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Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c0046966
EISBN: 978-1-62708-229-7
...Abstract Abstract A turbine vane made of cast cobalt-base alloy AMS 5382 (Stellite 31; composition: Co-25.5Cr-10.5Ni-7.5W) was returned from service after an undetermined number of service hours because of crack indications on the airfoil sections. This alloy is cast by the precision investment...
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
.... The cooling holes' surface was not coated. Investigation supported the conclusions that the cracking at the cooling holes was due to grain-boundary oxidation and nitridation at the cooling hole surface, embrittlement and loss of local ductility of the base alloy, temperature gradient from the airfoil surface...
Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001366
EISBN: 978-1-62708-215-0
...Abstract Abstract An AMS 4126 (7075-T6) aluminum alloy impeller from a radial inflow turbine fractured during commissioning. Initial examination showed that two adjacent vanes had fractured through airfoils in the vicinity of the vane leading edges, and one vane fractured through an airfoil...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c0091761
EISBN: 978-1-62708-229-7
... after 2500 to 6400 h of operation. Investigation (visual inspection, metallographic examination, and stress analysis) supported the conclusion that the differing microstructure of the airfoil resulted in changes in mechanical properties. Because normal operation includes cycling of loads...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0047720
EISBN: 978-1-62708-217-4
...Abstract Abstract Airfoil-shape impingement cooling tubes were fabricated of 0.25 mm (0.010 in.) thick Hastelloy X sheet stock, then pulse-laser-beam butt welded to cast Hastelloy X base plugs. Each weldment was then inserted through the base of a hollow cast turbine blade for a jet engine...
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
...Abstract Abstract This article describes the visual, fractographic, and metallographic evidence typically encountered when analyzing stress rupture of turbine airfoils. Stress-rupture fractures are generally heavily oxidized, tend to be rough in texture, and are primarily intergranular...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001024
EISBN: 978-1-62708-214-3
..., hollow 6061-T651 aluminum alloy extrusion and 26 fiberglass “pockets” that provided the trailing-edge airfoil shape. Visual examination of the fracture surface of the aluminum extrusion indicated fatigue crack growth followed by ductile overload separation. Examination of the fatigue fracture region...
Series: ASM Handbook
Volume: 11A
Publisher: ASM International
Published: 30 August 2021
DOI: 10.31399/asm.hb.v11A.a0006824
EISBN: 978-1-62708-329-4
.... In cases where material is released in the turbine flow path, such as a broken airfoil, downstream components typically suffer secondary damage, and so the first component to fail is typically at the upstream end of the damaged zone ( Fig. 1 ). Fig. 1 Failed gas turbine rotor. From left to right...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.marine.c9001657
EISBN: 978-1-62708-227-3
... a turbine blade disintegration and another one concerning a vane failure. Examination of the second stage turbine rotor blades of the first engine (no. 1), revealed that the majority of the blade tips were ripped off. One exception to this was a blade with most of its airfoil section removed...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c9001602
EISBN: 978-1-62708-229-7
... suffered tip shroud fracture, illustrated in Fig. 1 . Details of the fracture zone from the concave side of the airfoil are shown in Fig. 2 . Fig. 1 The 37.5 mW gas turbine third stage bucket tip shroud fracture Fig. 2 Details of the tip shroud fracture zone The buckets...
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
... as the gradual deterioration and eventual cracking of a material by alternating heating and cooling, during which free thermal expansion is partially or fully constrained. The constraint of a part or material does not allow free expansion to occur. For example, thermal strains are generated in the airfoils...
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
... ). The area with the highest density of cavities was LE (60–90% span). The airfoil surface was very rough and the bottoms of the cavities had a greenish appearance ( Fig. 4 ). In [ reference 4 ], it is reported that a greenish color is a macroscopic feature of HTHC. The visual observation suggested hot...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.marine.c0046969
EISBN: 978-1-62708-227-3
... The airfoils of the uncoated blades exhibited splitting along the leading edges and swelling on the surfaces, indicating severe hot corrosion ( Fig. 1a ). Metallographic examination of an uncoated blade confirmed hot-corrosion damage by revealing the characteristic sulfidation-oxidation attack of the base...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0046972
EISBN: 978-1-62708-217-4
... that of the base metal. It was also determined that directionally solidified blades could minimize thermal fatigue cracking by eliminating intersection of grain boundaries with the surface. However, this improvement would be more costly than applying a protective coating. Airfoils Turbine blades Superalloy...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003521
EISBN: 978-1-62708-180-1
.... It is also very useful to examine the failed component in undamaged areas. For example, turbine blade roots in steam turbines are not exposed to service environment steam and temperature as airfoils are. Comparison of properties between the root and airfoil can provide useful information about service...
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006756
EISBN: 978-1-62708-295-2
... to the same service environment steam and temperature as are the airfoils. Comparing properties from the root and airfoil can provide useful information about service degradation of the exposed airfoils and identify damage characteristics. One of the most important clues in identifying damage mechanisms...
Series: ASM Handbook
Volume: 11A
Publisher: ASM International
Published: 30 August 2021
DOI: 10.31399/asm.hb.v11A.a0006815
EISBN: 978-1-62708-329-4
... to the drawing on a napkin. Only enough engineering analysis is done at this stage to determine what likely could be made to work and what likely could not. The aerodynamics engineers define the flowpath and the airfoil geometries. The mechanical engineers commit that definition into metal and then determine...
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
... G.W. : Progress in coating for gas turbine airfoils . Surf. Coat. Technol . 108–109 , 73 – 79 ( 1998 ) 10.1016/S0257-8972(98)00667-7 2. Tolpygo V.K. , Clarke D.R. : Rumpling induced by thermal cycling of an overlay coating: the effect of coating thickness . Acta Mater . 52...
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
... Vibration and Failures in Gas Turbines, Part B: Compressor and Turbine Airfoil Distress ,” Paper 95-GT-419, American Society of Mechanical Engineers , New York , 1995 10.1115/95-GT-419 95. Kolagar A.M. , Tabrizi N. , Cheraghzadeh M. , and Shahriaari M.S. , Failure Analysis...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003555
EISBN: 978-1-62708-180-1