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Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.usage.c9001508
EISBN: 978-1-62708-236-5
.... A contributing factor was the length of time spent in the packaging, 21 years. Cracking (fracturing) Heat shields Residual stress Weld defects 321 UNS S32100 Stress-corrosion cracking The standard depot level maintenance of Pratt & Whitney/U.S. Navy J52-P-6, J52-P-8, and J52-P-408 gas...
Series: ASM Failure Analysis Case Histories
Volume: 3
Publisher: ASM International
Published: 01 December 2019
DOI: 10.31399/asm.fach.v03.c9001758
EISBN: 978-1-62708-241-9
... at carbides and other microconstituents, especially in single crystal castings that do not possess grain boundaries. gas turbine engine components creep deformation overheating nickel-base superalloy interdendritic stress-rupture fracture stress-rupture testing stress-rupture life Cast nickel...
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006787
EISBN: 978-1-62708-295-2
... failures, molten salts for energy storage, and degradation and failures in gas turbines. The article describes the effects of environment on aero gas turbine engines and provides an overview of aging, diffusion, and interdiffusion phenomena. It also discusses the processes involved in high-temperature...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001081
EISBN: 978-1-62708-214-3
... Abstract Several compressor disks in military fighter and trainer aircraft gas turbine engines cracked prematurely in the bolt hole regions. The disks were made of precipitation-hardened AM355 martensitic stainless steel. Experimental and analytical work was performed on specimens from...
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Published: 15 January 2021
Fig. 31 Different views of possible calcium-magnesium-alumino-silicate attack on a shipboard turbine blade under the platform in a marine gas turbine engine. Source: Ref 235 . Courtesy of U.S. Navy More
Image
Published: 01 January 2002
blades (B) with significant airfoil damage from the overtemperature condition, which had a detrimental effect on their microstructures. The fourth-stage blades (C) ruptured as a result of lower fracture toughness and creep resistance, which is caused by elevated-temperature operation in gas turbine More
Series: ASM Failure Analysis Case Histories
Volume: 3
Publisher: ASM International
Published: 01 December 2019
DOI: 10.31399/asm.fach.v03.c9001756
EISBN: 978-1-62708-241-9
... 108 (nickel-base alloy) Nimonic 115 (nickel-chromium base alloy) Introduction Military gas turbine engines operate at extremely severe operating conditions with high throttle excursion and under arduous environmental conditions. This often leads to premature failures of engine components...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.mech.c9001748
EISBN: 978-1-62708-225-9
... reoccurrence, specific inspection criteria were issued defining maximum limits for spline wear. A procedure and requirements were specified for installing the coupling and pinion gear at the next overhaul. Gas turbine engines Inspection Pinions Specifications Splines AMS 6470 UNS K24065 (Other...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c0090181
EISBN: 978-1-62708-229-7
... was considered generic, and the conclusion was that the primary failure mechanism was LCF. Material imperfections were a secondary deficiency that had the effect of causing the blades from the bad HIP lot to crack first. Gas turbine engines Hot isostatic pressing Low cycle fatigue Turbine blades Nickel...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c0047645
EISBN: 978-1-62708-229-7
... of the welding torch were overhauled to ensure that leak-in or entrainment of air was eliminated. Also, the purity of the shielding-gas supplies was rechecked to make certain that these had not become contaminated. Contaminants Gas turbine engines Shielded arc welding Thermal stresses Ti-5Al-2.5Sn UNS...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0047072
EISBN: 978-1-62708-217-4
... Abstract Postflight inspection of a gas-turbine aircraft engine that had experienced compressor stall revealed that the engine air-intake bullet assembly had dislodged and was seated against the engine-inlet guide vanes at the 3 o'clock position. The bullet assembly consisted of an outer...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c0090114
EISBN: 978-1-62708-229-7
... applying the specially designed methods given in this case study to estimate the metal temperature and stresses in order to predict the life of turbine blades under similar operating conditions. Gas turbine engines Grain boundaries Stress and strain analysis Thermal stresses Turbine blades...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c0047681
EISBN: 978-1-62708-229-7
... current to reduce the temperature, by an increase in the electrode force, or both. Compressors Gas turbine engines Welding parameters Ti-6Al-4V UNS R56406 Joining-related failures Fatigue fracture A fluorescent liquid-penetrant inspection of an experimental stator vane of a first-stage...
Series: ASM Failure Analysis Case Histories
Volume: 3
Publisher: ASM International
Published: 01 December 2019
DOI: 10.31399/asm.fach.v03.c9001827
EISBN: 978-1-62708-241-9
... propulsion and the generation of electricity (marine gas turbines) [ 1 ]. The corrosion issues for industrial gas turbines are similar for all applications and depend more on the quality of the fuel and air used in the engine than on the specific industrial application. In the combustor and turbine...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0090030
EISBN: 978-1-62708-217-4
... Gas turbine engines Microcracking Phase transformations Rotors Titanium Fatigue fracture Brittle fracture In 1989, a United Airlines DC-10 in transit from Denver to Chicago experienced failure of the center engine. The titanium compressor disk burst and severed the hydraulics of the plane...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0047986
EISBN: 978-1-62708-217-4
... examination of circumferential section of the largest cavity, was exhibited by the second bearing. It was concluded that the fracture of the cage was caused by overheating and misalignment caused excessive stressing of the bearing on the main shaft. Bearing races Gas turbine engines Overheating...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c0047621
EISBN: 978-1-62708-229-7
..., and flange and more skillful welding techniques to avoid undercutting and unfused interfaces. Arc welding Combustion chamber Flanges Gas turbine engines Pipe fitting Undercuts Welding defects Inconel 718 (Nickel-base superalloy) UNS N07718 Fatigue fracture Joining-related failures...
Series: ASM Failure Analysis Case Histories
Volume: 3
Publisher: ASM International
Published: 01 December 2019
DOI: 10.31399/asm.fach.v03.c9001757
EISBN: 978-1-62708-241-9
.... , Saravanamutto H.I.H. : Gas Turbine Theory , 2nd edn. , pp. 111 – 119 . Longman , London ( 1981 ). 2. Huenecke K. : Fundamentals of theory, design and operation . In: Jet Engines , 4th edn. , pp. 110 – 114 . Motorbooks International , Osceola ( 2000 ). 3. Scherer R. : Blade...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003517
EISBN: 978-1-62708-180-1
... life of gas turbine blades depends on the time it requires to initiate engineering-size cracks, or irreparable loss of metal occurs by FOD or corrosion. Cracks may initiate due to the exhaustion of creep life (which may manifest in the form of numerous creep cavities at critical locations of a blade...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001028
EISBN: 978-1-62708-214-3
... fracture was caused by engine vibrations during operation of the aircraft. Fracture characteristics indicated that the fatigue would not have occurred if the initial damage had not taken place. Aerospace engines Engine components Gas turbine engines Lubrication systems Tanks Tearing 321 UNS...