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Turbine vanes

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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 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 method...
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Published: 01 June 2019
Fig. 12 The cracked turbine vane fracture surface (lightly shaded area is the lab induced overload region). More
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Published: 01 June 2019
Fig. 14 Turbine vane erosion in the leading and the trailing edge areas. (a) Leading edge; (b) Trailing edge. Arrows indicating severe corrosion. More
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Published: 01 June 2019
Fig. 1 Airfoil segment from a cast Stellite 31 turbine vane that failed by thermal fatigue. (a) and (b) Thermal fatigue cracks emanating from a leading edge and progressing along grain boundaries. The microstructure shows evidence of age hardening by intragranular precipitation of carbide More
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Published: 01 January 2002
Fig. 1 Creep damage (bowing) of a cobalt-base alloy turbine vane from overheating More
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Published: 01 January 2002
Fig. 2 Creep crack in a turbine vane. Courtesy of Mohan Chaudhari, Columbus Metallurgical Services More
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Published: 15 January 2021
Fig. 1 Creep damage (bowing) of a cobalt-base alloy turbine vane from overheating More
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Published: 15 January 2021
Fig. 2 Creep crack in a turbine vane. Courtesy of M. Chaudhari, Columbus Metallurgical Services More
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Published: 30 August 2021
Fig. 7 (a) Photograph of turbine vane. (b) Photograph showing axial cracking at midheight of leading edge. (c) Composite optical micrograph showing leading-edge crack in cross section. Etched with Marble’s reagent. Original magnification: 100×. (d) Scanning electron micrographs showing gamma More
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Published: 30 August 2021
Fig. 22 (a) Photograph of stage 1 turbine blade. Material loss was most severe at the tip and trailing-edge airfoil. (b) Photograph of second-stage turbine vane. Note the rounded discoloration patterns, material loss at the trailing edge, and airfoil perforation (arrow). (c) Optical micrograph More
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
... Abstract The circumstances surrounding the in-service failure of a cast Ni-base superalloy (Alloy 713LC) second stage turbine blade and a cast and coated Co-base superalloy (MAR-M302) first stage air-cooled vane in two turbine engines used for marine application are described. An overview...
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Published: 30 August 2021
Fig. 6 Illustration of how cycling of the gas turbine generates thermal-mechanical fatigue cracking of a turbine vane More
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Published: 01 June 2019
Fig. 15 The corroded and overload fracture features in the cracked MAR-M302 turbine vane. (a) Transition of corroded region ‘C’ and the laboratory induced overload region ‘O’; (b) Corroded area adjacent to overload region; (c) Laboratory induced overload area with cleavage and ductile dimples. More
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
... components. Stationary components such as combustors and turbine vanes can develop creep deformation (deflection, distortion), which can lead to decreased turbine performance and increased component degradation, although catastrophic creep failures of such components are rare. Turbine blades residing...
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 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 near the hub...
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...
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Published: 01 June 2019
Fig. 2 Cracked first steps MAR-M302 Turbine engine vane in the as-received condition. (a) Concave airfoil surface; (b) Convex airfoil surface. Metallographic sampling location indicated by arrow M. More
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Published: 30 August 2021
Fig. 20 (a) Photograph of first-stage vane ring following removal from the turbine. (b) Photograph of a vane following removal from the vane ring. (c) Optical micrograph of remnant thermal barrier coating from a hot (white) region. (d) Detail of coating interface from (c). Note the fragment More
Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001358
EISBN: 978-1-62708-215-0
... Abstract Several compressor diaphragms from five gas turbines cracked after a short time in service. The vanes were constructed of type 403 stainless steel, and welding was performed using type 309L austenitic stainless steel filler metal. The fractures originated in the weld heat-affected...
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
... and the air can lead to deposition of alkali metal sulfates on the blade or vane surfaces, resulting in hot corrosion attack [ 2 ]. Overview of Gas Turbine Engine Hot Parts The areas of the gas turbine where the temperature is the highest and which are therefore, most subject to high-temperature...