance is antioxidant property.Due to the thermograde in parts, therefore SPLCF or TMF ability is very important for the hardware of cooling.
Fig. 2 provides the contrast diagram of the data of weight loss in time in explanation 2150 °F lower mach one speed loop oxidation test process, shows that some embodiment disclosed herein has the antioxidant property of improvement.
Fig. 3 provides the contrast diagram of the data of weight loss in time in explanation 2000 °F lower mach one speed loop oxidation test process, shows that some embodiment disclosed herein has the antioxidant property of improvement.
Fig. 4 provides the contrast diagram of the data of weight loss in time in explanation 2000 °F lower mach one speed loop oxidation test process, shows that some embodiment disclosed herein has the antioxidant property of improvement.
Fig. 5 is the diagram of the creep rupture data normalization under 2100 °F/10ksi to the s-generation nickel based super alloy of the Re containing about 3% weight.Some embodiment disclosed herein is comparable to s-generation superalloy and is significantly improved than first-generation superalloy.It is believed that, especially at the temperature more than 2100 °F, the stability of γ ' phase is done to contribute to the performance improved.In this article in some composition disclosed, the volume fraction of 2150 °F of lower γ ' phases is about 46%, comparable with s-generation superalloy, and usually above first-generation superalloy.The relative stability of γ ' phase is of value to anti-SPLCF performance and by the creep resistance fracture property under favourable influence 2100 °F.
The creep rupture data normalizing to s-generation nickel based super alloy show that the embodiment with low Re content disclosed herein is more comparable to s-generation superalloy than first-generation superalloy.1600 °F, 1800 °F, 2000 °F and the 2100 °F of lower alloys 5 normalization method creep rupture data to alloy 14 (table 1) are given in Fig. 6.
Fig. 7 is the diagram of the SPLCF data normalization under 2000 °F and 1600 °F to the s-generation nickel based super alloy of the Re containing about 3% weight.
Fig. 8 is the diagram of the SPLCF data normalization under 2000 °F to the s-generation nickel based super alloy of the Re containing about 3% weight.
Superalloy compositions disclosed herein can be used to prepare the single crystal articles of the equal temperature capability of goods had and obtain from s-generation superalloy.The goods of such generation can be the parts of gas turbine engine.Such goods can be the airfoil component of gas turbine engine blade or wheel blade.The goods of such generation can be nozzle, housing, splash plate or other high-temperature components.
Some exemplary disclosed herein when directional freeze be flyer gas turbine engine heating section component particularly rotating paddle time be particularly useful.
The method preparing any goods disclosed herein one or more the starting material preparation comprised in the rhenium of nickeliferous, cobalt, chromium, molybdenum, tungsten, aluminium, tantalum, optional titanium, basic 0% weight, hafnium, optional carbon, optional yttrium, cerium and lanthanum has the nickel base single crystal element material of the chemical constitution provided in disclosed embodiment.The thermal treatment making described superalloy element material stand to be suitable for and suitable follow-up casting technique.Embodiment as an alternative comprises and substitutes at least part of described starting material with superalloy returns.Therefore, when using returns, the embodiment that nominal is described as not conforming to Re can contain the high Re to about 1.3% weight.
Therefore, superalloy compositions disclosed herein provides required thermomechanical property, creep strength and antioxidant property by the contribution of equilibrium composition element with the Re content lowered.
This specification sheets uses the open the present invention of embodiment, comprises optimal mode, also makes those skilled in the art can realize and utilize the present invention.Scope of patent protection of the present invention is defined by the claims, and may comprise other embodiments that those skilled in the art expect.Other embodiments this kind of will contain within the scope of the claims, if if its textural element is not different from the word language of claim or it contains and the equivalent structural elements of the word language of claim without substantial differences.
Claims (16)
1. a nickel base superalloy compositions, described superalloy compositions is made up of following:
The Cr of 5-6% weight;
The Co of 7-8% weight;
The Mo of 1.5% weight;
The W of 6-6.5% weight;
The Ta of 6.0-7.0% weight;
The Al of 6.0-6.5% weight;
The Hf of 0.15-0.6% weight;
The C of 0.03-0.06% weight;
The B of 0.004-0.008% weight;
High one or more to 0.03% weight are selected from the rare earth element of Y, La and Ce altogether, if present; Wherein said superalloy compositions does not substantially contain Re and under 2000 F/18 ksi, exhibits greater than the anti-sustained peak low cycle fatigue of 10500 weeks;
Surplus comprises nickel and adjoint impurity.
2. nickel base superalloy compositions according to claim 1, the feature of described superalloy compositions is that P-value is lower than 3360, and wherein said P-value is defined as: P=-200 Cr+80 Mo – 20 Mo
2-250 Ti
2– 50 (Ti x Ta)+15 Cb+200 W – 14 W
2+ 30 Ta – 1.5 Ta
2+ 2.5 Co+1200 Al – 100 Al
2+ 100 Re+1000 Hf – 2000 Hf
2+ 700 Hf
3– 2000 V – 500 C – 15000 B – 500 Zr.
3. nickel base superalloy compositions according to claim 2, the feature of described superalloy compositions is that P-value is lower than 3050.
4. nickel base superalloy compositions according to claim 1, the nominal of described superalloy compositions consists of: the Mo of the Cr of the Al of 6.2% weight, the Ta of 6.5% weight, 6% weight, the W of 6% weight, 1.5% weight, the Re of 0% weight, the Co of 7.5% weight, the C of 0.03% weight, the B of 0.004% weight, the Hf of 0.15% weight, surplus is nickel and adjoint impurity.
5. nickel base superalloy compositions according to claim 1, the nominal of described superalloy compositions consists of: the Mo of the Cr of the Al of 6.2% weight, the Ta of 6.5% weight, 6% weight, the W of 6.5% weight, 1.5% weight, the Re of 0% weight, the Co of 7.5% weight, the C of 0.03% weight, the B of 0.004% weight, the Hf of 0.15% weight, surplus is nickel and adjoint impurity.
6. nickel base superalloy compositions according to claim 1, the nominal of described superalloy compositions consists of: the Mo of the Cr of the Al of 6.2% weight, the Ta of 6.5% weight, 6% weight, the W of 6.5% weight, 1.5% weight, the Re of 0% weight, the Co of 7.5% weight, the C of 0.03% weight, the B of 0.004% weight, the Hf of 0.6% weight, surplus is nickel and adjoint impurity.
7. nickel-based monocrystal goods, described goods comprise superalloy, and described superalloy is made up of following:
The Cr of 5-8% weight;
The Co of 7-8% weight;
The Mo of 1.5% weight;
The W of 4.75-6.75% weight;
The Ta of 6.0-7.0% weight;
The Al of 6.0-6.5% weight;
The Hf of 0.15-0.6% weight;
The C of 0.03-0.06% weight;
The B of 0.004-0.008% weight;
High one or more wherein said superalloy compositions of rare earth element being selected from Y, La and Ce to 0.03% weight substantially do not contain Re and under 1600 F/18 ksi, exhibit greater than the anti-sustained peak low cycle fatigue of 2000 weeks altogether;
Surplus comprises nickel and adjoint impurity.
8. nickel-based monocrystal goods according to claim 7, wherein said superalloy provides at least one in the high temperature oxidation resistance comparable with the superalloy of the rhenium with at least 3% weight and anti-sustained peak low cycle fatigue property.
9., from a combustion turbine engine components for nickel base superalloy compositions casting, wherein said superalloy compositions is made up of following:
The Cr of 5-8% weight;
The Co of 7-8% weight;
The Mo of 1.5-2.0% weight;
The W of 4.75-6.75% weight;
The Ta of 6.0-7.0% weight;
The Al of 6.0-6.5% weight;
The Hf of 0.15-0.6% weight;
The C of 0.03-0.06% weight;
The B of 0.004-0.008% weight;
High one or more to 0.03% weight are selected from the rare earth element of Y, La and Ce altogether, if present; Wherein said superalloy compositions does not substantially contain Re and under 1600 F/18 ksi, exhibits greater than the anti-sustained peak low cycle fatigue of 2500 weeks; Surplus comprises nickel and adjoint impurity.
10. combustion turbine engine components according to claim 9, described parts are cast into single crystal articles.
11. combustion turbine engine components according to claim 9, described parts are directional freeze goods.
12. combustion turbine engine components according to claim 9, described parts are at least one in nozzle, housing and splash plate.
13. 1 kinds of nickel base superalloy compositions, described superalloy compositions is made up of following:
The Cr of 5-6% weight;
The Co of 7-8% weight;
The Mo of 2.0% weight;
The W of 6-6.5% weight;
The Ta of 6.0-7.0% weight;
The Al of 6.0-6.5% weight;
The Hf of 0.15-0.6% weight;
The C of 0.03-0.06% weight;
The B of 0.004-0.008% weight;
High one or more to 0.03% weight are selected from the rare earth element of Y, La and Ce altogether, if present; Wherein said superalloy compositions does not substantially contain Re and under 2000 F/18 ksi, exhibits greater than the anti-sustained peak low cycle fatigue of 10500 weeks;
Surplus comprises nickel and adjoint impurity.
14. nickel base superalloy compositions according to claim 13, the nominal of described superalloy compositions consists of: the Mo of the Cr of the Al of 6.2% weight, the Ta of 6.5% weight, 6% weight, the W of 6% weight, 2% weight, the Re of 0% weight, the Co of 7.5% weight, the C of 0.03% weight, the B of 0.004% weight, the Hf of 0.15% weight, surplus is nickel and adjoint impurity.
15. nickel base superalloy compositions according to claim 13, the nominal of described superalloy compositions consists of: the Mo of the Cr of the Al of 6.2% weight, the Ta of 6.5% weight, 6% weight, the W of 6.5% weight, 2% weight, the Re of 0% weight, the Co of 7.5% weight, the C of 0.03% weight, the B of 0.004% weight, the Hf of 0.15% weight, surplus is nickel and adjoint impurity.
16. nickel base superalloy compositions according to claim 13, the nominal of described superalloy compositions consists of: the Mo of the Cr of the Al of 6.2% weight, the Ta of 6.5% weight, 6% weight, the W of 6% weight, 2% weight, the Re of 0% weight, the Co of 7.5% weight, the C of 0.03% weight, the B of 0.004% weight, the Hf of 0.6% weight, surplus is nickel and adjoint impurity.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US96936007P | 2007-08-31 | 2007-08-31 | |
| US60/969,360 | 2007-08-31 | ||
| US11/964,668 | 2007-12-26 | ||
| US11/964,668 US20130230405A1 (en) | 2007-08-31 | 2007-12-26 | Nickel base superalloy compositions being substantially free of rhenium and superalloy articles |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200880105530.5A Division CN101790593A (en) | 2007-08-31 | 2008-08-25 | Nickel base superalloy compositions being substantially free of rhenium and superalloy articles |
Publications (1)
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|---|---|
| CN104313397A true CN104313397A (en) | 2015-01-28 |
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| CN200880105530.5A Pending CN101790593A (en) | 2007-08-31 | 2008-08-25 | Nickel base superalloy compositions being substantially free of rhenium and superalloy articles |
| CN201410525776.5A Pending CN104313397A (en) | 2007-08-31 | 2008-08-25 | Nickel base superalloy compositions being substantially free of rhenium and superalloy articles |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN200880105530.5A Pending CN101790593A (en) | 2007-08-31 | 2008-08-25 | Nickel base superalloy compositions being substantially free of rhenium and superalloy articles |
Country Status (6)
| Country | Link |
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| US (1) | US20130230405A1 (en) |
| EP (1) | EP2188401A1 (en) |
| JP (1) | JP5595917B2 (en) |
| CN (2) | CN101790593A (en) |
| CA (1) | CA2696939A1 (en) |
| WO (1) | WO2009032579A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106906382A (en) * | 2015-12-09 | 2017-06-30 | 通用电气公司 | Nickel based super alloy and its manufacture method |
| US10577679B1 (en) | 2018-12-04 | 2020-03-03 | General Electric Company | Gamma prime strengthened nickel superalloy for additive manufacturing |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009085420A1 (en) * | 2007-12-26 | 2009-07-09 | General Electric Company | Nickel base superalloy compositions, superalloy articles, and methods for stabilizing superalloy compositions |
| US20100254822A1 (en) * | 2009-03-24 | 2010-10-07 | Brian Thomas Hazel | Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom |
| US20100329921A1 (en) * | 2009-06-30 | 2010-12-30 | Joshua Leigh Miller | Nickel base superalloy compositions and superalloy articles |
| US20110076181A1 (en) * | 2009-09-30 | 2011-03-31 | General Electric Company | Nickel-Based Superalloys and Articles |
| US20110076180A1 (en) * | 2009-09-30 | 2011-03-31 | General Electric Company | Nickel-Based Superalloys and Articles |
| US9850765B2 (en) | 2011-12-07 | 2017-12-26 | MTU Aero Engines AG | Rhenium-free or rhenium-reduced nickel-base superalloy |
| ES2625825T3 (en) | 2012-10-26 | 2017-07-20 | MTU Aero Engines AG | Super-alloy with rhenium-free and creep-resistant nickel |
| EP3091095B1 (en) | 2015-05-05 | 2018-07-11 | MTU Aero Engines GmbH | Low density rhenium-free nickel base superalloy |
| US10253396B2 (en) * | 2016-09-02 | 2019-04-09 | General Electric Company | Modified articles, coated articles, and modified alloys |
| FR3072717B1 (en) * | 2017-10-20 | 2019-10-11 | Safran | SUPERALLIATION TURBINE PIECE COMPRISING RHENIUM AND METHOD OF MANUFACTURING THE SAME |
| CN108256192B (en) * | 2018-01-10 | 2021-06-01 | 中国科学院金属研究所 | Low-cycle fatigue-based thermomechanical fatigue life prediction method for metal material |
| US20230357897A1 (en) * | 2022-05-05 | 2023-11-09 | General Electric Company | Nickel-based superalloys and articles |
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| US3655458A (en) * | 1970-07-10 | 1972-04-11 | Federal Mogul Corp | Process for making nickel-based superalloys |
| GR80049B (en) * | 1983-12-27 | 1984-12-30 | Gen Electric | Nickel-based superalloys especially useful as compatible protective environmental coatings for advanced superalloys |
| GR80048B (en) * | 1983-12-27 | 1984-11-30 | Gen Electric | Yttrium and yttrium-silicon bearing nickel-based superalloys especially useful as comptible coatings for advanced superalloys |
| US4719080A (en) * | 1985-06-10 | 1988-01-12 | United Technologies Corporation | Advanced high strength single crystal superalloy compositions |
| US6074602A (en) * | 1985-10-15 | 2000-06-13 | General Electric Company | Property-balanced nickel-base superalloys for producing single crystal articles |
| US5100484A (en) * | 1985-10-15 | 1992-03-31 | General Electric Company | Heat treatment for nickel-base superalloys |
| US5011353A (en) * | 1988-12-06 | 1991-04-30 | Allied-Signal Inc. | High temperature turbine engine structure |
| US5435861A (en) * | 1992-02-05 | 1995-07-25 | Office National D'etudes Et De Recherches Aerospatiales | Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production |
| JPH09157777A (en) * | 1995-12-12 | 1997-06-17 | Mitsubishi Materials Corp | Nickel base alloy excellent in thermal fatigue resistance, high temperature creep resistance and high temperature corrosion resistance |
| US5630700A (en) * | 1996-04-26 | 1997-05-20 | General Electric Company | Floating vane turbine nozzle |
| JPH10168534A (en) * | 1996-12-10 | 1998-06-23 | Toshiba Corp | Turbine blade and its production |
| US6096141A (en) * | 1998-08-03 | 2000-08-01 | General Electric Co. | Nickel-based superalloys exhibiting minimal grain defects |
| US20020007877A1 (en) * | 1999-03-26 | 2002-01-24 | John R. Mihalisin | Casting of single crystal superalloy articles with reduced eutectic scale and grain recrystallization |
| EP1184473B1 (en) * | 2000-08-30 | 2005-01-05 | Kabushiki Kaisha Toshiba | Nickel-base single-crystal superalloys, method of manufacturing same and gas turbine high temperature parts made thereof |
| JP2002167636A (en) * | 2000-10-30 | 2002-06-11 | United Technol Corp <Utc> | Low density oxidation resistant superalloy material capable of thermal barrier coating retention without bond coat |
| WO2003080882A1 (en) * | 2002-03-27 | 2003-10-02 | National Institute For Materials Science | Ni-BASE DIRECTIONALLY SOLIDIFIED SUPERALLOY AND Ni-BASE SINGLE CRYSTAL SUPERALLOY |
| US6706241B1 (en) * | 2002-11-12 | 2004-03-16 | Alstom Technology Ltd | Nickel-base superalloy |
-
2007
- 2007-12-26 US US11/964,668 patent/US20130230405A1/en not_active Abandoned
-
2008
- 2008-08-25 CN CN200880105530.5A patent/CN101790593A/en active Pending
- 2008-08-25 EP EP08798597A patent/EP2188401A1/en not_active Withdrawn
- 2008-08-25 WO PCT/US2008/074171 patent/WO2009032579A1/en active Application Filing
- 2008-08-25 JP JP2010523068A patent/JP5595917B2/en not_active Expired - Fee Related
- 2008-08-25 CN CN201410525776.5A patent/CN104313397A/en active Pending
- 2008-08-25 CA CA2696939A patent/CA2696939A1/en not_active Abandoned
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106906382A (en) * | 2015-12-09 | 2017-06-30 | 通用电气公司 | Nickel based super alloy and its manufacture method |
| CN106906382B (en) * | 2015-12-09 | 2019-05-14 | 通用电气公司 | Nickel based super alloy and its manufacturing method |
| US10378087B2 (en) | 2015-12-09 | 2019-08-13 | General Electric Company | Nickel base super alloys and methods of making the same |
| US10801088B2 (en) | 2015-12-09 | 2020-10-13 | General Electric Company | Nickel base super alloys and methods of making the same |
| US10577679B1 (en) | 2018-12-04 | 2020-03-03 | General Electric Company | Gamma prime strengthened nickel superalloy for additive manufacturing |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2696939A1 (en) | 2009-03-12 |
| US20130230405A1 (en) | 2013-09-05 |
| EP2188401A1 (en) | 2010-05-26 |
| JP2011514431A (en) | 2011-05-06 |
| JP5595917B2 (en) | 2014-09-24 |
| WO2009032579A1 (en) | 2009-03-12 |
| CN101790593A (en) | 2010-07-28 |
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