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Image
Hot-corrosion attack of René 77 nickel-base alloy turbine blades. (a) A lan...
Available to PurchasePublished: 30 November 2013
Fig. 9 Hot-corrosion attack of René 77 nickel-base alloy turbine blades. (a) A land-based, first-stage turbine blade. Notice the deposit buildup and flaking and splitting of the leading edge. (b) Stationary vanes. (c) A land-based, first-stage gas turbine blade that had type 2 hot-corrosion
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Image
in Life-Assessment Techniques for Combustion Turbines
> Damage Mechanisms and Life Assessment of High-Temperature Components
Published: 01 December 1989
Image
Air-cooled combustion turbine blades ( Ref 5 ; original source, Westinghous...
Available to Purchase
in Life-Assessment Techniques for Combustion Turbines
> Damage Mechanisms and Life Assessment of High-Temperature Components
Published: 01 December 1989
Fig. 9.6. Air-cooled combustion turbine blades ( Ref 5 ; original source, Westinghouse Electric Corp.).
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Image
Macrostructure of three turbine blades: polycrystalline (left), columnar gr...
Available to PurchasePublished: 01 March 2002
Fig. 3.8 Macrostructure of three turbine blades: polycrystalline (left), columnar grain directionally solidified (center), and single crystal directionally solidified (right)
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Image
First-stage turbine blades of a wrought nickel-base superalloy showing crac...
Available to PurchasePublished: 01 March 2002
Fig. 14.12 First-stage turbine blades of a wrought nickel-base superalloy showing cracks (arrows) caused in the leading edge by TMF
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Image
in Common Causes of Failures
> Failure Analysis of Engineering Structures: Methodology and Case Histories
Published: 01 October 2005
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Suppression of fatigue damage of Inconel 713C turbine blades by shot peenin...
Available to Purchase
in Avoidance, Control, and Repair of Fatigue Damage[1]
> Fatigue and Durability of Structural Materials
Published: 01 March 2006
Fig. 11.63 Suppression of fatigue damage of Inconel 713C turbine blades by shot peening. Source: Ref 11.72
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Book Chapter
Failure of a Turbine Blade in an Aircraft Engine
Available to PurchaseSeries: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270087
EISBN: 978-1-62708-301-0
... Abstract A turbine blade in an aircraft engine failed, fracturing at the root above the fir tree region. Fractography indicated that a fatigue crack initiated at the trailing edge of the blade and the final fracture occurred when the crack reached critical length. Although the exact cause...
Abstract
A turbine blade in an aircraft engine failed, fracturing at the root above the fir tree region. Fractography indicated that a fatigue crack initiated at the trailing edge of the blade and the final fracture occurred when the crack reached critical length. Although the exact cause of crack initiation could not be established, material defects, improper root loading, and high operating temperatures were ruled out. This chapter describes how investigators came to their conclusions and what they learned through visual and SEM examination and qualitative elemental analysis. It includes images of the microstructure and fracture surfaces and explains what some of the details reveal about the failure.
Book Chapter
Failure of a Second-Stage Turbine Blade in an Aircraft Engine
Available to PurchaseSeries: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270135
EISBN: 978-1-62708-301-0
... Abstract A second-stage turbine blade in an aircraft engine failed in service, fracturing along a path through the shroud hole. Cracks were also found in the shroud holes of the two adjacent blades. Based on the results of visual examination and SEM fractography, investigators concluded...
Abstract
A second-stage turbine blade in an aircraft engine failed in service, fracturing along a path through the shroud hole. Cracks were also found in the shroud holes of the two adjacent blades. Based on the results of visual examination and SEM fractography, investigators concluded that the fracture and cracks were due to the fretting action of the pins inside the shroud holes.
Book Chapter
Failure of a High-Pressure Turbine Blade in an Aircraft Engine
Available to PurchaseSeries: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270138
EISBN: 978-1-62708-301-0
... Abstract A high-pressure turbine blade in an aircraft engine failed prematurely, fracturing close to the root. Visual examination revealed significant plastic deformation on the leading edge of the blade, blocky cleavage on the trailing edge, and a region covered with fissures in between. Based...
Abstract
A high-pressure turbine blade in an aircraft engine failed prematurely, fracturing close to the root. Visual examination revealed significant plastic deformation on the leading edge of the blade, blocky cleavage on the trailing edge, and a region covered with fissures in between. Based on their observations and the results of SEM imaging described in the chapter, investigators concluded that the blade failed by low-cycle fatigue, acting on a preexisting crack.
Image
Ashby deformation maps for MAR-M 200 ( Ref 14 ). A turbine blade will defor...
Available to PurchasePublished: 01 December 1989
Fig. 3.2. Ashby deformation maps for MAR-M 200 ( Ref 14 ). A turbine blade will deform rapidly by boundary diffusion at a grain size of 100 μ m (a) but not at a grain size of 1 cm (b).
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Published: 01 June 2010
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Investment-cast turbine blade with convex wall removed showing complex inte...
Available to PurchasePublished: 01 March 2002
Fig. 5.2 Investment-cast turbine blade with convex wall removed showing complex internal arrangement produced by the core standing alongside the blade
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Image
Polycrystalline cast hollow nickel-base turbine blade of simple cooling geo...
Available to PurchasePublished: 01 March 2002
Fig. 5.8 Polycrystalline cast hollow nickel-base turbine blade of simple cooling geometry shown with cross sections of some other cooling configurations
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Image
Published: 01 March 2002
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Location and relative size of test bar from same first-stage turbine blade ...
Available to PurchasePublished: 01 March 2002
Fig. 12.19 Location and relative size of test bar from same first-stage turbine blade as in Fig. 12.18
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Comparative impact data for turbine blade alloys as a function of temperatu...
Available to PurchasePublished: 01 March 2002
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Nimonic 100 nickel-base superalloy first-stage turbine blade from turboprop...
Available to PurchasePublished: 01 March 2002
Fig. 13.10 Nimonic 100 nickel-base superalloy first-stage turbine blade from turboprop engine showing deterioration from sulphidation-type hot corrosion
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Image
Published: 01 March 2002
Image
Leading edge of a Waspaloy nickel-base superalloy turbine blade showing int...
Available to PurchasePublished: 01 March 2002
Fig. 14.14 Leading edge of a Waspaloy nickel-base superalloy turbine blade showing intergranular oxidation attack
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