Chemical Composition C Carbon 0.08 – 0.16 Mn Manganese 1.00 – 2.00 max Si Silicon 1.00 max S Sulfur 0.03 max P Phosphorus 0.04 max Cr Chromium 20.00 – 22.5 Ni Nickel 19.00 – 21.00 Co Cobalt 18.5 – 21.00 Mo Molybdenum 2.5 – 3.5 W Tungsten 2.0 – 3.0 Cb + Ta Niobium + Tantalum 0.75 – 1.25 N Nitrogen 0.1 – 0.2

Mechanical Properties Material Form Ultimate Tensile Strength ksi Elongation in 2″ (min) Hardness HB Multimet N155 Bar (AMS 5769) 156-217 Multimet N155 Sheet / Plate (AMS 5532) 110-140 40 –

Chemical Composition C Carbon 0.08 – 0.16 Mn Manganese 1.00 – 2.00 max Si Silicon 1.00 max S Sulfur 0.03 max P Phosphorus 0.04 max Cr Chromium 20.00 – 22.5 Ni Nickel 19.00 – 21.00 Co Cobalt 18.5 – 21.00 Mo Molybdenum 2.5 – 3.5 W Tungsten 2.0 – 3.0 Cb + Ta Niobium + Tantalum 0.75 – 1.25 N Nitrogen 0.1 – 0.2

Mechanical Properties Material Form Ultimate Tensile Strength ksi Elongation in 2″ (min) Hardness HB Multimet N155 Bar (AMS 5769) 156-217 Multimet N155 Sheet / Plate (AMS 5532) 110-140 40 –

Multinet N155/UNS R30155

Grade: Multinet N155/UNS R30155

Sheet/Plate: 0.3mm-150mm

Strip/Foil: 0.02mm-16mm

Pipe: 6mm*0.5mm-1200mm*100mm

Bar: Ф6mm – Ф600mm

Wire: Ф0.01mm – Ф6mm

Others: Forged Rings, Flanges, Elbows, Tees, Reducers etc.

Standard: ASTM/ASME/AMS

Multimet N155 is a Nickel-Chromium-Cobalt alloy with additions of Molybdenum and Tungsten used typically in parts requiring high strength up to 1350°F and oxidation resistance up to 1800°F. Its high-temperature properties are inherent in the as-supplied condition (solution treated at 2150°F) and are not dependent on age-hardening. Multimet N155 is used in a number of aerospace applications such as tailpipes and tail cones, turbine blades, shafts and rotors, afterburner components and high-temperature bolts.

Chemical Composition

C	Carbon 0.08 – 0.16
Mn	Manganese 1.00 – 2.00 max
Si	Silicon 1.00 max
S	Sulfur 0.03 max
P	Phosphorus 0.04 max
Cr	Chromium 20.00 – 22.5
Ni	Nickel 19.00 – 21.00
Co	Cobalt 18.5 – 21.00
Mo	Molybdenum 2.5 – 3.5
W	Tungsten 2.0 – 3.0
Cb + Ta	Niobium + Tantalum 0.75 – 1.25
N	Nitrogen 0.1 – 0.2

Mechanical Properties

Material	Form	Ultimate Tensile Strength ksi	Elongation in 2″ (min)	Hardness HB
Multimet N155	Bar (AMS 5769)			156-217
Multimet N155	Sheet / Plate (AMS 5532)	110-140	40	–

Applications

▪ Air & land based turbine engines
▪ Aircraft tail cones & tail pipes
▪ Aircraft exhaust manifolds
▪ Aircraft combustion chambers
▪ Afterburners
▪ Buckets & bolts

Introduction

Specification

Chemical Composition

C	Carbon 0.08 – 0.16
Mn	Manganese 1.00 – 2.00 max
Si	Silicon 1.00 max
S	Sulfur 0.03 max
P	Phosphorus 0.04 max
Cr	Chromium 20.00 – 22.5
Ni	Nickel 19.00 – 21.00
Co	Cobalt 18.5 – 21.00
Mo	Molybdenum 2.5 – 3.5
W	Tungsten 2.0 – 3.0
Cb + Ta	Niobium + Tantalum 0.75 – 1.25
N	Nitrogen 0.1 – 0.2

Mechanical

Mechanical Properties

Material	Form	Ultimate Tensile Strength ksi	Elongation in 2″ (min)	Hardness HB
Multimet N155	Bar (AMS 5769)			156-217
Multimet N155	Sheet / Plate (AMS 5532)	110-140	40	–

Application

Applications

▪ Air & land based turbine engines
▪ Aircraft tail cones & tail pipes
▪ Aircraft exhaust manifolds
▪ Aircraft combustion chambers
▪ Afterburners
▪ Buckets & bolts