Gas turbine and gas turbine nozzle

Claim 2

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, each nozzle having two side walls and a blade portion formed between said two side walls, and being formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 15 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, the combination of (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10% W), D (5% of (Al+Ti) , 5% W) E(3.5% of (Al+Ti), 5% W), and F(2.5% of (Al+Ti), 7.5% W).

Claim 3

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, and being formed of a nickel-base superalloy which remains intact in a 900° C.-14 kg/mm 2 rupture test for 300 hours or longer, and which does not substantially cause a cracking in welding beads 80 mm 2 long formed by one-pass TIG-welding, each of said nozzles having two side walls and a blade portion formed between said two side walls and being of a casting of said nickel-base superalloy, and said blade portion having a dimension between said side walls of 70 mm or greater and a dimension between its inlet-side end and its outlet-side end of 100 mm or greater.

Claim 4

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, and being formed of a nickel-base superalloy which remains intact in a 900° C.-14 kg/mm 2 rupture test for 300 hours or longer, and which does not substantially cause a cracking in welding beads 80 mm 2 long formed by one-pass TIG-welding, each of said nozzles having two side walls and a blade portion formed between said two side walls and being of a casting of said nickel-base superalloy, and said blade portion having a dimension between said side walls of 70 mm or greater and a dimension between its inlet-side end and its outlet-side end of 100 mm or greater.

Claim 5

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, each of said nozzles having two side walls and a blade portion formed between said two walls, and being formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 15 to 25% Co; 15 to 25% Cr; 1.0 to 3.0 Al; 1.0 to 3.0% Ti; 1.0 to 3.0% Nb; 5 to 10% W; at least one of up to 0.05% Zr, 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and up to 0.5% one or more rare earth elements; and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L (5% of (Al+Ti), 10% W), D(5% of (Al+Ti), 5% W), E(3.5% of (Al+Ti), 5% W), and F(2.5% of (Al+Ti), 7.5% W).

Claim 6

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, each of said nozzles having two side walls and a blade portion formed between said two walls, and being formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 15 to 25% Co; 15 to 25% Cr; 1.0 to 3.0 Al; 1.0 to 3.0% Ti; 1.0 to 3.0% Nb; 5 to 10% W; at least one of up to 0.05% Zr, 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and up to 0.5% one or more rare earth elements; and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L (5% of (Al+Ti), 10% W), D(5% of (Al+Ti), 5% W), E(3.5% of (Al+Ti), 5% W), and F(2.5% of (Al+Ti), 7.5% W).

Claim 7

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including turbine discs of at least first, second and third stages arranged with respect to one another along the rotor in a direction of flow of said combustion gas; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades and each nozzle having two side walls and a blade portion formed between said two side walls, the first-stage disc being the most upstream disc of said discs and being a casting of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al; 1.0 to 3.0 Ti. 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, said casting remaining intact in a 900° C.-14 kg/mm 2 rupture test for 300 hours or longer, the second and latter-stage discs being formed of a Co-base alloy comprising, by weight: 0.2 to 0.6% carbon, up to 2% Si, up to 2% Mn, 25 to 35% Cr, 5 to 15% Ni, 3 to 10% W, 0.003 to 0.03% B, and at least 50% Co.

Claim 8

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including turbine discs of at least first, second and third stages arranged with respect to one another along the rotor in a direction of flow of said combustion gas; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades and each nozzle having two side walls and a blade portion formed between said two side walls, the first-stage disc being the most upstream disc of said discs and being a casting of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al; 1.0 to 3.0 Ti. 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, said casting remaining intact in a 900° C.-14 kg/mm 2 rupture test for 300 hours or longer, the second and latter-stage discs being formed of a Co-base alloy comprising, by weight: 0.2 to 0.6% carbon, up to 2% Si, up to 2% Mn, 25 to 35% Cr, 5 to 15% Ni, 3 to 10% W, 0.003 to 0.03% B, and at least 50% Co.

Claim 9

A gas turbine nozzle formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W, L(5% of (Al+Ti), 10% W), D(5% of (Al+Ti), 5% W), E(3.5% of (Al+Ti), 5% W), and F(2.5% of (Al+Ti), 7.5% W).

Claim 10

A gas turbine nozzle formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W, L(5% of (Al+Ti), 10% W), D(5% of (Al+Ti), 5% W), E(3.5% of (Al+Ti), 5% W), and F(2.5% of (Al+Ti), 7.5% W).

Claim 11

A gas turbine nozzle formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% Co; 15 to 25% Cr; 1.0 to 3.0% Al; 1.0 to 3.0% Ti; 1.0 to 3.0 of Nb; 5 to 10% W; at least one of UP to 0.05% Zr, 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and up to 0.5% one or more rare earth elements; and at least 42.5% Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(12.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10% W), D(5% of (Al+Ti), 5% W), E(3.5%, 5% W), and F (2.5% of (Al+Ti).

Claim 12

A gas turbine nozzle formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% Co; 15 to 25% Cr; 1.0 to 3.0% Al; 1.0 to 3.0% Ti; 1.0 to 3.0 of Nb; 5 to 10% W; at least one of UP to 0.05% Zr, 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and up to 0.5% one or more rare earth elements; and at least 42.5% Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(12.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10% W), D(5% of (Al+Ti), 5% W), E(3.5%, 5% W), and F (2.5% of (Al+Ti).

Claim 13

A nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% CO, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, the combination of the (Al+Ti)0 content and the tungsten content being determined with a tetragonal shadowed area including the boundary shown in FIG. 5, four vertices of which are: M(3.14% of (Al+Ti), 8.6% W), N(4.7% of (Al+Ti), 8.6% W), O(4.7% of (Al+Ti), 6.05% W), and P(3.14% (Al+Ti), 6.05% of W).

Claim 14

A nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% CO, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, the combination of the (Al+Ti)0 content and the tungsten content being determined with a tetragonal shadowed area including the boundary shown in FIG. 5, four vertices of which are: M(3.14% of (Al+Ti), 8.6% W), N(4.7% of (Al+Ti), 8.6% W), O(4.7% of (Al+Ti), 6.05% W), and P(3.14% (Al+Ti), 6.05% of W).

Claim 15

A nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% CO, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least one of up to 0.05% Zr, 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and 0.5% one or more of rare earth elements; and at least 42.5% Ni, the combination of the content and the tungsten content being determined within a tetragonal shadowed area including the boundary shown in FIG. 5, four vertices of which are: M(3.14% of (Al+Ti), 8.6%. W), N(4.7% of (Al+Ti), 8.6% W), O(4.7% of (Al+Ti), 6.05% W), and P of (3.14% (Al+Ti), 6.05% W).

Claim 16

A nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% CO, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least one of up to 0.05% Zr, 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and 0.5% one or more of rare earth elements; and at least 42.5% Ni, the combination of the content and the tungsten content being determined within a tetragonal shadowed area including the boundary shown in FIG. 5, four vertices of which are: M(3.14% of (Al+Ti), 8.6%. W), N(4.7% of (Al+Ti), 8.6% W), O(4.7% of (Al+Ti), 6.05% W), and P of (3.14% (Al+Ti), 6.05% W).

Claim 17

A combined power generating system having a total heat efficiency of 44% or higher and comprising: a gas turbine driven by combustion gas which flows at high speeds; a waste-heat recovering boiler for recovering energy of exhaust gas of said gas turbine in the form of steam; a steam turbine driven by the steam provided by said waste-heat recovering boiler; and a generator driven by said gas turbine and said steam turbine, wherein said gas turbine has blades at three or more stages, and a plurality of nozzles each having two side walls and a blade portion formed between said two side walls, said blade portion having a dimension between said side walls of 70 mm or greater and a dimension between its inlet-side end and its outlet-side end of 200 mm or greater and the combustion gas temperature at an inlet of said gas turbine is 1260° C. or higher and the exhaust gas temperature at an outlet is 530° C. or higher, said waste-heat recovering boiler provides steam having a temperature of 530° C. or higher, and wherein said steam turbine comprises: a high and low-pressure combined-type rotor formed of a Ni--Cr--Mo low alloy steel having a bainitic structure; blades, at the final stage longer than 26 inches; and a casing containing said steam turbine.

Claim 18

A combined power generating system having a total heat efficiency of 44% or higher and comprising: a gas turbine driven by combustion gas which flows at high speeds; a waste-heat recovering boiler for recovering energy of exhaust gas of said gas turbine in the form of steam; a steam turbine driven by the steam provided by said waste-heat recovering boiler; and a generator driven by said gas turbine and said steam turbine, wherein said gas turbine has blades at three or more stages, and a plurality of nozzles each having two side walls and a blade portion formed between said two side walls, said blade portion having a dimension between said side walls of 70 mm or greater and a dimension between its inlet-side end and its outlet-side end of 200 mm or greater and the combustion gas temperature at an inlet of said gas turbine is 1260° C. or higher and the exhaust gas temperature at an outlet is 530° C. or higher, said waste-heat recovering boiler provides steam having a temperature of 530° C. or higher, and wherein said steam turbine comprises: a high and low-pressure combined-type rotor formed of a Ni--Cr--Mo low alloy steel having a bainitic structure; blades, at the final stage longer than 26 inches; and a casing containing said steam turbine.

Claim 19

A gas turbine according to claim 1, said nickel-base superalloy further comprising less than 5% Mo.

Claim 20

A gas turbine according to claim 3, said nickel-base superalloy further comprising less than 5% Mo.

Claim 21

A gas turbine according to claim 4, said nickel-base superalloy further comprising less than 5% Mo.

Claim 22

A gas turbine according to claim 5, said nickel-base superalloy further comprising less than 5% Mo.

Claim 23

A gas turbine nozzle according to claim 6, said nickel-base superalloy further comprising less than 5% Mo.

Claim 24

A nickel-base superalloy according to claim 7, said nickel base superalloy further comprising less than 5% Mo.

Claim 25

A nickel-base superalloy according to claim 8, said nickel-base superalloy further comprising less than 5% Mo.

Claim 26

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each other of said discs, the combustion gas from said nozzle striking said blades so that said rotor with turbine discs rotates; said nozzles being provided in a ring-arrangement being opposite to said blades, and being of a casting of a nickel-base superalloy which remains intact in a 900° C.-14 kg/mm 2 rupture test for 300 hours or longer, and which does not substantially cause a cracking in welding beads 80 mm long formed by one-path TIG-welding, each said nozzle having two side walls and a blade portion formed between said two side walls, and said blade portion having a relatively larger thickness at a combustion gas inlet side than that at a combustion gas outlet side, and having a dimension between said side walls of 70 mm or greater and a dimension between its inlet-side end and its outlet-side end of 100 mm or greater, wherein there is provided a cavity at said larger thickness side of said blade portion, into which coolant gas enters through an opening at one of said side walls so as to cool said blade portion, there is provided a clearance formed by pin-fins at said smaller thickness side of said blade portion, and wherein there is provided a slit-clearance of a coolant gas outlet at the end edge portion of said smaller thickness side of said blade portion.

Claim 27

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each other of said discs, the combustion gas from said nozzle striking said blades so that said rotor with turbine discs rotates; said nozzles being provided in a ring-arrangement being opposite to said blades, and being of a casting of a nickel-base superalloy which remains intact in a 900° C.-14 kg/mm 2 rupture test for 300 hours or longer, and which does not substantially cause a cracking in welding beads 80 mm long formed by one-path TIG-welding, each said nozzle having two side walls and a blade portion formed between said two side walls, and said blade portion having a relatively larger thickness at a combustion gas inlet side than that at a combustion gas outlet side, and having a dimension between said side walls of 70 mm or greater and a dimension between its inlet-side end and its outlet-side end of 100 mm or greater, wherein there is provided a cavity at said larger thickness side of said blade portion, into which coolant gas enters through an opening at one of said side walls so as to cool said blade portion, there is provided a clearance formed by pin-fins at said smaller thickness side of said blade portion, and wherein there is provided a slit-clearance of a coolant gas outlet at the end edge portion of said smaller thickness side of said blade portion.

Claim 28

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzle striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, each nozzle having two side walls and and a blade portion formed between said two side walls, and being formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 15 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10%W), D(5% of (Al+Ti), 5% W), E(3.5% of (Al+Ti), 5% W) and F(2.5% of (Al+Ti), 7.5% W).

Claim 29

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said rotor including a plurality of turbine discs; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzle striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, each nozzle having two side walls and and a blade portion formed between said two side walls, and being formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 15 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10%W), D(5% of (Al+Ti), 5% W), E(3.5% of (Al+Ti), 5% W) and F(2.5% of (Al+Ti), 7.5% W).

Claim 30

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said turbine rotor including turbine discs of at least first, second and third stages arranged with respect to one another along the rotor in a direction of flow of said combustion gas; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, each nozzle having two side walls and a blade portion formed between said two side walls, the first-stage disc being the most upstream disc of said discs and being of a casting of a nickel-base alloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and the balance consisting essentially of Ni, said casting remaining intact in a 900° C.-14 kg/mm 2 rupture test for 300 hours or longer, the second and latter-stage discs being formed of a Co-base alloy comprising by weight: 0.2 to 0.6% carbon, up to 2% Si, up to 1% Mn, 25 to 35% Cr, 5 to 15% Ni, 3 to 10% W, 0.003 to 0.03% B, and at least 50% Co.

Claim 31

A gas turbine comprising: a compressor for compressing air; a plurality of nozzles for directing combustion gas which has been formed by using compressed air from said compressor and fuel; a turbine rotor; said turbine rotor including turbine discs of at least first, second and third stages arranged with respect to one another along the rotor in a direction of flow of said combustion gas; and a plurality of blades which are connected into each of said discs, the combustion gas from said nozzles striking said blades so that said rotor with turbine discs rotates, said nozzles being provided in a ring-arrangement being opposite to said blades, each nozzle having two side walls and a blade portion formed between said two side walls, the first-stage disc being the most upstream disc of said discs and being of a casting of a nickel-base alloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and the balance consisting essentially of Ni, said casting remaining intact in a 900° C.-14 kg/mm 2 rupture test for 300 hours or longer, the second and latter-stage discs being formed of a Co-base alloy comprising by weight: 0.2 to 0.6% carbon, up to 2% Si, up to 1% Mn, 25 to 35% Cr, 5 to 15% Ni, 3 to 10% W, 0.003 to 0.03% B, and at least 50% Co.

Claim 32

A gas turbine nozzle formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0 Ti, 1.0 to 3.0 Nb, 5 to 10% W, and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10% W), D(5% of (Al+Ti), 5% W), E(3.5% of (Al+Ti), [7/]5% W) and F(2.5% of (Al+Ti), 7.5%W).

Claim 33

A gas turbine nozzle formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0 Ti, 1.0 to 3.0 Nb, 5 to 10% W, and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10% W), D(5% of (Al+Ti), 5% W), E(3.5% of (Al+Ti), [7/]5% W) and F(2.5% of (Al+Ti), 7.5%W).

Claim 34

A gas turbine nozzle formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% Co; 15 to 25% Cr; 1.0 to 3.0% Al; 1.0 to 3.0% Ti; 1.0 to 3.0% Nb; 5 to 10% W; at least one of 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and up to 0.5% one or more of rare earth elements; and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10% W), D (5% of (Al+Ti), 5% W), E (3.5% of (Al+Ti), 5% W), and F(1.5% of (Al+Ti), 7.5% W).

Claim 35

A gas turbine nozzle formed of a nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% Co; 15 to 25% Cr; 1.0 to 3.0% Al; 1.0 to 3.0% Ti; 1.0 to 3.0% Nb; 5 to 10% W; at least one of 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and up to 0.5% one or more of rare earth elements; and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a pentagonal shadowed area including the boundary shown in FIG. 5, five vertices of which are: A(2.5% of (Al+Ti), 10% W), L(5% of (Al+Ti), 10% W), D (5% of (Al+Ti), 5% W), E (3.5% of (Al+Ti), 5% W), and F(1.5% of (Al+Ti), 7.5% W).

Claim 36

A nickel-base superalloy consisting essentially of, by weight: 0.05% to 0.20% carbon; 20 to 25% Co; 15 to 25% Cr, 1.0 to 3.0% Al; 1.0 to 3.0% Ti; 1.0 to 3.0% Nb; 5 to 10% W; the balance consisting essentially of Ni the combination of the (Al+Ti) content and the tungsten content being determined within a tetragonal shadowed area including the boundary shown in FIG. 5, four vertices of which are: M(3.14% of (Al+Ti), 8.6% W), N(4.7% of (Al+Ti), 8.6% W), O(4.7% of (Al+Ti), 6.05% W), and P of (3.14% (Al+Ti), 6.05% W).

Claim 37

A nickel-base superalloy consisting essentially of, by weight: 0.05% to 0.20% carbon; 20 to 25% Co; 15 to 25% Cr, 1.0 to 3.0% Al; 1.0 to 3.0% Ti; 1.0 to 3.0% Nb; 5 to 10% W; the balance consisting essentially of Ni the combination of the (Al+Ti) content and the tungsten content being determined within a tetragonal shadowed area including the boundary shown in FIG. 5, four vertices of which are: M(3.14% of (Al+Ti), 8.6% W), N(4.7% of (Al+Ti), 8.6% W), O(4.7% of (Al+Ti), 6.05% W), and P of (3.14% (Al+Ti), 6.05% W).

Claim 38

A nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% Co; 15 to 25% Cr; 1.0 to 3.0% Al; 1.0 to 3.0% Ti; 1.0 to 3.0% Nb; 5 to 10% W; at least one of 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and up to 0.5% one or more of rare earth elements; and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a tetragonal shadowed area including the boundary shown in FIG. 5, four vertices of which are: M(3.14% of (Al+Ti), 8.6% W), N(4.7% of (Al+Ti), 8.6% W), 0(4.7% of (Al+Ti), 6.05% W), and P of (3.14% (Al+Ti), 6.05% W).

Claim 39

A nickel-base superalloy consisting essentially of, by weight: 0.05 to 0.20% carbon; 20 to 25% Co; 15 to 25% Cr; 1.0 to 3.0% Al; 1.0 to 3.0% Ti; 1.0 to 3.0% Nb; 5 to 10% W; at least one of 0.001 to 0.03% B, up to 1.5% Hf, up to 2% Re, up to 2% V, up to 0.5% Y, up to 0.5% Sc and up to 0.5% one or more of rare earth elements; and the balance consisting essentially of Ni, the combination of the (Al+Ti) content and the tungsten content being determined within a tetragonal shadowed area including the boundary shown in FIG. 5, four vertices of which are: M(3.14% of (Al+Ti), 8.6% W), N(4.7% of (Al+Ti), 8.6% W), 0(4.7% of (Al+Ti), 6.05% W), and P of (3.14% (Al+Ti), 6.05% W).