ESDU 77033-1977 变形与铸造退火态 Ti-5Al-2.5Sn 钛合金的疲劳性能（弯曲与轴向加载）

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77033

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FATIGUE OF WROUGHT AND CAST ANNEALED Ti–5Al–2.5Sn TITANIUM ALLOY

(In bending and under axial loading)

1. NOTATION

Both SI and British units are quoted in the notation but throughout the Item only SI units are used. For

convenience the following conversion factors are provided.

2. INTRODUCTION

This Item presents data on the fatigue strength of the 5 per cent aluminium, 2.5 per cent tin, titanium alloy

at normal room temperature. Data are presented for this alpha phase alloy (alpha transus temperature 950°C)

in the annealed condition for forged bar, forged sheet, rolled sheet and castings. The mechanical properties

and details of the specimens are given in Table 6.1. The tensile strength and 0.2 per cent proof stresses

quoted in the table have been obtained from tests on specimens cut from the same material as were the

fatigue test specimens.

3. NOTES

Fatigue data are provided for forged bar specimens axially loaded and in bending, sheet specimens in

bending and cast specimens loaded axially. The curves are presented in terms of KtSa/ft , so that comparisons

of the fatigue strength of plain and notched specimens can be made. The effect of variations in the value

of mean stress, represented by the ratio , were available only for the cast material data.

0.2 per cent proof stress N/m2lbf/in2

tensile strength N/m2lbf/in2

elastic stress concentration factor based on net area

endurance

alternating stress, based on net area N/m2lbf/in2

mean stress, based on net area N/m2lbf/in2

mean stress at stress concentration, Kt Sm or N/m2lbf/in2

′

pKtSa if KtSaSm

() f

–

MN/m2145.038 lbf/in2

1 m 39.37 in

′/ft

Issued December 1977

ESDU product release: 2006-01. For current status, contact ESDU. Observe Copyright.

北极星标准文库-高清标准规范分享平台 www.bjxwk.com

77033



4. PRESENTATION OF DATA

4.1 Forged Bar

Figure 1 presents data for plain and notched (Kt = 4.2) forged bar axially loaded. Figure 2 presents data for

plain and notched (Kt = 3.6) forged bar under rotating bending. On these two figures, the curves for the

notched data have been drawn by eye using the logarithmic mean endurances and the curves for the plain

specimen data have been drawn by eye through the main body of the data. Comparison of these two figures

shows that the axially loaded specimens have lower fatigue endurances for given values of KtSa/ft for both

the plain and the notched specimens; the difference between the two sets of curves is largest at very high

endurances.

4.2 Flat Specimens Made from Rolled Sheet and Forged Sheet

Figure 3 presents data for flat specimens (4 mm thick) in reverse bending made from both rolled sheet and

forged sheet. Plain and notched specimen data are presented for specimens made from forged sheet. The

plain specimens were considered to be slightly notched, with a Kt = 1.2 , obtained from Derivation 1. The

notched specimens were of two types, one with symmetrical edge notches (Kt = 6.7) and the other with a

central hole (Kt = 2.8). Only plain specimens were made from the rolled sheets with the longitudinal axis

of the test pieces cut parallel to the direction of rolling.

Curves have been drawn by eye using the logarithmic mean of each set of data, except the plain specimen

forged sheet data where the curve has been drawn by eye through the main body of the data. These particular

data show that there is a very significant difference between the fatigue strengths of plain specimens

manufactured from rolled sheet and plain specimens manufactured from forged sheet. The rolled sheet

specimens have very much higher fatigue strengths than the forged sheet specimens at high endurances and

appear to show a fatigue limit at values of KtSa/ft of about 0.6. The differences in endurance between the

forged sheet specimens and the rolled sheet specimens are probably due to the differences in their

microstructure, the forged sheet specimens tending to have a coarser grain structure than the rolled sheet

specimens.

4.3 Machined Cast Alloy

Figures 4 and 5 present data for axially loaded plain and notched flat bar specimens, approximately 1.8 mm

thick. These specimens were cut from investment castings that were produced using a “lost-wax” casting

process.

Figure 4 presents data for plain specimens and Figure 5 presents data for specimens with symmetrical edge

notches (Kt = 3.0). On Figure 4, curves have been drawn by eye using the logarithmic mean endurances of

the data for two values of mean stress. The scatter in the test results for mean stress values in the range 0.25

to 0.33 was too large for a reasonable curve to be drawn. The large scatter in these test results may be

associated with the differences in the microstructure of the individual test specimens. The figure shows that

the fatigue strengths of plain specimens made from casting material are sensitive to changes in the value

of mean stress. On Figure 5 there are insufficient data for curves to be drawn to show the effects of variations

in the values of mean stress on fatigue endurance and therefore only a curve for zero mean stress is presented.

When predicting fatigue lives of components made from cast alloy, it is recommended that testing of

samples manufactured by the particular process to be employed be carried out (see Item No. 77027*,

Section 7).

*Data Item No. 77027 “Fatigue of wrought and cast Ti–6Al–4V titanium alloy. (In bending and under axial loading)”.

ESDU product release: 2006-01. For current status, contact ESDU. Observe Copyright.

北极星标准文库-高清标准规范分享平台 www.bjxwk.com

77033

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5. DERIVATION

1. PETERSON, R.E. Stress concentration design factors. John Wiley and Sons Inc., New

York, USA, 1953

2. HEMPEL, M.

HILLNHAGEN, E. Dauerschwingfestigkeit der technischen Titanlegierungen. Archiv für

das Eisenhüttenwesen, Vol. 37, No. 3, 1966, pp. 263-274. Translated as,

The fatigue strength of commercial titanium alloys, RAE Lib. Trans.

No. 1353, Farnborough, UK, March 1969.

3. McCLAREN, S.W.

COOK, O.H.

PASCADOR, G.

Processing, evaluation and standardization of titanium alloy castings.

Air Force Materials Laboratory, Wright Patterson Air Force Base, Ohio,

USA, AFML-TR-68-264, April 1969.

ESDU product release: 2006-01. For current status, contact ESDU. Observe Copyright.

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标签： #合金 #变形 #铸造

摘要：

本页面详细介绍 ESDU 77033-1977 标准规范中关于变形与铸造退火态 Ti-5Al-2.5Sn 钛合金在弯曲与轴向加载条件下的疲劳性能数据。该文档为工程设计与材料选型提供权威参考，涵盖合金在不同热处理状态（变形与铸造退火）下的疲劳强度、S-N 曲线及加载方式差异对比。适用于航空航天、医疗器械及高端制造领域中对钛合金疲劳寿命评估有严格要求的专业人员，帮助优化结构件的耐久性与可靠性设计，提升产品安全性与使用寿命。

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ESDU 77033-1977 变形与铸造退火态 Ti-5Al-2.5Sn 钛合金的疲劳性能（弯曲与轴向加载）

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