U.S. patent application number 15/867823 was filed with the patent office on 2018-05-17 for precipitation strengthened nickel based welding material for fusion welding of superalloys.
This patent application is currently assigned to Liburdi Engineering Limited. The applicant listed for this patent is Liburdi Engineering Limited. Invention is credited to Alexander B. Goncharov, Joseph Liburdi, Paul Lowden.
Application Number | 20180133846 15/867823 |
Document ID | / |
Family ID | 53477239 |
Filed Date | 2018-05-17 |
United States Patent
Application |
20180133846 |
Kind Code |
A1 |
Goncharov; Alexander B. ; et
al. |
May 17, 2018 |
PRECIPITATION STRENGTHENED NICKEL BASED WELDING MATERIAL FOR FUSION
WELDING OF SUPERALLOYS
Abstract
A precipitation strengthened nickel based welding material that
comprises 5-15 wt. % Co, 5-25 wt. % Cr, 1-6 wt. % Al, 0.05-0.2 wt.
% C, 0.015-0.4 wt. % B, 1-3 wt. % Si, chemical elements selected
from among tungsten and molybdenum from about 1 to 20 wt. %,
chemical elements selected from among titanium, zirconium, hafnium,
tantalum and rhenium from about 1 to 18 wt. % and nickel with
impurities to balance, wherein the boron content is inversely
proportional to silicon content and decreases from about 0.3 wt. %
to about 0.015 wt. % when silicon content increases from about 1
wt. % to about 3 wt. % produces sound high strength and high
oxidation resistance crack free welds on precipitation strengthened
superalloys and single crystal materials.
Inventors: |
Goncharov; Alexander B.;
(Toronto, CA) ; Liburdi; Joseph; (Dundas, CA)
; Lowden; Paul; (Cambridge, CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Liburdi Engineering Limited |
Dundas |
|
CA |
|
|
Assignee: |
Liburdi Engineering Limited
Dundas
CA
|
Family ID: |
53477239 |
Appl. No.: |
15/867823 |
Filed: |
January 11, 2018 |
Related U.S. Patent Documents
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
|
|
14800045 |
Jul 15, 2015 |
9902021 |
|
|
15867823 |
|
|
|
|
PCT/CA2013/001075 |
Dec 24, 2013 |
|
|
|
14800045 |
|
|
|
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B23K 35/0222 20130101;
B23K 35/3033 20130101; B23P 6/00 20130101; B23K 35/0255 20130101;
C22C 19/057 20130101; B23K 35/24 20130101; C22F 1/10 20130101; B23K
35/0227 20130101; B23K 35/0261 20130101; C22C 19/05 20130101; B23K
35/304 20130101; B23K 35/30 20130101; C22C 19/056 20130101 |
International
Class: |
B23K 35/30 20060101
B23K035/30; C22F 1/10 20060101 C22F001/10; C22C 19/05 20060101
C22C019/05; B23P 6/00 20060101 B23P006/00; B23K 35/02 20060101
B23K035/02; B23K 35/24 20060101 B23K035/24 |
Claims
1. A method of producing a precipitation strengthened nickel based
welding material for fusion welding of superalloys, the method
comprising: combining the following in weight percentages:
TABLE-US-00007 Cobalt from about 5 to 15 wt. % Chromium from about
5 to 25 wt. % Aluminum from about 1 to 6 wt. % Carbon from about
0.05 to 0.2 wt. % Boron from about 0.015 to 0.4 wt. % Silicon from
about 1 to 3 wt. % a combination of one or more of Tungsten and
Molybdenum for a combined total wt. % from about 1 to 20 wt. % a
combination of one or more of Titanium, Zirconium, Hafnium,
Tantalum and Rhenium for a combined total wt. % from about 1 to 18
wt. %, and Nickel with impurities to balance;
wherein the boron content is reduced proportionately from about an
initial 0.4 wt. % to about a final 0.015 wt. % with a proportionate
increase in the silicon content from about an initial 1 wt. % to
about a final 3 wt. % such that the total combined boron and
silicon content ranges from about 1.4 wt. % to 3.015 wt. %.
2. A method of producing precipitation strengthened nickel based
welding material for fusion welding of superalloys, the method
comprising: combining the following in weight percentages:
TABLE-US-00008 Cobalt from about 8 to 10 wt. % Chromium from about
14 to 18 wt. % Molybdenum from about 3 to 5 wt. % Tungsten from
about 3 to 5 wt. % Titanium from about 3 to 6 wt. % Zirconium from
about 0.04 to 0.06 wt. % Aluminum from about 2 to 4 wt. % Carbon
from about 0.05 to 0.2 wt. % Boron from about 0.1 to 0.35 wt. %
Silicon from about 1 to 3 wt. %, and a combination of one or more
of Titanium, Zirconium, Hafnium, Tantalum and Rhenium for a
combined total wt. % from about 1 to 18 wt. %, and Nickel with
impurities to balance;
wherein the boron content is reduced proportionately from about an
initial 0.35 wt. % to about a final 0.1 wt. % with a proportionate
increase in the silicon content from about an initial 1 wt. % to
about a final 3 wt. % such that the total combined boron and
silicon content ranges from about 1.35 wt. % to 3.1 wt. %.
3. The method of precipitation strengthening nickel based welding
material for fusion welding of superalloys of claim 1, wherein the
following are combined: TABLE-US-00009 Cobalt from about 11 to 13
wt. % Chromium from about 6 to 8 wt. % Molybdenum from about 1 to 3
wt. % Tungsten from about 4 to 6 wt. % Zirconium from about 0.01 to
0.03 wt. % Aluminum from about 5 to 6 wt. % Carbon from about 0.1
to 0.15 wt. % Rhenium from about 1 to 3 wt. % Tantalum from about 5
to 7 wt. % Boron from about 0.015 to 0.3 wt. % Silicon from about
1.2 to 1.8 wt. %, and Nickel with impurities to balance
4. The method of precipitation strengthening nickel based welding
material for fusion welding of superalloys of claim 3, wherein the
boron content is reduced proportionately from about 0.4 wt. % to
about 0.1 wt. % with a proportionate increase in the silicon
content from about 1 wt. % to about 3 wt. % such that the total
boron and silicon content ranges from about 1.4 wt. % to 3.1 wt.
%.
5. The method according to claim 1, wherein the precipitation
strengthened nickel based welding material for fusion welding of
superalloys produced is a welding powder.
6. The method according to claim 1, wherein the precipitation
strengthened nickel based welding material for fusion welding of
superalloys produced is a welding wire.
7. The method according to claim 1, wherein the precipitation
strengthened nickel based welding material for fusion welding of
superalloys produced is for use in a repair section of a turbine
engine component.
8. A precipitation strengthened nickel based welding material for
fusion welding of superalloys comprised of the following elements
in weight percentages: TABLE-US-00010 Cobalt from about 5 to 15 wt.
% Chromium from about 5 to 25 wt. % Aluminum from about 1 to 6 wt.
% Carbon from about 0.05 to 0.2 wt. % Boron from about 0.015 to 0.4
wt. % Silicon from about 1 to 3 wt. % Selected from among Tungsten
and Molybdenum from about 1 to 20 wt. % Selected from among
Titanium, Zirconium, Hafnium, Tantalum and Rhenium from about 1 to
18 combined total wt. %, and Nickel with impurities to balance;
wherein the boron content is reduced proportionately from about an
initial 0.4 wt. % to about a final 0.015 wt. % with a proportionate
increase in the silicon content from about an initial 1 wt. % to
about a final 3 wt. % such that the total combined boron and
silicon content ranges from about 1.4 wt. % to 3.015 wt. %.
9. A precipitation strengthened nickel based welding material for
fusion welding of superalloys comprised of the following elements
in weight percentages: TABLE-US-00011 Cobalt from about 8 to 10 wt.
% Chromium from about 14 to 18 wt. % Molybdenum from about 3 to 5
wt. % Tungsten from about 3 to 5 wt. % Titanium from about 3 to 6
wt. % Zirconium from about 0.04 to 0.06 wt. % Aluminum from about 2
to 4 wt. % Carbon from about 0.05 to 0.2 wt. % Boron from about 0.1
to 0.35 wt. % Silicon from about 1 to 3 wt. %, and Selected from
among Titanium, Zirconium, Hafnium, Tantalum and Rhenium from about
1 to 18 combined total wt. %, and Nickel with impurities to
balance;
wherein the boron-silicon content is determined wherein the boron
content is reduced proportionately from about an initial 0.35 wt. %
to about a final 0.1 wt. % with a proportionate increase in the
silicon content from about an initial 1 wt. % to about a final 3
wt. % such that the total combined boron and silicon content ranges
from about 1.35 wt. % to 3.1 wt. %.
10. The precipitation strengthened nickel based welding material
for fusion welding of superalloys of claim 8, limited to the
following in weight percentages: TABLE-US-00012 Cobalt from about
11 to 13 wt. % Chromium from about 6 to 8 wt. % Molybdenum from
about 1 to 3 wt. % Tungsten from about 4 to 6 wt. % Zirconium from
about 0.01 to 0.03 wt. % Aluminum from about 5 to 6 wt. % Carbon
from about 0.1 to 0.15 wt. % Rhenium from about 1 to 3 wt. %
Tantalum from about 5 to 7 wt. % Boron from about 0.015 to 0.3 wt.
% Silicon from about 1.2 to 1.8 wt. %, and Nickel with impurities
to balance
11. The precipitation strengthened nickel based welding material
claimed in claim 10 wherein the boron content reduced
proportionately from about 0.4 wt. % to about 0.1 wt. % with a
proportionate increase in the silicon content from about 1 wt. % to
about 3 wt. % such that the total boron and silicon content ranges
from about 1.4 wt. % to 3.1 wt. %.
Description
[0001] This application is a continuation-in-part of prior
application Ser. No. 14/800,045, filed Jul. 15, 2015, under the
title, "PRECIPITATION STRENGTHENED NICKEL BASED WELDING MATERIAL
FOR FUSION WELDING OF SUPERALLOYS," having a first inventor
Alexander B. Goncharov.
[0002] The invented material in a form of welding wire and powder
can be used for fusing welding including laser beam (LBW), plasma
(PW), microplasma (MPW), electron beam (EBW) and Gas Tungsten Arc
Welding (GTAW) of precipitation strengthening nickel and cobalt
based superalloys.
[0003] The precipitation strengthening nickel based superalloy
comprised of: 5-15 wt. % Co, 13-15.6 wt. % Cr, 2.5-5 wt. % Mo, 3-6
wt. % W, -6 wt. % Ti, 2-4 wt. % Al, 0.15-0.3 wt. % C, 0.005-0.02
wt. % B, up to 0.1 wt. % Zr and nickel with impurities to balance
as per U.S. Pat. No. 3,615,376 has been widely used for turbine
engine applications for decades. This superalloy has a good
combination of mechanical properties, oxidation resistance up to
1742.degree. F. and weldability. The embodiment of this alloy also
known as Rene 80 superalloy is comprised of: 9.5 wt. % Co, 14 wt. %
Cr, 4 wt. % Mo, 4 wt. % W, 5 wt. % Ti, 3 wt. % Al, 0.17 wt. % C,
0.015 wt. % B, 0.03 wt. % Zr and nickel to balance in a form of
welding wire and powder has been used for welding of Inconel 738,
GTD 111, GTD 222, Rene 77 polycrystalline and CMSX-4, Rene N5 and
other single crystal materials. Welding of precipitation
strengthened nickel based superalloys with high content of gamma
prime phase results in a severe heat affected zone (HAZ) liquation
cracking. The susceptibility of Inconel 738 superalloy to liquation
cracking is aggravated by solidification and thermal stresses
making it almost impossible to produce crack free welds at an
ambient temperature using known welding materials, refer to M.
Montazeri, F. Malek Ghaini and O. A. Ojo in the article "Heat Input
and the Liquation Cracking of Laser Welded IN738LC Superalloy",
Welding Journal, 2013, Vo. 92, 2013, pp.: 258-264.
[0004] To produce sound crack free welds engine components
manufactured of Inconel 738, GTD 111 and other high gamma prime
superalloys should be preheated prior to welding to high
temperatures as per U.S. Pat. No. 5,897,801 and U.S. Pat. No.
6,659,332. However, preheating reduces productivity, increases cost
and affects health and safety conditions.
[0005] In addition to the above, after weld repair turbine blades
are prone to accelerated oxidation that increases clearance between
turbine blades and stator assembly reducing efficiency and
increasing fuel consumption and emission of green house gases.
[0006] To increase the oxidation resistance of welds the rhenium
bearing Rene 142 welding wire that is comprised of: 10-13 wt. % Co,
3-10 wt. % Cr, 0.5-2 wt. % Mo, 3-7 wt. % W, 0.5 10 wt. % Re, 5-6
wt. % Al, 5-7 wt. % Ta, 0.5-2 wt. % Hf, 0.01-0.15 wt. % C,
0.005-0.05 wt. % B, 0-0.1 wt. % Zr with nickel to balance as per
patent U.S. Pat. No. 4,169,742, was introduced to the industry.
However, due to a high cost of rhenium Rene 142 welding wire is
extremely expensive. Also, the quality of welds produced using Rene
142 welding wire is even more sensitive to a preheating temperature
than Rene 80 due to a higher susceptibility of Rene 142 alloy to
cracking.
[0007] To prevent HAZ cracking either residual stress should be
minimized by preheating of engine components to high temperature as
discussed in U.S. Pat. No. 5,897,801 and U.S. Pat. No. 6,659,332 or
the melting temperature of welding materials be reduced to prevent
overheating of HAZ by additional alloying of welding materials
using melting point depressants, such as boron, as per US RE 29920
and RE 2868. These nickel based alloys comprise of: 0.05-0.3 wt. %
B, up to 0.35 wt. % C from 5 to 22 wt. % Cr, up to 8 wt. % and up
to 3 wt. % Nb respectively with nickel to balance.
[0008] However, as it was found by experiments, boron in amounts up
to 0.3 wt. % does not prevent HAZ microfissuring of Inconel 738,
GTD 111 and Mar M247 superalloys during welding at an ambient
temperature. In addition to the above, boron significantly reduces
oxidation resistance of welds.
[0009] Silicon is another well known melting point depressant. Si
has been used for manufacturing of welding wire such as Haynes
HR-160 (UNS Number N12160) that comprises of: Ni--29 wt. % Co--28
wt. % Cr--2 wt. % Fe--2.75 wt. % Si--0.5 wt. % Mn--0.5 wt. %
Ti--0.05 wt. % C--1 wt. % W--1 wt. % Mo--1 wt. % Nb. Welds produced
using Haynes HR-160 welding wire have a superior oxidation
resistance. However, mechanical properties of these welds at
temperatures exceeding 1800.degree. F. are extremely low. As a
result, silicon has not been considered for manufacturing of nickel
based superalloys due to harmful effects on mechanical properties
of nickel based superalloys.
[0010] For example, as per Robert V. Miner, Jr. addition of 0.5 and
1 wt. % Si to nickel based Inconel 713C and Mar M200 superalloys
drastically affected high temperature mechanical properties of
these alloys, refer to Robert V. Miner, Jr. "Effect of Silicon on
the Oxidation, Hot-Corrosion, and Mechanical Behaviour of Two Cast
Nickel-Base Superalloys", Metallurgical Transactions, Volume 8A,
December 1977, and pp. 1949-1954. Furthermore, this degradation
could not be explained by obvious changes of either the phase
compassion or morphologies of precipitancies and their reaction
with other alloying elements and Ni at high temperatures.
[0011] As a result, Si has been used mostly for manufacturing of
high temperature cobalt and nickel based brazing materials such as
AMS4775, which includes 3.1 wt. % B and 4 wt. % Si, AMS4777 that is
comprised of: 3.1 wt. % B and 4.5% Si, AMS 4779 with 1.85 wt. % B
and 3.5 wt. % Si, Amdry 788 with 2 wt. % B and 2 wt. % Si, as well
as special nickel based alloy disclosed in U.S. Pat. No. 2,868,667
that is comprised of: 2.5-4.5 wt. % B and 3.5-5.5 wt. % Si.
[0012] Joints produced using brazing alloys described in the prior
art are free of cracks due to the nature of high temperature
brazing process, which is carried out with isothermal heating of
parts in vacuum furnaces, that minimizes residual stresses.
However, mechanical properties of brazed joints are significantly
lower than base materials. It significantly limits the use of
brazing for manufacturing and repair of highly stressed rotating
and structural components of turbine engines.
[0013] Therefore, there are substantial industrial needs in the
development of new high oxidation resistance, high strength and
ductility welding materials based on gamma prime nickel superalloys
that can produce crack free welds on precipitation hardening
superalloys at an ambient temperature.
BRIEF DESCRIPTION OF THE INVENTION
[0014] We have found that a precipitation strengthened nickel based
welding material that comprises of: 5-15 wt. % Co, 5-25 wt. % Cr,
1-6 wt. % Al, 0.05-0.2 wt. % C, 0.015-0.4 wt. % B, 1-3 wt. % Si,
and chemical elements selected from among tungsten and molybdenum
from about 1 to 20 wt. %, and chemical elements selected from among
titanium, zirconium, hafnium, tantalum and rhenium from about 1 to
18 wt. % and nickel and impurities to balance, wherein the boron
content is reduced proportionately from about an initial 0.4 wt. %
to about a final 0.015 wt. % with a proportionate increase in the
silicon content from about an initial 1 wt. % to about a final 3
wt. % such that the total combined boron and silicon content ranges
from about 1.4 wt. % to 3.015 wt. %, in the form of welding wire
and powder produces sound high strength and high oxidation
resistance crack free welds on precipitation hardening superalloys
and single crystal materials.
[0015] A method of producing the precipitation strengthened nickel
based welding material that by combining the elements in the
percentage weight as noted above is also provided.
[0016] An embodiment of the method includes combining 5-15 wt. %
Co, 5-25 wt. % Cr, 1-6 wt. % Al, 0.05-0.2 wt. % C, 0.015-0.4 wt. %
B, 1-3 wt. % Si, and chemical elements selected from among tungsten
and molybdenum from about 1 to 20 wt. %, and chemical elements
selected from among titanium, zirconium, hafnium, tantalum and
rhenium from about 1 to 18 wt. % and nickel and impurities to
balance, wherein the boron content is reduced proportionately from
about an initial 0.4 wt. % to about a final 0.015 wt. % with a
proportionate increase in the silicon content from about an initial
1 wt. % to about a final 3 wt. % such that the total combined boron
and silicon content ranges from about 1.4 wt. % to 3.015 wt. %. The
advantages of the developed welding material are as follows:
Firstly it enables fusion welding of Inconel 738, GTD 111, Mar
M002, Mar M277 and other high gamma prime nickel based
polycrystalline superalloys without HAZ cracking at an ambient
temperature. Secondly, it produces crack free welds with a unique
combination of high strength and high oxidation resistance on
Inconel 738, GTD 111, Mar M002, Mar M277 and other high gamma prime
nickel based polycrystalline superalloys. Thirdly it minimizes or
eliminates recrystallization of single crystal materials in the HAZ
along the fusion line.
[0017] The advantages of the developed welding material are as
follows: Firstly it enables fusion welding of Inconel 738, GTD 111,
Mar M002, Mar M277 and other high gamma prime nickel based
polycrystalline superalloys without HAZ cracking at an ambient
temperature. Secondly, it produces crack free welds with a unique
combination of high strength and high oxidation resistance on
Inconel 738, GTD 111, Mar M002, Mar M277 and other high gamma prime
nickel based polycrystalline superalloys. Thirdly it minimizes or
eliminates recrystallization of single crystal materials in the HAZ
along the fusion line.
[0018] In another preferable embodiment the welding material
comprises of 8-10 wt. % Co, 14-18 wt. % Cr, 3-5 wt. % Mo, 3-5 wt. %
W, 3-6 wt. % Ti, 0.04-0.06 wt. % Zr, 2-4 wt. % Al, 0.05-0.2 wt. %
C, 0.1-0.35 wt. % B, 1-3 wt. %, Si and chemical elements selected
from among Titanium, Zirconium, Hafnium, Tantalum and Rhenium from
about 1 to 18 combined total wt. %, and nickel with impurities to
balance, wherein the boron-silicon content is determined wherein
the boron content is reduced proportionately from about an initial
0.35 wt. % to about a final 0.1 wt. % with a proportionate increase
in the silicon content from about an initial 1 wt. % to about a
final 3 wt. % such that the total combined boron and silicon
content ranges from about 1.35 wt. % to 3.1 wt. %.
[0019] Another embodiment of the provided method includes combining
8-10 wt. % Co, 14-18 wt. % Cr, 3-5 wt. % Mo, 3-5 wt. % W, 3-6 wt. %
Ti, 0.04-0.06 wt. % Zr, 2-4 wt. % Al, 0.05-0.2 wt. % C, 0.1-0.35
wt. % B, 1-3 wt. %, Si and chemical elements selected from among
Titanium, Zirconium, Hafnium, Tantalum and Rhenium from about 1 to
18 combined total wt. %, and nickel with impurities to balance,
wherein the boron-silicon content is determined wherein the boron
content is reduced proportionately from about an initial 0.35 wt. %
to about a final 0.1 wt. % with a proportionate increase in the
silicon content from about an initial 1 wt. % to about a final 3
wt. % such that the total combined boron and silicon content ranges
from about 1.35 wt. % to 3.1 wt. %.
[0020] The preferable and most advanced embodiment of the welding
material for the welding of engine components exposed to extremely
high temperature, stresses and hot corrosion is comprised of 11-13
wt. % Co, 6-8 wt. % Cr, 1-3 wt. % Mo, 4-6 wt. % W, 0.01-0.03 wt. %
Zr, 5-7 wt. % Al, 0.1-0.15 wt. % C, 1-3 wt. % Re, 5-7 wt. % Ta,
0.015-0.3 wt. % B, 1.2-1.8 wt. % Si and nickel with impurities to
balance.
[0021] In another preferable embodiment the content of boron is
reduced proportionately from about 0.4 wt. % to about 0.1 wt. %
with proportionate increase of the silicon content from about 1 wt.
% to about 3 wt. % such that the total boron and silicon content
ranges from about 1.4 wt. % to about 3.1 wt. % allowing to enhance
either mechanical properties or oxidation resistance of welds as
necessary for a particular application avoiding at the same time
HAZ cracking of polycrystalline superalloys and recrystallization
of single crystal materials.
[0022] Preferable embodiments are welding wire or welding powder or
repaired using the wire or powder parts of the turbine engine
components.
DESCRIPTION OF DRAWINGS
[0023] FIG. 1 is the micrograph of the clad weld produced using
standard Rene 80 on GTD 111 superalloy in annealed condition that
depicts HAZ and weld cracking.
[0024] FIG. 2 is the micrograph of a longitudinal section of a
laser clad weld on GTD 111 superalloy in annealed condition
produced using Welding Material FM4 in a form of powder that
depicts crack free weld and HAZ.
[0025] FIG. 3 is the micrograph of a fusion zone of a laser clad
weld produced using Welding Material FM3 in the form of powder on
IN73 8 superalloy in aged heat treated condition depicts crack free
weld and HAZ.
[0026] FIG. 4 is the micrograph of the GTAW-MA clad weld produced
using Welding Material FM3 in a form of a welding wire on the
Nozzle Guide Vain manufactured of Mar M247 superalloy in post weld
aged heat treated condition that depicts crack free weld and
HAZ.
[0027] FIG. 5 is the micrograph of a laser clad weld produced using
Welding Material FM8 in the form of powder on GTD 111 superalloy
that depicts intergranular precipitation of borides and
silicides.
[0028] FIG. 6 is the micrograph of a GTAW-MA butt welded joint of
Rene 77 produced using Welding Material FM8 in the form of a
welding wire.
[0029] FIG. 7 is the micrograph of the GTAW-MA clad weld on single
crystal material Rene N5 produced using Welding Material FM 7 in
the form of welding wire that depicts crack free weld and HAZ
without any evidence of recrystallization.
[0030] FIG. 8 is the micrograph of the GTAW-MA clad weld on single
crystal CMSX-4 material produced using Welding Material FM9 that
depicts crack free weld and HAZ without any evidence of
recrystallization.
[0031] FIG. 9 depicts weld samples produced using GTAW-MA and
standard Rene 80 Welding Material (100 and 101) and Welding
Material FM3 (200 and 201), wherein 100 and 200--top view and 101
and 201 side view of samples after testing at a temperature of
2012.degree. F. for 300 hours that depicts a superior oxidation
resistance of the weld produced using Welding Material FM4 in the
form of welding wire.
[0032] FIG. 10 is the micrograph of the weld metal produced using
Welding Alloy FM8 in the form of a welding powder and laser beam
welding on Inconel 738 superalloy in aged heat treat condition.
[0033] FIG. 11 depicts tip and radial crack repair of the High
Pressure Turbine (HPT) blade manufactured of single crystal Rene N5
superalloy of an aero engine that was produced using GTAW-MA and
Welding Material FM7 in the form of welding wire (Weld Example 15),
wherein 250 --HPT blade, 251 and 252 radial crack welds; 253--tip
weld, 254--the calliper that demonstrates the extent of the
successful repair of the radial crack.
[0034] FIG. 12 demonstrates the tip repair of the High Pressure
Turbine (HPT) bucket manufactured of GTD111 polycrystalline
superalloy of Industrial Gas Turbine Engine using automatic laser
cladding and Welding Material FM11 in the form of welding powder
(Weld Example 16), wherein 300--HPT bucket, 301--laser weld.
STANDARD ACROMYMS
[0035] AMS--Aerospace Material Specification (standards) [0036]
ASTM--American Society for Testing and Materials (standards) [0037]
AWS--American Welding Society (standards) [0038] HAZ--Heat Affected
Zone [0039] HPT--High Pressure Turbine [0040] IGT--Industrial Gas
Turbine Engines [0041] LPT--Nozzle Gide Vane [0042] NDT--Non
Destructive Testing [0043] NGV--Nozzle Gide Vane [0044]
OEM--Original Equipment Manufacture [0045] PWHT--Post Weld Heat
Treatment [0046] UNS--Unified Numbering System is an alloy
designation system widely accepted in North America [0047]
UTS--Ultimate Tensile Strength
Glossary
[0047] [0048] Alloys--metal compounds consisting of a mixture of
two or more materials. [0049] Austenite--a solid solution of one or
more elements in the face-centered cubic phase. Base Metal or
Material--one of the two or more metals to be welded together to
tom" a joint. Borides--compounds consisting of two elements of
which boron is the more electronegative one. Boron form borides
with metal and non-metal elements. [0050] Carbides--compounds
composed of carbon and a less electronegative element. Carbon can
produce carbides with metals (such as chromium, niobium,
molybdenum, tantalum, titanium, tungsten, and other metals of IVB,
VB and VIB groups) and non-metal (such as boron, calcium, or
silicon). Metal carbides are characterized by their extreme
hardness and resistance to high temperatures. [0051] Cladding--the
process of the application of a relatively thick layer (>0.5 mm
(0.02 in.)) of welding material and/or composite welding powder for
the purpose of improved wear and/or corrosion resistance or other
properties and/or to restore the part to required dimensions with
minimum penetration into the base material. [0052] Cold Rolling--a
process that carried out at a temperature below of the
recrystallization temperature of alloy. [0053] Cold
Working--shaping of metal at temperatures substantially below the
point of recrystallization. Cold working adds strength and
hardness. [0054] Crack--fracture-type discontinuity that is
characterized by a sharp tip and high ratio of length to width,
usually exceeding three (3). [0055] Cracking--fracture that
develops in the weld during or after solidification of a welding
pool is completed. [0056] Creep (properties)--is the tendency of a
solid material to move slowly or deform permanently under the
influence of stresses. Creep occurs when a metal is subjected to a
constant tensile load at an elevated temperature. [0057] The Creep
and Rupture Tests--are tests that carried out by applying a
constant load to a tensile specimen maintained at a constant
temperature according to ASTM E139. The rupture test in carried out
in a similar manner to the creep test but at a higher stress level
until the specimen fails and the time at failure is measured. Time
prior to rupture at given loading is used to characterize rupture
properties of materials. [0058] Dilution--the change in a chemical
composition of a welding material caused by the admixture of the
base material or previous weld metal in the weld bead that is
measured by the percentage of the base metal or previous weld metal
in the weld bead. [0059] Discontinuity--an interruption of the
typical structure of a weld metal, such as a lack of homogeneity in
the mechanical, metallurgical or physical characteristics of the
base or weld metal. [0060] Ductility--ability of metals and alloys
to be drawn, stretched, or formed without breaking. [0061]
Extrusion--a process of shaping by forcing a rod stock through a
single die or series of dies. [0062] Fissuring--small crack-like
discontinuities with only slight separation (opening displacement)
of the fracture surfaces. The prefixes macro--or micro--indicate
relative size. [0063] Fusion Welding--the welding process that used
fusion of the base metal to make the weld. [0064] Gamma (y)
Phase--the continuous matrix (called gamma) is a
face-centered-cubic (fcc) nickel-based austenitic phase that
usually contains a high percentage of solid-solution elements such
as Co, Cr, Mo, and W. [0065] Gamma Prime (7') Phase--the primary
strengthening phase in nickel-based superalloys is a compound
consisting of nickel and either aluminum or titanium Ni3Al or Ni3Ti
that coherently precipitates in the austenitic y matrix. [0066] Gas
Atomization--the process to manufacture high quality metal powders
by forcing a molten metal stream through an orifice and atomizing
it by inert gas jets into fine metal droplets followed by rapid
cooling. [0067] Gas Tungsten Arc Welding (GTAW)--in accordance with
the AWS definition it is the arc welding process that produces
coalescence of metals by heating them with an arc between a
tungsten (non-consumable) electrode and the work also know as a
base material. Shielding is obtained from a gas or a gas mixture.
Pressure may or may not be used and filler metal may or may not be
used. [0068] Hardness--ability of metals and alloys to resist
indentation, penetration, and scratching. [0069] Heat Affected Zone
(HAZ)--the portion of the base metal that has not been melted, but
whose mechanical properties or microstructure were altered by the
heat of welding. [0070] Heat Treatment--the controlled heating and
cooling processes used to change the structure of a material and
alter its physical and mechanical properties. [0071] Hot Rolling--a
process that carried out at a temperature exceeding the
recrystallization temperature of alloy. [0072] Induction Melting--a
process in which an induced electrical current known also as Eddy
Current heat and melt metals and alloys. [0073] Inverse
Proportion--is a relationship where a number either increases as
another decreases or decreases as another increases. Inversely
proportional is the opposite of directly proportional. [0074] Laser
Beam Welding and Cladding (LBW)--in accordance with AWS definition
it is a welding process that produces coalescence of materials with
the heat obtained from the application of concentrated coherent
light beam impinging upon the joint or base material respectively.
[0075] Linear Discontinuities--weld defects with the ratio of a
length to a with 3:1 or greater. [0076] Liquation Crack--a crack in
the weld that occurs during solidification and caused by the
melting of low melting-point grain boundary constituents. [0077]
Multi Pass Cladding and Welding--a weld that is formed by two or
more passes [0078] Nickel based superalloys--materials whereby the
content of nickel exceeds the content of other alloying elements.
[0079] Plasma Arc Welding (PAW)--in accordance with AWS definition
it is an arc welding process that produces coalescence of metals by
heating them with a constricted arc between an electrode and the
workpiece (base metal) known also as transferred arc or the
electrode and the constricting nozzle known also as non-transferred
arc. [0080] Precipitation Heat Treatment or Hardening--the process
of heating of alloys to a temperature at which certain elements
precipitate, forming a harder structure, and then cooling at a rate
to prevent return to the original structure. [0081]
Recrystallization--is a formation of a new, strain-free grain
structure from existing one that usually accompanied by grain
growth during heat treatment. [0082] Recrystallization
temperature--is an approximate temperature at which
recrystallization of an existing grain structure occurs within a
specific time. [0083] Rolling--a process in which metal stock is
passed through a set of mechanically driven rolls. [0084] Rupture
Strength--is a nominal stress developed in a material at rupture,
which in not necessarily is equal to ultimate strength. [0085]
Solidification Shrinkage--the volume contraction of a metal during
solidification. Solution Heat Treatment--the heat treatment method
that is used to heat alloys to a specific temperature for a certain
period of time allowing one or more alloying elements to dissolve
in a solid solution and then cool rapidly. [0086]
Superalloys--metallic materials with oxidation resistance and
mechanical properties for service at elevated temperatures. [0087]
Ultimate Tensile Strength (UTS)--the resistance of a material to
longitudinal stress, measured by the minimum amount of longitudinal
stress required to rupture the material. [0088] Weld and Clad
Bead--a localized coalescence of metal or non-metals produced
either by heating the materials to the welding temperature, with or
without the application of pressure, or by the application of
pressure alone, with or without the use of welding material. [0089]
Weld Defects--discontinuities that by nature or accumulated effect
render a part or product unable to meet minimum applicable
acceptance standards or specifications. [0090] Weld Pass--a single
progression of a welding or cladding operation along a joint, weld
deposit or substrate. The result of a pass is a weld bead, layer or
spray deposit. [0091] Weld Pool--the localized volume of molten
metal in a weld prior to its solidification as weld metal. [0092]
Welding--the material joining processes used in making welds.
[0093] Welding Material--the material to be added in making a
welded, brazed, or soldered joint [0094] Welding Powder--the
welding material in a form of powder that is added in making of
welded joints or clad welds. [0095] Welding Wire--welding material
in a form of wire that is added in making of welded joints or clad
welds. [0096] Yield Strength--the ability of a metal to tolerate
gradual progressive force without permanent deformation
DETAILED DESCRIPTION OF THE INVENTION
[0097] The invented alloy, and method of producing same, can be
used in the form of casting, wrought materials, plates, strips,
sheets, powders and other welding materials. However, welding
materials in the form of welding wire and powder are major
applications.
[0098] Welding wire and powders are manufactured of ingots, which
are also known as billets, produced in vacuum or argon using
standard induction melting technologies and equipment or other
melting processes.
[0099] For a manufacturing of welding wire billets are usually
produced in the form of rods with a diameter exceeding 0.75 inch
and reduced to a diameter of 0.50 inch by rolling or extrusion at a
high temperature followed by standard surface finishing.
[0100] Nickel based alloys, in accordance with the present concept,
are ductile at temperatures above 1600.degree. F. During hot
rolling rods with the initial diameter of 0.50 inch are reduced
down to 0.020-0.062 inch. Rolling increases the yield strength and
hardness of welding wires. Therefore, to increase ductility the
welding wire is subjected to annealing heat treatment every so
often to allow restoration of workability.
[0101] During final processing the welding wire is passed through a
standard rigorous cleaning procedure that ensures the welds will be
free from contamination.
[0102] Welding powders about of 45-75 um in diameter are
manufactured by standard gas atomization processes. During this
process the melted superalloy with chemical composition as per the
preferable embodiment is atomized by inert gas jets into fine metal
droplets that cool down during their fall in the atomizing
tower.
[0103] Metal powders obtained by gas-atomization have a perfectly
spherical shape and high cleanliness level. Welding powder is used
for plasma, microplasma and laser welding and cladding also known
as fusion welding and cladding processes.
[0104] During fusion welding powder is fed into the welding pool
with a jet of argon using standard powder feeders. After
solidification welding powder is fused with the base material
producing the weld metal. To reduce overheating and prevent HAZ
cracking, welding and cladding are carried out with minimum
dilution. The best results in cladding were achieved with a
dilution of 5-15%.
[0105] Boron and silicon combine with other alloying elements,
which are disclosed in the preferable embodiment, as well as with
the base material in the welding pool to produce the following
beneficial effects:
[0106] First of all, boron and silicon as melting point
depressants, reduce the temperature of the welding pool and
overheating of the HAZ enhancing formation of sound crack free
welds on Inconel 738, GTD111, Mar M002, Mar M247 superalloys as
shown in FIG. 2 through 6 and eliminate recrystallization of CMSX-4
and Rene N5 single crystal materials as shown in FIGS. 7 and 8. The
solidus temperature of these welds is much higher than brazing
materials due to a low amount of boron and silicon but below the
melting temperature of base materials. As a result, welds are able
to maintain the required geometry during the PWHT at temperatures
of about 2200.degree. F., while brazed joints at this temperature
are completely melted.
[0107] Secondly, boron prevents segregation and precipitation of
continuous silicide films along grain boundaries enhancing
precipitation of high strength cuboidal borides and silicides shown
in FIG. 5 within grain matrix, which in combination with a
formation of fine cuboidal gamma prime phase shown in FIG. 10,
significantly improved high temperature mechanical properties of
welds in comparison with welds produced using known welding
materials.
[0108] And finally, silicon compensates for the damaging affect of
boron on oxidation resistance and significantly improves oxidation
resistance of welds even in comparison with welds produced using
standard Rene 80 and Rene 142 welding materials as shown in Tables
4 and 5.
Examples of Welding of INCONEL 738, GTD 111, Mar M002, Mar M247,
CMSX-4 and Rene N5 Superalloys and Single Crystal Materials
[0109] Welding wires and powders with the chemical compositions as
per preferable embodiments shown in Table 1 were manufactured using
known methods to carry out welding experiments 1 through 16 and
demonstration of the industrial applicability of the developed
welding materials for a repair of HPT blades of aero and IGT
engines.
[0110] Multi pass laser cladding was made on samples manufactured
of Inconel 738, GTD 111, Mar M247, Rene 77 and Mar M002
polycrystalline superalloys and Rene N5 and CMSX-4 single crystal
materials. These materials have been widely used for manufacturing
of HPT and LPT turbine blades and NGV for industrial and aero
turbine engines and therefore have a significant practical
interest. Also, Inconel 738, GTD 111 and Mar M247 are extremely
susceptible to the HAZ cracking during welding. Rene N5 and CMSX-4
single crystal materials are prone to a recrystallization in the
HAZ that can result in cracking of turbine blades in service
conditions.
[0111] Laser clad welds on Inconel 738 and GTD 111 superalloys were
made using invented welding materials (FM) in the form of powders
shown in Table 3 and standard Rene 80 welding powder for comparison
of susceptibility of welds to cracking.
[0112] Butt joints of Inconel 738, GTD 111 and Mar M002 of 0.5'' in
thickness and clad welds on Mar M247 superalloy were produced using
multi pass GTAW-MA welding with welding wires of 0.030 and 0.045
inch in diameters manufactured of Welding Material FM2 and FM5 and
standard Rene 80 wire for comparison following up standard welding
procedure for aerospace applications AMW 2685. To control dilution
welding current was restricted to 100 A for butt welding and 60 A
for cladding at an arc voltage about 12-14 V.
[0113] To produce multi pass laser clad welds of 0.10-0.24 inch in
width, 0.12-5 inch in height and 2-6 inch in length the laser head
was oscillated during welding with the amplitude of (0.03-0.07)
inch and speed of about 30 inch/min at welding speed of 3=5
inch/min. Laser beam power was varied from 400 to 420 W and powder
feed rate from 3 to 7 g/min.
[0114] Prior to welding samples manufactured of Inconel 738, GTD
111, Mar M247 and Rene 77 precipitation strengthening superalloys
were subjected to a standard pre-weld annealing heat treatment at a
temperature of 2190.+-.15.degree. F. for two (2) hours followed by
an argon quench to improve weldability.
[0115] After welding all samples manufactured of Inconel 738 and
GTD 111 superalloys were subjected to the PWHT comprised annealing
at a temperature of 2190.degree. F. for two (2) hours followed by a
primary aging at temperatures of 2050.degree. F. for two (2) hours
and followed by secondary aging at a temperature of 1555.degree. F.
for twenty four (24) hours.
[0116] Weld samples manufactured of Mar M247 and Mar M002
superalloys were subjected to standard PWHT comprised secondary
aging at a temperature of 1975.degree. F. for two hours four (4)
hours followed by a secondary aging at a temperature of
1560.degree. F. for twenty (20) hours.
[0117] Samples manufactured of single crystal CMSX-4 and Rene N5
materials were stress relieved at a temperature of 2050.degree. F.
for two (2) hours.
[0118] Prior to mechanical testing weld samples were subjected to
fluoro penetrant (FPI) as per ASTM E1209-05 and radiographic
inspection as per ASTM E1742-08. No cracks and other weld
discontinuities exceeding 0.002 inch in size were permitted.
[0119] Clad weld metal and butt weld joints were subjected to
tensile testing as per ASRM E21 and rupture testing as per ASTM
E139. Test results and parameters for rupture tests are shown in
Tables 2 and 3 respectively.
[0120] The cyclic oxidation testing of samples of 0.25'' in
diameter and 1.0 inch in length was made at a temperature of
1825.+-.15.degree. F., which correspond to the maximum permitted
Exhaust Gases Temperature (EGT) of turbine engines, for 20 hours
followed by cooling for four (4) hours to a total test time at a
maximum temperature of 820 hours.
[0121] The accelerated cyclic oxidation testing was made by heating
of flat samples of 0.060 inch in thickness machined to surface
roughness of 32 microns in air to a temperature of
2012.+-.15.degree. F. followed by one (1) hour soaking at this
temperature and rapid cooling to an ambient temperature in air.
[0122] We are seeking to achieve the below four characteristics for
the manufacture and repair of precipitation strengthening nickel
based welding materials manufactured from the preferable
embodiments: [0123] 1. Crack free welds on Inconel 738, GTD 111,
Mar M247, Rene 77, Mar M002 and similar precipitation strengthened
superalloys at an ambient temperature. [0124] 2. Exclude
recrystallization and cracking of HAZ of CMSX-4, Rene N5 and other
single crystal materials. [0125] 3. Achieve a minimum 0.2% Offset
Yield Strength of 25 KSI at a temperature of 1800.degree. F. and
withstanding minimum 10 hours at stresses of 15 KSI at a
temperature of 1800.degree. F. [0126] 4. Produce superior than Rene
80 oxidation resistance at a temperature of 1825.+-.15.degree. F.
and test during minimum of 500 hours.
[0127] Welding materials with lower level of mechanical and
oxidation properties and ability to produce crack free welds
manufactured as per the current concept can be used for dimensional
restoration of engine components and crack repair on low stressed
areas in combination with protective coating of engine
components.
[0128] Mechanical properties and oxidation resistance of welds is
given in Tables 2-5.
[0129] As follows from test results shown in Table 2 welds produced
using Welding Material FM1 comprised 1.6-1.8 wt. % Si without boron
additives exhibited the HAZ cracking. However, despite HAZ cracking
the silicon bearing weld metal was subjected to rupture testing
that confirmed a harmful effect of silicon on creep properties of
welds as shown in Table 3.
[0130] Welds produced using Welding Material FM2 that comprised of
2.7-3.0 wt. % Si and low amounts of boron were free of cracks and
had low mechanical properties. Therefore, Welding Material FM2 can
be used mostly for a dimensional restoration of engine
components.
[0131] Welds that were produced using Welding Alloy FM5 with a high
content of boron and silicon were prone to cracking and did not
have practical interest.
[0132] Welds that were produced using silicon free Welding Material
FM11 were free of cracks but due to insufficient boron content of
0.3 wt. %, the HAZ of Inconel 738 and GTD 111 superalloys exhibited
micro cracking. Also, boron without silicon reduced oxidation
resistance of welds as shown in Table 4.
[0133] Combination of boron, silicon and other alloying elements in
Welding Materials FM3, FM4, FM6, FM7, FM8, FM9 and FM10 resulted in
a formation sound crack free welds with unique combination of high
mechanical and oxidation resistance properties and excluded
recrystallization of single crystal CMSX-4 and Rene N5 single
crystal materials in the HAZ shown in FIG. 8-9.
[0134] Mechanical properties of welds were improved by a formation
of gamma prime phase as shown in FIG. 10 and preferential
precipitation of cuboidal borides and silicides within grain matrix
as shown in FIG. 5.
[0135] Welding with standard Rene 80 welding alloys on single
crystal materials resulted in the recrystallization of the HAZ and
cracking of welds produced on high gamma prime GTD 111 superalloys
as shown in FIG. 1. Similar cracking was observed on Inconel 738,
Mar M247 and Rene 77 superalloys.
[0136] The demonstration of a practical applicability of developed
Welding Materials in the form of welding wire for GTAW-MA and
powder for an automatic laser welding is presented by Weld Examples
16 shown in FIG. 11 that demonstrate radial repair of 0.5 inch long
crack with welds 251 and 252 of about 066 inch long and tip weld
253. Welding was made at ambient temperature using standard
equipment for manual GTAW-MA welding and Welding Material FM7 in
the form of welding wire.
[0137] After welding the HPT blade was subjected to PWHT stress
relief at a temperature of 2050.degree. F., polishing to restore
the original geometry of the blade, chemical etching, FPI and
radiographic inspection. No unacceptable weld discontinuities were
found.
[0138] Weld Example 17 shown in FIG. 12 was carried out to
demonstrate the tip restoration of the IGT bucket by an automatic
multi pass laser cladding at an ambient temperature on the LAWS1000
laser welding system equipped with 1 kW laser using Welding
Material FM11 in the form of powder.
[0139] After welding the bucket manufactured of GTD 111 superalloy
was subjected to post weld standard aging heat treatment,
machining, polishing, FPI and radiographic inspection. The weld was
acceptable as it achieved all four characteristics described
above.
TABLE-US-00001 TABLE 1 Chemical Composition of Filler Materials
(FM) in Wt. % with Ni and Impurities to Balance Example of Welding
Materials (FM) Co Cr Mo W Al C B Si Others Example 1 8 14 3 3 2
0.15 -- 1.6 4-6 Ti, 0.04-0.06 Zr FM1 10 18 5 5 4 0.16 1.8 Example 2
8 14 3 3 2 0.05 0.15 2.7 2-4 Ti, 0.04-0.06 Zr FM2 10 18 5 5 4 0.1
0.18 2.8 Example 3 6 14 2.5 2.5 2 0.05 0.10 1.2 2-4 Ti, 0.04-0.06
Zr FM3 8 16 3.5 3.5 4 0.1 0.20 1.5 Example 4 8 16 3.5 3.5 2 0.05
0.20 1.5 2-4 Ti, 0.03-0.06 Zr FM4 10 18 5.0 5.0 4 0.1 0.30 2.0
Example 5 8 14 3 3 2 0.08 0.40 3.0 3-6 Ti, 0.03-0.06 Zr FM5 10 18 5
5 4 0.10 0.50 3.5 Example 6 10 6 1 4 6 0.13 0.01 1.6 1.6-1.8 Re;
6-7Ta, FM6 12 8 2 5 7 0.15 0.015 1.8 1-2 Hf, 0.03-0.06 Zr Example 7
11 7 1 4 5 0.13 0.10 1.8 2.0-4.0 Re; 2-4Ta, FM7 13 9 3 6 6.5 0.15
0.15 2.0 1-2 Hf, 0.03-0.06 Zr Example 8 8.5 12 0.5 2 4 0.14 0.30
2.0 2.2-2.4 Re; 6-7Ta, FM8 9.5 14 0.8 3 5 0.16 0.40 2.2 1-2 Hf,
0.03-0.06 Zr Example 9 18 10 9 -- 1 0.1 0.20 1.6 3-3.3 Ti FM9 20 12
11 2 0.12 0.30 1.8 Example 10 9 10 0.4 9 4.5 0.15 0.15 1.0 0.8-1.2
Ti, 1.2-1.5 Hf FM10 11 12 0.6 11 5.5 0.17 0.20 1.2 2.5-3.5 Ta
Example 11 9 10 0.4 9 4.5 0.15 0.25 -- 0.8-1.2 Ti, 1.2-1.5 Hf FM11
11 12 0.6 11 5.5 0.17 0.30 2.5-3.5 Ta
TABLE-US-00002 TABLE 2 Weld Examples of Crack Susceptibility and
Tensile Properties of Laser Clad Welds at a Temperature of
1800.degree. F. Produced on Inconel 738 Substrate Using Welding
Materials in Form of Powders Weld 0.2% Offset Exam- Yield ple
Welding Strength, UTS, Elong. Cracks, Crack No. Material KSI KSI %
Yes/No Location 1 FM1 -- -- -- Yes HAZ 2 FM3 38.3 50.4 14.0 No -- 3
FM4 37.7 51.2 11.2 No -- 4 FM2 22.8 28.9 9.8 No -- 5 FM 5 -- -- --
Yes WELD 6 FM6 32.2 39.8 10.8 No -- 7 FM8 33.8 49.2 12.8 No -- 8
FM9 22.8 34.5 16.0 No -- 9 FM11 -- -- -- Yes HAZ 10 Rene 80 39.1
51.sup. 7.8 Yes HAZ Note: Despite of HAZ cracking clad welds
produced using standard Rene 80 and FM1 filler material were
subjected to tensile and rupture testing respectively to obtain the
base line data for comparison.
TABLE-US-00003 TABLE 3 Rupture Properties of Laser Clad Welds
Produced Using Powder Welding Materials Test Welding Temperature,
Stresses, Rupture Material .degree. F. KSI Time, Hours Elongation,
% FM1 1800 15 2.8 9.7 FM4 1350 67 1,000* -- FM4 1800 15 60.5 9.0
FM7 1350 67 1,000* -- FM7 1800 15 25.9 4.1 FM10 1350 67 1,000* --
FM10 1800 15 30.9 5.4 Note: *Testing was discontinued
TABLE-US-00004 TABLE 4 Oxidation Resistance of Laser Clad Welds at
a Temperature of 1825.degree. F. Type of Filler Material That Was
Used to Weight Loss in grams at 1825 .+-. 15.degree. F. for Produce
Weld 820 Hours Rene 80 -1.5059 FM11 -1.6916 FM4 -0.8622
TABLE-US-00005 TABLE 5 Oxidation Resistance of Laser Clad Welds at
a Temperature of 2050.degree. F. Type of Filler Material That Was
Used to Weight Change g/cm.sup.2 at 2012 .+-. 15.degree. F. for
Produce Weld 300 Hours Rene 80 -0.3014 FM4 -0.1935 FM6 +0.0953
TABLE-US-00006 TABLE 5 Mechanical Properties of Butt Joints at a
Temperature of 1800.degree. F. Produced Using GTAW-MA with
Preferable Welding Materials in the Form of Wire Weld 0.2% Offset
Rupture Exam- Yield Test Rupture ple Base Welding Strength, UTS,
Elong. Stresses, Time, Elong. No. Material Material KSI KSI % KSI
Hours % 11 Inconel 738 FM3 40 51.05 9.75 15 78 9.5 12 Rene 77 FM9
42.3 48.7 12 15 48 11.4 13 GTD 111 FM4 44.2 52.1 14.5 15 92 7.8 14
Mar M002 FM10 60.95 80.95 9.35 22 173.3 12
* * * * *