Chemical composition Element Weight percent Element Weight percent Ni Balance Cr 14–16 Co 13–15.5 Mo 3–5 Ti 3.5–4.5 Al 4.5–5.5 C 0.12–0.20 B 0.010–0.025 Si 1.0 max Mn 1.0 max Fe 1.0 max Cu 0.20 max Zr 0.15 max Pb 0.0015 max S 0.015 max — —

Mechanical properties Typical 1,000-hour rupture strength, precipitation-hardened condition; Special Metals handbook, printed page 30. The handbook does not specify the product form or exact aging cycle for these values. Test temperature °C 1,000 h rupture strength MPa 760 450 815 310 870 210 925 130 980 80 These stresses correspond to rupture in approximately 1,000 hours. They are not tensile strengths or allowable design stresses. The bulletin presents tensile properties graphically; numerical values are not inferred here.

Application areas Aircraft gas turbine blades Forged or machined turbine blading requiring high creep strength

Chemical composition Element Weight percent Element Weight percent Ni Balance Cr 14–16 Co 13–15.5 Mo 3–5 Ti 3.5–4.5 Al 4.5–5.5 C 0.12–0.20 B 0.010–0.025 Si 1.0 max Mn 1.0 max Fe 1.0 max Cu 0.20 max Zr 0.15 max Pb 0.0015 max S 0.015 max — —

Mechanical properties Typical 1,000-hour rupture strength, precipitation-hardened condition; Special Metals handbook, printed page 30. The handbook does not specify the product form or exact aging cycle for these values. Test temperature °C 1,000 h rupture strength MPa 760 450 815 310 870 210 925 130 980 80 These stresses correspond to rupture in approximately 1,000 hours. They are not tensile strengths or allowable design stresses. The bulletin presents tensile properties graphically; numerical values are not inferred here.

Application areas Aircraft gas turbine blades Forged or machined turbine blading requiring high creep strength

Alloy 115/Nimonic 115

Grade: Nimonic 115/W.Nr 2.4636

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

NIMONIC 115 is a nickel chromium cobalt superalloy designed for heavily loaded turbine blades. Aluminum and titanium develop precipitation strengthening, while molybdenum contributes solid-solution strength. Its principal advantage is resistance to creep at very high temperatures. Product selection should account for forging practice, final aging and the operating stress, because these factors strongly influence blade life.

Chemical composition

Element	Weight percent	Element	Weight percent
Ni	Balance	Cr	14–16
Co	13–15.5	Mo	3–5
Ti	3.5–4.5	Al	4.5–5.5
C	0.12–0.20	B	0.010–0.025
Si	1.0 max	Mn	1.0 max
Fe	1.0 max	Cu	0.20 max
Zr	0.15 max	Pb	0.0015 max
S	0.015 max	—	—

Mechanical properties

Typical 1,000-hour rupture strength, precipitation-hardened condition; Special Metals handbook, printed page 30. The handbook does not specify the product form or exact aging cycle for these values.

Test temperature °C	1,000 h rupture strength MPa
760	450
815	310
870	210
925	130
980	80

These stresses correspond to rupture in approximately 1,000 hours. They are not tensile strengths or allowable design stresses. The bulletin presents tensile properties graphically; numerical values are not inferred here.

Application areas

Aircraft gas turbine blades
Forged or machined turbine blading requiring high creep strength

Introduction

Specification

Chemical composition

Element	Weight percent	Element	Weight percent
Ni	Balance	Cr	14–16
Co	13–15.5	Mo	3–5
Ti	3.5–4.5	Al	4.5–5.5
C	0.12–0.20	B	0.010–0.025
Si	1.0 max	Mn	1.0 max
Fe	1.0 max	Cu	0.20 max
Zr	0.15 max	Pb	0.0015 max
S	0.015 max	—	—

Mechanical

Mechanical properties

Typical 1,000-hour rupture strength, precipitation-hardened condition; Special Metals handbook, printed page 30. The handbook does not specify the product form or exact aging cycle for these values.