Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys
Выполнены экспериментальные исследования трещиностойкости -сплава на базе TiAl сплавов при различных температурах. Оценено влияние температуры на характеристики роста усталостной трещины и определены формула, описывающая ее скорость на участке II (область развития), а также конкретные значения кон...
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Інститут проблем міцності ім. Г.С. Писаренко НАН України
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irk-123456789-1127282017-01-27T03:02:34Z Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys Feng, R.C. Rui, Z.V. Zuo, Y. Yan, C.F. Zhang, G.T. Научно-технический раздел Выполнены экспериментальные исследования трещиностойкости -сплава на базе TiAl сплавов при различных температурах. Оценено влияние температуры на характеристики роста усталостной трещины и определены формула, описывающая ее скорость на участке II (область развития), а также конкретные значения констант уравнения с использованием экспериментальных результатов. Испытания проводили в вакууме при температурах 25, 750 и 850C. Полученные экспериментальные результаты показывают, что температура существенно влияет на скорость роста усталостных трещин. При повышении температуры до 750C скорость роста таких трещин увеличивается, по достижении этой температуры имеет место хрупковязкий переход TiAl сплава. Аналогичная зависимость наблюдается также для традиционных сплавов. Проведено експериментальні дослідження тріщиностійкості -сплава на базі TiAl сплавів за різних температур. Оцінено вплив температури на характеристики росту тріщин від утомленості і визначено формулу, що описує її швидкість на ділянці II (область розвитку), та конкретні значення констант рівняння з використанням експериментальних результатів. Випробування проводили в вакуумі за температур 25, 750 і 850C. Отримані експериментальні дані показують, що температура суттєво впливає на швидкість росту тріщин від утомленості. Із підвищенням температури до 750 С швидкість росту таких тріщин збільшується, при досягненні цієї температури має місце крихков’язкий перехід TiAl сплаву. Аналогічна залежність відмічається також для традиційних сплавів. 2014 Article Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys / R.C. Feng, Z.V. Rui, Y. Zuo, C.F. Yan, G.T. Zhang // Проблемы прочности. — 2014. — № 3. — С. 149-154. — Бібліогр.: 12 назв. — англ. 0556-171X http://dspace.nbuv.gov.ua/handle/123456789/112728 539.4 en Проблемы прочности Інститут проблем міцності ім. Г.С. Писаренко НАН України |
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Научно-технический раздел Научно-технический раздел |
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Научно-технический раздел Научно-технический раздел Feng, R.C. Rui, Z.V. Zuo, Y. Yan, C.F. Zhang, G.T. Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys Проблемы прочности |
| description |
Выполнены экспериментальные исследования трещиностойкости -сплава на базе TiAl сплавов при различных температурах. Оценено влияние температуры на характеристики роста
усталостной трещины и определены формула, описывающая ее скорость на участке II
(область развития), а также конкретные значения констант уравнения с использованием
экспериментальных результатов. Испытания проводили в вакууме при температурах 25, 750
и 850C. Полученные экспериментальные результаты показывают, что температура существенно влияет на скорость роста усталостных трещин. При повышении температуры
до 750C скорость роста таких трещин увеличивается, по достижении этой температуры
имеет место хрупковязкий переход TiAl сплава. Аналогичная зависимость наблюдается
также для традиционных сплавов. |
| format |
Article |
| author |
Feng, R.C. Rui, Z.V. Zuo, Y. Yan, C.F. Zhang, G.T. |
| author_facet |
Feng, R.C. Rui, Z.V. Zuo, Y. Yan, C.F. Zhang, G.T. |
| author_sort |
Feng, R.C. |
| title |
Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys |
| title_short |
Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys |
| title_full |
Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys |
| title_fullStr |
Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys |
| title_full_unstemmed |
Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys |
| title_sort |
influence of temperature on fatigue crack propagation in tial alloys |
| publisher |
Інститут проблем міцності ім. Г.С. Писаренко НАН України |
| publishDate |
2014 |
| topic_facet |
Научно-технический раздел |
| url |
http://dspace.nbuv.gov.ua/handle/123456789/112728 |
| citation_txt |
Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys / R.C. Feng, Z.V. Rui, Y. Zuo, C.F. Yan, G.T. Zhang // Проблемы прочности. — 2014. — № 3. — С. 149-154. — Бібліогр.: 12 назв. — англ. |
| series |
Проблемы прочности |
| work_keys_str_mv |
AT fengrc influenceoftemperatureonfatiguecrackpropagationintialalloys AT ruizv influenceoftemperatureonfatiguecrackpropagationintialalloys AT zuoy influenceoftemperatureonfatiguecrackpropagationintialalloys AT yancf influenceoftemperatureonfatiguecrackpropagationintialalloys AT zhanggt influenceoftemperatureonfatiguecrackpropagationintialalloys |
| first_indexed |
2025-07-08T04:32:47Z |
| last_indexed |
2025-07-08T04:32:47Z |
| _version_ |
1837051857454759936 |
| fulltext |
UDC 539.4
Influence of Temperature on Fatigue Crack Propagation in TiAl Alloys*
R. C. Feng,a,b,1 Z. Y. Rui,a,b,2 Y. Zuo,a,3 C. F. Yan,a,b,4 and G. T. Zhanga,b,5
a Key Laboratory of Digital Manufacturing Technology and Application, Ministry of Education,
Lanzhou University of Technology, Lanzhou, China
b School of Mechanical and Electronical Engineering, Lanzhou University of Technology, Lanzhou,
China
1 frcly@163.com
2 zhiy_rui@163.com
3 825738568@qq.com
4 changf_yan@163.com
5 zhangguotao_good@126.com
ÓÄÊ 539.4
Âëèÿíèå òåìïåðàòóðû íà ðîñò óñòàëîñòíûõ òðåùèí â TiAl ñïëàâàõ
Ð. ×. Ôåíãà,á,1, Æ. É. Ðóèà,á,2, ß. Çóîà,3, ×. Ô. ßíà,á,4, Ã. Ò. Æàíãà,á,5
à Ëàáîðàòîðèÿ ïðîèçâîäñòâà è ïðèìåíåíèÿ öèôðîâûõ òåõíîëîãèé, Ìèíèñòåðñòâî îáðàçîâàíèÿ,
Ëàíü÷æîóñêèé òåõíîëîãè÷åñêèé óíèâåðñèòåò, Ëàíü÷æîó, Êèòàé
á Ôàêóëüòåò ìàøèíîñòðîåíèÿ è ýëåêòðîíèêè, Ëàíü÷æîóñêèé òåõíîëîãè÷åñêèé óíèâåðñèòåò,
Ëàíü÷æîó, Êèòàé
Âûïîëíåíû ýêñïåðèìåíòàëüíûå èññëåäîâàíèÿ òðåùèíîñòîéêîñòè �-ñïëàâà íà áàçå TiAl ñïëà-
âîâ ïðè ðàçëè÷íûõ òåìïåðàòóðàõ. Îöåíåíî âëèÿíèå òåìïåðàòóðû íà õàðàêòåðèñòèêè ðîñòà
óñòàëîñòíîé òðåùèíû è îïðåäåëåíû ôîðìóëà, îïèñûâàþùàÿ åå ñêîðîñòü íà ó÷àñòêå II
(îáëàñòü ðàçâèòèÿ), à òàêæå êîíêðåòíûå çíà÷åíèÿ êîíñòàíò óðàâíåíèÿ ñ èñïîëüçîâàíèåì
ýêñïåðèìåíòàëüíûõ ðåçóëüòàòîâ. Èñïûòàíèÿ ïðîâîäèëè â âàêóóìå ïðè òåìïåðàòóðàõ 25, 750
è 850�C. Ïîëó÷åííûå ýêñïåðèìåíòàëüíûå ðåçóëüòàòû ïîêàçûâàþò, ÷òî òåìïåðàòóðà ñó-
ùåñòâåííî âëèÿåò íà ñêîðîñòü ðîñòà óñòàëîñòíûõ òðåùèí. Ïðè ïîâûøåíèè òåìïåðàòóðû
äî 750�C ñêîðîñòü ðîñòà òàêèõ òðåùèí óâåëè÷èâàåòñÿ, ïî äîñòèæåíèè ýòîé òåìïåðàòóðû
èìååò ìåñòî õðóïêîâÿçêèé ïåðåõîä TiAl ñïëàâà. Àíàëîãè÷íàÿ çàâèñèìîñòü íàáëþäàåòñÿ
òàêæå äëÿ òðàäèöèîííûõ ñïëàâîâ.
Êëþ÷åâûå ñëîâà: ðîñò óñòàëîñòíîé òðåùèíû, TiAl ñïëàâ, òåìïåðàòóðà.
Introduction. Significant interest in TiAl alloys for high-temperature structural
applications is determined by some of their advantages over conventional metallic systems
[1–3]. TiAl-based alloys are promising structural intermetallic materials, which may be
considered as potential high-temperature materials. �-TiAl alloys are highly competitive
materials for heat-resistant structural parts of aerospace, aviation, and automotive engines.
The effect of temperature can be of great significance for �-alloys as these materials
undergo the brittle–ductile transition at about 700�C [4]. Fatigue fracture at high
temperatures was predominantly intergranular, probably, due to a higher slip activity,
© R. C. FENG, Z. Y. RUI, Y. ZUO, C. F. YAN, G. T. ZHANG, 2014
ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2014, ¹ 3 149
* Report on Second Global Annual Conference “Materials Science and Engineering” (CMSE2013,
November 20–22, 2013, Xianning, Hubei, China).
inducing crack initiation in these ranges [5]. An increase in temperature enhances the
fatigue crack growth resistance only in inert environment. The fatigue resistance does not
significantly degrade with temperature, at least up to 800�C. While the fatigue crack growth
resistance is almost unaffected under 500�C, it grows above 500�C, and mainly at high
crack growth rates, which results in flatter slope of the da dN curve [6]. Therefore, it is
essential to study the influence of temperature on fatigue crack propagation in �-TiAl
alloys.
Based on the experimental data of Mabru et al. [7], the present study is aimed at
investigating the fatigue crack propagation patern in range II. The influence of temperature
on fatigue crack growth rate is investigated at three different temperatures in vacuum. Then
the propagation behavior is analyzed according to the data obtained in the experiment.
Then the modified formula for the fatigue crack propagation pattern is derived to describe
the influence of temperature on its behavior.
1. Experimental Methods. The experimental results were taken from Mabru et al. [7]
and the material used in the experiment is �-TiAl alloy with duplex microstructure. Fatigue
crack propagation experiments were performed on CT specimens. The experimental data
are shown in Fig. 1.
Figure 1 presents crack propagation rate curves obtained in vacuum for a lamellar
TiAl alloy at different temperatures and the stress ratio R � 0.1. In these tests, the three
temperatures, which are 25, 750, and 850�C, respectively, are chosen to characterize their
influence on fatigue crack propagation. The threshold values (�K th ) are similar for all
temperatures.
The experiments were carried out in vacuum to minimize interference with other
factors, like environment.
As is seen in Fig. 1, at the onset of crack growth, the three curves are close. The
behavior of the curves at 750�C is almost the same as that at room temperature, whereas the
curve at 850�C is slightly lower than those at 25 and 750�C as �K eff is increased.
2. Modification of the Fatigue Crack Propagation Rate Formula at Different
Temperatures. The complete formula of the fatigue crack growth rate covers the
near-threshold, central stable propagation and rapid propagation ranges (I, II, and III,
respectively.
R. C. Feng, Z. Y. Rui, Y. Zuo, et al.
150 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2014, ¹ 3
Fig. 1. Influence of temperature on the crack propagation pattern.
da dN , m/cycle
�K eff , MPa m
2.1. Several Formulas of the Fatigue Crack Growth Rate.
2.1.1. The Paris [8] Formula. In 1963, Paris presented the formula for calculating
crack propagation patterns under constant amplitude loading:
da
dN
C K m� ( ) ,� (1)
where �K is the stress intensity factor range, � � �K K K� �max min , and C and m are
the material constants. The formula is generally applied to various materials, but suitable
only for describing the behavior in range II.
2.1.2. The Forman [9] Formula. The Paris formula does not reflect the influence of
average stress on the crack propagation rate and does not show the effects of accelerated
crack propagation when the stress intensity factor �K approaches the critical value K c .
Considering the above factors, Forman proposed another formula of the crack growth rate
da
dN
C K
R K K
m
c
�
� �
( )
( )
,
�
�1
(2)
where K c is the critical value of stress intensity factor, R is stress ratio, and C and m are
the material constants.
This equation mainly describes the medium-rate crack propagation behavior of range
II and the rapid crack propagation of range III.
2.1.3. The Zheng–Hirt [10] Formula. Zheng and Hirt designed a reasonable model of
the fatigue crack propagation rate, termed the passivation cracking model of the crack tip
da
dN
B K K th� �( ) ,� � 2
(3)
where B represents the fatigue crack growth factor, and �K th is the threshold value. It
can be applied to describe the propagation range II and near-threshold range I. The formula
is simple and easy for engineering applications.
2.2. Modified Formula of the Fatigue Crack Growth Rate. Based on formulas of the
fatigue crack propagation rate (1), (2), and (3), the modified formula can be derived to
demostrate the influence of temperature on fatigue crack propagation of range II.
According to the above formulas and the data in Fig. 1, the modified formula for range II at
different temperatures can be presented as
da
dN
C T K eff
m� ( )( ) ,� (4)
where �K eff is the variable range of the effective stress intensity factor, m equals 3.52,
C T( ) is the temperature-dependent coefficient, T is the temperature. According to Fig. 1,
C T( ) will be 2 92 10 9. ,� � 935 10 9. ,� � and 6 18 10 9. � � when T equals 25, 750, and 850�C,
respectively.
The results can be used to plot the graph demostrating the influence of temperature on
the fatigue crack growth rate of range II (Fig. 2).
As can be seen in Fig. 1, the crack propagation rate is growing with time. Meanwhile,
as Eq.(4) and Fig. 2 show, within range II at temperatures of 25 and 850�C, the C T( ) values
are slightly lower than those at 750�C, which indicates that the fatigue crack growth rate is
fastest at a certain temperature in range II.
Influence of Temperature on Fatigue Crack Propagation ...
ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2014, ¹ 3 151
When the temperature is between 25 and 750�C, the material constant m remains
invariant, while C T( ) grows with temperature in range II. As is seen, the fatigue crack
propagation rate grows with temperature. However, when the temperature is between 750
and 850�C, C T( ) exhibited a decrease, instead of an increase. As is seen, the fatigue crack
propagation rate decreases with temperature.
In range III, growth rates increase rapidly when the temperatures are 25 and 750�C,
and the respective curves are close. The curve at 25�C is higher than that at 750�C when
�K eff increases. Although the growth rate at 850�C increases, the curve becomes flatter
and is apparently lower than the curves at 25 and 750�C. It also can be seen that the curves
are very close before entering range III. Therefore, temperature exerts a significant effect
on the fatigue crack propagation rate according to the modified formula.
3. Discussion. Based on the Paris equation, which is applicable only to the
medium-rate propagation range II, the modified formula is derived. The formula of the
temperature effect on the fatigue crack growth rate in the near-threshold range I and the
rapid propagation range III was not yet derived. If the formulas for rangea I and III were
available, the temperature effect on the fatigue crack propagation rate would be more
pronounced, as well as additional information may be gained. Numerous experiments
should be performed, and it is still very necessary to examine and derive the formula of the
whole process as regards the temperature effect on the fatigue crack growth rate.
The three basic elements of crack propagation are the elastic modulus E, the threshold
value �K eff , and the fracture toughness K c , which are the basic parameters of crack
propagation resistance. The variable range of the stress intensity factor K c is the driving
force of fatigue crack propagation. So the question, which factors are affected, should be
identified accurately in the case of temperature variation. According to Fig. 1, the three
curves at different temperatures began to deviate at different starting points, so the
threshold value �K eff may vary. The questions are how temperature affects the threshold
value �K eff and what is the magnitude of �K eff at each temperature.
It also can be seen that the three curves are close in the near-threshold (I) and
medium-rate (II) propagation ranges. When entering the rapid propagation range, the curve
at 850�C is apparently different from those at 25 and 750�C. Generally, the ductile–brittle
transition temperature is between 700–750�C. So it may be suggested that 750�C is
approximately the ductile–brittle transition temperature of TiAl alloys. This conclusion may
explain the reason why the rate of fatigue crack growth at 850�C is less than that at 750�C.
When temperature rises, the material creep occurs, and the crack propagation resistance
enhances, so the crack propagation rate drops down.
It can also be seen that the fatigue crack growth curve at 25�C comes to an end earlier
than that at 750�C, and finally this occurs to the curve at 850�C (Fig.1). That is, if the
temperature is higher, the fracture of TiAl alloys occurs earlier. It may be suggested that if
the temperature is higher, material molecules are more active, which, of course, needs
further substantiation. Further experimental verification would be required to clarify
152 ISSN 0556-171X. Ïðîáëåìû ïðî÷íîñòè, 2014, ¹ 3
Fig. 2. Influence of temperature on the fatigue crack growth rate for range II.
R. C. Feng, Z. Y. Rui, Y. Zuo, et al.
whether the facts mentioned above are correct and whether there is a fast-slow transition
temperature like the ductile-brittle temperature. The influence of temperature on high crack
growth rates is related to the variation of toughness as a function of temperature. Moreover,
different authors agree that the toughening mechanisms are still active under cyclic loading,
but solely under high crack propagation rate conditions [11, 12].
This paper examines only three temperatures, namely 25, 750, and 850�C. The curves
of temperature effect on fatigue crack propagation are few. Several sets of experiments
should be performed to get more data to demostrate the temperature effect on fatigue crack
growth rates.
Conclusions. Fatigue crack growth patterns of TiAl alloys were investigated under
three different temperatures, namely 25, 750, and 850�C in vacuum to elucidate the effect
of temperature. It turned out that, in range II, the fatigue crack growth rate increases when
the temperature is between 25 and 750�C, and the rate decreases when the temperature is
between 750 and 850�C. Therefore, when the temperature rises to a certain extent, the
acceleration of fatigue crack growth rates starts to decrease. This suggests that the fatigue
crack propagation mechanism is the same as the mechanism active in conventional alloys.
Therefore, this characteristic of alloys influenced by temperature can be used for practical
purposes.
The shortcoming of this paper is the limitation of the modified formula, which can
characterize only range II. Also, the new formula to represent the whole process influenced
by temperature is failed to be derived.
Acknowledgments. This study was supported by National Natural Science Fund of
China (51065014). R. C. Feng would like to thank Key Laboratory of Digital Manufacturing
Technology and Application, Ministry of Education, Lanzhou University of Technology for
providing help.
Ð å ç þ ì å
Ïðîâåäåíî åêñïåðèìåíòàëüí³ äîñë³äæåííÿ òð³ùèíîñò³éêîñò³ �-ñïëàâà íà áàç³ TiAl
ñïëàâ³â çà ð³çíèõ òåìïåðàòóð. Îö³íåíî âïëèâ òåìïåðàòóðè íà õàðàêòåðèñòèêè ðîñòó
òð³ùèí â³ä óòîìëåíîñò³ ³ âèçíà÷åíî ôîðìóëó, ùî îïèñóº ¿¿ øâèäê³ñòü íà ä³ëÿíö³ II
(îáëàñòü ðîçâèòêó), òà êîíêðåòí³ çíà÷åííÿ êîíñòàíò ð³âíÿííÿ ç âèêîðèñòàííÿì åêñïå-
ðèìåíòàëüíèõ ðåçóëüòàò³â. Âèïðîáóâàííÿ ïðîâîäèëè â âàêóóì³ çà òåìïåðàòóð 25, 750
³ 850�C. Îòðèìàí³ åêñïåðèìåíòàëüí³ äàí³ ïîêàçóþòü, ùî òåìïåðàòóðà ñóòòºâî âïëèâàº
íà øâèäê³ñòü ðîñòó òð³ùèí â³ä óòîìëåíîñò³. ²ç ï³äâèùåííÿì òåìïåðàòóðè äî 750� Ñ
øâèäê³ñòü ðîñòó òàêèõ òð³ùèí çá³ëüøóºòüñÿ, ïðè äîñÿãíåíí³ ö³º¿ òåìïåðàòóðè ìàº
ì³ñöå êðèõêîâ’ÿçêèé ïåðåõ³ä TiAl ñïëàâó. Àíàëîã³÷íà çàëåæí³ñòü â³äì³÷àºòüñÿ òàêîæ
äëÿ òðàäèö³éíèõ ñïëàâ³â.
1. D. M. Shah and D. N. Duhl, “Evaluation of multicomponent nickel base LI2 and other
intermetallic alloys as high temperature structural materials,” MRS Proc., 81, 411–418
(1986). DOI: http://dx.doi.org/10.1557/PROC-81-411 (About DOI).
2. G. Sauthoff, “Intermetallic phases – materials development and prospects,” Z. Metall-
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