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gas turbines
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Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 November 2007
DOI: 10.31399/asm.tb.htcma.t52080249
EISBN: 978-1-62708-304-1
... Abstract This chapter examines the hot corrosion resistance of various nickel- and cobalt-base alloys in gas turbines susceptible to high-temperature (Type I) and low-temperature (Type II) hot corrosion. Type I hot corrosion is typically characterized by a thick, porous layer of oxides...
Abstract
This chapter examines the hot corrosion resistance of various nickel- and cobalt-base alloys in gas turbines susceptible to high-temperature (Type I) and low-temperature (Type II) hot corrosion. Type I hot corrosion is typically characterized by a thick, porous layer of oxides with the underlying alloy matrix depleted in chromium, followed (below) by internal chromium-rich sulfides. Type II hot corrosion is characterized by pitting with little or no internal attack underneath. As the chapter explains, chromium additions make alloys more resistant to all types of hot corrosion attacks.
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Published: 01 March 2002
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in Cold Spray Applications in Repair and Refurbishment for the Aerospace, Oil and Gas, and Power-Generation Industries
> High Pressure Cold Spray: Principles and Applications
Published: 01 June 2016
Fig. 11.19 Inconel 738LC cold spray coatings for gas turbine repair. (a) Nitrogen vs. helium in the as-sprayed condition. (b) Nitrogen coatings before and after heat treatment, revealing (c) decrease in porosity, (d) increase in strength and ductility, (e) increase in bond adhesion strength
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in Deformation and Fracture Mechanisms and Static Strength of Metals
> Mechanics and Mechanisms of Fracture: An Introduction
Published: 01 August 2005
Fig. 2.99 Intergranular cracks in a gas turbine disk made of 2014-6 aluminum. Note crack initiation at a corrosion pit (or pits) and branching along grain boundaries, typical of stress-corrosion failure. Source: Ref 2.73
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Published: 01 October 2012
Fig. 5.29 Complex investment-cast titanium components used for gas turbine applications. Source: Ref 5.14
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Published: 01 October 2012
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Published: 01 March 2002
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Published: 01 March 2002
Fig. 2.5 Schematic of gas turbine engine showing principal sections and the general operating temperatures related to section position
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Published: 01 March 2002
Fig. 5.11 Investment-cast gas turbine engine. (a) Polycrystalline integral nozzles, and (b) integral rotors
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Published: 01 March 2002
Fig. 6.24 Potential components for gas turbine applications, superplastically formed of IN-718. Noise suppressor assembly (top) and exhaust mixer nozzle component (bottom)
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Published: 01 March 2002
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Published: 01 March 2002
Fig. 7.1 Possible processing sequences for a gas turbine compressor disk illustrating the input weight reductions possible with P/M superalloy technology
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Published: 01 March 2002
Fig. 9.19 Welding information on Waspaloy nickel-base superalloy gas turbine shroud Joint type Butt Weld type Square-groove Welding process Automatic GTAW Power supply 200 to 300 A transformer-rectifier, constant current Torch Mechanical, water cooled Electrode
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Published: 01 March 2002
Fig. 14.9 Engine-operated aircraft gas turbine combustion chamber showing metal loss and degradation, owing to oxidation
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Published: 01 November 2007
Fig. 4.10 The dynamic burner rig used by Lai ( Ref 36 ) for simulating a gas turbine combustion environment in evaluating the oxidation/nitridation behavior of gas turbine combustor alloys. Courtesy of Haynes International, Inc.
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in Melting, Casting, and Powder Metallurgy[1]
> Titanium: Physical Metallurgy, Processing, and Applications
Published: 01 January 2015
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Published: 01 December 2000
Fig. 2.6 Typical titanium alloy casting for aircraft gas turbine use. Courtesy of Precision Castparts Corp.
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Published: 01 December 2000
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Published: 01 December 2000
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in Life-Assessment Techniques for Combustion Turbines
> Damage Mechanisms and Life Assessment of High-Temperature Components
Published: 01 December 1989
Fig. 9.2. Past and future trends of heavy-duty gas-turbine firing temperatures and corresponding blade-material developments ( Ref 4 and 5 ).
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