摘要：
The invention is related to a high gamma prim nickel based superalloy, its use and a method of
manufacturing of turbine engine components by welding, 3D additive manufacturing, casting and
hot forming, and the superalloy comprises by wt%: from 9.0 to 10.5 % Cr, from 16 to 22 % Co,
from 1.0 to 1.4 % Mo, from 5.0 to 5.8 % W, from 2.0 to 6.0 % Ta, from 1.0 to 4.0% Nb provided
that total content of Ta and Nb remains with a range from 3.0 to 7.0%, from 3.0 to 6.5 % Al, from
0.2 to 1.5 % Hf, from 0.01 to 0.2% C, from 0 to 1.0 % Ge, from 0 to 1.0 wt. % Si, from 0 to 0.2
wt. % Y, from 0 to 0.015 wt. % B, from 1.5 to 3.5 wt. % Re, and nickel with impurities to balance.
Fig. 11c
权利要求：
1. A high gamma prime nickel-based superalloy, comprising by wt. %:
- Chromium from 9.0 to 10.5 %,
- Cobalt from about 16 to 22 %,
- Molybdenum from 1.0 to 1.4 %,
- Tungsten from 5.0 to 5.8 %,
- Tantalum from 2.0 to 6.0 %,
- Niobium from 1.0 to 4.0 %,
- Tantalum plus Niobium from 3.0 to 7.0 %,
- Aluminum from 3.0 to 6.5 %,
- Hafnium from 0.2 to 1.5 %,
- Germanium from 0 to 1.0 %,
- Yttrium from 0 to 0.2 %,
- Silicon from 0 to 1.0 %,
- Boron from 0 to 0.015 %,
- Carbon from 0.01 to 0.2%,
- Rhenium from 1.5 to 3.5 %, and
- Nickel with impurities to balance.
2. The high gamma prime nickel-based superalloy as per claim 1 wherein the total content
of germanium and silicon is within 0.9 – 1.1 wt. %.
3. The use of the high gamma prime nickel-based superalloy as per claim 1 or 2 as the
material for a welding wire, welding powder, or turbine engine components.
4. A method of manufacturing a turbine engine component, wherein it comprises a step of
using the high gamma prime nickel-based superalloy as per one of claims 1-2.
5. The method of manufacturing a turbine engine component as per claim 4, wherein the
method comprises one or more steps selected from among:
a) Casting,
b) Annealing at 2190 – 2290°F for 1 – 2 hours,
c) Hot forming by a plastic deformation at 1500 – 1800?F,
d) Primary aging at 1975 – 2050°F for 2 – 4 hours, and
e) Secondary aging at 1300 – 1500°F for 16 – 24 hours
6. The method of manufacturing a turbine engine component as per claim 5, wherein the
method comprises a heat treatment selected from among an annealing within a temperature
range from 2190?F to 2290?F for 1 – 2 hours, a primary aging within a temperature range
from 1975?F to 2050?F for 2 – 4 hours, and a secondary aging within a temperature range
from 1300?F to 1500?F for 16 – 24 hours.
7. The method of manufacturing a turbine engine component as per claim 5, wherein prior
to the step of hot forming at the temperature of 1500 – 1800°F, the method comprises an
additional step of a hot isostatic pressure treatment at a temperature of 2200 – 2290°F,
pressure of 15 – 20 KSI for 2 – 6 hours.
8. The method of manufacturing a turbine engine component as per claim 5, wherein the
method comprises the hot forming by the plastic deformation by 5 - 80%.
9. The method of manufacturing a turbine engine component as per claim 5, wherein the
temperature of the primary aging is selected above the service temperature of the turbine
engine component.
10. The method of manufacturing a turbine engine component as per claim 4, wherein the
method comprises steps of:
a) a fusion welding by a melting in a welding pool and deposition of a powder mix
comprising at least two dissimilar nickel and cobalt based powders in quantities of
(70 – 80) wt. % and (20 – 30) wt. % respectively, wherein:
The nickel-based powder comprises by wt. %:
- Chromium from 6 to 8 %,
- Cobalt from 6 to12 %,
- Molybdenum 1.3 to1.6 %,
- Tungsten from 4.5 to 5 %,
- Tantalum from 2.0 to 6.0 %,
- Niobium from 1 to 4.0%,
- Tantalum plus Niobium from 3.0 to 7.0 %,
- Aluminum from 3.0 to 6.5 %,
- Hafnium from 0.2 to 1.5 %,
- Rhenium from 2.5 to 3 %,
- Germanium from 0 to 1.0 %,
- Silicon from 0 to 1 %,
- Yttrium for 0 to 0.2 %,
- Boron from 0 to 0.015 %,
- Carbon from 0.01 to 0.1%, and.
- Ni with impurities to balance, and
The cobalt based powder comprises by wt. %:
- Nickel from 10 to18 %,
- Chromium from 19 to 21 %,
- Tungsten from 8 to10 %,
- Aluminum from 3 to 6.5 %,
- Germanium from 0 to 1.0 %,
- Silicon from 0 to 1 %,
- Yttrium from 0 to 0.45 %,
- Hafnium from 0 to 1.5 %,
- Niobium from 0 to 4%,
- Carbon from 0.01 to 0.2% and
- Co with impurities to balance;
b) Progressively moving and solidifying the welding pool as per a preprogrammed
welding path, forming welding beads with the same chemical composition as the
high gamma prime nickel-based superalloy of claim 1.
11. The method of manufacturing a turbine engine component as per claim 10, wherein the
fusion welding is selected from among a laser beam, plasma arc, micro plasma, electron beam, and
gas tungsten arc welding.
12. The method of manufacturing a turbine engine component as per claim 10, wherein the
method further comprises a post weld heat treatment selected from among the high isostatic
pressure, annealing, aging or combination of the annealing and aging.
13. The method of manufacturing a turbine engine component as per claim 12, wherein after
post weld heat treatment, the method further comprises a step of machining to a required geometry.
14. The method of manufacturing a turbine engine component as per claim 13, wherein the
method further comprises a step of non-destructive testing.
15. The method of manufacturing a turbine engine component as per claim 10, wherein the
powder mix is in the form of a pre-alloyed powder blend comprising the nickel and cobalt based
powders or in the form of the dissimilar nickel and cobalt based powders that are mixed in the
welding pool directly during welding.
16. The method of manufacturing a turbine engine component as per one of claims 4-15,
wherein the turbine engine component is manufactured by a 3D additive manufacturing method.
17. A turbine engine component as obtained by the method according to one of claims 4-16.