Skip Nav Destination
Close Modal
Search Results for
fatigue crack growth rates
Update search
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
NARROW
Format
Topics
Book Series
Date
Availability
1-20 of 226 Search Results for
fatigue crack growth rates
Follow your search
Access your saved searches in your account
Would you like to receive an alert when new items match your search?
1
Sort by
Image
in Elevated-Temperature Life Assessment for Turbine Components, Piping, and Tubing
> Failure Analysis and Prevention
Published: 01 January 2002
Fig. 39 (a) Comparison of creep-fatigue crack growth rates with fatigue crack growth plotted as a function of Δ K . (b) The effect of hold time estimated for engineering structures when the creep crack growth rate is plotted as a function of ( C t ) avg
More
Image
in An Investigative Analysis of the Properties of Severely Segregated A441 Bridge Steel
> ASM Failure Analysis Case Histories: Buildings, Bridges, and Infrastructure
Published: 01 June 2019
Fig. 8 Fatigue crack growth rates through the segregated region compared to known growth rate values.
More
Image
in Elevated-Temperature Life Assessment for Turbine Components, Piping, and Tubing
> Failure Analysis and Prevention
Published: 01 January 2002
Fig. 3 Variation of the fatigue crack growth rate as a function of temperature. (a) Temperature effect on fatigue crack threshold and growth rates. (b) Variation of fatigue crack growth rates at Δ K of 30 MPa m (27 ksi in. )
More
Image
Published: 01 January 2002
Fig. 6 Schematic illustration of variation of fatigue-crack-growth rate, da / dN , with alternating stress intensity, Δ K , in steels, showing regions of primary crack-growth mechanisms. Source: Ref 5
More
Image
in Thermomechanical Fatigue: Mechanisms and Practical Life Analysis
> Failure Analysis and Prevention
Published: 01 January 2002
Fig. 13 Effect of hold time on the fatigue crack growth rate properties of 2.25Cr-1Mo cast steel. The 2 h hold time tests were performed in steam at 538 °C (100 °F). Source: Ref 13
More
Image
Published: 15 January 2021
Fig. 12 Schematic illustration of variation of fatigue crack-growth rate, da / dN , with alternating stress intensity, Δ K , in steels, showing regions of primary crack-growth mechanisms. Source: Ref 13
More
Image
in Thermomechanical Fatigue—Mechanisms and Practical Life Analysis
> Failure Analysis and Prevention
Published: 15 January 2021
Fig. 17 Effect of hold time on the fatigue crack growth rate properties of 2.25Cr-1Mo cast steel. The 2 h hold time tests were performed in steam at 538 °C (1000 °F). Source: Ref 28
More
Image
in Brittle Fracture of the Tension Flange of a Steel Box-Girder Bridge
> Handbook of Case Histories in Failure Analysis
Published: 01 December 1992
Fig. 18 Log-log da/dN versus delta K fatigue crack growth-rate test results for 310 MPa (45 ksi) maximum stress and stress ratio of 0.73. The scatterband (two parallel lines) is for quenched and tempered martensitic steels from NCHRP 12–14. Note that the A517 grade, F, plate D, test results
More
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.bldgs.c9001135
EISBN: 978-1-62708-219-8
... higher than specified by the ASTM standards. The fatigue crack growth rate through this area was much faster than expected. All of these property changes resulted from increased carbon levels, higher yield strength, and larger than normal grain size. Bridges (structural) Grain size Segregation...
Abstract
In 1979, during a routine bridge inspection, a fatigue crack was discovered in the top flange plate of one tie girder in a tied arch bridge crossing the Mississippi River. Metallographic analysis indicated a banding or segregation problem in the middle of the plate, where the carbon content was twice what it should have been. Based on this and results of ultrasonic testing, which revealed that the banding occurred in 24-ft lengths, it was decided to close the bridge and replace the defective steel. The steel used in the construction of this bridge was specified as ASTM A441, commonly used in structural applications. Testing showed an increase in hardness and weight percent carbon and manganese in the banded region. Further testing revealed that the area containing the segregation and coarse grain structure had a lower than expected toughness and a transition temperature 90 deg F higher than specified by the ASTM standards. The fatigue crack growth rate through this area was much faster than expected. All of these property changes resulted from increased carbon levels, higher yield strength, and larger than normal grain size.
Image
in Failure Analysis and Life Assessment of Structural Components and Equipment
> Failure Analysis and Prevention
Published: 01 January 2002
Fig. 9 Fractographic evaluation of multiple-site fatigue damage in a lower wing skin. The evaluation determined that the damage was caused by abusive machining marks that accelerated the fatigue crack growth rate. (a) Location of cracks in the a lower wing skin pocket. (b) Machine marks
More
Image
in Failure Prevention through Life Assessment of Structural Components and Equipment
> Analysis and Prevention of Component and Equipment Failures
Published: 30 August 2021
Fig. 9 Fractographic evaluation of multiple-site fatigue damage in a lower wing skin. The evaluation determined that the damage was caused by abusive machining marks that had accelerated the fatigue crack growth rate. (a) Location of cracks in the lower wing skin pocket. (b) Machine marks
More
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003539
EISBN: 978-1-62708-180-1
... in fatigue is macroscopically flat. This region is generally transverse to the direction of cyclic or fluctuating tensile stress that caused fatigue. However, at high loads/high fatigue crack growth rates in relatively thin components made of relatively tough material, a transition to propagation on a slant...
Abstract
This article commences with a summary of fatigue processes and mechanisms. It focuses on fractography of fatigue. Characteristic fatigue fracture features that can be discerned visually or under low magnification are described. Typical microscopic features observed on structural metals are presented subsequently, followed by a brief discussion of fatigue in nonmetals. The article reviews the various macroscopic and microscopic features to characterize the history and growth rate of fatigue in metals. It concludes with a description of fatigue of polymers and composites.
Image
Published: 15 January 2021
between two grains. da / dN , fatigue crack growth rate. (c) Cleavage striations superimposed on rivers during cyclic crack growth. Source: Ref 29
More
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006776
EISBN: 978-1-62708-295-2
... that caused fatigue. However, at high loads/high fatigue crack growth rates in relatively thin components made of relatively tough material, a transition to propagation on a slant plane can occur ( Fig. 12 ). Macroscopically, fatigue fracture ordinarily has a brittle appearance and lacks the gross plastic...
Abstract
Fatigue failure of engineering components and structures results from progressive fracture caused by cyclic or fluctuating loads. Fatigue is an important potential cause of mechanical failure, because most engineering components or structures are or can be subjected to cyclic loads during their lifetime. This article focuses on fractography of fatigue. It provides an abbreviated summary of fatigue processes and mechanisms: fatigue crack initiation, fatigue crack propagation, and final fracture,. Characteristic fatigue fracture features that can be discerned visually or under low magnification are then described. Typical microscopic features observed on structural metals are presented subsequently, followed by a brief discussion on fatigue in polymers and polymer-matrix composites.
Image
Published: 15 January 2021
Fig. 53 Fatigue striations in a vanadium high-strength, low-alloy steel. (a) Longitudinal-transverse orientation; stress-intensity range (Δ K ) = 32.3 to 34.3 M P a m (29.4 to 31.2 ksi in .); and fatigue crack growth rate ( da / dN ) = 3.3 to 3.8 × 10 −5 cm/cycle. (b
More
Image
Published: 15 January 2021
Fig. 47 Scanning electron micrographs of the fracture surfaces of Inconel 718 specimens tested at room temperature. (a) Stress-intensity range (Δ K ) = 30 M P a m (27 ksi in .); striation spacing = ∼0.2 μm; and fatigue crack growth rate ( da / dN ) = ~0.1 μm/cycle. Arrow
More
Book Chapter
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003544
EISBN: 978-1-62708-180-1
... these topics in more detail. Fatigue Crack Growth Rates The limitation of the S - N and ε- N methods is the inability of the controlling quantities to make sense of the presence of a crack. In traditional stress analysis of applied loads, basic elasticity calculations show that both stress and strain...
Abstract
This article describes three design-life methods or philosophies of fatigue, namely, infinite-life, finite-life, and damage tolerant. It outlines the three stages in the process of fatigue fracture: the initial fatigue damage leading to crack initiation, progressive cyclic growth of crack, and the sudden fracture of the remaining cross section. The article discusses the effects of loading and stress distribution on fatigue cracks, and reviews the fatigue behavior of materials when subjected to different loading conditions such as bending and loading. The article examines the effects of load frequency and temperature, material condition, and manufacturing practices on fatigue strength. It provides information on subsurface discontinuities, including gas porosity, inclusions, and internal bursts as well as on corrosion fatigue testing to measure rates of fatigue-crack propagation in different environments. The article concludes with a discussion on rolling-contact fatigue, macropitting, micropitting, and subcase fatigue.
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001144
EISBN: 978-1-62708-217-4
... is useful for analysing crack growth rates, the presence of random loading makes the process much more difficult ( 1 , 2 , 3 ). Fig. 3 Fatigue striations from random loading on fracture surface of failed spar. (638× approx.). The fatigue crack progressed approximately 5.6 mm in a uniform mode...
Abstract
A helicopter was hovering approximately 10 ft above a ship when one spar section failed explosively. Visual inspection revealed a crack had progressed through one member of a dual spar plate assembly at a fold pin lug hole. The remaining spar plate carried the blade load until the aircraft was landed. The helicopter main rotor blade spar fracture was analyzed by conventional and advanced computerized fractographic techniques. Digital fractographic Imaging Analysis of theoretical and actual fracture surfaces was applied for automatic detection of fatigue striation spacing. The approach offered a means of quantification of fracture features, providing for objective fractography.
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.marine.c9001657
EISBN: 978-1-62708-227-3
... place in the blade trailing edge. An estimate of the crack-growth rate for the stage II fatigue fracture region coupled with the metallographic results helped to identify the final mode of the turbine blade failure. A detailed metallographic and fractographic examination of the air-cooled vane revealed...
Abstract
The circumstances surrounding the in-service failure of a cast Ni-base superalloy (Alloy 713LC) second stage turbine blade and a cast and coated Co-base superalloy (MAR-M302) first stage air-cooled vane in two turbine engines used for marine application are described. An overview of a systematic approach, analyzing the nature of degeneration and failure of the failed components, utilizing conventional metallurgical techniques, is presented. The topographical features of the turbine blade fracture surface revealed a fatigue-induced crack growth pattern, where crack initiation had taken place in the blade trailing edge. An estimate of the crack-growth rate for the stage II fatigue fracture region coupled with the metallographic results helped to identify the final mode of the turbine blade failure. A detailed metallographic and fractographic examination of the air-cooled vane revealed that coating erosion in conjunction with severe hot-corrosion was responsible for crack initiation in the leading edge area.
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001081
EISBN: 978-1-62708-214-3
... are presented in Fig. 15 . The spin-pit tests showed that the crack propagation rates remained relatively constant up to a crack length of approximately 10 mm (0.4 in.). A typical fatigue striation pattern observed during spin-pit crack growth is shown in Fig. 16 . Using striation counting methods...
Abstract
Several compressor disks in military fighter and trainer aircraft gas turbine engines cracked prematurely in the bolt hole regions. The disks were made of precipitation-hardened AM355 martensitic stainless steel. Experimental and analytical work was performed on specimens from the fifth-stage compressor disk (judged to be the most crack-prone disk in the compressor) to determine the cause of the failures. Failure was attributed to high-strain low-cycle fatigue during service. It was also determined that the cyclic engine usage assumed in the original life calculations had been under estimated, which led to low-cycle fatigue cracking earlier than expected. Fracture mechanics analysis of the disks was carried out to assess their damage tolerance and to predict safe inspection intervals.
1