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CREEP AND STRESS-RUPTURE

STRENGTH

HAYNES

188 alloy is a solid-

solution-strengthened material

which combines excellent high-

temperature

strength

with good

tabricability at room tempera

ture.

It

is particularly effective

for very

long-term

applications

at

temperatures

of 1200°F

50°C) or

more. It

is stronger

than nickel-base solid-solution-

strengthened alloys, and far

stronger than

smple

nckel

chromium

or

iron-nicke

chromium

heat-resistant alloys.

This

can allow for

significant

section

thickness reduction

when

it

is substituted for these

materials.

COMPARISON OF SHEET MATERIALS: STRESS TO PRODUCE 1

CREEP

IN 1000 HOURS

1600°F

CREEP

AND

RUPTURE STRENGTH

COLD-ROLLED AND

2150°F

1175C) SOLUTION-ANNEALED SHEET

Test

Temperature

°F °C)

Approximate

Initial

Stress,

Ksi

MPa)

to

Produce Specified

Creep in:

TEST TEMPERATURE

230

900°c

950°c

iooo°c

15

750°c 800°C 850°c

10

x

625

6

15

5

600

0

ft

3

2

0.9

I

1400°F 1500°F

TEST

TEMPERATURE

100

90

80

70

60

50

40

30

Ct

a

C’)

0

Ui

0

0

1700 F

10

1800°F

Creep,

10 Hrs.

100

Hrs. 1,000 Hrs.

1400 760)

0.5 22.5 155) 16.4 115) 11.7 81)

1.0

25.5

175) 18.5

130)

13.3

92)

Rupture 43.0 295) 32.0 220) 23.0 160)

1500 815) 0.5 15.5

105) 11.1 77)

7.8 54)

1.0 17.6

120) 12.6 7) 8.8 61)

Rupture 31.0 215) 21.7 150)

15.0 105)

HAYNES 188

alloy

4

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CREEP AND

RUPTURE STRENGTH

COLD-ROLLED

AND 2150°F 175°C) SOLUTION-ANNEALED SHEET continued)

Approximate

Init ial Stress,

Ksi

MPa)

to Produce

Specified

Creep in:

1

Hrs.

HOT-ROLLED

AND 2150°F 175°C) SOLUTION-ANNEALED PLATE

Test

Temperature

°FrC)

Creep,

1 0 H rs . 1 ,000 Hrs .

1600

70) 0.5

10.7

4) 7.5 52) 5.0 34)

1.0

12.2 4) 8.4 58) 5.7 39)

Rupture

21.0 145)

14.4 99)

9.4 65)

1700 925) 0.5 7.3

0) 4.9 34)

3.1 21)

1.0 8.2 57) 5.6

39)

3.6 25)

Rupture 14.3 99) 9.1 3) 5.5 38)

1800

80) 0.5 4.9 34) 3.1 21)

1.8

12)

1.0

5.6 39) 3.6 25) 2.1 14)

Rupture 9.1 63)

5.4

7) 2.4

17)

T

Approximate Initial Stress, Ksi MPa)

Temperature

Creep,

to Produce Spec if ied

Creep in:

°F °C) 10 H rs. 100 H rs .

1,000

Hrs. 10,000 Hrs.

1300

05) 0.5 42.0 289) 28.0 193)

18.0

124) —

1.0

48.0 339) 32.5 224) 22.0 152) —

Rupture

76.0

24)* 56.0

386)

40.0 276)

28.0 193)*

1400 760)

0.5 26.0 179)

17.0

117) 11.5 79) —

1.0

29.0 200) 20.5 141) 14.0 97) —

Rupture

52.0 359) 37.0 255) 26.0 179)

18.5

128)

1500 815) 0.5 17.0

117)

11.0 6) 7.4 51)

—

1.0 19.0

131)

13.5 3) 9.3

64) —

Rupture 36.0 248) 25.0 172) 17.5 121) 12.0 83)

1600

70) 0.5

11.5

79)

7.5

52)

5.0 34)

1.0 13.0

0) 9.0 62) 6.4 44)

Rupture

25.0 172)

17.0

117)

11.6 0) 7.8

54)*

1700 925)

0.5 8.0 56) 5.2 30) 3.4 23) —

1.0

9.2 63) 6.0 41) 4.0 28) —

Rupture 16.5 114) 11.1 77) 7.3 50) —

1800

980)

0.5

1.0

Rupture

•S gniticant extrapolation.

5.6

6.3

11.5

39)

43)

79)

3.6 25)

3.9 27)

7.0

48)

2.3 16)

2.9

20)

4.3 30)

HAYNES

188

alloy

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TYPICAL TENSILE PROPERTIES

COLD-ROLLED AND

2150°F 175°C)

SOLUTION-ANNEALED

SHEET

HOT-ROLLED

AND

2150°F

175°C)

SOLUTION-ANNEALED PLATE*

Test

Temperature

°F °C)

Room

1000 540)

1200 650)

1400

760)

1600

870)

1800

980)

2000 1095)

2100 1150)

2200 1205)

* mited

data.

Ultimate

Tensile

Strength

Ksi MPa

142.6

985

112.6 775

109.8 755

94.0 650

65.3 450

38.7

265

21.0

145

13.9 96

12.0

83

0.2

Yield

Strength

Ksi

MPa

68.5 470

39.9

275

38.3

265

38.9 270

36.1 250

27.1

185

12.8 88

6.9 48

4.0

28

Elongation

in 2 in. 51 mm)

56

69

73

70

77

84

89

60

71

IMPACT

STRENGTH

PROPERTIES*

Ft-lbs. Joules

-300 -185)

116 158

-150 -100) 131

178

70 20)

143 194

1000 540) 117

159

1300

705)

107 145

*Avemge

of longitudinal and

transverse

tests on

solution-annealed

plate

Ultimate

Test Tensile 0.2

Yield Elongation

Temperature Strength Strength

in

2 in.

51

mm)

°F °C) Ksi

MPa

Ksi MPa

Room 137.2 945

67.3

465 53

1000 540)

108.5 750

42.0

290 61

1200

650)

103.3 710

39.7 275

59

1400 760)

89.9 620 38.9 270

63

1600

870) 60.0 415 35.9 250

64

1800

80) 35.2

245 19.0 130 59

2000

1095)

18.7

130 93

64 32

Test

Temperature

°F

°C)

Typical Charpy V-Notch

Impact

Resistance

HAYNES

188

alloy

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THERMAL STABILITY

HAYNES® 188 alloy is

similar

to

the

solid-solution-strengthened

superalloys, such

as

alloy 625

or HASTELLOY® X alloy, which

will precipitate deleterious

phases

upon such long term

exposure.

In

this case, the

phase

in question is a

C02W

laves phase, which serves to

impair both tensile

ductility and

impact

strength.

The behavior

of 188 alloy is significantly bet

ter

in this regard than HAYNES

25

alloy,

which it replaced; but

for applications where thermal

stability

is

important, 230°alloy

is

recommended.

ROOM-TEMPERATURE

PROPERTIES OF PLATE AFTER THERMAL

EXPOSURE

Ultimate

Exposure Tensile

Temperature Strength

°F

°C)

EXPOSURE

TEMPERATURE °C)

AT

500

600

70 0

800 900 1000

I I I I I I

2

~

.

Retained Room-Temperature

Tensile

Ductility

after 8000

z Hour Exposure

at

Temperature

9 5f3

uJ

Ui

j

E5 40 -

z

Ui

~

D

20

0-

2

Lii

I 10

2

0

RT

1000 1200 1400 1600 1800

ExPOSURE

TEMPERATURE

°F)

0.2 Yield

Elongation

Impact

Strength

in

2 in.

51

mm)

Strength

Hours

Ksi MPa

Ksi MPa Ft-lbs.

Joules

1200

0

140.0

965 65.0 450 56.0 143 194

650C)

8000

151.6

1045 79.7 550 29.1 23 31

1400 0 140.0 965 65.0 450 56.0 143 194

7600) 8000

147.9 1020

74.0 510 10.8 3 4

1600

0* 146.0

1005

70.1 485 50.4 143 194

8700)

1000 157.5 1085

70.7 490 28.7 10 13

4000

156.0

1075 68.8

475

26.6 10 13

8000*

147.4

1015 64.5 445 22.2 9 12

16000 146.1 1005

63.8

440

24.0

8 11

Average

of two

test

exposures. All

others single exposures.

COMPARATIVE

IMPACTS

ENOTH AFTER

8000-HOUR

EXPOSURES

Solution-Annealed Charpy V-Notch Impact Following Exposure

Charpy

V-Notch

Impact

For

8000 Hours

at Temperatures, Ft-lbs. Joules)

Material Ft.-lbs.

Joules) 1200°F 50°C) 1400°F

60°C) 1600°F 870°C)

230® alloy 54 73) 30 41)

21

28)

21

28)

188

a by

XalIoy 54 73) 15 20) 8 11) 15 20)

625 alloy 81 110)

5

7) 5 7) 15 2’

7 HAYNES

188

aloy

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TYPICAL PHYSICAL

PROPERTIES

Temp., °F British Units Temp.,

°C

Metric Units

Density Room 0.324 Ibm Room

8.98

9/cm

Melting

Range

2400-2570 1315-1410

Electric Room 39.6 microhm-in.

Room 101.0 mcrohm-cm

Resistivity 200 40.3

microhm-in.

100

103.0 mcrohm-cm

400 41.5 microhm-in. 200 105.0

mcrohm-cm

600

42.7

microhm-in. 300 107.7 microhm-cm

800 43.8 microhm-in. 400 110.5 microhm-cm

1000 44.7 microhm-jn. 500 112.7 microhm-cm

1200

45.6 microhm-in. 600 114.8

microhm-cm

1400 46.1 microhm-in. 700 116.4 microhm-crn

1600 46.5 microhm-in. 800

117.5 microhm-cm

1800

46.7

microhm-in.

900

118.3 microhm-cm

2000 46.8 microhm-in.

1000 119.1 microhm-cm

Thermal Diffusivity

Room 4.5

x

10~ mY/sec. Room

29.2

x 10~ cm7sec.

200 5.0

x

10~ in.2/sec. 100

32.7 x

10~ cm2/sec.

400

5.6

x

10~ in.2/sec. 200

36.5

x 10~

cm2/sec.

600

6.Ox

10~ in.2/sec. 300 38.7x10~ cm2/sec

800

6.4

x

10~ nY/sec.

400 40.8

x 10~ cm2/sec.

1000

6.7 x 10

n.2/sec.

500 43.5 x 10~

cm2/sec.

1200 7.1

x

10

in.2/sec

600 45.7

x

10 ~

cm2/sec.

1400 7.6

x

10 in.2/sec. 700 48.2 x 10~

cm2/sec.

1600 7.6

x

10

nY/sec. 800

50.4

x

10~ cm2/sec.

1800

8.0

x

10

in.2/sec.

900 50.4

x

10~

cm2/sec.

2000

8.4 x 10 n.2/sec. 1000

53.0

x

10~ cm2/sec.

Thermal

Conductivity Room 72 Btu-in./ft.2 hr.-°F Room 10.4

W/m-K

200 84

Btu-in./tt.2

hr.-°F 100 12.2

W/m-K

400 100

Btu-in./ft.2

hr.-°F 200 14.3 W/m-K

600

112 Btu-in./ft.2 hr i’

300

15.9 W/m-K

800

125 Btu-mn./ft.2

hr.-°F 400 17.5 W/m-K

1000 138 Btu-in./ft.2

hr.-°F 500

19.3

W/m-K

1200 152 Btu-in./ftYhr.-°F 600 21.1

W/m-K

1400 167 Btu-in./tt.2

hr.-°F

700

23.0 W/m-K

1600

174

Btu-in./tt.2 hr-i’

800 24.8 W/m-K

1800 189

Btu-mn./ftY

hr.-°F

900 25.5

W/m-K

_______________

2000 204 Btu-in./ft.2

hr i’

1000

27.6

W/m-K

HAYNES

188

alloy

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Temp.,°F BritishUnits Temp.,°C MetricUnits

SpecificHeat Room 0.096BTU/lb.-°F Room 12.1J/Kg-K

200 0.101BTU/lb.-°F 100 423J/Kg-K

400 0.106BTU/lb.-°F 200 444J/Kg-K

600 0.112BTU/lb.-°F 300 465J/Kg-K

800 0.117BTU/lb.-°F 400 486J/Kg-K

1000 0.122BTU/lb.-°F 500 502J/Kg-K

1200 0.127BTU/lb.-°F 600 523J/Kg-K

1400 0.131BTU/lb.-°F 700 540J/Kg-K

1600 0.136BTU/lb.-°F 800 557J/Kg-K

1800 0.140BTU/lb.-°F 900 573J/Kg-K

2000 0.145BTU/lb.-°F 1000 590J/Kg-K

MeanCoefficientofThermalExpansion

70-200 6.7microinches/in-°F 25-100 12.1μm/m-°C









25-1000 16.5μm/m-°C

Temp.,°F

DynamicModulusofElasticity,10

6psi Temp.,°C

DynamicModulusofElasticity,GPa

Room 33.6 Room 232200 32.8 100 225

400 31.5 200 217

600 30.2 300 209

800 28.9 400 201

1000 27.6 500 193

1200 26.2 600 184

1400 24.9 700 176

1600 23.6 800 169

1800 22.3 900 161

2000 21.0 1000 153

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LOW

CYCLE

FATIGUE PROPERTIES

HAYNES® 188 alloy exhibits for strain-controlled

tests

run machined from bar. Tests were

very

good low

cycle fatigue

in

the temperature

range

from

run with

fully reversed strain

properties

at elevated

tempera- 800°F 425°C)

to 1600°F

R

= -1) at a frequency of

tures. Results shown below are 870°C).

Samples

were 20 cpm 0.33 Hz).

COMPARATIVE LOW CYCLE FATIGUE

PROPERTIES

The

graph below

compares 60°C)/1

000 hour pre- again

run with

fully reversed

the low

cycle

fatigue

lives of

a

exposed condition.

Samples strain

R

—

1)

at

a

frequency

of

number of alloys tested at were machined from plate

or 20

cpm 0.33

Hz). TSR = Total

800°F 425°C)

in both the bar,

after

exposure

for

ex- Strain Range.

as-received and 1400°F

posed

samples.

Tests were

800°F

25°C)

LCF

Life for Various Alloys

0

0

188 230

X

625 617 188 230

X

625 617

As

Received

1400°F

60°C)/1000

Hr

prior exposure

w

CD

z

z

1)

2.5

2.0

1.5

1.0

0.9

0.8

0.7

0.6

0.5

0.4

0.3

02

x

j*~discontinued

800°F 25°C)

o3

I

tl6000F

70°c)

10~

CYCLES

TO

FAILURE

10°

10~

60

TSR=

10 TSR=065

~5

.5 .5

wo

Lii

r

40

D D

30

o

I—

1)

s

— U)

w

tu 20

-3

o

0

10 —

HAYNES

188

alloy 10

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OXIDATION

RESISTANCE

HAYNES® 188

alloy

exhibits

environments, and can

be

used sures

of

short

duration,

188

very good resistance to both air

for

long-term

continuous expo- alloy can

be used at higher

and combustion gas oxidizing sure at temperatures up to temperatures.

2000°F

095°C). Fo r expo

COMPARATIVE BURNER

RIG

OXiDATION RESISTANCE

1000

HOUR

EXPOSURE

AT 1100°F

80°C)

Material Mils

pam

230® alloy 0.8 20 2.8

71

3.5 89

HAYNES® 188 alloy 35 89 4.2 107

HASTELLOY

X alloy

2.7

69 5.6 142 6.4 153

625

alloy

4.9 124 7.1 180 7.6 193

617 alloy 2.7 69 9.8 24 9

10.7

272

Oxidation

Test

Parameters

Burner

r g

ox

dation

tests were combustion of No . 2 fuel oil from the gas stream every 30

conducted

by

exposing

sam-

burned

at a ratio of

air

to

fuel

of minutes and

fan-cooled

to near

pIes 3/8

in.

x 2.5 in. x

thickness

about 50:1. Gas velocity was amb ent

temperature and

then

9

mm

x 64

mm

x thickness), in about 0.3 mach). Samples reinserted into the

flame

tunnel.

a

rotating holder,

to products of

were automatically removed

Metal

Loss

Average

Metal Affected

Mils

pam

Maximum

Metal

Affected

Mils pam

COMPARA1HVE

BURNER

RIG

OXIDATION

RESISTANCE

AT

2000°F 1095°C)

FOR 500 HOURS

OXDATION DAMAGE sM

100

200 300 400

500

600

700 800

900

Maximum

230® alloy Metal Internal

Loss Penetration

188

alloy

x alloy

617 alloy >24 mils)

625

alloy >31

mils)

5

10

15

20 25 30 35

OXIDATION DAMAGE,

MILS

HAYNES

188

alloy

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COMPARATIVE OXIDAT~ON RESISTANCE IN FLOWING

A~R*

Average Metal

Affected in 1008

Hours”

1800°F

980°C

2000°F 1095°C 2100°F 1150°C

Material

Mils

jim

Mils jim Mils jim

230®alloy 0.7 18 1.3 33 3.4 86

HAYNES® 188 alloy 8.0

203

6l7alloy

1.3

33

1.8

46

3.4 86

HASTELLOY®Xalloy

0.9

23 2.7 69

5.8 147

625 alloy

0.7

18

4.8

122

18.2

462

Flowing air at a velocity of 7.0 ftimin. 213.4

cnvmin.

past the samples. samples cycled to room temperature once-a-week.

Metal Loss + Average

Internal

Penetration.

HOT

CORROSION RESISTANCE AT 1650°F 900°C

HAYNES

188 alloy exhibits

No. 2

Fuel

oil with

0.4

percent cycled

out of the gas stream

excellent

resistance to

sulfate

sulfur. The

air:fuel

ratio was

once-an-hour

and cooled to

deposit type hot corrosion.

30:1.

Artificial

sea

water was near ambient temperature. Gas

Tests were

conducted in a low injected at a rate

equivalent

to velocity was 13 ft/sec. 4 mIs .

velocity burner

rig

burning

5

ppm

salt. Tests were

run

for

1000 hours,

with samples

Metal Loss Average Metal Affected

Material Mils

j.tm

Mils jim

HAYNES

188 alloy 0.8 20

23Oalloy 1.2

30 5.1 130

625 alloy 1.8 46 5.2 132

HASTELLOYXaIIoy 1.6 41 5.5 140

SULFIDATION

RESISTANCE

AT

1400°F 760°C

HAYNES

188

al oy has

very a gas mixture consisting of a severe

test,

with equilibrium

good resistance to

gaseous

5

percent

H2 5 percent

CO, su fur partial

pressure of 106 to

sulfidation envronments

percent CO

,

0.15 percent 10 and oxygen partia pres

encountered

in

various

indus- H2S

and 0.1

percent H 0,

bal- sures

less than that needed to

trial applications.

Tests

were ance Ar . Coupons

were

produce

protective chromium

conducted at

1400°F

760°C

in

exposed for

21 5

hours.

This is

oxide scales.

16

14

°~o 12

~~~

t 1

8

6

4

2

400

300

200

r

100

188 556 310 617 800H 625 x

HAYNES

188 a

oy

12

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SCHEMATIC

REPRESENTATION OF

METALLOGRAPHJC

TECHNIOUE

USED

FOR EVALUATING ENVIRONMENTAL

TESTS

1.

Metal Loss

=

A

8)12

2. Average Internal Penetration = C

3. Maximum

Internal Penetration

=

D

4. Average

Metal

Affected = A 8)12) +

C

5. Maximum Metal Affected

=

A

8)12) +

D

FABRICATION

CHARACTERISTICS

HEAT

TREATMENT

HAYNES 188 alloy is normally

final so ution heat-treated at

2150°F 1175 C)for a

time

commensurate with section

thickness.

Annealing during

tabricat

on can be

performed

at

even lower

temperatures,

but a

final, subsequent

solution

heat

treatment is

needed

to produce

optimum properties

and

struc

ture. Please cal l Haynes

International

for further

nforma

ton.

EFFECT OF

COLD

REDUCT~ON

UPON

ROOM-TEMPERATURE

PROPERTIES*

Cold

Reduction

Ultimate

Tensile

Strength

I

:‘E.~r

v~rt:n. 0

Subsequent

Temperature

0.2 Yield

Strength

Elongation

in

2 in. 51

mm)

Ksi

MPa

Ksi

MPa Hardness

0 137.2 945 66.9 460

54.2

RB 98.1

10

151.5 1045 105.9 730 45.1 R~32.1

20 None 165.9

1145

132.9

915

28.3

R~37.1

30 195.1 1345 167.0 1150 13.4 R~41.2

40

214.9 1480

176.8

1220

9.8

R~43.5

10

148.5 1025

91.2 630 41.4

R~29.7

20

1950°F 153.3 1055

87.8 605 41.0 R~27.8

30 158.3 1090 84.2 580 41.3 R~29.6

40 162.7 1120

90.8

625

39.8

R~31.1

10

143.0 985 64.7 445

50.1

R~21.9

20

2050°F 149.0 1025

71.4 490 47.2 R~24.5

11120°C~

30 br s mir~ 155.2 1070 80.3 555

43.7

Ac

27.6

40 159.0

1095

86.9 600 43.2

Ac

29.5

10

139,6 965

61.9

425

55.3 RB95.6

20 2150°F 141.3 975 64.9 445 53.3

A9

97.1

30 142.8 985

66.5 460 51.8 RB 98.5

40

141.5

975 64.1 440 55.5 RB 97.2

* Based upon rolling reduction taken upon 0.125 in. 3.2

mm)

thick sheet. Duplicate tests.

13

HAYNES

188

alloy

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WELDING

HAYNES

188 alloy is readi y

welded by Gas Tungsten Arc

TIG),

Gas

Metal Arc MIG),

Shie ded

Metal

Arc coated

electrodes), electron beam

welding

and

resistance

welding

techniques. Its welding charac

teristics

are

similar

to

those for

HAYNES

25

alloy.

Submerged

Arc

welding

is not recom

mended

as

this process

is

characterized by high heat

input to

the

base metal and

slow

cooIng

of the weld. These

factors can ncrease weld

restraint and promote cracking.

Base

Metal

Preparation

The

joint surface and

adjacent

area should be

thoroughly

cleaned

before

welding. All

grease, oil,

crayon marks, su l

fur

compounds

and other

foreign

matter

should

be

removed.

Contact with copper

or

copper-bearing materials in

the joint area should

be

avoided.

It

is preferable, but

not

necessary, that the alloy

be

in

the

solution-annealed

condi

tion when welded.

Filler Metal

Selection

Matching composition filler

metal is

recommended

for

join

ing 188 alloy. Fo r

joining

section

thicknesses greater

than

3/8 in. .5 mm)

230~Ww

filler

wire is suggested. Fo r

shielded metal arc welding,

HAYNES 25

alloy electrodes

AMS 5796) are suggested. Fo r

dissimilar metal joining of 188

alloy to nickel-,

cobalt-

or iron-

base materials, 188 alloy

itself,

230-W

filler

wire, 556TM alloy,

HASTELLOY S

alloy

AMS

5838) or HASTELLOY W alloy

MS 5786,

5787) welding

products are suggested,

depending upon the particular

case.

Preheating, Interpass

Temperatures

and

Post-Weld

Heat Treatment

Preheat

is

no t

usually required

so ong

as

base

meta

to be

welded is above 32 F °C).

Interpass

temperatures

gener

ally

should

be

low. Auxiliary

cooling methods may

be

used

between weld passes,

as

needed, prov d

ng

that such

methods

do

not

introduce

con

taminants.

Post-weld heat

treatment

is not

normal

y

required

for

188

alloy.

Fo r

fur

ther information, please contact

Haynes International.

HEALTH AND SAFETY INE

RMATION

Welding can be a safe occupa

tion.

Those

in the

welding

industry, however, should be

aware of the potential hazards

associated

with

welding fumes,

gases, radiation, electric

shock,

heat, eye

injuries, burns,

etc. Also,

local,

municipal,

state,

and

federal regulations

such

as

those issued by

OSHA) relative

to weldng and

cutting processes should be

considered.

Nickel-, cobalt-, and iron-base

alloy products may

contain,

in

varying concentrations,

the

fol

lowing

elemental

constituents:

auminum, cobalt, chromium,

copper, iron, manganese,

molybdenum,

nickel

and tung

sten

Fo r

specific

concentrations

of

these and

other

elements present, refer

to

the Materal Safety Data Sheets

MSDS) H3095

and

H1072

for

the product.

Inha

ation of metal dust or

fumes

generated

from weldng,

cutting, grind ng ,

melting,

or

dross handling of these alloys

may cause

adverse

health

effects such

as

reduced

lung

function,

nasal

and mucous

membrane

irritation. Exposure

to dust or fumes which may be

generated

in working with

these alloys

may also

cause eye irritation, skin

rash

and

effects

on

other

organ

systems.

The

operation and

mainte

nance

of welding and cutting

equipment

should conform to

the provisions of American

Nat onal Standard ANSI/AWS

Z491, Safely

in

Welding and

Cuffing”) Attention

s

espe

cia y

ca l ed

to Section 7

Protect on of Personnel) and 8

Heath

Protect on

and

Ventilat

on )

of ANSI/AWS Z491.

Mechanical ventilation s advis

able

and, under certain

conditions such

as

a very

con

fined space, is necessary

during

welding

or cuffing

oper

ations,

or both,

to prevent

possible

exposure to haz

ardous fumes, gases, or

dust

that may occur.

HAYNES

188

alloy

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MACH

NING

Operation High Speed Steel

Tools

Carbide

Tools

Normal

Roughing

M-40 series,

M-2 , M -33,

T-4, C-i or C

2

grade

square

insert,

Turning/Facing)

T-8

and

T-15. 45 SCEA,

-5 Back

Rake,

45

SCEA’, 0°

Back

Rake, -5°Side Rake,

+10°Side Rake, 1/16

in.

Nose Radius.

1/16

in.

Nose Radius.

1/4

in.

depth

of

cut max.,

1/4

in.

depth

of

cut

max., .020

feed

max.,

60-80

sfm

0.020 feed

max.,

depending on rigidity of

setup

25 sfm cutting speed. Dry3, oil4, or

water-base

coo ant.

Water base

coolant.

F nish ng M-40 series, M-33, M-3 , T -8 0-2 or 0-3

grade

square insert,

Turning/Facing) and

T-15.

if possible.

15-45°

SCEA, +10° Back Rake,

15-45°

SCEA, +5°Side Rake,

+15~

Side Rake, +5

Back

Rake,

1/32-1/16

in.

Nose Radius. 1/32-1/16

in.

Nose Rad us.

0.040-0.010 in.

depth

of cut, 0.040-0.010 in.

depth

of cut,

Water-base coolant.

Dry or

water-base

coolant.

Drilling C-2

grade

not

recommended,

but solid or tipped

dr

Is may

be

successful on rigid setups.

The web

must

be

thinned

to

reduce thrust.

Use 135° included

angle on

point.

30-60

sfm.

Coolant-feed

carbide tipped

drills can

be

economical

in

some setups.

Q~

or

water-base coolant.

M-33, M-40 series, or T-15.

Peed

0.001 in/Rev. 1/16

in.

dia.

0.002

in./Rev.

1/4

in. dia.

0.003

in/Rev. 1/2 in. da.

0.004 in/Rev. in. d

a.

Speed

10-20 sfm.

Oil

or

water-base coolant.

Use

coolant feed drills

if p055

ble.

Use short drills, heavy web

135°

crankshaft

grind

points

wherever

possible.

SCEA — side

cutting

edge

angle

or

lead angle

of the

tool.

2 Water-base coolant should be premium quality, sulfochiorinated water soluble oil or chemical emulsion with extreme pressure additives. Dilute with water to

make 5: mix.

3 At any

point

where dry cutting is

recommended,

an

air let

directed on the

tool may provide substantial

tool life increases. A water-base

coolant mist may

also

be

effective.

4 Oi l

coolant should

be a premium

quality,

sulfochiorinated oil with extreme pressure

additives.

A

viscosity at

6F

from 50

to

125 ssu

5 Water4ase

coolant

may cause chipping and rapid failure of carbide tools in interrupted cuts.

6 Negative

rake

tools should be

used for

interrupted

cuts.

NOTES:

HAYNES

188

alloy

8/16/2019 h3001.pdf

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STANDARD PRODUCTS By Brand or Alloy Designation:

B-3®, C-4, C-22®, C-22HS®, C-276, C-2000®, G-30®, G-35®, G-50®, HYBRID-BC1™, and N

Corrosion-Wear Resistant Alloy

ULTIMET®

25, R-41, 75, HR-120®, HR-160®, HR-224™, 188, 214®, 230®, 230-W®, 242®, 263, 282®, 556®, 617, 625,

625SQ®, 718, X-750, MULTIMET®, NS-163™, and Waspaloy

Wear-Resistant Alloy

Ti-3Al-2.5V

HASTELLOY ® High-Temperature Alloys

HASTELLOY ® Corrosion-Resistant Alloys

S, W, and X

HAYNES ® High-Temperature Alloys

6B

HAYNES ® Titanium Alloy Tubular

Properties Data: The data and information in this publication are

based on work conducted principally by Haynes International,

Inc. and occasionally supplemented by information from the open

literature, and are believed to be reliable. However, Haynes

does not make any warranty or assume any legal liability or

responsibility for its accuracy, completeness, or usefulness,

nor does Haynes represent that its use would not infringe

upon private rights.

An y su gg es ti on s as to us es an d appl ic at io ns fo r sp ec if ic

alloys are opinions only and Haynes International, Inc. makes no

warranty of results to be obtained in any particular situation. For

specific concentrations of elements present in a particular product

and a discussion of the potential health affects thereof, refer to

the Material Safety Data Sheet supplied by Haynes International,

Inc. All trademarks are owned by Haynes International, Inc.

Standard Forms: Bar, Billet, Plate, Sheet, Strip, Coils, Seamless or Welded Pipe & Tubing, PipeFittings, Flanges, Fittings, Welding Wire, and Coated Electrodes

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P.O. Box 9013

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Phone: 1-800-354-0806 or (765) 456-6012

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