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Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c9001515
EISBN: 978-1-62708-229-7
... to full-power operation and ensured a low probability of a similar occurrence for all CANDU reactors. Fracture mechanics Laminations Nuclear reactor components Pressure tubes Zr-2.5Nb UNS R60901 Hydrogen damage and embrittlement Mixed-mode fracture Metalworking-related failures...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.process.c0046028
EISBN: 978-1-62708-235-8
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.med.c0048423
EISBN: 978-1-62708-226-6
... cobalt-chromium-molybdenum alloy. (a) Radiograph of total hip prosthesis. Circular wire marks acetabulum component made from plastics. Arrows (from top to bottom) indicate the area where the prosthesis stem is loosening at the collar, a stem fracture, and a fracture of bone cement at the end of the stem...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.usage.c9001545
EISBN: 978-1-62708-236-5
.... Caustic, not chloride, stress corrosion was the culprit. Had material substitutions been made on the original premise of countering chloride stress corrosion, most of the loop's highly stressed components would have eventually failed. Bearings Bellows Caustic stress corrosion cracking 304 UNS...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001517
EISBN: 978-1-62708-217-4
... Abstract The purpose of this investigation was to determine the cause of the ultrasonic signal attenuation noted during an inspection of a composite aircraft component. Although ultrasonics was able to identify the location of the defective areas, destructive analysis had to be utilized...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001489
EISBN: 978-1-62708-217-4
... loading; the comparison is being made with the polished surfaces and the tensile specimen fracture surfaces. The inclusions in the failed retaining ring were compared with the ones in a similar component obtained from a used engine. In the case of the latter, a large number of fine and elongated (Mn, Cr...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001706
EISBN: 978-1-62708-217-4
... of the 4340 steel MLG components during fabrication and overhaul to minimise their propensity for SCC. Adequate corrosion prevention measures should be undertaken to prevent future occurrences should concentrate on corrosion prevention by: ensuring that all the specified protective coatings...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.modes.c9001632
EISBN: 978-1-62708-234-1
... materials) and subsystems for the Accelerator Production of Tritium (APT) project target area. 4 Materials and components used in the APT target and blanket would experience proton and neutron particle fluxes and spectra similar to the samples and components placed in the LANSCE beam stop area...
Series: ASM Failure Analysis Case Histories
Volume: 3
Publisher: ASM International
Published: 01 December 2019
DOI: 10.31399/asm.fach.v03.c9001829
EISBN: 978-1-62708-241-9
... Abstract An investigation was conducted to better understand the time-dependent degradation of thermal barrier coated superalloy components in gas turbines. First-stage vanes are normally subjected to the highest gas velocities and temperatures during operation, and were thus the focus...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001026
EISBN: 978-1-62708-214-3
... support would have fractured under service loads, because no other flap support failures have ever been experienced, for the following reasons. Design limit stresses for aircraft components of this type are always set at some fraction of the specified minimum yield stress, based on fatigue experience...
Series: ASM Handbook
Volume: 11A
Publisher: ASM International
Published: 30 August 2021
DOI: 10.31399/asm.hb.v11A.9781627083294
EISBN: 978-1-62708-329-4
Series: ASM Handbook
Volume: 11A
Publisher: ASM International
Published: 30 August 2021
DOI: 10.31399/asm.hb.v11A.a0006821
EISBN: 978-1-62708-329-4
... Abstract This article focuses on failure analyses of aircraft components from a metallurgical and materials engineering standpoint, which considers the interdependence of processing, structure, properties, and performance of materials. It discusses methodologies for conducting aircraft...
Series: ASM Handbook
Volume: 11A
Publisher: ASM International
Published: 30 August 2021
DOI: 10.31399/asm.hb.v11A.a0006840
EISBN: 978-1-62708-329-4
... Abstract This glossary is a compilation of terms related to the analysis and prevention of component and equipment failures. It is intended to help promote clear thinking and useful failure analysis. The definitions presented are those used in this Volume and reflect a common and modern...
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Published: 01 January 2002
Fig. 1 Schematic view of a component that has fractured in multiple pieces. If chevrons are visible on the fracture surface, the sequence of crack formation can be used to obtain the crack formation sequence and the location of the initiation site. Source: Ref 25 More
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Published: 01 January 2002
Fig. 49 Steel shaft (AISI 4817) carburized and hardened to HRC 60. Component loaded in rotating bending. Fracture initiation in six fillet areas around the periphery. Six initiation sites are visible as evidenced by multiple sets of beach marks (curved black lines). Source: Ref 29 More
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Published: 01 January 2002
Fig. 66 When there is insufficient height or width of a component containing a crack, the K field created by the cracklike defect is altered by the free surfaces of the component. (And, in this case, linear elastic fracture mechanics is not valid.) The figure shows the effect of inadequate More
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Published: 01 January 2002
Fig. 4 A cleavage fracture in a carbon steel component is shown. Scanning electron micrograph. 593× More
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Published: 01 January 2002
Fig. 10 Stainless steel component that was flexed in service. The transition between fatigue and dimple rupture is shown. Scanning electron micrograph. 1187× More
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Published: 01 January 2002
Fig. 27 Near-surface cracking present on a heavily abraded mining component. Continued abrasion after intergranular crack formation has deflected the perpendicular cracks. Unetched. 30× More
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Published: 01 January 2002
Fig. 1 Fretting damage incurred in a bearing shell component because of insufficient contact pressure between the shell and housing of a bearing. Source: Ref 7 More