High Cycle Fatigue: A Mechanics of Materials Perspective part 15 ppsx

Such data, often obtained from vibratory tests on a specimen or component, are then used to construct a Modified Goodman diagram using a straight line extrapolation from the zero mean st

and of mean log-lives for a material having variable scatter, provided that the precision

at the highest stress level is markedly lower than the others Their results also showed that results obtained from test programs with different number of specimens per level are better than those of plans with uniform replication For the particular set of data used, from which experimental results were chosen at random for the statistical analysis, a confidence level of 90% could be obtained over the range ± using the following test programs: 10–3–5–6 specimens (a total of 24 specimens) tested at levels 550–520–490–460 MPa for the exponential (Nelson) model, Equation (3.22), and 10–3–6–10 specimens (a total

of 29 specimens) tested at the same stress levels for the linear model, Equation (3.23)

3.8.1 Run-outs and maximum likelihood (ML) methods

A unique feature of testing in the HCF regime is the occurrence of run-out tests where the test is terminated after a certain (large) number of cycles Alternately, a test that fails after N cycles can be used in an analysis describing the behavior for fewer than N cycles,

so it can then be treated as a run-out for the fewer cycles being considered Run-outs,

in statistics terms, are considered to be censored data, that is, they fall outside the range

of behavior (lives) being considered In fitting models to data containing run-outs, the run-outs cannot be used in least-square fits because the exact location of the data point

is unknown All that is known is the fatigue life was greater than some quantity Since least-squares methods cannot use censored data because the data points do not really exist, other methods have been employed As mentioned in the discussion of the RFL model previously, maximum likelihood (ML) estimation schemes are able to deal with censored data from a statistical point of view The virtue of the ML method is that it applies to virtually any assumed statistical distribution of lives or fatigue strengths as well

as any form of data including run-outs Details regarding ML theory and its application

to fatigue data, particularly in the HCF regime, can be found in the book by Nelson [57], for example The ML method not only provides valid estimates of the mean and standard deviation of a distribution function, it also provides confidence intervals for coefficients in the distributions or models The application to various models for variable standard deviation, , as a function of stress, for example, was discussed above ML estimates have good statistical properties for almost any assumed form of the fatigue life distribution and for almost any assumed form for the equation for the distribution parameters as functions of the stress or other variable [56] In some simple cases where fatigue life is described by a lognormal distribution with constant  and there are no run-outs, ML estimates of model coefficients are the same as standard least-squares regression estimates Although ML methods are mathematically complex, they are easy

to apply in practice using special computer packages that are now widely available [57] The procedure involves writing equations for the likelihood of an event (failure in a given lifetime, for example) in terms of the unknown parameters of the distribution

function and/or model The values of the coefficients that maximize the likelihood are then determined This procedure generally involves nonlinear equations that cannot be solved algebraically, thus numerical methods are employed The solution of these types

of equations is what statistical computer codes are designed to accomplish using various numerical techniques It is important that the solutions provide a global maximum of the likelihood function, not a local maximum nor a saddle point Existence and uniqueness of the solutions also have to be established There are some models for which the likelihood equations can be solved explicitly [57]

As a simple example of the ML method, we consider a set of ten hypothetical exper-iments at constant stress where the log lives to failure from each test are tabulated in ascending order in Table 3.10 These data are labeled “actual” and represent a data set where all tests would have been carried out to failure

If these same tests had been conducted up to 107cycles (log life= 7) and terminated

at that point if no failure had occurred, then 3 of the tests would be recorded as run-outs (censored) Both sets of data are shown in Figure 3.42 on a probability plot assuming the log lives follow a normal distribution The actual data are fit with a straight line to determine the constants for the normal distribution that represents this data set

If the same data are taken with run-outs, the data set including 3 censored points that indicate only that the observed log lives were >7, the ML method can be employed Using a commercial software package called Minitab, the data were evaluated assuming

a normal fit to log life as was the case for the real data [58] The results of that evaluation are shown in Figure 3.43 which shows both the best fit to a normal distribution of log life (time) as well as the 95% confidence bounds The fit is almost identical to that of the entire (uncensored) data set shown in Figure 3.42

For comparison purposes, the results of both fits are presented in Table 3.11 The analyses show that the ML method, using 7 data points and 3 run-outs, produces essentially

Table 3.10. Hypothetical log life data for testing with and without run-outs

5 5.5 6 6.5 7 7.5 8 01

.1 1 5 10 20 50 70 90 95 99 99.9 99.99

Log cycles

Censored Actual

Figure 3.42. Statistical distribution of lives to failure with and without run-outs.

9 8

7 6

5

99

95

90

80

70

60

50

40

30

20

10

5 1

Time to failure

Figure 3.43. Statistical analysis of censored data using ML method.

Table 3.11. Constants for normal distribution of log life from standard and ML methods

the same normal distribution as standard least squares methods for the specific data set

of 10 data points chosen for this numerical example

Structural components subjected to high frequency vibrations, such as those used in rotating parts of gas turbine engines, are usually required to be designed using a lifetime failure-free criterion for a very large number of cycles, or an endurance limit Tools, such

as the constant life Haigh or Goodman diagram, described earlier in Chapter 2, are often used, but these diagrams are usually constructed using uniaxial fatigue data only, and the design is based on uniaxial stresses While it is desirable to have data at many values of mean stress, or equivalent stress ratio, R, there are many cases in design where data at a single value of R= −1, fully reversed loading with zero mean stress, are the only data available Such data, often obtained from vibratory tests on a specimen or component, are then used to construct a Modified Goodman diagram using a straight line extrapolation from the zero mean stress data point to the yield or ultimate strength of the material which is considered as zero alternating stress (see Figure 2.17 in Chapter 2) Alternate approaches such as the Jasper or other equation, as described earlier, can be used to construct a Haigh diagram by using an equation to represent behavior at all values of mean stress or stress ratio, but data for at least one value of R are needed to establish the constants

Uniaxial fatigue tests on conventional test machines are the type of test normally conducted to obtain the required data for construction of a Haigh diagram These tests require long time periods to achieve a large number of cycles approaching the endurance limit Even a servo-hydraulic test machine operating at 60 Hz requires approximately

46 hours to accumulate 107 cycles for a point on an S–N curve Additionally, for each value of mean stress or stress ratio, several data points are needed in order to interpolate the value of stress at the desired life (107in this example) to get a single point

on the Haigh diagram Therefore, significant amounts of time are required to characterize the uniaxial fatigue properties of a material While newer machines are available which can achieve higher frequencies, and ultrasonic machines that operate at 20 kHz have been developed [2], these tests are typically limited to uniaxial tension Accelerated test methods, described in previous sections in this chapter, and test procedures such as step

or staircase testing, described above, can save some time However, these provide only uniaxial fatigue data which may be insufficient for assessing high cycle FLSs which often occur in components that are subjected to biaxial loading over a wide range of cyclic frequencies In turbine blades, for example, fatigue failure often occurs under high order bending or combined bending and twist modes that produce short wave length stress states at very high frequencies Unfortunately, the current capability to conduct

biaxial fatigue tests, especially under bending or torsion as well as axial stress states,

is limited by the high cost of development of such testing methods as well as the lack

of existing equipment to conduct the necessary tests at anything other than very low frequencies

Resonant fatigue testing of some unique geometric configurations has recently been proposed [59] as a method for obtaining data heretofore unavailable because they involve both high frequencies and either uniaxial or biaxial bending stress states It should be noted that resonant fatigue testing procedures have been in existence for over a century

In reviewing the history of resonant techniques, it can be pointed out that in the time period from 1879 to 1925, no fewer than 35 journal articles appeared describing new test procedures and methods for fatigue testing [60] The earliest test methods involved coupling a specimen and a driver in order to obtain a resonance or near resonance condition

to decrease the power requirements It was recognized early on that “working in or near the resonance (unstable dynamic equilibrium) demands special controlling devices” [61] These early machines were only able to achieve frequencies up to approximately

100 Hz and were confined to either pure axial or torsion modes under either resonant

or non-resonant conditions [62] Among the early test machines that operated on the resonance principle were those built by Sontag that produced a constant force at 30 Hz The Schenck machines, of the 1930s and later [63], operated in a fairly stable manner by using a very large spring coupled to a much smaller specimen and could run continuously under constant load at approximately 30 Hz Later on, such machines were controlled with automatic feedback from a load cell to correct for any deformation of the specimen during the test such as creep or initiation of a fatigue crack A very large version of a Schenck machine [64] was used in the Messerschmitt factory during World War II to test large components, but the loading was still uniaxial Electromagnetic resonant fatigue test machines are currently available having high-test frequencies of 40–300 Hz and boast of the same advantage of the first machines, namely low power consumption

One of the advantages of a resonant machine where the specimen is part of the mechanical system is that upon incipient failure, the spring constant of the specimen changes and throws the system off resonance which is a warning of impending failure

if it is desired to examine the specimen before total destruction of the sample [65] In addition to mechanically driven machines, magnetic excitation to drive a machine/sample combination into resonance dates back to prior to World War II (see, e.g [66])

Tests of structural components and full-scale structures conducted under both resonant and non-resonant conditions [67] date back to the 1860s [68] Because of the expense

of the test articles as well as the test machines, such tests are normally limited to very few components and are not very useful for extracting fatigue properties of the material, even though the stress state at a failure point may be complex Whatever information is extracted is limited to the specific number of cycles to failure due to the applied loading

condition Fatigue limit strengths of the structure or the material are rarely obtained for cycle numbers near the endurance limit

As discussed earlier in this chapter, a step-test procedure has been shown to produce fatigue limit data that are consistent with those obtained from interpolation of S–N curves at fixed values of mean stress or stress ratio With a limited number of samples, since each sample produces a FLS data point, a Haigh diagram can be constructed

in a reasonable amount of time To achieve the goal of determining the FLS under uniaxial or biaxial bending, stress states that are commonly achieved in turbine blades under resonance conditions, a combination of the concepts described above have been utilized and expanded to develop a new testing procedure [59] This vibration-based fatigue testing concept uses a base-excited plate specimen that is driven into a high frequency resonant mode Using the step-testing procedure and finite element analysis

of the vibrating specimen, the loads and stresses necessary to produce HCF failure corresponding to a fixed number of cycles (106or 107) can be determined The geometry

of a plate that is driven into resonance by base excitation on a shaker can be either a square plate for uniaxial bending or a more complicated geometry as shown in Figure 3.44 for biaxial bending For a square plate of steel with dimensions of 114 mm on a side, the natural frequency under a two-stripe mode is approximately 1200 Hz The out-of-plane displacement profile and corresponding vonMises stresses are shown in Figure 3.45 for

61.0

162.6 81.3

Clamped edge

35.6

50.8

Figure 3.44. Resonant biaxial specimen dimensions (mm).

(b) (a)

Figure 3.45. Out of plane displacements (a), and vonMises stresses (b), for square steel plate.

the steel plate of 2.4 mm thickness The maximum stress occurs at the middle of the free end (top of picture) and is higher than any stresses at the fixed end (bottom) which is being excited by the shaker The stresses at the free end were sufficient to cause cracks

to form within 106cycles using a conventional laboratory shaker/amplifier system [59] For biaxial loading, the specimen shown in Figure 3.44 was base excited into a resonant two-stripe mode frequency of approximately 1600 Hz The specimen was aluminum with

a thickness of 3.1 mm The out-of-plane displacements and vonMises stresses for the square steel and aluminum biaxial specimens are compared in Figures 3.45 and 3.46

Figure 3.46. Out of plane displacements (a), and vonMises stresses (b), for aluminum biaxial specimen.

Figure 3.46 shows that the maximum stresses for the aluminum biaxial specimen occur along the centerline and away from the free end by approximately one-third of the length For this particular geometry, the ratio of y(vertical direction) to x(horizontal direction)

at the point of maximum stress is approximately 0.59

These specimen geometries and the resultant two-stripe mode shapes of interest have been used to determine FLSs under uniaxial or biaxial bending with a step-test procedure The mode shapes that were predicted by finite element method (FEM) and verified experimentally provided a method for calibrating stresses at the critical locations with observed transverse displacement amplitudes recorded with a laser vibrometer

The fatigue limit strength in typical uniaxial tension tests, performed using conventional testing machines, is determined as the stress at which complete failure occurs under constant load, either by conventional S–N or step testing For long life tests, total life, where the fatigue crack propagates through the specimen and failure occurs, is not distinguished from crack nucleation or crack initiation life Computations have shown that the fatigue crack propagation life in a tensile bar is only a small fraction of total life when testing at stress levels near the HCF limit defined as 107 cycles [69] In the case

of vibration-based fatigue testing under resonance conditions, however, there does not exist a definitive phenomenon such as abrupt failure Therefore, in the vibration-based tests, from the start of the test until the time of fatigue crack initiation, the response amplitude of the plate as measured by a laser vibrometer has to be monitored and adjusted

by changing the amplitude and frequency of the shaker to keep the system in resonance and to maintain the desired stress level In this technique, the fatigue limit is defined at the instant corresponding to a sudden change in the response of the plate, as opposed

to the typical gradual changes in the dynamic response of the plate associated with the stiffness changes associated with fatigue crack development A resonant frequency shift away from the shaker driving frequency was observable even in the initial stage of fatigue crack development [59]

In the tests conducted by George et al [59], the vibration testing was continued in one of two ways after the FLS was determined By varying the experimental technique, they were able to produce both short and long cracks The technique to produce short cracks, on the order of a few millimeters or less, was to leave the shaker amplitude fixed after the FLS was determined and to propagate the crack by repeatedly re-tuning the shaker driving frequency to the resonant specimen frequency As the crack propagated, the resonant frequency of the specimen decreased With this technique, using a constant shaker amplitude, the maximum stress level in the crack tip region ultimately dropped to

a level where the crack arrested This technique produced cracks on the order of 1–2 mm

in the case of steel specimens and 0.1 mm in the case of Ti-6Al-4V To produce long cracks, on the order of tens of mm, the shaker amplitude had to be increased as necessary

to continue propagating the crack

For the biaxial specimen of Figure 3.44, the frequency response exhibited nonlinear hardening which produces specimen response at the natural frequency which is unstable [59] As the fatigue crack begins to develop and decrease the stiffness of the plate the natural frequency begins to drop and the response immediately decreases drastically This sudden drop enables small cracks to initiate and then arrest because of the sudden decrease in the forcing function This phenomenon enabled George et al [59] to produce

an approximately 0.4 mm long series of microcracks in their biaxial specimen

One of the most important observations from the experiments of George et al [59] is that the formation of a crack in a specimen reduces the natural frequency of the system

If the frequency of the excitation remains fixed, the level of response at that frequency will be reduced, and a new peak response will be present at a lower frequency This observation in itself is not new, but its implication on gas turbine engine fatigue could drastically change widely held design and maintenance conventions From the fatigue perspective, this implies that for a constant level and frequency of excitation, once a crack is initiated, the level of strain in the component is reduced If this level of strain is reduced below the level needed to propagate the crack, the crack will self-arrest In order

to continue crack growth, the frequency of excitation must be reduced to meet the new peak response frequency, and if it does, the fatigue process continues For the case of forced response in a gas turbine engine, where the excitation consists of distinct tones, or narrow bands, of aerodynamic drivers, a crack could self arrest once the peak response frequency shifts away from the forcing frequency For high order modes, where mode shapes tend to have localized areas of high strain, a small crack might form, propagate slightly and then arrest without having an adverse effect on the overall structure For

a broadband excitation, such as inlet distortion or low order excitation of the turbine from combustor effects, the above scenario is less likely and the crack would continue to propagate since an excitation would be strong over a wide range of frequencies As with classic laboratory fatigue experiments in which a crack is chased by changing frequency

to continue crack propagation, as the natural frequency of the component changed, there would be an excitation waiting to continue fatigue through to failure

3.10 FREQUENCY EFFECTS

Questions have arisen over the years about frequency effects on the HCF behavior and fatigue limit strength of materials and structural components While laboratory testing has traditionally dealt with frequencies typically below 100 Hz,∗ components in turbine engines can undergo vibratory stresses well into the kHz regime It is natural to ask, therefore, what effect does frequency have upon the fatigue behavior of materials Dealing

∗

See Chapter 2, Section 2, for a discussion of gigacycle fatigue and testing at 20 kHz.

solely with material behavior, data on a number of structural materials [70], show that metals exhibit very little difference in strength in terms of strain rate effects up to nominal strain rates in the 1–100 s−1 regime However, these rate effects are confined to the inelastic regime of material behavior, so these numbers should not necessarily apply to fatigue in the HCF regime where behavior is nominally elastic Further, for the purpose

of translating strain rates into equivalent frequencies, consider that nominal maximum strains in the HCF regime are of the order of less than 1% (0.01), so a frequency of 1 kHz would correspond to a strain rate of less than 10 s−1 Finally, gigacycle fatigue testing conducted at frequencies of 20 kHz has shown little or no difference in fatigue strength than results obtained at conventional frequencies It is significant to note that, for reasons not related to frequency effects, gigacycle fatigue testing is being conducted by many on rotating beam machines that operate at under 60 Hz

It is with great interest and curiosity that examination of the results of fatigue tests conducted in the 1950s and earlier show what appear to be frequency effects in a number

of materials Lomas et al [71] summarize many of the findings up to their publication date in 1956 which includes much speculation as to the validity of many of the early results reporting frequency effects Most of the data were considered unreliable and some

of the findings were attributed to heating effects at higher frequencies They cite the work of Jenkin [72] and Jenkin and Lehmann [73], the latter of who’s work they plot

in their paper, reproduced here as Figure 3.47 The materials represented here include copper, aluminum, and several steels: 0.86% carbon, 0.11% carbon, rolled, Armco iron,

Copper Aluminium

a

Armco iron

FREQUENCY-CYCLES PER SEC.

10,000 3,000

1,000 300

14 16 18 20 22 24 26 28 30 32 34 4 5 6

0.11% carbon, rolled

0.11% carbon, normalized

Figure 3.47. Endurance stress data of [73] replotted by Lomas et al [71].