Niobium Hafnium Alloy (C103)

  • Niobium Hafnium C103 alloy
  • Nb10Hf C-103

Product Details

Niobium C-103 History

In 1965, Niobium C-103 alloy is first manufactured in America and then used in nozzle extended segment of Apollo manned lunar module rocket engine. In 1975, China succeeded in producing NbHf10Ti1Zr0.7 niobium alloy.

Niobium C-103 Application

Niobium alloy C-103 is an excellent material for liquid rocket thruster nozzles, lightweight propulsion systems and rocket engine thrust chamber in aerospace industry. Niobium alloy C-103 is also used in the manufacture of turbopump and high-temperature jet engine parts. It is obvious that niobium alloy C-103 is an ideal material in space engineering fabrication.

Niobium C-103 Fabrication Process

Niobium alloy C-103 has high melting point. Fabrication process involves C-103 ingots production process and mechanical process. Niobium hafnium alloy is processed into ingots by combining electron-beam cast with vacuum consumable electrode arc furnace. Then C-103 is extruded or forged over 1200℃. After rolling and drawing under 500℃, niobium hafnium alloy C-103 is manufactured into sheets, strips, rods, wire or other fittings.

Niobium C-103 Welding

Niobium alloy C-103 has good weldability. The welding methods include argon tungsten-arc welding and electron-beam fusion welding. Welding quality depends on the purity of argon and vacuum. The purer the argon and the lower remaining pressure is, the better the welding quality will be.

Niobium C-103 Heat Treatment

Vacuum or inert gas protection is usually applied in the process of annealing, solution and aging treatment.

C-103 Chemical Composition Maximum Weight % (Except Where Otherwise Specified)
Products C O N H Hf Ti Zr W Ta
C-103 0.015 0.025 0.01 0.0015 9 - 11 0.7 - 1.3 0.7 0.5 0.500
C-103 Physical Properties
Products Composition Density/g·cm-3 Temperature/˚C Coefficient of Line-expansion/10-6K-1 Recrystallization Temperature/˚C Anneal Temperature/˚C Elongation Brittle Transition Temperature/˚C
C-103 Nb-10Hf-1Ti-0.7Zr-0.1W-0.1Mo-0.05Ta 8.86 2349 4.5 (1203˚C) 1038 - 1316 871 - 196
Niobium Alloys C-103 Foil, Sheet, Strip and Plate Mechanical Property
  Ultimate Tensile Strength, Min, Psi (MPa) Yield Strength(0.2 % offset), Min,Psi (MPa) Elongation In 1 In.(25 mm) Gage Length, Min, %
Material 0.05 in. (1.3 mm) and thinner:
Room temperature 56 000 (385) 40 000 (275) 20
2000 ± 25°F
(1100 ± 15°C)		 21 000 (145) 16 000 (110) 20
Material greater than 0.05 in. (1.3 mm) in thickness:
Room temperature 54 000 (370) 38 000 (260) 20
2000 ± 25°F
(1100 ± 15°C)		 21 000 (145) 16 000 (110) 20
Niobium Alloys C-103 Rod Bar and Wire Mechanical Property
  Ultimate Tensile Strength, Min, Psi (MPa) Yield Strength(0.2 % offset), Min,Psi (MPa) Elongation In 1 In.(25 mm) Gage Length, Min, %
Material 0.050 in. (1.27 mm) and smaller in diameter:
Room temperature 56 000 (385) 40 000 (275) 20
2000 ± 25°F
(1100 ± 15°C)		 21 000 (145) 16 000 (110) 20
Material 0.051 in. (1.30 mm) and larger in diameter:
Room temperature 54 000 (370) 38 000 (260) 20
2000 ± 25°F
(1100 ± 15°C)		 21 000 (145) 16 000 (110) 20
C-103 High-temperature Properties
Products Composition Shape Temperature/˚C Tensile Strength/MPa Temperature/˚C Modulus of Elasticity Break Strength/MPa
C-103 10Hf, 1Ti, 0.7Zr Sheet 1093 189.8 - 112 490 -

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