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interaction damage rule
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Image
in Strain-Range Partitioning—Concepts and Analytical Methods
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 3.25 An example application of the Interaction Damage Rule for PP + CP loading over the entire spectrum of life from N PP = 10,000 cycles to failure to N CP = 100 cycles to failure
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Image
in Strain-Range Partitioning—Concepts and Analytical Methods
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 3.27 Application of the Interaction Damage Rule to (PP + CC) cycling of AISI type 316 stainless steel at 816 °C (1500 °F) for Δε in = 0.0047. Source: Ref 3.26
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Image
in Strain-Range Partitioning—Concepts and Analytical Methods
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 3.28 Application of the Interaction Damage Rule to PP + CC cycling of A-286 at 595 °C (1100 °F) for Δε in = 0.009. Source: Ref 3.26
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Image
in Strain-Range Partitioning—Concepts and Analytical Methods
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 3.29 Application of the Interaction Damage Rule to (PP + CC) and (PP + CP) cycling of AISI type 304 stainless steel at 650 °C (1200 °F) at various strain ranges and cycle times. Source: Ref 3.26
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Image
in Strain-Range Conversion—An Extended View of Strain-Range Partitioning
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Image
in Strain-Range Partitioning—Concepts and Analytical Methods
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 3.24 Example set of strain-range partitioning life relationships for comparison of the Life Fraction Rule and the Interaction Damage Rule
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Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060043
EISBN: 978-1-62708-343-0
... N PP / N CP = 30 f PP ≤ 0.968 N PP / N CP = 100 f PP ≤ 0.990 N PP / N CP = 300 f PP ≤ 0.997 Fig. 3.25 An example application of the Interaction Damage Rule for PP + CP loading over the entire spectrum of life from N PP = 10,000 cycles to failure to N CP...
Abstract
Strain-range partitioning is a method for assessing the effects of creep fatigue based on inelastic strain paths or strain reversals. The first part of the chapter defines four distinct strain paths that can be used to model any cyclic loading pattern and describes the microstructural damages associated with each of the four basic loading cycles. The discussion then turns to fatigue life prediction for different types of materials and more realistic loading conditions, particularly those in which hysteresis loops have more than one strain-range component. To that end, the chapter considers two cases. In one, the relationship between strain range and cyclic life is established from test data. In the other, a rule is required to determine the damage of each concurrent strain and the total damage of the cycle is used to predict creep-fatigue life. The chapter presents several such damage rules and discusses their applicability in different situations.
Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060069
EISBN: 978-1-62708-343-0
... 1 0 0 1 0 0 1 0 3 0 3 0 3 Fig. 4.2 Nine different hysteresis loops with the same PP, CC, and CP components of strain. Source: Ref 4.1 Fig. 4.1 Hysteresis loop summation by the Interaction Damage Rule. Source: Ref 4.1 Fig. 4.3 Analysis of interaction...
Abstract
This chapter demonstrates the versatility of the strain-range partitioning method and its application to creep-fatigue problems involving complex loading histories. It begins with a derivation showing that it is possible to assess the damage of hysteresis loops combining two or more strain ranges using generic loops based on fundamental data. It then explains how to treat problems involving sequential loading with both healing and damage cycles and presents a general solution for combining two loops with arbitrary amounts of the four strain-range components. The chapter also derives closed-form equations that account for interactions among any number of adjacent loops and can be used, through successive application, to analyze any loading history.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060173
EISBN: 978-1-62708-343-0
... 8.26 ABD LFR Life Fraction Rule 8.85 ABD TCD Turbine component design 8.86 ABD ITC Interactive time-cycle fractions 8.78 ABD RCF Relaxation creep fatigue 8.87 ABE CDC Cumulative damage under creep 8.88 ABDE PFC Phenomenological fatigue creep 8.89 ABDN...
Abstract
This chapter provides a detailed review of creep-fatigue analysis techniques, including the 10% rule, strain-range partitioning, several variants of the frequency-modified life equation, damage assessment based on tensile hysteresis energy, the OCTF (oxidation, creep, and thermomechanical fatigue) damage model, and numerous methods that make use of creep-rupture, crack-growth, and void-growth data. It also discusses the use of continuum damage mechanics and includes examples demonstrating the accuracy of each method as well as the procedures involved.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060155
EISBN: 978-1-62708-343-0
... Laboratories Report ANL-8009 , Nov 1973 Step 6: The Strain-Range Partitioning Life Relationships Step 7: Interaction Damage Rule Step 9: Nonproportional Loading Example and Comparison of Predicted and Observed Lives Step 8: Triaxiality Factor Concluding Remarks on Multiaxiality...
Abstract
This chapter addresses the question of how to deal with multiaxial stresses and strains when using the strain-range partitioning method to analyze the effects of creep fatigue. It is divided into three sections: a general discussion on the rationale used in formulating rules for treating multiaxiality, a concise listing of the rules, and an example problem in which axial creep-fatigue data is used to predict the torsional creep-fatigue life of type 304 and 316 stainless steel. The chapter also includes a brief introduction in which the authors outline the challenges presented by multiaxial loading and set practical limits on the problem they intend to treat.
Image
Published: 01 March 2006
Fig. 6.21 Double linear damage rule applied to block loading involving two loading levels. (a) Conventional interaction lines. (b) Reiteration as damage lines. Source: Ref 6.10
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Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 March 2006
DOI: 10.31399/asm.tb.fdsm.t69870123
EISBN: 978-1-62708-344-7
... two loading levels. (a) Conventional interaction lines. (b) Reiteration as damage lines. Source: Ref 6.10 Fig. 6.22 Double linear damage rule applied to block loading involving four loading levels. (a) Representation by damage lines. (b) Application for N 1 = 10 3 and N 2 = 10 6...
Abstract
This chapter addresses the cumulative effects of fatigue and how to determine its impact on component lifetime and performance. It begins by defining a loading history and its corresponding hysteresis loops that exposes the deficiencies of some of the theories discussed. It then proceeds to demonstrate the methods commonly used to analyze cumulative fatigue damage and its effect on component life starting with the classical linear damage rule. After pointing out the inherent limitations of the model, it presents a method that incorporates two linear damage rules, one applying prior to crack initiation and the other after the crack has started. Although the method accounts somewhat better for loading-order effects, the transition in behavior that the rules presume to model occurs prior to any signs of cracking. Two modified versions of the double linear damage rule method, neither of which are related to a physical crack initiation event, are subsequently presented along with several applications showing how the different methods compare. The examples provided include two-level and multilevel tests, a gas-turbine engine compressor disk, and the cumulative damage associated with the irreversible hardening of type 304 stainless steel.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 December 1989
DOI: 10.31399/asm.tb.dmlahtc.t60490111
EISBN: 978-1-62708-340-9
... steels ( Ref 20 ). Fig. 4.27. Comparison of crack-growth behavior of Fe-Ni alloy A-286 in air and vacuum at 595 °C (1100 °F) ( Ref 69 ). Fig. 4.28. Creep-rupture/low-cycle-fatigue damage interaction curve for 1Cr-Mo-V rotor steel at 540 °C (1000 °F) (after Ref 82 ). Fig. 4.29...
Abstract
This chapter describes the phenomenological aspects of fatigue and how to assess its effect on the life of components operating in high-temperature environments. It explains how fatigue is measured and expressed and how it is affected by loading conditions (stress cycles, amplitude, and frequency) and factors such as temperature, material defects, component geometry, and processing history. It provides a detailed overview of the damage mechanisms associated with high-cycle and low-cycle fatigue as well as thermal fatigue, creep-fatigue, and fatigue-crack growth. It also demonstrates the use of tools and techniques that have been developed to quantify fatigue-related damage and its effect on the remaining life of components.
Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060111
EISBN: 978-1-62708-343-0
... were conducted on a nominally completely reversed strain condition. Furthermore, the degree of inelastic strain range to elastic strain range was rather great (≥0.1) for the tests performed. The CCOP test data were then analyzed using the Interaction Damage Rule to back out the “pure PC” bithermal life...
Abstract
This chapter explains why it is sometimes necessary to separate inelastic from elastic strains and how to do it using one of two methods. It first discusses the direct calculation of strain-range components from experimental data associated with large strains. It then explains how the method can be extended to the treatment of very low inelastic strains by adjusting tensile and compressive hold periods and continuous cycling frequencies. The chapter then begins the presentation of the second approach, called the total strain-range method, so named because it combines elastic and inelastic strain into a total strain range. The discussion covers important features, procedures, and correlations as well as the use of models and the steps involved in predicting thermomechanical fatigue (TMF) life. It also includes information on isothermal fatigue, bithermal creep-fatigue testing, and the predictability of the method for TMF cycling.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060231
EISBN: 978-1-62708-343-0
... ⅕ the required design life of 1 × 10 5 , suggesting a need to reconsider and hence improve the original design or reduce the PF. The nonlinear cumulative damage interaction indicated a factor of more than 40 loss in life. The classic Linear Damage Rule would have predicted only a factor of 1.08 loss in life due...
Abstract
This chapter explains how the authors assessed the potential risks of creep-fatigue in several aerospace applications using the tools and techniques presented in earlier chapters. It begins by identifying the fatigue regimes encountered in the main engines of the Space Shuttle. It then describes the types of damage observed in engine components and the methods used to mitigate problems. It also discusses the results of analyses that led to changes in design or approach and examines fatigue-related issues in turbine engines used in commercial aircraft.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060083
EISBN: 978-1-62708-343-0
... cycle as the tests progressed. Life predictions were made using Eq 5.5 , 5.7 , and the Interaction Damage Rule. How well the described approach succeeded in predicting the creep-fatigue lives is given in Fig. 5.15 . The central 45° line represents perfect predictions, and the bounding lines on either...
Abstract
This chapter compares and contrasts empirical approaches for partitioning hysteresis loops and predicting creep-fatigue life. The first part of the chapter presents experimental partitioning methods, explaining how they can be used to partition any loading cycle into its basic strain-range components. The methods covered include rapid cycling between peak stress extremes, half-cycle rapid loading and unloading, and variations of the incremental step-stress approach. The methods are then compared based on their ability to predict creep-fatigue life. The chapter goes on from there to describe how fatigue life can be estimated from ductility measurements when cyclic data are unavailable or are likely to change. It also explains how cyclic life is influenced by the time-dependent nature of creep-plasticity and the physical and metallurgical effects of environmental exposure.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 December 1989
DOI: 10.31399/asm.tb.dmlahtc.t60490415
EISBN: 978-1-62708-340-9
... ∊ in 3 0.35 5.2 0.33 3.8 Ostergren, with frequency modification σ max Δ ∊ in 3 0.32 6.5 0.30 3.3 Analogous to ASME code Δ ∊ in , σ 4 0.31 4.8 0.32 4.5 SRP-linear damage rule Δ ∊ in 8 0.31 3.0 0.33 3.0 SRP-interaction damage rule Δ ∊ in 8 0.30 3.3...
Abstract
Combustion turbines consist of a compressor, a combustor, and a turbine. As commonly configured, the compressor and turbine mount on a single shaft that connects directly to a generator. This chapter reviews the materials of construction, damage mechanisms, and life-assessment techniques for nozzles and buckets. It also presents key information from a detailed review of the literature and the results of a survey on combustion-turbine material problems.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 March 2012
DOI: 10.31399/asm.tb.pdub.t53420239
EISBN: 978-1-62708-310-2
..., if made by melting, or that cannot be melted to a homogeneous liquid can sometimes be produced by powder metallurgy techniques. Contamination from the atmosphere is often very damaging. In extreme cases, the liquidus temperature has been observed to be depressed several hundred degrees simply...
Abstract
This chapter discusses some of the methods and measurements used to construct phase diagrams. It explains how cooling curves were widely used to determine phase boundaries, and how equilibrated alloys examined under controlled heating and cooling provide information for constructing isothermal and vertical sections as well as liquid projections. It also explains how diffusion couples provide a window into local equilibria and identifies typical phase diagram construction errors along with problems stemming from phase-boundary curvatures and congruent transformations.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 December 2003
DOI: 10.31399/asm.tb.cfap.t69780276
EISBN: 978-1-62708-281-5
... the possibility of mutual interaction of the constituents causing a deviation in the wear resistance of a hybrid composite based on the rule of mixture calculation. The practical application of such composite was justified on the basis of performance-to-cost ratio. Fig. 20 Specific wear rate as a function...
Abstract
This article briefly reviews abrasive and adhesive wear failure of reinforced polymers and polymer composites, namely particulate-filled polymers, short-fiber-reinforced polymers, polymers with continuous fibers, and mixed reinforcements and fabrics. It includes scanning electron microscope micrographs of abraded surfaces of composites against 80-grade SiC paper and under 14 N load, and worn surfaces of abraded polyether-imide composites and polyamide 66 unidirectional composites and 66 hybrid composites.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 December 1989
DOI: 10.31399/asm.tb.dmlahtc.t60490059
EISBN: 978-1-62708-340-9
... 6 - 13 49. Voorhees H.R. and Freeman F.W. , “ Notch Sensitivity of Aircraft Structural and Engine Alloys, ” Wright Air Development Center Technical Report, Part II , Jan 1959 , p 23 50. Abo M.M. El Ata and I. Finnie, “ A Study of Creep Damage Rules, ” ASME Paper...
Abstract
This chapter provides a detailed overview of the creep behavior of metals and how to account for it when determining the remaining service life of components. It begins with a review of creep curves, explaining how they are plotted and what they reveal about the operating history, damage mechanisms, and structural integrity of the test sample. In the sections that follow, it discusses the effects of stress and temperature on creep rate, the difference between diffusional and dislocation creep, and the use of time-temperature-stress parameters for data extrapolation. It explains how to deal with time dependent deformation in design, how to estimate cumulative damage under changing conditions, and how to assess the effect of multiaxial stress based on uniaxial test data. It also includes information on rupture ductility, creep fracture, and creep-crack growth and their effect on component life and performance.
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