Rene 41 - Heanjia Super-metals Co., Ltd.

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Rene 41

René 41 is a nickel-based high temperature alloy developed by General Electric which retains high strength in the 1200/1800°F (649/982°C) temperature range. It is used in jet engine and missile components, and other applications requiring high strength at extremes of temperature.

René 41 was used to create the outer shell of the Mercury capsule due to its ability to retain high strength at very high temperatures.

The composition is: Chromium 18-20%, cobalt 12%, molybdenum 9-10.5%, titanium 3.0-3.3%, aluminium 1.4-1.6% with the rest being nickel.

DESCRIPTION

Rene 41 is a precipitation hardening, nickel-based high temperature alloy possessing high strength in the 1200/1800°F (649/982°C) temperature range. This alloy is designed for use in severely stressed high temperature applications.

APPLICATIONS

Rene 41 has found applications in jet engine and high speed airframe components such as: afterburner parts, turbine casings, wheels, buckets, bolts, and fasteners.

CORROSTION RESISTANCE

Rene 41 is highly corrosion and oxidation resistant. It provides very good resistance to jet engine combustion gases up to 1800°F (982°C).

PHYSICAL PROPERTIES

Electrical resistivity

CONDITION	0.075" strip at 68°F (20°C)
CONDITION	khms c/mf	microhm-mm
A. Hot rolled	787.1	1310
B. A plus 1950°F (1066°C), 4 hrs, AC	751.6	1250
C. B plus 1400°F (760°C), 16 hrs, AC	761.4	1270
D. A plus 2150°F (1177°C), 30 min, AC	803.0	1330
E. D plus 1650°F (899°C), 4 hrs, AC	807.2	1340

Mean coefficient of thermal expansion

TEMPERATURE		10-6/°F	10-6/°C
70°F to	21°C to	10-6/°F	10-6/°C
200	93	6.7	12.1
600	316	7.0	12.6
1000	538	7.5	13.5
1200	649	7.8	14.0
1400	760	8.2	14.8
1600	871	8.8	15.8
1800	982	9.3	16.7
2000	1093	9.0	17.8

Thermal conductivity

Temperature		Btu-in/ft²-hr-°F	W/m-K
°F	°C	Btu-in/ft²-hr-°F	W/m-K
300	149	80	11.5
600	316	102	14.7
1000	538	131	18.9
1200	649	146	21.1
1400	760	161	23.2
1600	871	175	15.2

HEAT TREATMENT

Annealing

Lowest hardness is obtained by quenching from temperatures above the gamma prime solvus temperature - 1950°F (1066°C) is usually satisfactory. Hardness will be in the Rockwell B 98/C 30 range, depending on the rapidity of the quench. It is unlikely that large sections can be quenched rapidly enough to obtain low hardness.

Stress rupture properties may be improved if a temperature "above solvus" is employed - 1975°F (1080°C), hold 1 hour, then air cool.

In general, high temperature treatments should be avoided.

If the M6C carbide, normally present in this alloy, is solutioned by treating above 2100°F (1149°C), it will precipitate during cooling or aging as M23C6,a continuous grain boundary film which results in low ductility. Resolutioning - at least 1800°F (982°C) and preferably 1900°F (1038°C) - is required to restore ductility by reforming M6C

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