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Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270191
EISBN: 978-1-62708-301-0
... tripped following the failure of the turbine rotor. The damage was maximum in the 18th/19th-stage seal land region of the compressor, with the 19th-stage blades sheared off. Metallurgical investigations were carried out on the roots and airfoil sections of the damaged blades. The blade roots had suffered...
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Published: 30 November 2013
Fig. 11 First-stage compressor blades that fractured due to corrosion fatigue originating in corrosion pits like those shown in Fig. 10 . Note that (a) had one fatigue origin (arrow) on the mid-pressure side (5×; shown at 70%). Arrows in (b) show fatigue origins on both the suction More
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270141
EISBN: 978-1-62708-301-0
...Abstract Abstract A compressor blade made of titanium alloy fractured during an engine test. The material and processing conditions of the blade were found to be satisfactory, turning the focus of the investigation to operating anomalies and human error. A photograph of the failed blade shows...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270150
EISBN: 978-1-62708-301-0
...Abstract Abstract This chapter discusses the failure of a compressor blade in an aircraft engine and explains how investigators determined the cause. Based on visual examination and the results of SEM fractography and chemical analysis, it was concluded that blade failed due to fatigue fracture...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270118
EISBN: 978-1-62708-301-0
...Abstract Abstract A first-stage compressor blade failed prematurely in an aircraft engine, fracturing at the midpoint of the root transition region. An examination of the fracture surface revealed beach marks, striations, and pitting, indicating that the blade failed by fatigue due to a crack...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270128
EISBN: 978-1-62708-301-0
...Abstract Abstract This chapter discusses the failure of a first-stage compressor blade in an aircraft engine and explains how investigators determined that it was caused by fatigue, with a crack originating from corrosion pits that developed in the root transition region on the convex side...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270133
EISBN: 978-1-62708-301-0
...Abstract Abstract A second-stage compressor blade in an aircraft engine fractured after 21 h of service. The remaining portion of the blade was removed and examined as were several adjacent blades. Based on the results of SEM fractography, microstructural analysis, and hardness testing...
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Published: 01 November 2012
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×. Source: Ref 1 More
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Published: 01 December 2000
Fig. 7.5 Cold isostatically pressed-plus-sintered compressor blade preform and final part forged from preform. At left, a preform; at right, finished part. Courtesy of Imperial Clevite Technology Center More
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Published: 01 January 2015
Fig. 10.2 Fan blades, compressor discs, and many other engine components use forged titanium parts. More
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Published: 01 January 2000
Fig. 43 Fretting corrosion on the root surface of an aircraft power plant compressor blade. Fatigue cracks can initiate as a result of this fretting pitting damage. More
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Published: 30 November 2013
Fig. 5 Example of well-formed striations in a forged high-pressure compressor blade made of titanium alloy. The striation density is approximately 30,000 striations/in. (~3.3 × 10 –5 in./striation). The arrow denotes the crack propagation direction. More
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Published: 30 April 2020
compressor blade fabricated by ink jet printing. (j) Tool steel compaction punch formed by slurry casting. Courtesy of J. Thomas. (k) Radiation-absorption tungsten sheet fabricated by tape casting. Courtesy of T. Puzz More
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.9781627083010
EISBN: 978-1-62708-301-0
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270115
EISBN: 978-1-62708-301-0
...Abstract Abstract Two compressor rotors of similar design and construction were severely damaged during operation. In one rotor, all the blades in the third and fourth stages had been sheared off and some had lifted from the dovetail portion of the drum. The damage in the other rotor was more...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270005
EISBN: 978-1-62708-301-0
...: Failure of Titanium Alloy Compressor Blades Compressor blades made of an alpha-beta titanium alloy (IMI 550, Ti-4Al-2Sn-4Mo) during routine vibratory fatigue testing were found to have unusually low fatigue life. The reason for this was not immediately apparent. The fatigue cracks were associated...
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Published: 01 March 2002
Fig. 15.1 Temperature-strength capability of selected superalloys as a function of year of availability (about 1945–1970). (a) Compressor and turbine disks, (b) burner cans and combustors, (c) turbine vanes, and (d) turbine blades More
Series: ASM Technical Books
Publisher: ASM International
Published: 01 January 2015
DOI: 10.31399/asm.tb.tpmpa.t54480353
EISBN: 978-1-62708-318-8
... duct Ti-5Al-2.5Sn 8Al-1Mo-1V Al alloy Fan duet fairings Ti (b) 5Al-2.5Sn Al alloy Front compressor blades 8Al-1Mo-1V 6Al-4V, 6Al-6V-2Sn 12Cr steel Front compressor, disk 8Al-1Mo-1V 6Al-4V, 6Al-6V-2Sn Low-alloy steel, 12Cr Multistage disk 6Al-2Mo-4Zr-2Sn 6Al-4V None Front...
Series: ASM Technical Books
Publisher: ASM International
Published: 01 November 2010
DOI: 10.31399/asm.tb.sap.t53000009
EISBN: 978-1-62708-313-3
... of total wrought superalloy production worldwide ( Ref 3 ). It is used in aircraft GTE components such as the compressor and turbine discs, casings, compressor blades, and fasteners. Some alloys may contain combined aluminum, titanium, and niobium, which could result in dual strengthening by γ′ and γ...
Book Chapter

Series: ASM Technical Books
Publisher: ASM International
Published: 01 November 2010
DOI: 10.31399/asm.tb.sap.t53000001
EISBN: 978-1-62708-313-3
... design and Curtis’s working models had a common flaw, which was that the compressor required more power than the turbine could produce, therefore making them mechanical curiosities rather than useful devices. The first self-sustaining GTE, unveiled in Paris in 1903, consisted of a three-cylinder...