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gas turbine
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Series: ASM Handbook
Volume: 18
Publisher: ASM International
Published: 31 December 2017
DOI: 10.31399/asm.hb.v18.a0006428
EISBN: 978-1-62708-192-4
... Abstract This article illustrates typical wear and friction issues encountered in gas and steam turbines and their consequences as well as commonly adopted materials solutions. It contains tables that present the summary of wear and friction related issues encountered in steam turbines and gas...
Abstract
This article illustrates typical wear and friction issues encountered in gas and steam turbines and their consequences as well as commonly adopted materials solutions. It contains tables that present the summary of wear and friction related issues encountered in steam turbines and gas turbines. The article outlines the differences in the operating conditions and the nature of the components involved in gas and steam turbines. It discusses the constraints and applicable coating solutions for wear and friction issues, and concludes with a broad set of challenges that need to be addressed to improve performance and operability of gas and steam turbines.
Book: Thermal Spray Technology
Series: ASM Handbook
Volume: 5A
Publisher: ASM International
Published: 01 August 2013
DOI: 10.31399/asm.hb.v05a.a0005737
EISBN: 978-1-62708-171-9
... Abstract This article provides an overview of key thermal spray coatings used in compressors, combustors, and turbine sections of a power-generation gas turbine. It describes the critical components, including combustors, transition ducts, inlet nozzle guide vanes, and first-stage rotating...
Abstract
This article provides an overview of key thermal spray coatings used in compressors, combustors, and turbine sections of a power-generation gas turbine. It describes the critical components, including combustors, transition ducts, inlet nozzle guide vanes, and first-stage rotating airfoils. Design requirements are reviewed and compared between aerospace and power generation coatings. Application process improvement areas are also discussed as a method of reducing component cost.
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Published: 01 August 2013
Fig. 7 Temperature profile through gas turbine ngine. Gas temperatures exceed melting point of structural materials. LPC, low-pressure compressor; HPC, high-pressure compressor; HPT, high-pressure turbine; LPT, low-pressure turbine
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Published: 01 August 2013
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in Directionally Solidified and Single-Crystal Superalloys
> Properties and Selection: Irons, Steels, and High-Performance Alloys
Published: 01 January 1990
Fig. 24 Dynamic oxidation, 1177 °C (2150 °F), cyclic. Source: Allison Gas Turbine Division, General Motors Corporation
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in Titanium and Titanium Alloy Castings
> Properties and Selection: Nonferrous Alloys and Special-Purpose Materials
Published: 01 January 1990
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Published: 01 January 2006
Fig. 27 High-temperature oxidation of the tip of an industrial gas turbine blade. Below the tip, a coating is protecting the base metal. See the article “Corrosion of Industrial Gas Turbines” in this Volume.
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Published: 01 January 2006
Fig. 28 Severe attack of an aeroderivative gas turbine blade by hot corrosion. See the article “Corrosion of Industrial Gas Turbines” in this Volume.
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Published: 01 January 2006
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Published: 01 January 2006
Fig. 2 Titanium alloy gas-turbine ring that was produced by compression forming. Dimensions given in inches
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Published: 01 December 2008
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Published: 01 January 1997
Fig. 8 Gas turbine engine and components. Scroll and rotor are made from structural ceramics. Courtesy of Allison Engine Company
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Published: 01 November 1995
Fig. 18 Duty cycles and lifetime requirements for different types of gas turbine engines. Lifetime is given in hours.
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Published: 01 November 1995
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Published: 31 December 2017
Fig. 1 (a) Schematic illustration of a gas turbine with key components and examples of wear. Source: Ref 2 , 3 , 4 . (b) Fretting damage location on dovetail joint, Courtesy of Lambda Technologies Group. (c) Microcracks on dovetail joint, Courtesy of Lambda Technologies Group. (d) Droplet
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Published: 31 December 2017
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Published: 01 January 1993
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Published: 01 January 1987
Fig. 835 Segment of a fractured second-stage gas-turbine wheel, cast from alloy 713C, that broke from fatigue in service. (About half of the disk portion of the wheel was never recovered.) The fracture origin (at arrow) was in a grinding-relief groove adjacent to the wheel-balancing pad
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Published: 30 August 2021
Fig. 1 Failed gas turbine rotor. From left to right: first-, second-, and third-stage turbine blades. The failure originated in the second stage; fragments