US3778256A - Heat-resistant alloy for a combustion liner of a gas turbine - Google Patents

Heat-resistant alloy for a combustion liner of a gas turbine Download PDF

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US3778256A
US3778256A US00213050A US3778256DA US3778256A US 3778256 A US3778256 A US 3778256A US 00213050 A US00213050 A US 00213050A US 3778256D A US3778256D A US 3778256DA US 3778256 A US3778256 A US 3778256A
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weight percent
alloy
accordance
combustion liner
niobium
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R Sasaki
T Kashimura
H Hataya
Y Fukui
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Hitachi Ltd
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Hitachi Ltd
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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
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W

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  • ABSTRACT An alloy for a combustion liner of a gas turbine, characterized by comprising 0.03 to 0.10 weight percent of carbon, 0.3 to 1.0 weight percent of silicon, 0.50 to 3.00 weight percent of manganese, 43.0 to 50.0 weight percent of nickel, 22.0 to 30.0 weight percent of chromium, 0.10 to 0.50 weight percent of titanium, at least one of 0.005 to 0.20 weight percent of elements of cerium group in rare earth elements and 0.20 to 0.90 weight percent of niobium, and the balance irohfii'c'l inipiiritie's accompanying thereto.
  • a combustion liner of a gas turbine is usually formed by shaping alloy sheets having thickness of l to 4 mm to a cylindrical form, pressing one end of the cylinder to form a tapered shape, thenwelding the sheets, and forming louvers for allowing air into the combustion liner and holes for mounting cross fire tubes.
  • the number of the louvers is determined in accordance with the dimension of the combustion liner.
  • combustion liner of gas turbine there is passed combustion gas of l,000 to 1,700C, so that in order to prevent the combustion liner from being molten by the high temperature to which it is exposed, the outer surface of the combustion liner is air-cooled and at the same time air is allowed to flow into the combustion liner.
  • the temperature to which the combustion liner is usually heated is limited to 600 to 850C.
  • the material in manufacturing the combustion liner, the material must be subjected to bending and welding and, in use, it is brought into contact with a high temperature combustion gas and air. Therefore, the material for forming the combustion liner must have superior characteristics in respectof formability, weldability, heat resistant characteristics and oxidation resistant characteristics at a high temperature. Further, since the combustion liner is subjected to sudden temperature change during each starting and stopping of the gas turbine engine, the material must have a substantial resistance to thermal shock. Further, the material must also have a superior ductility and a substantial resistance against becoming brittle after heating. These factors are all essential and particularly the high temperature corrosion resistant characteristics and the thermal shock resistant characteristics are important in determining the life of the combustion linen.
  • a combustion liner for a gas turbine has been made of a heat resistant steel in accordance with the A181 specification 309 (a heat resistant steel including 22 weight percent of chromium and 12 weight percent of nickel) or 310 (a heat resistant steel including 25 weight percent of chromium and 20 weight percent of nickel).
  • A181 specification 309 a heat resistant steel including 22 weight percent of chromium and 12 weight percent of nickel
  • 310 a heat resistant steel including 25 weight percent of chromium and 20 weight percent of nickel
  • alloys which have a substantial resistance to the corrosive gas produced by a combustion of heavy oil. They include a heat resistant alloy including 25 weight percent of chromium, 45 weight percent of nickel, 3 weight percent of cobalt, 3 weight percent of molybdenum, and 3 weight percent of tungsten, and a heat resistant alloy including 22 weight percent of chromium, 47 weight percent of nickel, 1.5 weight percent of cobalt, 9
  • a primaryobject of the present invention is to provide a novel alloy for a combustion liner of a gas turbine.
  • Another object of the present invention is to provide an alloy for a combustion liner for a gas turbine which is resistant to a corrosive gas produced by the combustion of heavy oil as well as to a thermal shock.
  • a further object of the present invention is to provide an alloy for a combustion liner of a gas turbine which also has a substantial resistance to a sulfurized corrosion.
  • a further object of the present invention is to provide an alloy for a combustion liner of a gas turbine which is less expensive as compared with a heat resistant alloy including 25 weight percent of chromium, 45 weight percent of nickel, 3 weight percent of cobalt, 3 weight percent of molybdenum, and 3 weight percent of tungsten, or a heat resistant alloy including 22 weight percent of. chromium, 47 weight percent of nickel, 1.5 weight percent of cobalt, 9 weight percent of molybdenum and 0.6 weight percent of tungsten.
  • an alloy including 0.03 to 0.10 weight percent of carbon,,0.30 to 1.00 weight percent of silicon, 0.50 to 3.00 weight percent of manganese, 43.0 to 50.0 weight percent of nickel, 22.0 to 30.0 weight percent of chromium, 0.10 to 0.50 weight percent of titanium, at least one of 0.005 to 0.20 weight percent of elements of cerium group in rare earth metals and 0.20 to 0.90 weight percent of niobium, and the balance iron and impurities accompanying thereto.
  • the alloy in accordance with the present invention has been developed to obtain superior formability, weldability, high temperature corrosion resistant characteristics, high temperature oxidation resistant characteristics, thermal shock resistance, ductility and re sistance against becoming brittle :after heating, which are required for an combustion liner of a gas turbine, and particularly to improve high temperature corrosion resistant characteristics and thermal shock resistance.
  • the present invention has been achieved by noting that, in a heat resistant alloy mainly including nickel and chromium, the high temperature corrosion resistant characteristics is substantially affected by the amount of the nickel content and that it is possible to improve the thermal shock resistance by adding titanium together with elements of cerium group in rare earth metals and/or niobium.
  • the present invention is characterized by the fact that the nickelchromium type heat resistant alloy including more than 43.0 weight percent of nickel further includes titanium and elements of cerium groups in rare earth metals and/or niobium.
  • the amounts of the components have been determined from the following reasons.
  • the amount of the carbon content should be small in order to obtain a good ductility but from the viewpoint of strength the carbon should be contained as much as possible. Therefore, in order to have the both requirements suitably met, the amount of carbon content is determined to 0.03 to 0.10 weight percent.
  • the raw material usually includes at least 0.03 percent carbon and, in order to have the carbon content less than this value, a material of higher purity must be used or particular melting process must be employed. Therefore, the manufacturing cost is increased. Further, less carbon content decreases the strength of the alloy. For these reasons, the minimum value of the carbon content is determined to 0.03 percent.
  • the carbon content is more than 0.10 percent, the ductility is reduced and cracks may be produced during forming. Further, much carbides precipitate during a use at high temperature causing a brittleness of the material.
  • the silicon content is added as a deoxidizing agent. If the content is less than 0.30 percent, a sufficient deoxidizing effect cannot be obtained, but if the content is more than 1.0 percent, it will adversely affect on the ductility and enhances precipitation of sigma phases at a high temperature.
  • Manganese is added for the purpose of deoxidization and desulfurization. If the content is less than 0.50 percent, a sufficient effect cannot be obtained, but if it exceeds 3.0 percent, the oxidation resistant characteristics of the alloy is deteriorated and precipitation of sigma phases is enhanced. Therefore, the content is determined between 0.30 to 3.0 percent.
  • Chromium is essential for improving the high temperature corrosion resistant characteristics against for example V
  • This content is determined to 22.0 to 30.0 percent in view of the fact that it is not effective to provide a sufficient oxidation resistant characteristics and high temperature corrosion resistant characteristics if the amount of the content is less than 22.0 percent, but has an adverse effect on the formability and enhances the precipitation of the sigma phases if the content exceeds 30.0 percent.
  • Nickel serves to stabilize the austenite structure, to prevent the precipitation of sigma phases even under a prolonged period of heating and to improve the oxidation resistant characteristics and the high temperature corrosion resistant characteristics against V 0
  • the content must be more than 43.0 percent. Otherwise, a sufficient high temperature corrosion resistant characteristics cannot be obtained.
  • the corrosion resistance against V 0 can be improved by increasing the nickel content, however, the increased nickel content reduces the resistance against the corrosion by S0 gas which may be encountered when heavy oil is used as fuel. Moreover, an increased amount of nickel will correspondingly increase the cost of the alloy. Therefore, the upper limit of the nickel content is determined to 50.0 percent.
  • Titanium is effective to provide a deoxidization effect and to improve a creep rupture strength by precipitation of fine carbides.
  • the content is less than 0.10 percent, it is not so effective but, if it exceeds 0.50 percent, the amount of inclusions increase and much carbides precipitate resulting in a brittle structure. Therefore, the content is determined within the range of 0.10 to 0.50 percent.
  • the elements of cerium group in rare earth metals has a high deoxidizing and desulphurizing power, and by adding them, the oxygen and the sulphur content in an alloy can be reduced to provide an increased ductility at a high temperature and an increased resistance against thermal shock.
  • the content is less than 0.005 weight percent, it is not possible to obtain a sufficient deoxidizing and desulphurizing effect and may result in an insufficient ductility under a high temperature and an insufficient resistance to thermal shock.
  • the content is more than 0.20 weight percent, the elements may be produced as inclusions to make the alloy brittle.
  • the elements of cerium group includes lanthanum, cerium, praseodymium, neodymium and samarium, among which a mixture of lanthanum, cerium and neodymium is available in market as Mishmetal" with a cheap price, so that it is advisable to use the mixture. Since the elements of cerium group are easily oxidized, it is advisable to add these elements into a molten pool of alloy at the end of melting process, preferably after the titanium is added and oxygen content is reduced due to the deoxidization effect of the titanium.
  • Niobium is precipitated in the form of cai'bides and improves the high temperature strength of the alloy. Further, it has a deoxidizing effect and is effective to reduce the oxygen content in the steel and improve the ductility at a high temperature. If the niobium content is less than 0.20 weight percent, the effect is insufficient while, if it exceeds 0.90 weight percent, precipitation and coagulation of carbides are promoted at a high temperature with the result that the creep rupture strength is reduced and the ductility and toughness at the room temperature are decreased after a prolonged period of heating. It is favourable to control the content of niobium in the range of 0.40-0.70 weight percent.
  • FIG. 1 is a perspective view of a combustion liner of a gas turbine which may be formed from the alloy in accordance with the present invention
  • FIG. 2 is a diagram showing the relation between the weight loss due to corrosion'as measured through a V 0 corrosion test and the amount of nickel content in the sample;
  • FIG. 3 is a diagram showing the results of V corrosion tests performed on the specimens Nos. 11 through 18;
  • FIG. 4 is a diagram showing the results of 75 weight percent V 0 and weight percent Na2SO1 corrosion tests
  • FIG. 5 is a diagram showing the tensile strength and the proof stress of the specimens 11 through 18 as measured at the room temperature;
  • FIG. 6 is a diagram showing the elongation and the reduction of area of the same specimens as measured at the room temperature
  • FIG. 7 is a diagram showing the tensile strength and the proof stress of the specimens 11 through 18 as measured at 800C;
  • FIG. 8 is a diagram showing the elongation and the Note: The values in the parentheses show intended amounts.
  • the bal ance is iron and impurities.
  • FIG. 2 shows the results of V 0 corrosion tests.
  • the weight loss due to corrosion widely varies in accordance with the amount of nickel content. More specifically, the weight loss increases as the nickel content increases when the TABLE 2.-CI-1EMICAL COMPOSITION OF ALLOYS (ppm) No. c Si Mn Ni Cr MO w C6 Nb Ti La C N 0 H .05 1.02 1.53 44.22 165 137 Trace Note:
  • the balance is iron and impurities.
  • FIG. 9 is a diagram showing the results of creep rupture tests performed at 800C.
  • FIG. 10 is a picture showing the results of the thermal shock tests performed on the specimens 11 through 18.
  • FIG. 1 shows a general form of a combustion liner for a gas turbine.
  • the combustion liner is formed by shaping sheets to a cylindrical form, making louvers and holes for mounting cross-tire tubes, pressing one end to form a tapered shape and thereafter welding a seamed joint of these shaped sheets.
  • the reference numeral (1) designates the louver, and (2) the hole for mounting the cross-fire tube.
  • the alloy for making the combustion liner is required to have superior formability, weldability, high temperature oxidation resistant property, high temperature cor rosion resistant property, thermal shock resistance, ductility, and resistance against becoming brittle after heating.
  • the formability, weldability and the high temperature oxidation resistant property have been sufficiently attained by conventional heat resistant alloys containing high amount of nickel and chromium. In view of the fact, tests have been performed for the purpose of knowing the high temperature corrosion resistant propety.
  • Table 1 shows the compositions of materials used for the tests. These materials were melted, casted, forged and heat treated at 1100C for 1 hour then cooled in water and cut to specimens of 5 X 8 X 5 mm. The corrosion weight loss was measured by sprinkling 0.1 g of V 0 on each of the specimens and heating at 1200C for 100 hours in a heating pot.
  • nickel content is less than 33 weight percent.
  • the weight loss remarkably decreases. A remarkable change in the weight loss is seen at a point corresponding to a nickel content of 43.0 weight percent. For this reason, the nickel content must be more than 43.0 weight percent in order to obtain an excellent high temperature corrosion resistant property.
  • the specimens all included more than 43.0 weight percent of nickel as well as additional elements for improving the properties of the alloy. Specimens were prepared by melting the material in the air, heating at 1 150C for 1 hour after forging, and cooling in water.
  • FIGS. 5 and 6 show results of tensile tests performed at the room temperature. The tests were performed on specimens which were processed by solution treatment and other specimens which were heated at 850C for 1000 hours after solution treatment. The latter specimens were tested in order to know the properties of the alloy after it was exposed to an actual operating condition of a gas turbine engine under which the combustion liner was subjected to a temperature of 600 to 850C and large amounts of carbides might precipitate therein. In order that the material is not made brittle when used at a high temperature, it is essential that the material shows an excellent property in respect of elongation and reduction of area. The strength should be as high as possible, but it is not an essential factor. FIG. 5 shows tensile strength and proof stress, and FIG.
  • Tension tests should preferably performed at a temperature to which the combustion liner of the gas turbine is heated during operation. Otherwise, it would not be possible to obtain practical data.
  • the inventors performed tension tests at 800C. The tensile strength and the proof stress obtained through the tests are shown in FIG. 7, while elongation and reduction of area are shown in FIG. 8.
  • a combustion liner of a gas turbine is not subjected to a substantial stress because the internal pressure thereof is relatively low. However, since it is used at an elevated temperature for a long period, creep rupture tests were performed.
  • FIG. 9 shows the results of the creep rupture tests. From FIG. 9, it should be noted that the specimens 15 through 18 have creep rupture strength slightly inferior to that of the specimens 13 and 14 which contain cobalt, tungsten and molybdenum, but superior to that of the specimens 11 and 12. As described above, the combustion liner of gas turbine is not subjected to a substantial stress, so that the creep rupture strength of this order is satisfactory for use in a combustion liner of a gas turbine.
  • the alloy in accordance with the present invention which contains titanium and niobium and/or elements of cerium group in rare earth metals in combination has a superior properties as an alloy for a combustion liner of a gas turbine.
  • An alloy consisting essentially of 0.03 to 0.10 weight per cent of carbon, 0.30 to 1.00 weight per cent of silicon, 0.50 to 3.00 weight per cent of manganese, 43.0 to 50.0 weight per cent of nickel, 22.0 to 30.0 weight percent of chromium, 0.10 to 0.50 weight per cent of titanium, 0.20 to 0.90 weight per cent of niobium and the balance iron and impurities accompanying therewith and possessing high ductility.
  • An alloy consisting essentially of 0.03 to 0.10 weight per cent of carbon, 0.30 to 1.00 weight per cent of silicon, 0.50 to 3.00 weight per cent of manganese, 43.0 to 50.0 weight percent of nickel, 22.0 to 30.0 weight per cent of chromium, 0.10 to 0.50 weight per cent of titanium, 0.20 to 0.90 weight per cent of niobium, 0.005 to 0.20 weight per cent of at least one ele ment selected from a cerium group in rare earth metals, and the balance iron and impurities accompanying therewith and possessing high ductility.
  • An alloy in accordance with claim 7 which contains 0.20 to 0.90 weight percent of niobium, and 0.005 to 0.20 weight percent of at least one element selected from cerium group in rare earth metals.
  • An alloy in accordance with claim 8 which contains less than 0.010 weight percent of oxygen.
  • An alloy in accordance with claim 7 which contains 0.40 to 0.70 weight percent of niobium, and 0.03 to 0.17 weight percent of at least one element selected from cerium group in rare earth metals.
  • An alloy in accordance with claim 10 which contains less than 0.010 weight percent of oxygen.
  • cerium group elements are a mixture of lanthanum, ce-

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4174213A (en) * 1977-03-04 1979-11-13 Hitachi, Ltd. Highly ductile alloys of iron-nickel-chromium-molybdenum system for gas turbine combustor liner and filler metals
US4195987A (en) * 1975-12-29 1980-04-01 Cabot Corporation Weldable alloys
RU2149202C1 (ru) * 1996-04-16 2000-05-20 Сименс Акциенгезелльшафт Изделие для направления горячего, окисляющего газа
US20170020702A1 (en) * 2004-09-30 2017-01-26 Abbott Cardiovascular Systems Inc. Deformation of a polymer tube in the fabrication of a medical article
US20170059165A1 (en) * 2015-08-28 2017-03-02 Rolls-Royce High Temperature Composites Inc. Cmc cross-over tube
JP6144402B1 (ja) * 2016-10-28 2017-06-07 株式会社クボタ 炉床金物用の耐熱鋼
CN110014248A (zh) * 2019-05-15 2019-07-16 丹阳市华龙特钢有限公司 一种镍基耐高温抗腐蚀焊丝的制备方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS54103667A (en) * 1978-02-01 1979-08-15 Matsushita Electronics Corp Magnetron

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641540A (en) * 1951-07-19 1953-06-09 Allegheny Ludlum Steel Ferrous base chromium-nickel-titanium alloy
US2955934A (en) * 1959-06-12 1960-10-11 Simonds Saw & Steel Co High temperature alloy
US3366473A (en) * 1965-11-17 1968-01-30 Simonds Saw & Steel Co High temperature alloy
US3420660A (en) * 1963-09-20 1969-01-07 Nippon Yakin Kogyo Co Ltd High strength precipitation hardening heat resisting alloys
US3552950A (en) * 1967-06-14 1971-01-05 Simonds Saw And Steel Co High temperature corrosion resistant fe-g-ni-mn alloy
US3582318A (en) * 1967-09-05 1971-06-01 Mckay Co Heat-resistant crack-resistant ductile steel weld deposit
US3658516A (en) * 1969-09-05 1972-04-25 Hitachi Ltd Austenitic cast steel of high strength and excellent ductility at high temperatures
US3660080A (en) * 1969-01-31 1972-05-02 Armco Steel Corp Austenitic alloy and weld
US3681059A (en) * 1968-12-13 1972-08-01 Int Nickel Co Nickel-chromium alloy for reformer tubes

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641540A (en) * 1951-07-19 1953-06-09 Allegheny Ludlum Steel Ferrous base chromium-nickel-titanium alloy
US2955934A (en) * 1959-06-12 1960-10-11 Simonds Saw & Steel Co High temperature alloy
US3420660A (en) * 1963-09-20 1969-01-07 Nippon Yakin Kogyo Co Ltd High strength precipitation hardening heat resisting alloys
US3366473A (en) * 1965-11-17 1968-01-30 Simonds Saw & Steel Co High temperature alloy
US3552950A (en) * 1967-06-14 1971-01-05 Simonds Saw And Steel Co High temperature corrosion resistant fe-g-ni-mn alloy
US3582318A (en) * 1967-09-05 1971-06-01 Mckay Co Heat-resistant crack-resistant ductile steel weld deposit
US3681059A (en) * 1968-12-13 1972-08-01 Int Nickel Co Nickel-chromium alloy for reformer tubes
US3660080A (en) * 1969-01-31 1972-05-02 Armco Steel Corp Austenitic alloy and weld
US3658516A (en) * 1969-09-05 1972-04-25 Hitachi Ltd Austenitic cast steel of high strength and excellent ductility at high temperatures

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4195987A (en) * 1975-12-29 1980-04-01 Cabot Corporation Weldable alloys
US4174213A (en) * 1977-03-04 1979-11-13 Hitachi, Ltd. Highly ductile alloys of iron-nickel-chromium-molybdenum system for gas turbine combustor liner and filler metals
RU2149202C1 (ru) * 1996-04-16 2000-05-20 Сименс Акциенгезелльшафт Изделие для направления горячего, окисляющего газа
US20170020702A1 (en) * 2004-09-30 2017-01-26 Abbott Cardiovascular Systems Inc. Deformation of a polymer tube in the fabrication of a medical article
US10058439B2 (en) * 2004-09-30 2018-08-28 Abbott Cardiovascular Systems Inc. Deformation of a polymer tube in the fabrication of a medical article
US20170059165A1 (en) * 2015-08-28 2017-03-02 Rolls-Royce High Temperature Composites Inc. Cmc cross-over tube
US11359814B2 (en) 2015-08-28 2022-06-14 Rolls-Royce High Temperature Composites Inc. CMC cross-over tube
JP6144402B1 (ja) * 2016-10-28 2017-06-07 株式会社クボタ 炉床金物用の耐熱鋼
JP2018070945A (ja) * 2016-10-28 2018-05-10 株式会社クボタ 炉床金物用の耐熱鋼
CN110014248A (zh) * 2019-05-15 2019-07-16 丹阳市华龙特钢有限公司 一种镍基耐高温抗腐蚀焊丝的制备方法

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