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MAR-M302

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Cracked first steps MAR-M302 Turbine engine vane in the as-received conditi...

in Metallurgical Investigation of a Turbine Blade and a Vane Failure from Two Marine Engines > ASM Failure Analysis Case Histories: Offshore, Shipbuilding, and Marine Equipment
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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The corroded and overload fracture features in the cracked MAR-M302 turbine...

in Metallurgical Investigation of a Turbine Blade and a Vane Failure from Two Marine Engines > ASM Failure Analysis Case Histories: Offshore, Shipbuilding, and Marine Equipment
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
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Coating degeneration and corrosion attack in MAR-M302 vane along the concav...

in Metallurgical Investigation of a Turbine Blade and a Vane Failure from Two Marine Engines > ASM Failure Analysis Case Histories: Offshore, Shipbuilding, and Marine Equipment
Published: 01 June 2019
Fig. 17 Coating degeneration and corrosion attack in MAR-M302 vane along the concave airfoil side. (a) Fine cracking; (b) Subsurface shrinkage porosity; (c) Corrosion product penetration in the subsurface porosity. More
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EDX analysis of the coating and corroded area of MAR-M302 vane. (a) Al and ...

in Metallurgical Investigation of a Turbine Blade and a Vane Failure from Two Marine Engines > ASM Failure Analysis Case Histories: Offshore, Shipbuilding, and Marine Equipment
Published: 01 June 2019
Fig. 18 EDX analysis of the coating and corroded area of MAR-M302 vane. (a) Al and S peaks observed in the coating; (b) Corroded fracture region showing Na, S, Al and Si peaks. More
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Etched microstructural features of the investment cast MAR-M302 vane. (a) E...

in Metallurgical Investigation of a Turbine Blade and a Vane Failure from Two Marine Engines > ASM Failure Analysis Case Histories: Offshore, Shipbuilding, and Marine Equipment
Published: 01 June 2019
Fig. 19 Etched microstructural features of the investment cast MAR-M302 vane. (a) Eutectic carbide pools and script-type carbides; (b) Coarse peppery secondary carbide in the background. More
Book Chapter

Metallurgical Investigation of a Turbine Blade and a Vane Failure from Two Marine Engines

By A. K. Koul, R. V. Dainty, C. Marchand
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...
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 of a systematic approach, analyzing the nature of degeneration and failure of the failed components, utilizing conventional metallurgical techniques, is presented. The topographical features of the turbine blade fracture surface revealed a fatigue-induced crack growth pattern, where crack initiation had taken place in the blade trailing edge. An estimate of the crack-growth rate for the stage II fatigue fracture region coupled with the metallographic results helped to identify the final mode of the turbine blade failure. A detailed metallographic and fractographic examination of the air-cooled vane revealed that coating erosion in conjunction with severe hot-corrosion was responsible for crack initiation in the leading edge area.