Low cycle fatigue, creep and creep-fatigue behaviour of forged thick section tube plate of 9Cr1Mo ferritic steel

Fatigue austenitic These

ate&.

3 16LN

materials

satisfy

RCCMR.

The and

fast

particularly

used

The

crack

gated

considering

aging

to simulate

stainless

steel

(FCC)

these

materials

the

long

a scale

of

of

bounded

is used The

for

threshold in

use effects. These

nocivities Graphs.

FCG

T9l

crack

and

for

water

are more

in fast

reactors.

were

and

after

a thermal of

compared

each

to obtain

components,

in

order

Fatigue properties of materials surface hardened by plasma laser beam. Maznl, P., Dlouhy, 1. crnd St&r, P. Mnterrcrls md Mntwfimrring Procrsscs ( 1997 1 12. 83-93 Carbon

steel,

ively,

investi-

characteristics

are then

structural

studied.

RCCM

steels

propagation state

The

were

in

steam-generator

results

in

T91,

components and

a normalized

term

propertie\.

many 800

and

analyzed.

default

steel indicated

in

Alloy

as materials

growth

are succea\ively

one ferritic

specifications

reactors.

or proposed

siles

800 and

nuclear

nuclear

material define

Alloy

the

3 16LN

pressurized fatigue

and

Asbstracts

to

were

low

temperature

and

treatment

layers

nucleation, show

thick

without as the life.

Detailed

investigations

(LCF),

creep

and

thick

9Cr-IMo

with

increasing the

thin

tube

of

steady

state

-5-6

behaviour mation

in

for

9Cr-

thin

sections. showed

Graphs,

I4

increased was

the

the

exponent

of

- 4 and

found

time

data

of unity

and

both

the

The

and

under

\lope energy defor-

regimes.

compared

The

to those

using

linear

damage

summation

this

material

could

be conscrva-

for

Very

Important are often

sory

definitions

tests

and

terms of

numerical

and

the

arc

way

given.

of

and

urgent.

to

he

an

of compul-

methods

of

The

sine

arc

outstanding

purposes,

is

are

discussed

numerical

data,

27 ref.

Z

RP

and

hah no

coating

of the

the

the

the

associated

of of

the

factors

affecting

fatigue

layer

on

surface

the

findings from grain

the

growth

method

improved

by

nitriding. of

from

not only strength

titanium

ordinary

found

layer

with

nitriding. resistance

titanium.

Graphs,

by

low

grain and

effect

Al 9

number

of

fretting

7 IX alloys

under

mechanics-based predict initial

flaw

Thib for

lifting

fatigue

lives

\ize

tests

closely

controlled

model under

wab used

approach

was

different

fatigue

\ize.

nitriding

fracture

The and

low-temperature

growth.

This

the corrosion

found

values

photomicrographa.

developed

a range

of

to describe to give

of I5

was

bulk

carried

I4

and

stress

the

hut

until

Paris

and

early

the

steel A

Law

same

the

life

fretting

to

effective

failure

in

element under

a crankshaft

(FE) load.

introducing stress

point

plate.

The

component.

analysis The

to derive

novel

a crack

is examined fatigue

limit

compared

to experimental

prediction

was

the

technique

of

the

technique

a component;

the

and

compared

to

for

a crankshaft

threshold

data.

The

stress

only intensity

here

uses

a &tress Intensity

feature into

The

is used factor

load.

is that stress

field

Graphs,

for

around

for

was

successfully

range,

a standard parameter f1

predict

fatigue

elastic the

finite

component

K is calculated

that material

to

a linear (0

uncoated

a\ well on fatigue

limit.

At

The by

amplitudes,

coating

Ar

Initiation

Graph\.

on fatigue 0

crack

line

no

and

tensile

of

the

propertie\:

the

for

alloy.

due

to the slip appear

tricrystal\. Cu-AI

The

Sigma

9

triple

photomicrographa.

The

notch

the

triple

tip

against

junctions

under

Cu.3

at.%

hound-

along

the

before

depends

crack

rate the

zone.

The

fracture

present

upon

growth affects

intergranular

u

can he drawn. beginning

junction

the

the

intergranularly

in the boundary-affected

strong

of

grain

retardation

of

amplitude\

m Cu and

is found of

retardation

concentration to he very

degree

the

and copper-3

conclusions

rate

shift

8 ref.

propagated

following

growth

the

improvo-

strehh

) adjoined

at the

ax,?, and

The

its

growth

initiated

crack

both

than

3-

heen

the

for

Cu

3 boundaries

has

may

in copper

9(22l

or

at

improvement

propagation

3( I I 11-w

was encountered.

retardation

jtmctlon

Sigma

to

behaviour

a \light

high

and

Thuh,

initiation

photomicrographa,

crack

I 1)-u

3( I

fatigue

crack Hence.

is ohwved.

crack

the

surface.

a coating

of the specimens.

IS mainly Therefore,

amplitudes

specimen

lifetimes.

investigated

S 6-S-2

stress

were

process.

micropIpe\.

high

the

governed

contin g

52100)

was

steel

and

at

mean stress

6 (AISI

specimens

of the uncoated

mainly

on

by

The

for

I\

crack Sigma

in Sigma

testing

condition\.

24 ref.

On the dual slope Coffin-Manson relationship during low cycle fatigue of nickel-base alloy IN 718. Bhottctchnryn. A.. Strstry ti. V.S. wzd Kutwnhunw. V. V. Scripto Matc~ricrlicr ( I997 ) 36, 4 I I3 15 A

detalled

the

without maximum

centre-cracked predicted, required

K,h. Graphs,

TEM

study

has

tests interrupted the

reason

in

the

alloy

IN

In

the

low

strain

the

high

(c)

Change

in

been

after

for

conducted

different

The

dual

following

region

the

deformation

mode

of

slope

plot

from

by

rewlted

in

cycle

amplitudes temperature

this

is essentially occur\

low

strain

at room

emerge

principally has

from

ar two

C-M

mode

deformation

photomicrograph\,

specimens

of cyclea

conclwiona

deformation

region

on

number

the observed

718.

strain

Graphs.

study:

twinning.

slip

hand

dual

(a)

(h)

In

formation.

slope

C--M

plot.

12 ref.

Variability of fatigue crack growth properties for 2024-T3 aluminium Oldervntr. A. (2nd Wmhill, R.J.H. Nrrtimnl Aemrpnw Lohorrrtor~ NLR. Amsterdam. Netherlands ( 1996)

alloy.

Discussions

varw

bility

in

when for

14 ref.

this

between

D-BAA

fatigue

crack

damage

tolerant

aluminium

reasons:

(1) design such

as

of

changes

aging. sheet

and

an

refer

In

NLR

is any

From

the

term

natural

in

fatigue

T3.

The

long

results

it can

aging crack

effect

batch-to-batch when

term

long

are done

sheet.

This

comparison\ properties

a comparison from

1966) Two

to

NASA

the same aging

properties term The in

effect

important

were

on fatigue

crack

is possible is of

less cycle air.

for than

used

similar

frequency Graphr,

has

numerical

properties.

effect

to

of

long

variability

batche\ to

of which

to determine

Significant

different or

Al

variahihty

growth

is a significant

the term

1958-1959)

1969-1988).

of material,

of 2024.T3.

is

2024-T3

batch

(from

two

long

(from

effect

there

to

between to

for

candidate topic

owing

batch

standard

different

reports

reports

properties

laboratory

industry

batch that

aging

significant

the

IS Important

made

NASA

examine

other

growth

was

two

that

of

Another

be concluded

variation. test\

(2)

for

tolerance

natural

growth

shown

2024.T3.

from

on crack of

2024-T3 and

obtained

rates.

have

is possible

with

(from

growth

NLR

damage

report,

growth

to test specimens

if there

even

in

report

crack

alloy,

601%T6, thi\

crack

the

properties

assumptions

materials,

alloy

and

growth

possibility

fatigue

modelling,

homogeneous

hardening intlucnce

100 Cr

fatigue

low

by

junction

greater

A

as crack

of he

can

of cracks. of specimens

ref.

known

limit

perpendicular

material

natural

techmque,

is

At

containing

the triple

Prediction of fatigue failure in a crankshaft using the technique of crack modelling. Tczylor, D., Cirpalowicr., A.J., Rogers. P. ond Devlukin, J. Fotipe wld Fmmre of En@wirzg Mntrrials and Structures ( 1997) 20, 13-Z I new

influence

and

fracture

employed An

propagation

of fatigue

hut

iron

and

DC-magnetron-sputtering

i), initiated

higher 6

and

clusters

the

mfluence

of triple

significant

fatigue

ref.

CMV

conditions.

predictions under

on

thin surface

and

cast

treatment

resistance

conditions.

experimental

initiation

good

out

experimental

the

negative

carbide

to the interior

no

is examined.

Graphs,

result\

strength

photomicrographc,

were

Cr

he achieved

boundary

3-

Analysis of crack initiation and propagation in fretting fatigue: the effective initial flaw size methodology. Fellow, L.J., Now//. D. ond Hills, D.A. Frrti,qrr nnd Fwctrm of Eqinwring Motrrirrls and Structures ( 1997) 20, 6 I-71) lNC0

like

causes 100

fatigue

tricrystah

to find

A

weaken

very

crack

thickness

the grey

relationship

grain

Furthermore

10 oppress

the wear

the

strength

clardied.

of the compound

a Hall-Petch and

fatigue

were

strength

titanium

in the

proposed

of

nitrided

We

nitrided

of the compound

24 h) was

fatigue

of

on the fracture

the reduction

occurring

(620°C.

the

that

strength

strongly

strength

formation

nitriding aho

the

fatigue

indicated hoth

fatigue

depended

formed

between

the

strength

and limit

material

specimens.

ha\

can

coated

on

M2)

a reactive

fatigue

influence

place

the

lifetime

of

wrface

initiation

(AISI

by

defects

steel

coating

A

Factors controlling the fatigue strength of nitrided titanium. Moritn. T.. Tokrrhoshi. H., Shimix M. and Kmvosoki. K. Frrri,que nnd Froctwr of Enginrering Mrrteriols and Structures ( 1997) 20, X5-92 The

yield

S 6-S-2

uncoated

uncoated

the triple

The

of

10 the almost

The

internal

of

ariea

evaluation Both

by

a coating

The

planning

reviewed.

evaluation

case

layer

with

hardening

Effect of triple junction on fatigue crack growth at.% aluminium tricrystals. Vi,qyodov. A. mrd Hoshimofo. S. Scripto Motrri&~ ( 1997) 36. 4 I7--123

minimum

introduction

be

proved

Graphs,

strength

this,

to statistical to

10 engineering

graphical

papers

has

fatigue

avoid

regard ,eems

now

regard

i.e., To

with

resulta

until

special

testing,

terms

their

which

with

probability

fatigue

ambiguously.

these

analyzing

transformation. method

of

the

heads

nitride

bending.

failure

ment

interpreted

in

of discontinuous

behaviour

cychc

governed

the

life.

layer

Application

steels

titanium

fatigue

surface

effective tool for graphical and numeriexperiments.

of the

with

crack

ref.

Arc sine root P transformation-an cal evaluation of planned Wohler &ngr/. D. nrzd Khoni. K.

can

surface

hardened

fatigue

12 ref.

Specimens coated

dis-

creep

stress

(graphite)

case

Fatigue properties of steel coated with TIN by a PVD process. Bomns. H., Mopr, P. md Kurth. B. Motericds md Mmuf~~cturir~,q Procrssr.s C1997 1 12. 17-27

and

a single

that

overlapping

Graph\.

stresses

activation

to he lower

to

dependence K)

stress, a true

oxidation.

compared

(773-873

suggested

in

was

strain

10.2 at high

resisting

observations

decreased

stress

two

constituent

materials

the

hardened

obtained

mhomogeneous effects

layer.

the

influences

and

all

300mm

was attributed

lower

negative

surface

case

For

of

reapect-

fatigue

and

forging

The

law of

of

controlled

hold

size.

power

cycle

in life

to be

grain

concept

damage

inelastic

exponents

These

of

total

of

found

Norton’s

forging

Analysis that

with

is climb

plate

resistance

low

diameter

K) and the reduction

stress

stress

the

IOOOmm

forging

with

steel

tube

to evaluate

of

LCF

obeyed

obtained.

IMo of

out

to its coarse

Invoking

were

approach tivc.

rate

a unified

strength

the

hehaviour

stresses.

with

of

ascribed

creep

of - 250 KJ/mol creep

forging.

associated

was

slope

at low

carried hehaviour

(723-793

resistance

and

two

plate

effects

LCF

sections

played

been

temperature

to the combined Also,

have

creep-fatigue

these

the

that

results

steel,

and

hardening

curves.

homogeneity

factor

than

structural

transformation

(Wohler’s)

the

Contradictory

and

laser

on S-N

important

but

cast iron, of

important

a microstructural

hardened

B.P.

most

more

high

grey effect

examined,

to be the

relatively

steel the

nitriding

of hardening.

that

the

Low cycle fatigue, creep and creep-fatigue bebaviour of forged section tube elate of 9Cr-1Mo ferritic steel. Choudhnry. B:K.. Bhnnu Sankam Rae, K., Mnnnon, S.L. and Koshyp, Cmfrrmre: Ewrmor Y6, Bournemouth, UK (21-23 Oct. 1996)

plasma

much

level

bearing

to determine

conditions

seems

total

4 ref.

standard used

nitriding

the

of

2024.

effect

he considered data,

6 ref.

of