KR970021341A - High Temperature Corrosion Resistant Monocrystalline Nickel-Base Super Heat-resistant Alloy - Google Patents

Abstract

The present invention relates to a high temperature corrosion resistant nickel-base heat resistant alloy comprising the following elements, the super heat resistant alloy having a phase stability value (N _V3B ) of about 2.45 or less: about 14.2 to about 15.5 weight percent of chromium, about 2.0 to about 2.0 About 4.0 wt%, molybdenum about 0.30 to about 0.45 wt%, tungsten about 4.0 to about 5.0 wt%, tantalum about 4.5 to about 5.8 wt%, niobium about 0.05 to about 0.25 wt%, aluminum about 3.2 to about 3.6 wt%, About 4.0 to about 4.4 weight percent titanium, about 0.01 to about 0.06 weight hafnium and residual amounts of nickel and incidental impurities.

Single crystal products can be suitably produced from the super heat resistant alloy of the present invention. The product may be a part for a gas turbine engine, and more particularly, the part may be a gas turbine blade or a gas turbine vane.

Description

High Temperature Corrosion Resistant Monocrystalline Nickel-Base Super Heat-resistant Alloy

Since this is an open matter, no full text was included.

FIG. 1 is a plot of high temperature corrosive test results at three exposure temperatures for one embodiment of the invention and four different alloys.

2 is a comparative graph of high temperature corrosion data obtained from tests conducted at 732 ° C. (1350 ° F.) for one embodiment of the invention and two different alloys.

Claims (20)

High temperature corrosion resistant nickel-based superalloy containing the following elements and having a phase stability value (N _V3B ) of about 2.45 or less. About 14.2 to 15.5 weight percent chromium, about 2.0 to 4.0 weight percent cobalt, about 0.30 to 0.45 weight percent molybdenum, about 4.0 to 5.0 weight percent tungsten, about 4.5 to 5.8 weight percent tantalum, about 0.05 to 0.25 weight percent niobium, about aluminum 3.2 to 3.6 weight percent titanium, about 4.0 to 4.4 weight percent hafnium, about 0.01 to 0.06 weight percent and nickel plus incidental impurities. The superalloy according to claim 1, further comprising the following elements. About 0 to 0.05 weight percent carbon, about 0 to 0.03 weight percent boron, about 0 to 0.03 weight percent zirconium, about 0 to 0.25 weight percent rhenium, about 0 to 0.10 weight percent silicon and about 0 to 0.10 weight percent manganese. The superheat resistant alloy according to claim 1, wherein the sum of niobium and hafnium is 0.06% by weight to 0.31% by weight. The super heat resistant alloy according to claim 1, wherein the Ti: A1 ratio is 1 or more. The super heat resistant alloy according to claim 1, wherein the sum of aluminum and titanium is 7.2% by weight to 8.0% by weight. The super heat resistant alloy according to claim 1, wherein Ta: W ratio is 1 or more. The super heat resistant alloy according to claim 1, wherein the oxidation resistance is improved. A single crystal product made from the super heat resistant alloy of claim 1. The single crystal product according to claim 8 which is a component for a turbine engine. 10. The article of claim 9, wherein the component is a gas turbine blade or gas turbine vane. A single crystal casting characterized by improved high temperature corrosion resistance, which is prepared from a nickel-based _superheat resistant alloy containing the following elements and having a phase stability value (N _V3B ) of about 2.45 or less. About 14.3 to 15.0 weight percent chromium, about 2.5 to 3.5 weight percent cobalt, about 0.35 to 0.43 weight percent molybdenum, about 4.2 to 4.8 weight percent tungsten, about 4.8 to 5.4 weight percent tantalum, about 0.05 to 0.12 weight percent niobium, about aluminum 3.3 to 3.5 weight percent, about 4.1 to 4.3 weight percent titanium, about 0.02 to 0.05 weight percent hafnium and nickel plus incidental impurities. 12. The single crystal casting of Claim 11 further comprising the following elements. About 0 to 0.5 weight percent carbon, about 0 to 0.03 weight percent boron, about 0 to 0.03 weight percent zirconium, about 0 to 0.25 weight percent rhenium, about 0 to 0.10 weight percent silicon and about 0 to 0.10 weight percent manganese. 12. The single crystal casting of claim 11 wherein the niobium and hafnium add up to 0.06% to 0.31% by weight. 12. The single crystal casting of claim 11 wherein the sum of aluminum and titanium is between 7.2 weight percent and 8.2 weight percent. The single crystal casting of claim 11 wherein the Ti: Al ratio and the Ta: W ratio are both at least one. The single crystal casting of claim 11, wherein the oxidation resistance is improved. The single crystal casting of claim 11, wherein the creep-rupture strength is improved. 12. The single crystal casting of claim 11 which is a gas turbine blade or gas turbine vane. A single crystal casting characterized by improved high temperature corrosion resistance made from a nickel-based _superheat resistant alloy containing the following elements and having a phase stability value (N _V3B ) of about 2.45 or less. Bromine about 14.5%, cobalt about 3.0%, molybdenum about 0.40%, tungsten about 4.4%, tantalum about 4.95%, niobium about 0.10%, aluminum about 3.40%, titanium about 4.2%, hafnium about 0.04 weight%, about 0 to 0.05 weight% carbon, about 0 to 0.03 weight% boron, about 0 to 0.03 weight% zirconium, about 0 to 0.25 weight% rhenium, about 0 to 0.10 weight% silicon, about 0 to 0.10 weight manganese % And nickel remaining amount. Rain is 1 or more) 20. The single crystal casting of claim 19 which is a gas turbine blade or gas turbine vane. ※ Note: The disclosure is based on the initial application.