GH4049 introduces:
GH4049 is a Ni-Co-Cr-based precipitation hardening deformed superalloy with application temperature below 950ºC. The alloy has good oxidation resistance below 1000°C and high high-temperature compressive strength below 950°C, and is suitable for producing natural gas turbocharger blades with a working temperature of 850°C to 950°C. Key equipment includes hot rolled and forged bars and free forged turbine blades.
Application and Characteristics of GH4049 Superalloy
Alloys have been used to make aircraft engine turbine blades and other high-temperature load-bearing components. After long-term manufacture and application, it has become one of the most widely used foliar raw materials.
Compared with similar nickel-based alloys, the thermal processing plasticity of this alloy is weak, but after electroslag remelting or vacuum pump electric remelting, its production and processing plasticity is improved, and the fracture toughness at 1000ºC~1170ºC increases by 1~3. times.
Heat treatment process specification: 1200ºC±10ºC heat preservation for 2 hours air cooling +1050ºC±10ºC heat preservation for 4 hours air cooling +850ºC±10ºC heat preservation for 8 hours air cooling, HB363~302.
GH4049 is a nickel-based aging-strengthened alloy with high temperature strength below 950 degrees, low notch sensitivity, good oxidation resistance and fatigue strength, but poor hot working plasticity. Vacuum consumables or electroslag remelting can improve its heat treatment plasticity.
GH4049 alloy has been used to make aero-engine turbine blades and other high-temperature load-bearing parts. After long-term production and use test, it has become one of the most widely used blade materials.
The new process of constant temperature toughening rolling was applied to the production practice of GH4049 alloy hot-rolled bar. The production process and product quality are relatively stable, and the products can meet the market demand in large quantities, so they have been well evaluated by users, both in terms of economic and social benefits. relatively significant.
Grade: GH4049
C(%): ≤0.10
Cr(%): 9.50~11.0
Mo(%): 4.50~5.50
Ni(%): Margin
W(%): 5.00~6.00
Al(%): 3.70~4.40
Ti(%): 1.40~1.90
Fe(%): ≤1.5
Si(%)≤: 0.50
Mn(%)≤: 0.50
P(%): 0.010
S(%): 0.010
Others (%): B≤0.015, Ce≤0.02, V0.20~0.50
Density: ρ=8.24g/cm3
Melting point: 1260-1320ºC
Scope of application of GH4049: Gas turbine working blades below 900°C and other high-temperature components with greater stress.
Characteristics and uses of GH4049 superalloy:
GH4049 is a nickel-based aging-strengthened alloy with high high temperature strength below 950 degrees, small notch sensitivity, good oxidation resistance and fatigue strength, but poor hot working plasticity.
Vacuum consumable or electroslag remelting can improve its heat processing plasticity for manufacturing gas turbine blades, aero-engines, combustion chambers, afterburner parts, etc. at 900 degrees.
Extension:
Superalloy refers to a kind of metal material based on iron, nickel and cobalt, which can work for a long time under the action of high temperature above 600ºC and certain stress; and has high high temperature strength, good oxidation resistance and corrosion resistance, Good fatigue properties, fracture toughness and other comprehensive properties. The superalloy is a single austenite structure, which has good structure stability and reliability at various temperatures.
Based on the above performance characteristics, and the high degree of alloying of superalloys, also known as "super alloys", is an important material used in aviation, aerospace, petroleum, chemical industry, and ships. According to the matrix elements, superalloys are divided into iron-based, nickel-based, cobalt-based and other superalloys. The operating temperature of iron-based superalloys can only reach 750~780ºC. For heat-resistant parts used at higher temperatures, nickel-based and refractory metal-based alloys are used. Nickel-based superalloys occupy a special and important position in the entire field of superalloys, which are used to manufacture hot-end components of aviation jet engines and various industrial gas turbines.
If the lasting strength of 150MPA-100H is used as the standard, the higher temperature that the nickel alloy can withstand is >1100ºC, while the nickel alloy is about 950ºC, and the iron-based alloy is <850ºC, that is, the nickel-based alloy is correspondingly higher than 150ºC. °C to about 250 °C. So people call the nickel alloy the heart of the engine. At present, nickel alloys have accounted for half of the total weight of the engine, not only the turbine blades and combustion chambers, but also the turbine disks and even the latter stages of the compressor blades have begun to use nickel alloys. Compared with iron alloys, nickel alloys have the advantages of higher working temperature, stable structure, less harmful phases and greater resistance to oxidation and corrosion. Compared with cobalt alloys, nickel alloys can work at higher temperatures and stresses, especially in rotor blades.
Nickel alloys have the above advantages related to some of their own properties. Nickel is a face-centered cube, and its structure is very stable, and does not undergo allotropic transformation from room temperature to high temperature; this is very important for selection as a matrix material. It is well known that austenite structure has a series of advantages over ferrite structure.
Nickel has high chemical stability, hardly oxidizes below 500 degrees, and is not affected by warm air, water and some salt solutions at room temperature. Nickel dissolves very slowly in sulfuric acid and hydrochloric acid, but dissolves very quickly in nitric acid.
Nickel has great alloying ability, and even adding more than ten alloying elements does not appear harmful phase, which provides potential possibilities for improving various properties of nickel.
Although the mechanical properties of pure nickel are not strong, the plasticity is excellent, especially the plasticity changes little at low temperature.
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