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compressor blades

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Published: 01 August 2013
Fig. 13 High-pressure compressor blades coated with physical vapor deposition process for improved wear resistance. Source: Ref 22 More
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Published: 01 January 2005
Fig. 3 Wrought gamma titanium products. (a) Compressor blades. (b) Subscale isothermally forged disk. (a) and (b) Source: D.U. Furrer, Ladish Company. (c) Large, conventionally (pack) rolled sheet. Source: Battelle Memorial Institute, Air Force Research Laboratory More
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Published: 30 August 2021
Fig. 15 Solid-particle-erosion-damaged compressor blades (titanium alloy) from flight service. The white dashed lines indicate the approximate original contour of the airfoils. The leading edges are facing left, as shown. Note the greater extent of material loss at the trailing edges, where More
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Published: 01 January 1990
Fig. 9 1000-h creep rupture strength of turbine rotor and compressor blade alloys. Source: Ref 14 More
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Published: 01 January 1990
Fig. 10 Yield strength at 0.2% offset of five candidate compressor blade alloys compared with that of 12Cr-0.6Mo steel. Source: Ref 14 More
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Published: 01 January 2002
Fig. 29 Compressor blade fracture surface showing fatigue origins on low pressure (i.e., right) side of blade, as indicated by the arrows. 13× More
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Published: 01 January 1993
Fig. 33 Brazing design for a titanium compressor blade with an additional mechanical fixture More
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Published: 15 January 2021
Fig. 22 Compressor blade fracture surface showing fatigue origins on low-pressure (i.e., right) side of blade, as indicated by the arrows. Original magnification: 13 × More
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Published: 30 August 2021
Fig. 9 Campbell diagram for a compressor blade showing various vibrational-mode frequencies of the blade (horizontal lines) and the frequency-versus-speed curve for wakes created by the upstream stationary vanes (black diagonal line). TE, trailing edge More
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Published: 30 August 2021
Fig. 26 (a) Photograph of fractured compressor blade. (b) Scanning electron fractograph showing fracture-initiation region. A band with a pronounced oxide scale was observed at the surface (arrows). (c) Optical micrograph of a cross section of the fracture in the initiation region. Original More
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Published: 01 January 2002
Fig. 28 Failed compressor rotor. Arrows indicate fractured portions of blades. 36× More
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Published: 15 January 2021
Fig. 21 Failed compressor rotor. Arrows indicate fractured portions of blades. Original magnification: 36 × More
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Published: 01 January 2006
Fig. 7 Corrosion pits exceeding allowable limits in the root section of a compressor blade More
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Published: 01 January 1994
Fig. 12 Relation of nozzle angle, angle of load face, and resulting angle of impingement in peening root serrations of compressor blades. Angle of impingement, 83° More
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Published: 01 January 2005
Fig. 10 Highly configured (twisted) alloy Ti-6Al-4V and alloy Ti-8Al-1Mo-1V turbine engine fan and compressor blades that were forged in screw presses More
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
... 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. aerospace engines combustors gas turbines high-power turbine blades high-pressure compressors...
Series: ASM Handbook
Volume: 13C
Publisher: ASM International
Published: 01 January 2006
DOI: 10.31399/asm.hb.v13c.a0004158
EISBN: 978-1-62708-184-9
... environmental attack in the form of high-temperature oxidation and hot corrosion are the most important. Corrosion in the Compressor Section Compressor blades and vanes are usually made from martensitic or precipitation-hardening stainless steels and can either be coated or bare. Compressor disks...
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
... of compressor and turbine blades ( Ref 1 ). Creep failure of turbine blades, mostly related to issues with cooling, was found to be the second-most costly damage mode. The failure of rotating components tends to be more costly because their significant kinetic energy results in greater collateral damage...
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
... filters past the struts and inlet guide vane (IGV) into a high-pressure compressor ( Ref 1 ). The compressor broadly consists of alternating stages of compressor blades and vanes which decrease in size as one goes from front to aft stages. The blades are attached to a rotor in the form of blade or bucket...
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Published: 01 August 2013
Fig. 9 Overview of abradable coating materials and their designated hardness (HR15Y) specified ranges according to blade material type compatibility and for different service temperature regimes. RT, room temperature; LPC, low-pressure compressor; HPC, high-pressure compressor; HPT, high More