Tests demonstrate the room temperature ductility of degraded Rene 41 can be increased to acceptable values by solution heat treatment at a temperature of 2050 degrees to 2150 degrees F /1 to 2 hours/ and cooling through a controlled temperature range followed by normal aging in air /16 hours at 1400 degrees F/

Prager, M.

English

NASA Technical Reports Server

February 1968	 Brief 68-10029 
NASA TECH BRIEF 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
Heat Treatment Procedure to Increase Ductility of Degraded Nickel Alloy 
A study has been conducted to establish a heat 
treatment procedure that will increase the room tem-
perature ductility of degraded René 41 (a nickel base 
alloy) in the form of thick plate and forgings. Tests 
have shown that the room temperature ductility of 
degraded hardware and out-of-specification mill stock 
of René 41 can be increased to acceptable values by 
solution heat treatment of the material at a tempera-
ture of 2050° to 2150°F (1 to 2 hours) and cooling 
through a controlled temperature range followed by 
normal aging in air (16 hours at 1400° F). Elongation 
(a measure of ductility) of test specimens of rejected 
forgings tested at room temperature was increased 
from the original 4 percent to approximately 13 
percent. (Specification grade René 41 from commer-
cial sources has an elongation of 15 to 20 percent.) 
After this heat treatment, the alloy can be subjected 
to additional heat treatment by conventional proced-
ures without appreciable decrease in ductility 
Although the feasibility of this procedure has been 
established for a number of specimens, several prob-
lem areas remain to be investigated. These include 
weldability, effects on cold-worked material, types of 
damage for which the procedure is effective, effect on 
elevated temperature properties, effect of carbon 
content of alloy, and impact properties. 
Note: 
Inquiries concerning this procedure may be di-
rected to:
Technology Utilization Officer 
Marshall Space Flight Center 
Huntsville, Alabama 35812 
Reference: B68-10029 
Patent status: 
No patent action is contemplated by NASA. 
Source: M. Prager 
of North American Aviation, Inc. 
under contract to 
Marshall Space Flight Center 
(MFS-12410) 
Category 03 
This document was prepared under the sponsorship of the National 
Aeronautics and Space Administration. Neither the United States 
Government nor any person acting on behalf of the United States
Government assumes any liability resulting from the use of the 
information contained in this document, or warrants that such use 
will be free from privately owned rights.
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Heat treatment procedure to increase ductility of degraded nickel alloy

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