GLTRS--Glenn
TITLE AND SUBTITLE:
Strain-Life Assessment of Grainex Mar-M 247 for NASA's Turbine Seal Test Facility

AUTHOR(S):
Irebert R. Delgado, Gary R. Halford, Bruce M. Steinetz, and Clare M. Rimnac

REPORT DATE:
April 2004

FUNDING NUMBERS:
WBS-22-714-09-18
1L161102AF20

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
John H. Glenn Research Center at Lewis Field
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-14460

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001
and
U.S. Army Research Laboratory
Adelphi, Maryland 20783-1145

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-2004-212985
ARL-TR-3178
GT2004-53939

SUPPLEMENTARY NOTES:
Prepared for the Turbo Expo 2004 sponsored by the American Society of Mechanical Engineers, Vienna, Austria, June 14-17, 2004. Irebert R. Delgado, U.S. Army Research Laboratory, NASA Glenn Research Center, Gary R. Halford and Bruce M. Steinetz, NASA Glenn Research Center; and Clare M. Rimnac, Case Western Reserve University, Cleveland, Ohio 44106. Responsible person, Irebert R. Delgado, organization code 0300, 216-433-3935.

ABSTRACT:
NASA's Turbine Seal Test Facility is used to test air-to-air seals for use primarily in advanced jet engine applications. Combinations of high temperature, high speed, and high pressure limit the disk life, due to the concern of crack initiation in the bolt holes of the Grainex Mar-M 247 disk. The primary purpose of this current work is to determine an inspection interval to ensure safe operation. The current work presents high temperature fatigue strain-life data for test specimens cut from an actual Grainex Mar-M 247 disk. Several different strain-life models were compared to the experimental data including the Manson-Hirschberg Method of Universal Slopes, the Halford-Nachtigall Mean Stress Method, and the Modified Morrow Method. The Halford-Nachtigall Method resulted in only an 18 percent difference between predicted and experimental results. Using the experimental data at a -99.95 percent prediction level and the presence of 6 bolt holes it was found that the disk should be inspected after 665 cycles based on a total strain of 0.5 percent at 649 °C.

SUBJECT TERMS:
Superalloy; Mar-M 247; Fatigue strain-life; Nickel-based; Crack initiation; Life estimation; Turbine sealing testing; Turbine disk

NUMBER OF PAGES:
13

PDF AVAILABLE FROM URL:
2004/TM-2004-212985.pdf ( 1,192 KB )
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