CN1036666C - Heat-resisting steel and combustion turbine made of it - Google Patents
Heat-resisting steel and combustion turbine made of it Download PDFInfo
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- CN1036666C CN1036666C CN88100065A CN88100065A CN1036666C CN 1036666 C CN1036666 C CN 1036666C CN 88100065 A CN88100065 A CN 88100065A CN 88100065 A CN88100065 A CN 88100065A CN 1036666 C CN1036666 C CN 1036666C
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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
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/46—Ferrous alloys, e.g. steel alloys containing chromium with nickel with vanadium
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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
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
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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
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
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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
- C22C19/07—Alloys based on nickel or cobalt based on cobalt
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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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2200/00—Mathematical features
- F05D2200/10—Basic functions
- F05D2200/11—Sum
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Heat-resistant steel consisting, in weight percent, of 0.05 to 0.2 % of C, up to 0.5 % of Si, up to 0.6 % of Mn, 8 to 13 % of Cr, 1.5 to 3 % of Mo, 2 to 3 % of Ni, 0.05 to 0.3 % of V, at least one of Nb and Ta with the sum being from 0.02 to 0.2 %, 0.02 to 0.1 % of N, and the balance consisting substantially of Fe. The heat-resistant steel of the present invention is used at least for a turbine disc of a gas turbine consisting of a turbine shaft, vane, axis, etc., so that, this gas turbine structure has high creep rupture strength and charpy impact value.
Description
The present invention relates to a kind of high temperature steel of novelty; More particularly, the present invention relates to a kind of novel internal combustion turbine, wherein use described high temperature steel.
At present, the impeller of internal combustion turbine adopts the Cr-Mo-V steel to do.
From the angle of save energy, exist the demand of improving thermal efficiency of gas turbine recently always.Improving the most feasible approach of thermal efficiency of gas turbine is to improve gases used temperature and pressure.By gases used temperature is brought up to 1300 ℃ by 1100 ℃, compression ratio is brought up to 15 by 10, thermo-efficiency is expected to improve 3%.
Yet, because therefore conventional Cr-Mo-V steel its insufficient strength under high like this temperature and compression ratio needs high-intensity steel.Creep-rupture strength has maximum influence to high-temperature behavior, so for intensity, it is a key condition.Known austenitic steel, Ni base alloy, Co base alloy and martensitic steel are than the high structural steel of Cr-Mo-V steel creep-rupture strength.Yet hot workability, machining property and the vibration damping etc. of Ni base alloy and Co base alloy are undesirable.Austenitic steel also is undesirable, and this is owing to when temperature is 400-450 ℃, and not high from its hot strength of angle of whole gas turbine engine systems.On the other hand, martensitic steel performs well in other building block, and has enough hot strengths.Typical martensitic steel has open in Japanese Patent Application Publication No58-110661 and No60-135054 and Japanese patent laid-open publication gazette No46-2739.Yet these materials can not reach high creep-rupture strength under 400-450 ℃ temperature, and therefore the toughness step-down after the common in addition long-time heat can not be used as turbine wheel, and the result can not realize the improvement to thermal efficiency of gas turbine.Can obviously find out only have the High Temperature High Pressure problem that high-intensity material solves internal combustion turbine by the above, just can not improve the temperature of gas if use.In a word, with the increase of intensity, toughness descends.
Therefore, an object of the present invention is to provide a kind of high temperature steel, described high temperature steel not only has hot strength, and still has high tenacity after long-time heat.
Another object of the present invention provides a kind of internal combustion turbine with high thermal efficiency.
For achieving the above object, according to a first aspect of the invention, a kind of high temperature steel is provided, the C that wherein contains 0.05-0.2% (weight), the Si that is less than 0.5% (weight), the Mn that is less than 0.6% (weight), the Cr of 8-13% (weight), the Mo of 1.5-3% (weight), the Ni of 2-3% (weight), the V of 0.05-0.3% (weight), total amount is Nb and/or the Ta of 0.02-0.2% (weight), the N of 0.02-0.1% (weight), the ratio (Mn/Ni) of above-mentioned Mn and Ni is less than 0.11, and surplus is iron basically.
According to a second aspect of the invention, a kind of high temperature steel is provided, the C that wherein contains 0.07-0.15% (weight), the Si of 0.01-0.1% (weight), the Mn of 0.1-0.4% (weight), the Cr of 11-12.5% (weight), the Ni of 2.2-3.0% (weight), the Mo of 1.8-2.5% (weight), total amount is Nb and/or the Ta of 0.04-0.08% (weight), the V of 0.15-0.25% (weight), the N of 0.04-0.08% (weight), above-mentioned Mn is 0.04-0.10 with the ratio (Mn/Ni) of Ni, and surplus is iron basically, and above-mentioned high temperature steel has tempered martensite structure completely.
In addition, steel of the present invention also can contain at least a material that is selected from down group: the W that is less than 1% (weight), the Co that is less than 0.5% (weight), the Cu that is less than 0.5% (weight), the B that is less than 0.01% (weight), the Ti that is less than 0.5% (weight), the Al that is less than 0.3% (weight), the Zr that is less than 0.1% (weight), the Hf that is less than 0.1% (weight), the Ca that is less than 0.01% (weight) is less than the Mg of 0.01% (weight), is less than the Y of 0.01% (weight) and is less than the rare earth element of 0.01% (weight).
The composition of steel of the present invention should be regulated like this, and the feasible Cr equivalent that is calculated by following equation preferably guarantees in fact not contain in the steel δ-ferritic phase less than 10.
The Cr equivalent=-40C-2Nn-4Ni-30N
+6Si+Cr+4Mo+11V
+ 5Nb+2.5Ta (in above-mentioned equation, uses the weight percent content of respective element in the alloy to calculate.)
According to a third aspect of the present invention, a kind of gas-turbine wheel is provided, described impeller partly has a plurality of grooves that blade is embedded at its excircle, its center is the thickest, there are a plurality of bolts that make to pass at its circumferential periphery, it is characterized in that this impeller made by the martensitic steel with following performance, promptly 500 ℃ of heating after 103 hours down to connect the open-work of a plurality of impellers, 450 ℃, 10
5-h creep-rupture strength is higher than 490 kPas, and 25 ℃, v-notch pendulum impact value is higher than 0.49 kPa-Mi, and has whole tempered martensite structures; Or make by having the above-mentioned high temperature steel of forming of this paper.
A plurality of turbine wheels link to each other at its circumferential periphery with bolts, and spacer is housed between the impeller, and these spacers are characterised in that by the martensitic steel with above-mentioned performance or have that the above-mentioned high temperature steel of forming makes.
According to a fourth aspect of the present invention, provide following parts (a) and (b) and (c), be characterised in that every kind of parts all make by having by the above-mentioned martensitic steel of forming:
(a) the cylindrical insulated chamber that turbine wheel is linked to each other and passed through with compressor impeller with bolt;
(b) at least one cover bolt and the another set of bolt that is connected a plurality of compressor impellers that a plurality of turbine wheels are continuous;
(c) compressor impeller, its excircle partly have a plurality of grooves that blade is embedded, and have a plurality of bolts that make to pass connecting the open-work of a plurality of impellers at its circumferential periphery, its center and have the part of open-work the thickest.
According to a fifth aspect of the present invention, a kind of internal combustion turbine is provided, comprise the turbine end axle, a plurality ofly be connected on the axle with turbine combination bolt, and the middle turbine wheel that spacer is arranged, embed the turbine vane of each turbine wheel, be connected in the insulated chamber of turbine wheel with turbine combination bolt, be connected in a plurality of compressor impellers of insulated chamber with the compressor combination bolt, embed the compressor blade of each compressor impeller and the compressor end axle that is connected as a single entity with the one-level impeller of compressor impeller, it is characterized in that turbine wheel is to make with the martensitic steel of following performance at least, promptly 500 ℃ of heating 10 down
3Have 450 ℃ after hour, 105
5-h creep-rupture strength is higher than 490 kPas and 25 ℃, and V-type pendulum notched Izod impact strength value is higher than 0.49 kPa-Mi, and has whole tempered martensite structures.Particularly the above-mentioned high temperature steel of forming constitutes described martensitic steel by having.
When adopting above-mentioned martensitic steel to make the impeller of internal combustion turbine according to the present invention, the ratio (t/D) of the thickness of the centre portions of impeller (t) and its diameter (D) is limited to 0.15～0.3 weight that can reduce impeller thus.Particularly, by with the proportional limit of t/D built in 0.18-0.22, just can shorten the distance between each impeller, this can improve thermo-efficiency.
Fig. 1 is the sectional view of rotating part of the internal combustion turbine of expression one embodiment of the invention;
Fig. 2 be after the expression embrittlement impact value and Mn/Ni than between the graphic representation of relation;
The graphic representation of Fig. 3 is similar to Fig. 2, but expression is the relation between impact value and the Mn content after the embrittlement;
The graphic representation of Fig. 4 is similar to Fig. 2, but expression is impact value after the embrittlement and the relation between the Ni content;
Fig. 5 is the graphic representation of the relation between expression creep-rupture strength and the Ni content;
Fig. 6 is the sectional view of the turbine wheel of one embodiment of the invention;
Fig. 7 is the synoptic diagram of the another embodiment preferably of the present invention, and partly section has been represented the rotating part of internal combustion turbine.
The below will tell about the reason that the compositional range to the material of body invention is limited.
In order to obtain high tensile strength and high proof stress, the requirement of C is minimum to be 0.05% (weight). Yet if add excessive C, when steel was exposed to high temperature for a long time, it is unstable that metal structure can become, so that reduce by 105-h creep rupture strength, so C content must be less than 0.20% (weight), the carbon content scope is 0.07-0.15% (weight) preferably, preferably 0.10-0.14% (weight).
Adding Si when steel melts is as deoxidier, and adding Mn is as deoxidier and desulfurizing agent, even these two kinds of element additions are very little effect is arranged also. Si is the delta ferrite formation, adds a large amount of Si and will cause delta ferrite to form, and reduce fatigue strength and toughness, so Si content must be less than 0.5% (weight). Sometimes adopt carbon vacuum deaeration method, at this moment electroslag melting method etc. do not need to add Si, therefore preferably do not add Si.
Particularly, from the embrittlement angle, Si content even do not add Si, still contains the Si impurity of 0.01～0.1% (weight) most preferably less than 0.2% (weight).
Because Mn has promoted the embrittlement after the heating, its content must be less than 0.6% (weight). Particularly, Mn is effectively as desulfurizing agent, so the better scope of the content of Mn is that 0.1-0.4% (weight) does not add thermal embrittlement in order to can not cause. The content range of Mn is 0.1-0.25% (weight) preferably. In addition, the total amount of Si+Mn is preferably and will be less than 0.3% (weight), to prevent embrittlement.
Cr strengthens corrosion resistance and elevated temperature strength, but, if add the Cr that surpasses 13% (weight), will cause forming the delta ferrite structure. If Cr content is less than 8% (weight), enough decay resistances and elevated temperature strength will be can not get. Therefore, the content range of Cr is limited to 8-13% (weight), and particularly, the content of Cr preferably should be 11-12.5% (weight).
Mo is because its solution strengthening effect and precipitation strength effect can improve creep rupture strength, and it prevents the effect of embrittlement in addition simultaneously. If Mo content is less than 1.5% (weight), can not get enough creep rupture strengths. Surpass 3.0% (weight), Mo can cause forming delta ferrite. Therefore, Mo content is limited in the scope of 1.5-3.0% (weight), is preferably in the scope of 1.8-2.5% (weight). In addition, when Ni content surpassed 2.1% (weight), the effect of Mo was that also its content is higher, and creep rupture strength is higher, and particularly when the content of Mo was higher than 2.0% (weight), this effect was particularly evident.
V and Nb make carbide precipitation, have therefore brought the effect that strengthens elevated temperature strength and improve toughness. If the content of V and Nb is lower than respectively 0.1% (weight) and 0.02% (weight), just can not obtain sufficient effect, yet, if the content of V and Nb is higher than respectively 0.3% (weight) and 0.2% (weight), will causes forming delta ferrite and the trend that reduces toughness will be arranged. Therefore, V content preferably scope is 0.15-0.25% (weight), and Nb content preferably scope is 0.04-0.08% (weight). The Ta that can add complete equivalent replaces Nb, also Nb and Ta combination can be added.
Ni can strengthen toughness for a long time behind high-temperature heating, but also has the effect that prevents that delta ferrite from forming. If Ni content is less than 2.0% (weight), can not get sufficient effect, if but be higher than 3% (weight), will reduce long creep rupture strength. The Ni content range is 2.2%-3.0% (weight) preferably, preferably surpasses 2.5% (weight).
Ni has the effect that prevents from adding thermal embrittlement, and on the contrary, Mn but destroys this effect. The inventor finds to exist close correlation between these elements, namely find to compare less than 0.11 the time as Mn/Ni, has prevented from significantly adding thermal embrittlement. Particularly, this ratio should be less than 0.10, preferably 0.04-0.10.
N is effectively improving creep rupture strength and preventing from forming aspect the delta ferrite, if but N content is lower than 0.02% (weight), can not get enough effects. If N content surpasses 0.1% (weight), will reduce toughness. The scope of N content can obtain superior performance when 0.04-0.08% (weight).
In heat resisting steel of the present invention, Co is effectively in the intensity that strengthens steel, but it promotes embrittlement, and therefore, the content of Co should be less than 0.5% (weight). Because the contribution of W aspect gaining in strength is similar to Mo, its content can be less than 1% (weight). In addition, can improve elevated temperature strength by adding following various element: be less than the B of 0.01% (weight), be less than the Al of 0.3% (weight). The Ti that is less than 0.5% (weight), the Zr that is less than 0.1% (weight), the Hf that is less than 0.1% (weight), the Ca that is less than 0.01% (weight), the Mg that is less than 0.01% (weight), the Y that is less than 0.01% (weight) is less than the rare earth element of 0.01% (weight) and is less than the Cu of 0.5% (weight).
About the heat treatment of material of the present invention, be to be enough to material changed into fully under the austenitic temperature (minimum 900 ℃, the highest 1150 ℃) its homogeneous heating, then to quench to obtain martensitic structure. The acquisition of martensitic structure is by under the speed that is higher than 100 ℃/h material quenching or sclerosis being obtained, be heated and remain on (tempering) under the 450-600 ℃ of temperature, then be heated and remain on and carry out double tempering under 550-650 ℃. During sclerosis, be preferably in a martensite generation temperature that slightly goes up and stop to quench, to prevent hardening flaw. Specifically, being preferably in temperature is higher than and stops under 150 ℃ quenching. Cure process preferably adopts oil hardening or water to spray sclerosis. Begin a tempering by the temperature that stops to quench.
More than one aforementioned isolation ward, turbine spacer, turbine combination bolt, compressor combination bolt and at least the eventually level impeller of compressor impeller can be made by the following heat resisting steel that forms, described heat resisting steel contains the C of 0.05-0.2% (weight), the Si that is less than 0.5% (weight), the Mn that is less than 0.1% (weight), the Cr of 8-13% (weight), the Ni that is less than 3% (weight), the Mo of 1.5-3% (weight), the V of 0.05-0.3% (weight), the Nb of 0.02-0.2% (weight), the N of 0.02-0.1% (weight), surplus is iron basically, and described heat resisting steel has whole tempered martensite structures. Consist of all these parts with this heat resisting steel, can further improve the temperature of gas to improve the thermal efficiency. Particularly when being made by the following heat resisting steel that forms, at least a parts can obtain high anti-embrittlement effect, obtain very safe gas turbine, described heat resisting steel contains the C of 0.05-0.2% (weight), the Si that is less than 0.5% (weight), the Mn that is less than 0.6% (weight), the Cr of 8-13% (weight), the Ni of 2-3% (weight), the Mo of 1.5-3% (weight), the V of 0.05-0.3% (weight), the Nb of 0.02-0.2% (weight), the N of 0.02-0.1% (weight), wherein Mn/Ni preferably is 0.04-0.10 than less than 0.11, surplus is iron basically, and described heat resisting steel has whole tempered martensite structures.
In addition, although employing has 450 ℃ that are higher than 392 kPas, 105-h creep rupture strength and be higher than 20 ℃ of 0.49 kPa-Mi, the martensite steel of v-notch impact value is as the material of these parts, still in its particularly preferred composition, after 500 ℃ of heating 103 hours, it has 450 ℃ that are higher than 490 kPas, and 105-h creep rupture strength and be higher than 20 ℃ of 0.49 kPa-Mi, v-notch pendulum impact value.
This material can further contain at least a element that is selected from lower group: the W that is less than 1% (weight), the Co that is less than 0.5% (weight), the Cu that is less than 0.5% (weight), the B that is less than 0.01% (weight), the Ti that is less than 0.5% (weight), the Al that is less than 0.3% (weight), the Zr that is less than 0.1% (weight), the Hf that is less than 0.1% (weight), the Ca that is less than 0.01% (weight), the Mg that is less than 0.01% (weight) is less than the Y of 0.01% (weight) and is less than the rare earth element of 0.01% (weight).
In compressor impeller, can adopt above-mentioned heat resisting steel to manufacture at least its eventually level or whole level, but, because the temperature of gas is low in the zone from the first order to the intergrade, available other low-alloy steel is manufactured the impeller in this zone, manufactures from intergrade to the whole impeller of level with above-mentioned heat resisting steel. For example, can use the Ni-Cr-Mo-V steel with following composition and character to do by the first order of the air-flow upstream impeller to intergrade, described Ni-Cr-Mo-V steel contains the C of 0.15-0.30% (weight), the Si that is less than 0.5% (weight), the Mn that is less than 0.6% (weight), the Cr of 1-2% (weight), the Ni of 2.0-4.0% (weight), the Mo of 0.5-1% (weight), the V of 0.05-0.2% (weight), surplus is iron basically, tensile strength is higher than 784 kPas under the described Ni-Cr-Mo-V steel room temperature, the v-notch impact value is higher than 1.96 kPas-Mi under the room temperature, can use the Cr-Mo-V steel with following composition and character to do impeller later from intergrade but except whole level, described Cr-Mo-V steel contains the C of 0.2-0.4% (weight), the Si of 0.1-0.5% (weight), the Mn of 0.5-1.5% (weight), the Cr of 0.5-1.5% (weight), the Ni that is less than 0.5% (weight), the No of 1.0-2.0% (weight), the V of 0.1-0.3% (weight), surplus is iron basically, tensile strength is higher than 784 kPas under the described Cr-Mo-V steel room temperature, percentage elongation is higher than 18%, and reduction of area is higher than 50%.
Above-mentioned Cr-Mo-V steel also can be used as compressor end axle and turbine end axle.
Compressor impeller of the present invention is oblate ring, and the hole of a plurality of insertion assembling bolts is arranged in its outside, and preferably the minimum thickness (t) of this impeller is limited in 0.05-0.10 with the ratio (t/D) of diameter (D).
Insulated chamber of the present invention is columnar, and two ends Zhuan You Qu orchid links to each other with bolt with turbine wheel with compressor impeller respectively, and preferably, the proportional limit of its minimum thickness (t) and maximum inner diameter (D) is built in 0.05-0.10.
For internal combustion turbine of the present invention, preferably the interval (l) between each impeller of turbine is limited in 0.15-0.25 with the ratio (l/D) of turbine wheel diameter (D).
For example, comprise that at compressor impeller assembly the 1st to the 12nd grade of impeller can be made with above-mentioned Ni-Cr-Mo-V steel under 17 grades the situation, the 13rd to the 16th grade of impeller can be made with above-mentioned Cr-Mo-V steel, and the 17th grade of impeller can be made with above-mentioned martensitic steel.
In compressor impeller assembly, first step impeller has higher rigidity than back one-level impeller, and the last step impeller has higher rigidity than previous stage impeller.And, these impellers on thickness from the first step to the end one-level be gradually little form, the stress that reduces high speed rotating thus and produced.
Each blade of compressor is preferably with the martensitic steel of following composition to be made, and described martensitic steel contains the C of 0.05-0.2% (weight), is less than the Si of 0.5% (weight), is less than the Mn of 1% (heavy), the Cr of 10-13% (weight), and surplus is an iron; Or use except that containing said components, also contain Mo that is less than 0.5% (weight) and the martensitic steel that is less than the Ni of 0.5% (weight) and make.
For annular, with the guard shield of the outer end sliding contact of turbine vane, can be at its part Ni base casting alloy corresponding to the first step, described alloy contains the C of 0.05-0.2% (weight), is less than the Si of 2% (weight), be less than 2 Mn for (weight), the Cr of 17-27% (weight) is less than the Co of 5% (weight), the Mo of 5-15% (weight), the Fe of 10-30% (weight), the W that is less than 5% (weight) is less than the B of 0.02% (weight), and surplus is mainly Ni; Use Fe base casting alloy in its part corresponding to other grade, described alloy contains the C of 0.3-0.6% (weight), the Si that is less than 2% (weight), the Mn that is less than 2% (weight), 20-27 is the Cr of (weight), and the Ni of 20-30% (weight), 0.1-0.5 are the Nb of (weight), the Ti of 0.1-0.5% (weight), surplus is mainly these alloys of Fe and forms the ring structure that is made of many cell mesh.
Dividing plate for the fixed turbine machine nozzle, part corresponding to first step turbine nozzle is made with the Cr-Ni steel, described Cr-Ni steel contains the C that is less than 0.05% (weight), the Si that is less than 1% (weight), the Mn that is less than 2% (weight), the Cr of 16-22% (weight), the Ni of 8-15% (weight), surplus is iron basically; Part corresponding to other turbine nozzle is that alloy is made with high C-Ni.
Each turbine vane is made with Ni base casting alloy, described alloy contains the C of 0.07-0.25 (weight), the Si that is less than 1% (weight), the Mn that is less than 1% (weight), the Cr of 12-20% (weight), the Co of 5-15% (weight), the Mo of 1.0-5.0% (weight), the W of 1.0-5.0% weight, the B of 0.005-0.03% (weight), the Ti of 2.0-7.0% (weight), the Al of 3.0-7.0% (weight), and at least a element of organizing from down of making: the Nb that is less than 1.5% (weight), the Zr of (0.01-0.5 weight), the V of the Hf of 0.01-0.5% (weight) and 0.01-0.5% (weight), surplus is Ni basically, described alloy has a kind of like this structure, and wherein r ' phase and r " are deposited in the austenite phase matrix mutually.Turbine nozzle is made with Co base casting alloy, described alloy contains the C of 0.20-0.60% (weight), the Si that is less than 2% (weight) is less than the Mn of 2% (weight), the Cr of 25-35% (weight), the Ni of 5-15% (weight), the W of 3-10% (weight), the B of 0.003-0.03% (weight), surplus is Co basically, described alloy has a kind of like this structure, and wherein eutectic carbides and secondary carbide are included in austenite mutually in the matrix; Or make: the Ti of 0.1-0.3% (weight) with further containing except that mentioned component at least a Co base casting alloy that is selected from following element, the Zr of the Nb of 0.1-0.5% (weight) and 0.1-0.3% (weight), described alloy has a kind of like this structure, and wherein eutectic carbides and secondary carbide comprise the Que Shi body mutually in the matrix.Above-mentioned these two kinds of alloys will carry out burin-in process after solution thermal treatment, to form above-mentioned throw out, strengthen the intensity of alloy thus.
In addition, corroded by high-temperature combustion gas in order to prevent turbine vane, can be with Al, Cr or Al+Cr diffusion coating coated are on turbine vane.Coat-thickness is preferably 30-150um, and the coating coated is being exposed on the blade of gas.
The turbine disposed about has a plurality of combustion chambers, and all there is the duplex that is made of out cylinder and inner cylinder each combustion chamber.Inner cylinder is made by the heat treated Ni base of solution alloy, described alloy contains the C of 0.05-0.2% (weight), is less than the Si of 2% (weight), is less than the Mn of 2% (weight), the Cr of 20-25% (weight), the Co of 0.5-5% (weight), the Mo of 5-15% (weight), the Fe of 10-30% (weight), the W that is less than 5% (weight), the B that is less than 0.02% (weight), surplus is Ni basically, described alloy has whole austenitic structure.Above-mentioned Ni base alloy sheets makes its thickness with 2-5mm through plastic working, constitutes inner cylinder by welding, and the crescent pore of supply air is set at the whole periphery of cylinder.
By the description of following examples, the present invention will be more readily apparent from.Embodiment 1
To have shown in the table 1 sample of forming (weight percent) and divide and gets 20 kilograms of fusings in addition, and be heated to 1150 ℃ after casting ingot, and under this temperature, forge, obtain test materials.With these materials 1150 ℃ the heating 2 o'clock after, the cooling of drying, reduce to 150 ℃ to temperature, cooling stops, then with its from then on temperature be heated to 580 ℃ and kept this temperature 2 hours, carry out the tempering first time, then carry out air cooling, be heated to 605 ℃ and kept this temperature 5 hours then, carry out double tempering, it is cold then to carry out stove.
Obtain the testpieces that carries out repture test, tension test and v-notch pendulum impact test from these through heat treated material, experimentize then.Shock test is at above-mentioned heat treated material is carried out at 500 ℃ of embrittlement materials that obtain after heating 1000 hours down.According to the Larson-Miller parameter, this embrittlement material has and heats 10 at 450 ℃
5The identical condition of material after hour embrittlement.
Table 1
| Number | Form (weight %) | ||||||||||
| C | Si | Mn | Cr | Ni | Mo | V | Nb | N | Mn/Ni | Fe | |
| 1 | 0.12 | 0.01 | 0.24 | 11.5 | 2.75 | 2.0 | 0.20 | 0.07 | 0.05 | 0.08 | |
| 2 | 0.12 | 0.25 | 0.71 | 11.5 | 2.83 | 1.8 | 0.32 | - | 0.03 | 0.25 | ″ |
| 3 | 0.10 | 0.02 | 0.38 | 11.8 | 2.09 | 2.0 | 0.29 | 0.05 | 0.07 | 0.18 | ″ |
| 4 | 0.10 | 0.09 | 0.71 | 12.0 | 2.41 | 1.9 | 0.29 | 0.04 | 0.06 | 0.30 | ″ |
| 5 | 0.08 | 0.15 | 0.82 | 11.9 | 1.62 | 2.5 | 0.27 | 0.06 | 0.07 | 0.51 | ″ |
| 6 | 0.09 | 0.09 | 0.84 | 11.8 | 2.10 | 2.3 | 0.35 | 0.05 | 0.07 | 0.40 | ″ |
| 7 | 0.09 | 0.05 | 0.20 | 11.0 | 1.71 | 1.9 | 0.20 | 0.05 | 0.06 | 0.12 | ″ |
| 8 | 0.10 | 0.04 | 0.15 | 10.9 | 2.51 | 2.4 | 0.19 | 0.06 | 0.06 | 0.06 | ″ |
Table 2
| Number | Tensile strength (kPa) | 0.2% proof stress (kPa) | Unit elongation (%) | Reduction of area (%) | 450 ℃ of breaking tenacitys (kPa) | 25 ℃ of impact values (kPa-Mi) | |
| Before the embrittlement | After the embrittlement | ||||||
| 1 | 1105.4 | 918.3 | 20.9 | 63.8 | 534.1 | 1.12 | 0.93 |
| 2 | 1128.0 | 921.2 | 19.8 | 60.0 | 411.6 | 1.02 | 0.33 |
| 3 | 1097.6 | 914.3 | 19.6 | 60.1 | 540.0 | 0.99 | 0.35 |
| 4 | 1112.3 | 974.1 | 19.5 | 59.9 | 530.2 | 0.96 | 0.28 |
| 5 | 1084.9 | 910.4 | 19.5 | 59.7 | 541.0 | 0.84 | 0.21 |
| 6 | 1094.7 | 917.3 | 19.8 | 60.2 | 532.1 | 0.74 | 0.24 |
| 7 | 1092.7 | 957.5 | 22.6 | 62.3 | 568.4 | 0.76 | 0.43 |
| 8 | 1116.2 | 933.9 | 24.8 | 61.1 | 569.4 | 1.04 | 0.86 |
Referring to table 1, wherein sample 1 and 8 is materials of the present invention, and sample 2-7 is contrast material (sample 2 is equivalent to be used as at present the M152 steel of impeller material).
What table 2 was showed is the mechanical property of these samples.Verified, material of the present invention (sample 1 and 8) has satisfied as high-temperature high-pressure fuel gas turbine material needed 450 ℃, 10 after embrittlement is handled
5-h creep-rupture strength (＞490 kPas) and 25 ℃, v-notch impact value (being higher than 0.49 kPa-Mi).Form and correlatedly be, be equivalent to M152 (sample 2), be used as the material material of combustion gas body turbine at present, because its 450 ℃; 10
5-h creep-rupture strength is 411.6 kPas, and 25 ℃, v-notch pendulum impact value is 0.33 kPa-Mi after embrittlement is handled, and can not satisfy as the desired mechanical property of high-temperature high-pressure fuel gas body turbine material.In addition, in sample 3-7, the content of Si+Mn is 0.4% to about 1% (weight), the Mn/Ni ratio is higher than 0.12, the mechanical property of these steel samples has satisfied respectively as the needed creep-rupture strength value of high-temperature high-pressure fuel gas body turbine material, but because v-notch pendulum impact value is lower than 0.42 kPa-Mi after its embrittlement, these steel samples can not satisfy this requirement.
Fig. 2 be after the expression embrittlement impact value and Mn/Ni than between the line chart of relation, as shown in the figure, when this than (Mn/Ni) when being higher than 0.12, do not occur significantly improving, but when this when being lower than 0.11, the embrittlement performance significantly is improved to and is higher than 0.49 kPa-Mi, and when this when being lower than 0.10, be improved to 0.74 kPa-Mi.Mn is absolutely necessary as reductor and sweetening agent, so the add-on of Mn will be lower than 0.6% (weight).
Fig. 3 is the graphic representation similar in appearance to Fig. 2, but expression is the relation between impact value and the Mn content after the embrittlement.As shown in the figure, when Ni content was less than 2.1% (weight), the minimizing of Mn content did not produce much effects, but when Ni content surpasses 2.1% (weight); The minimizing of Mn content has produced obvious effects.Particularly when Ni content is higher than 2.4% (weight), can obtain better effect.
In addition, when Mn content during near 0.7% (weight), though Ni content what; Do not improve impact value yet, if but Mn content is lower than 0.6% (weight), and Ni content is higher than 2.4% (weight), and at this moment Mn content is low more, and impact value is high more.
Fig. 4 is the graphic representation similar in appearance to Fig. 2, but expression is the relation between impact value and the Ni content after the embrittlement.As shown in the figure, when Mn content is higher than 0.7% (weight), the increase of Ni content; The embrittlement performance has only slight improvement, but clearly, when Mn content was less than 0.7% (weight), the increase of Ni content was obviously having improved the embrittlement performance.Particularly when Mn content when 0.15-0.4% (weight), if Ni content is higher than 2.2% (weight), the improvement of embrittlement performance is particularly evident, if promptly Ni content is higher than 2.4% (weight), impact value can be higher than 0.74 kPa-Mi, and if Ni content be higher than 2.5% (weight), impact value can be higher than 0.86 kPa-Mi.
Fig. 5 is expression 450 ℃ * 10
5The curve that concerns between-h breaking tenacity and the Ni content.As shown in the figure, Ni content reaches about 2.5% (weight) and does not influence creep-rupture strength basically, but when it surpassed 3.0% (weight), intensity was reduced to less than 490 kPas, therefore can not get needed intensity.And be also noted that Mn content is low more, and resulting intensity is high more, and Mn content is obtained the most significant effect of gaining in strength, thereby is provided high strength when 0.15-0.25% (weight) scope.
Fig. 6 is the diagrammatic cross-section of expression gas-turbine wheel of the present invention.Table 3 has been showed the chemical composition (weight percent) of this impeller.
Table 3
| No | C | Si | Mn | Cr | Ni |
| 9 | 0.12 | 0.04 | 0.20 | 11.1 | 2.70 |
| Mo | Nb | V | N | Mn/Ni | Fe |
| 2.05 | 0.07 | 0.20 | 0.05 | 0.07 | Surplus |
The melting of steel is to carry out with the method that adds the carbon vacuum deaeration.After the forging, forging good steel 1050 ℃ of heating two hours, and at 150 ℃ oil quenching, then the steel after quenching is heated to 520 ℃ and keep 5 hours to carry out the tempering first time from 150 ℃, then in air, cool off, heat 5 hours to carry out the tempering second time, again at the stove internal cooling at 590 ℃ then.After these thermal treatments are finished, steel are machined to shape shown in Figure 6, the impeller outer diameter of gained is 1000mm thus, thickness is 200mm.The diameter of centre hole 11 is 65mm, and the hole of inserting assembling bolt is arranged on 12 parts, embeds turbine blade on 13 parts.
This impeller has superior performance, and promptly its impact value is 0.98 kPa-Mi after aforesaid embrittlement, and 450 ℃, 10
5The creep-rupture strength of-h is 541.0 kPas.Embodiment 2
Fig. 1 is the sectional view of a kind of internal combustion turbine rotating part in embodiment of the present invention, and it has used above-mentioned impeller.Shown rotating part comprises turbine end axle 1, turbine blade 2; Turbine combination bolt 3, turbine spacer 4, insulated chamber 5, compressor impeller 6, compressor blade 7, compressor combination bolt 8, compressor end axle 9, turbine wheel 10 and centre hole 11.Internal combustion turbine of the present invention has 17 grades the compressor impeller 6 and the turbine vane 2 of two-stage.Turbine vane can be three grades, and two kinds of structures all can adopt steel of the present invention.
Material shown in the table 4 is made the massive casting that equate with physical size with esr process, then by forging and thermal treatment.Forging is carried out in 850～1100 ℃ temperature range, and thermal treatment is carried out under the conditions shown in Table 4.Table 4 is sample chemical constitutions of representing with weight percent.As for the microtexture of these materials, sample Nos6～9 all are the tempered martensite structures; 10～11 on sample all is the tempering bainite structure, and sample No.6 is used for insulated chamber and final step compressor impeller, and the former thickness is 60mm, wide 500mm, and long 1000mm, the latter's diameter are 1000mm, thick 180mm.The No.7 sample is used for turbine wheel, the diameter 1000mm of each, thick 180mm.Sample No, 8 are used for spacer, its external diameter 1000mm, internal diameter 400mm, thick 100mm.Sample No, 9 are used for the assembling bolt of turbine and compressor, the diameter 40mm of each, long 500mm.Sometimes sample No, 9 also are used to make the bolt that connects insulated chamber and compressor impeller.Sample Nos.10 and 11 forges into turbine end axle and compressor end axle respectively, the diameter 250mm of each, long 300mm.Also have, steel sample No. 0 is used for the 13 to 16 grade compressor impeller 6, and steel sample No.11 is used for the compressor impeller 6 of first to ten secondary, will make the impeller of turbine and compressor have same size when making all compressor impellers 6.Except steel sample No.9, all test parts all are to adopt the middle body of sample, and its direction should be perpendicular with the axis direction (vertically) of every sample.In the present embodiment, test parts is vertically taking at sample.
Table 5 is pointed out the room temperature test for tensile strength of steel sample shown in the table 4, the v-notch pendulum impact test under 20 ℃ and the result of repture test.Use the Lar-son-Mi11er method that adopts usually to record 450 ℃, 10
5-h creep-rupture strength.
By 6 to No. 9 steel of the present invention (12Cr steel), 450 ℃, 10
5The wriggling breaking tenacity of-h is greater than 499.8 kPas, and 20 ℃ v-notch pendulum impact value is greater than 0.69 kPa-Mi.Therefore can confirm that 6～No. 9 steel have enough intensity as the material of high-temperature fuel gas turbine.
In addition, for the low alloy steel Nos of end axle usefulness, 450 ℃ of creep-rupture strengths of 11 and 12 are low, but tensile strength surpasses 842.8 kPas, and 20 ℃ v-notch pendulum impact value is greater than 0.69 kPa-Mi.This has just confirmed that 10 and No. 11 steel satisfy the necessary intensity of end axle (tensile strength 〉=793.8 kPa, 0.49 kPa of 20 ℃ v-notch pendulum impact value-Mi) fully.
Can make compression ratio reach 14.7 with the common internal combustion turbine of forming of the present invention of above-mentioned materials, the temperature of permission is higher than 350 ℃, and manometric efficiency is greater than 86%, about 1200 ℃ of the gas temperature of first step nozzle inlet, thereby make thermo-efficiency greater than 32% (LHV).
Under these conditions, the temperature of insulated chamber and final step compressor impeller reaches as high as 450 ℃.The former thickness is preferably 25～30mm, and the latter's thickness is preferably 40～70mm.Turbine and compressor impeller all respectively have central bore, and leaving residual compression along the central bore of each turbine wheel should be square.
In addition, the above-mentioned high temperature steel shown in the table 3 is used for turbine spacer 4, the compressor impeller 6 of insulated chamber 5 and final step, and the also available above-mentioned similar steel of other building blocks is made.The structure of gained can make compression ratio reach 14.7, the temperature of allowing is higher than 350 ℃, manometric efficiency is greater than 86%, the gas temperature of first step nozzle inlet is 1200 ℃, the result not only can obtain the thermo-efficiency greater than 32%, and as mentioned above, after adding thermal embrittlement, also high creep-rupture strength and impact value can be arranged, therefore can obtain more reliable internal combustion turbine.
Table 4
| The kind of example steel | Form (%) | Thermal treatment | |||||||||
| C | Si | Mn | Cr | Ni | Mo | V | | N | Fe | ||
| 6 insulated chambers | 0.10 | 0.04 | 0.70 | 11.56 | 1.98 | 1.98 | 0.20 | 0.08 | 0.06 | Bal. | 1050℃×5hOQ 550℃×15hAC 600℃×15hAC |
| 7 (turbine wheels) | 0.10 | 0.05 | 0.65 | 11.49 | 1.70 | 2.04 | 0.19 | 0.08 | 0.06 | ″ | 1050℃×8hOQ 550℃×20hAC 600℃× |
| 8 spacers | 0.09 | 0.07 | 0.59 | 11.57 | 2.31 | 2.22 | 0.18 | 0.09 | 0.06 | ″ | 1050℃×3hOQ 550℃×10hAC 600℃×10hAC |
| 9 assembling bolts | 0.10 | 0.03 | 0.69 | 11.94 | 1.86 | 2.25 | 0.21 | 0.15 | 0.05 | ″ | 1050℃×1hOQ 550℃×2hAC 600℃×2hAC |
| 10 cr-Mo-V steel | 0.26 | 0.25 | 0.79 | 1.09 | 0.41 | 1.25 | 0.23 | - | - | ″ | 975℃×8hWQ 665℃×25hAC 665℃×25hAC |
| 11 Ni-cr-Mo-V steel | 0.20 | 0.21 | 0.36 | 1.51 | 2.78 | 0.62 | 0.10 | - | - | ″ | 840℃×8hWQ 635℃×25hAC 635℃×25hAC |
Table 5
Embodiment 3
| The kind of example steel | Tensile strength (kPa) | 0.02% proof stress (kPa) | Unit elongation (%) | Relative reduction in area (%) | Impact value vE 20(kPa-Mi) | 10 5-h creep-rupture strength (kPa) |
| 6 | 1097.6 | 777.1 | 19.8 | 60.1 | 0.85 | 500.8 |
| 7 | 1094.7 | 779.1 | 20.1 | 59.3 | 0.81 | 512.5 |
| 8 | 1120.1 | 795.8 | 19.5 | 62.5 | 0.71 | 502.7 |
| 9 | 1133.9 | 809.5 | 22.3 | 63.4 | 0.85 | 516.5 |
| 10 | 846.7 | - | 26.7 | 60.0 | 0.74 | 345.0 |
| 11 | 850.6 | 755.6 | 26.9 | 69.1 | 1.78 | 225.4 |
Fig. 7 is an expression another kind scheme preferably, and wherein gas-turbine wheel is made with high temperature steel of the present invention, also provides the cross section of the rotating part of internal combustion turbine especially.In this embodiment, the turbine wheel 10 of two-stage is housed, the turbine wheel of surveying in the flowing gas air inlet 10 has centre hole 11.All turbine wheels all use the high temperature steel shown in the table 3 to make in this embodiment.In addition, in this embodiment, the high temperature steel shown in the table 3 also is used for doing the final step compressor impeller 6 of flowing gas outlet side, insulated chamber 5, turbine spacer 4, turbine combination bolt 3 and compressor combination bolt 8.Alloy shown in the table 6 is used for miscellaneous part, and promptly turbine vane 2, turbine nozzle 14, the lining 17 of combustion chamber 15, compressor blade 7, compressor nozzle 16, dividing plate 18 and guard shield 19.Particularly turbine nozzle 14 and turbine vane 2 are cast.The compressor of the present embodiment has 17 grades compressor impeller, and identical with the distributing style of embodiment 2.The manufacture of turbine end axle 1 and compressor end axle 9 is also identical with embodiment 2 in the present embodiment.
Table 6
| C | Si | Mn | Cr | Ni | Co | Fe | Mo | B | W | Ti | Other | |
| Turbine vane | 0.15 | 0.11 | 0.12 | 15.00 | Bal. | 9.02 | - | 3.15 | 0.015 | 3.55 | 4.11 | Zr 0.05， Al 5.00 |
| Turbine nozzle | 0.43 | 0.75 | 0.66 | 29.16 | 10.18 | Bal. | - | - | 0.010 | 7.11 | 0.23 | Nb 0.21， Zr 0.15 |
| Combustion chamber lining | 0.07 | 0.83 | 0.75 | 22.13 | Bal. | 1.57 | 18.47 | 9.12 | 0.008 | 0.78 | - | - |
| Compressor blade and nozzle | 0.11 | 0.41 | 0.61 | 12.07 | 0.31 | - | Surplus | - | - | - | - | - |
| Guard shield (1) | 0.08 | 0.87 | 0.75 | 22.16 | Bal. | 1.89 | 18.93 | 9.61 | 0.005 | 0.85 | - | - |
| Guard shield (2) | 0.41 | 0.65 | 1.00 | 23.55 | 25.63 | - | Surplus | - | - | - | 0.25 | Nb 0.33 |
| Diaphragm | 0.025 | 0.81 | 1.79 | 19.85 | 11.00 | - | ″ | - | - | - | - | - |
The turbine vane that table 6 is pointed, turbine nozzle, guard shield (1) and dividing plate are used in the first step of gas flow upstream in the internal combustion turbine, and guard shield (2) is used in the second stage.
In the present embodiment, the minimum thickness (t) of final compressor impeller 6 is 0.08 with the ratio (t/D) of external diameter (D), (t/D) of insulated chamber 5 is than being 0.04 and the ratio (t/D) of the maximum ga(u)ge (t) of the middle body of each turbine wheel and its diameter (D) is 0.19 in the first step, in the second stage is 0.205, and the gap between impeller (l) is 0.21 with the ratio (l/D) of its diameter (D).All gapped between each turbine wheel.Each turbine wheel has a lot of equally spaced holes on week in whole garden, connect impeller so that put into bolt.
Said apparatus can make compression ratio reach 14.7, and the temperature of permission is higher than 350 ℃, and manometric efficiency is greater than 86%, and the gas temperature that is positioned at the nozzle inlet of turbine first stage is 1200 ℃, thereby the thermo-efficiency that provides is greater than 32%.Moreover above-mentioned have high creep-rupture strength and the heating back less high temperature steel of embrittlement can be used as turbine wheel, insulated chamber, spacer., the compressor impeller and the assembling bolt of final level.In addition, because use has high hot strength alloy and does each turbine vane, use has high temperature and high high temperature flexible alloy is done the turbine nozzle, with do combustion chamber lining with alloy with high high-temperature and high anti-fatigue performance, this just might obtain balanced and fully reliable internal combustion turbine.
According to the present invention, can obtain the high temperature steel (gas temperature: be higher than 1200 ℃ that after adding thermal embrittlement its creep-rupture strength and impact value meet the requirement of high-temperature high-pressure fuel gas engine blade wheel, compression ratio: 15), therefore the internal combustion turbine that uses above-mentioned steel grade to make can bring fabulous effect, for example can reach high thermo-efficiency.
Claims (2)
1. high temperature steel with excellent anti high-temperature brittleness, it is characterized in that containing the C of (weight) 0.05-0.2%, be lower than 0.5% Si, be lower than 0.33% Mn, the Cr of 8-13%, the Mo of 1.5-3% is higher than 2.1% but be lower than 3%Ni, the V of 0.05-3.%, the Nb of 0.02-0.2%, the N of 0.02-0.1%, described Mn is lower than 0.11 with the ratio (Mn/Ni) of Ni, and surplus is iron basically.
2. high temperature steel with excellent anti high-temperature brittleness is characterized in that containing the C of (weight) 0.05-0.2%, is lower than 0.5% Si, be lower than 0.33% Mn, the Cr of 8-13%, the Mo of 1.5-3% is higher than 2.1% but be lower than 3%Ni, the V of 0.05-0.3%, the Nb of 0.02-0.2%, the N of 0.02-0.1% is lower than 1% W, described Mn is lower than 0.11 with the ratio (Mn/Ni) of Ni, and surplus is iron basically.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1630/87 | 1987-01-09 | ||
| JP62001630A JPS63171856A (en) | 1987-01-09 | 1987-01-09 | Heat-resisting steel and gas turbine using same |
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| Publication Number | Publication Date |
|---|---|
| CN88100065A CN88100065A (en) | 1988-10-05 |
| CN1036666C true CN1036666C (en) | 1997-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN88100065A Expired - Fee Related CN1036666C (en) | 1987-01-09 | 1988-01-09 | Heat-resisting steel and combustion turbine made of it |
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| Country | Link |
|---|---|
| EP (1) | EP0298127B1 (en) |
| JP (1) | JPS63171856A (en) |
| KR (2) | KR950014312B1 (en) |
| CN (1) | CN1036666C (en) |
| WO (1) | WO1988005086A1 (en) |
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| US7859047B2 (en) | 2006-06-19 | 2010-12-28 | Fairchild Semiconductor Corporation | Shielded gate trench FET with the shield and gate electrodes connected together in non-active region |
| US7772668B2 (en) | 2007-12-26 | 2010-08-10 | Fairchild Semiconductor Corporation | Shielded gate trench FET with multiple channels |
Also Published As
| Publication number | Publication date |
|---|---|
| KR890700690A (en) | 1989-04-26 |
| JPS63171856A (en) | 1988-07-15 |
| WO1988005086A1 (en) | 1988-07-14 |
| EP0298127A4 (en) | 1993-05-26 |
| CN88100065A (en) | 1988-10-05 |
| EP0298127B1 (en) | 1996-07-31 |
| KR950009221B1 (en) | 1995-08-18 |
| KR950014312B1 (en) | 1995-11-24 |
| EP0298127A1 (en) | 1989-01-11 |
| JPH0563544B2 (en) | 1993-09-10 |
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