U.S. patent number 3,649,225 [Application Number 04/877,321] was granted by the patent office on 1972-03-14 for composite coating for the superalloys.
This patent grant is currently assigned to United Aircraft Corporation. Invention is credited to Alfred E. Simmons, Jr..
United States Patent |
3,649,225 |
Simmons, Jr. |
March 14, 1972 |
COMPOSITE COATING FOR THE SUPERALLOYS
Abstract
Improved operating lifetimes are provided for the superalloys
through use of a composite coating comprising a chromium or
chromium-rich interlayer adjacent the superalloy substrate surface
and an oxidation-resistant outer layer comprising an alloy of iron,
cobalt and/or nickel alloyed with selected amounts of chromium,
aluminum and yttrium.
Inventors: |
Simmons, Jr.; Alfred E. (East
Hartford, CT) |
Assignee: |
United Aircraft Corporation
(East Hartford, CT)
|
Family
ID: |
25369728 |
Appl.
No.: |
04/877,321 |
Filed: |
November 17, 1969 |
Current U.S.
Class: |
428/651; 428/656;
428/667; 428/938 |
Current CPC
Class: |
C23C
28/023 (20130101); C22C 38/18 (20130101); C23C
14/58 (20130101); C23C 14/16 (20130101); C23C
14/5886 (20130101); C23C 14/5806 (20130101); Y10T
428/12743 (20150115); Y10T 428/12778 (20150115); Y10S
428/938 (20130101); Y10T 428/12854 (20150115) |
Current International
Class: |
C22C
38/18 (20060101); C23C 14/58 (20060101); C23C
28/02 (20060101); C23C 14/16 (20060101); B32b
015/00 () |
Field of
Search: |
;29/198,194,196.6
;75/171 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Bizot; Hyland
Claims
What is claimed is:
1. A composite article resistant to oxidation at high temperature
comprising:
a substrate selected from the group consisting of the
high-temperature nickel-base and cobalt-base alloys having
strengths suitable for structural applications in a gas turbine
engine environment,
an interlayer, adjacent the substrate surface and bonded thereto,
selected from the group consisting of chromium and its alloys,
and an oxidation resistant outer layer thereover, bonded to the
interlayer, which consists essentially of chromium, aluminum, at
least one rare earth element, and at least one element selected
from the group consisting of iron, cobalt, and nickel.
2. A composite article according to claim 1 wherein: in the outer
layer,
the chromium content is 15-30 weight percent,
the aluminum content is 10-20 weight percent,
the rare earth element is yttrium,
and the yttrium content is at least 0.1 weight percent.
3. A coated gas turbine engine component comprising:
a substrate selected from the group consisting of the high
temperature, high-strength nickel-base and cobalt-base alloys,
an interlayer, adjacent the substrate surface and bonded thereto,
selected from the group consisting of chromium and its alloys,
and an oxidation resistant outer layer superimposed on and bonded
to the interlayer, the outer layer consisting essentially of, by
weight, 25-29 percent chromium, 10-14 percent aluminum, 0.4-0.9
percent yttrium, balance substantially iron.
4. A coated gas turbine engine component comprising:
a substrate selected from the group consisting of the high
temperature, high-strength nickel-base and cobalt-base alloys,
an interlayer, adjacent the substrate surface and bonded thereto,
selected from the group consisting of chromium and its alloys,
and an oxidation resistant outer layer superimposed on and bonded
to the interlayer, the outer layer consisting essentially of, by
weight, 21-25 percent chromium, 10-15 percent aluminum, 0.4-0.9
percent yttrium, balance substantially cobalt.
Description
BACKGROUND OF THE INVENTION
The present invention relates in general to high-temperature,
oxidation-resistant coatings for the superalloys, particularly as
applied to gas turbine engine components.
A limiting factor in the application of many of the superalloys to
demanding environments such as those encountered by jet engine
hardware is their susceptibility to high-temperature oxidation and
corrosion. For this reason these alloys are generally provided with
suitable surface coatings for increased oxidation resistance. For
current operating conditions the most widely used coatings have
been provided by reacting aluminum with the alloy to form surface
aluminides which preferentially oxidize to form surface oxides
through which the transport rates of the oxidizing species are low.
Typical of processes of this type is that described in the U.S.
Pat. No. to Joseph 3,102,044.
Both turbine blade and vane life in existing engines, and the
extent of power increases requiring higher engine operating
temperatures, are largely limited by the durability of the
coatings. In the past, the inadequacy of current coatings to give
long term protection against corrosion at very high temperatures
has prevented use of some of the stronger nickel-base alloys, such
as B-1900, in applications where their properties otherwise
indicate the desirability of their use.
At high temperatures in the dynamic oxidizing environment of a gas
turbine engine, temperature fluctuations caused by the mixing of
hot combustion gases with cooler secondary air, or those associated
with variations in engine power levels, give rise to thermally
induced strains in the coatings at the metal-oxide interface which
are sufficiently large to spall the protective oxide layer.
Furthermore, at a temperature of about 2,000.degree. F., nickel and
the nickel-base superalloys begin to exhibit a great alloying
affinity for the usual coating constituents, and particularly for
aluminum, as recognized in the U.S. Pat. No. to Maxwell 3,450,212.
Thus, a loss of coating protection in a dynamic oxidizing
environment at very high temperature, involves both an inward and
an outward loss of one or more of the protective species.
In a series of copending applications of the present assignee,
there are described a number of coating compositions for the
superalloys which have doubled the endurance of the coated
components at high temperature and have in addition permitted
engine performance increases associated with the higher
temperatures of current interest. In application Ser. No. 731,650,
filed May 23, 1968 for an Iron Base Coating for the Superalloys,
now U.S, Pat. No. 3,542,530 there is described a preferred coating
alloy comprising, by weight, 25-29 percent chromium, 12-14 percent
aluminum, 0.6-0.9 percent yttrium, balance iron, hereinafter
referred to as the FeCrAlY coating. In application Ser. No. 795,616
filed Jan. 31, 1969 for a Cobalt Base Coating for the Superalloys,
there is described a preferred coating composition comprising, by
weight, 19-24 percent chromium, 13-17 percent aluminum, 0.6-0.9
percent yttrium, balance cobalt, hereinafter referred to as the
CoCrAlY coating. A NiCrAlY coating comprising, by weight, 20-35
percent chromium, 15-20 percent aluminum, 0.05-0.3 percent yttrium,
balance nickel is disclosed in application Ser. No. 734,740 filed
June 5, 1968. All of the above coating alloys are resistant of
oxidation, thermal spalling, and to interdiffusion with the
substrate when compared to alternative coating schemes. However, it
has been found that even with these advanced coatings there exists
a measure of coating-substrate interdiffusion.
It is known that, in some instances, improved coating performance
may be obtained through coating processes involving multiple
surface treatments. In the U.S. Pat. No. to Gibson 2,809,127, the
surface of an alloy is first chromized and then aluminized to
increase the oxidation resistance at high temperature. As in the
case of Joseph, supra, the basic oxidation protection in Gibson is
dependent upon the reaction of aluminum with the constituents of
the substrate at the surface to be protected.
SUMMARY OF THE INVENTION
It is the object of the present invention to provide an improved
coating for the superalloys characterized by long term durability
in dynamic oxidizing environments at very high temperatures. There
is provided a composite coating comprising a chromium or
predominantly chromium interlayer at the superalloy surface to be
protected and an outer layer of high-oxidation resistance
comprising an alloy of iron, cobalt or nickel containing selected
amounts of chromium, aluminum and a rare earth element such as
yttrium.
In a preferred embodiment of the invention, the composite coating
comprises an interlayer of chromium and an outer layer consisting
essentially of, by weight, 25-29 percent chromium, 12-14 percent
aluminum, 0.6-0.9 percent yttrium, balance iron.
In another preferred embodiment, the composite coating comprises an
interlayer of chromium and an outer layer consisting essentially
of, by weight, 19-24 percent chromium, 13-17 percent aluminum,
0.6-0.9 percent yttrium, balance cobalt.
BRIEF DESCRIPTION OF THE DRAWING
The drawing is a chart comparing the various coatings for the
nickel-base superalloys in terms of durability.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Prior to the generation of the FeCrAlY, CoCrAlY and NiCrAlY coating
alloys, and as currently provided in production jet engines,
component surface protection has normally been provided by exposing
the substrate to aluminum or aluminum vapor at high temperature and
promoting a reaction of the aluminum with one or more of the
substrate constituents to form protective aluminides. In the
FeCrAlY-type coating system, the oxidation protection is effected,
not by a coating-substrate reaction, but rather by the coating
alloy per se. The coating alloy of itself is oxidation-resistant
and relatively immune to thermal spalling and no intermediate
coatings are required in terms of the basic function which the
coating is to provide, nor in fact is any interdiffusion of
substrate or intermediate layer constituents into the coating
desired. In the present composite coating, an interlayer of
chromium is provided to specifically reduce the outer
coating-substrate interdiffusion and by so doing to improve the
durability of the coating as demonstrated by an increased operating
lifetime for a component so coated.
Thus, the durability of the FeCrAlY-type coatings have been found
to be limited not by deficiencies in the oxidation-erosion
resistance of the coatings per se, but rather is a function of the
extent of aluminum depletion in the coating resultant from the
coating-substrate interdiffusion, particularly at temperatures in
excess of about 2,000.degree. F.
It was found that a substantial improvement in the endurance of the
FeCrAlY-type coatings can be provided by interposing an interlayer
of chromium or a predominantly chromium alloy between the outer
coating and the substrate to act as a diffusion barrier
therebetween, minimizing the depletion of aluminum in the outer
coating by this mechanism. This chromium interlayer may be produced
by any of the available methods for generating such coatings or
surface layers including electroplating, electroplating plus
diffusion heat treatment, pack cementation, plasma spray, slurry
spray, or any other technique providing a predominantly chromium
layer at or on the substrate surface. It is relatively immaterial
how the interlayer formed subject, however, to the requirement that
the process be one yielding an interlayer composed primarily of
chromium.
The FeCrAlY-type outer coatings are typically applied utilizing
vacuum vapor deposition methods and apparatus. As explained, the
efficacy of these coatings is dependent upon the correct coating
alloy composition being deposited on the surface to be protected.
These coatings are characterized by high-melting points as alloyed
and by diverse melting points insofar as the elemental constituents
are concerned. Care must taken in the coating formation process to
provide all of the desired coating alloy species in the correct
proportions in the coating as applied. Satisfactory results have
been attained by vapor deposition in a vacuum utilizing an electron
beam heat source, as suggested in the U.S. Pat. No. to Steigerwald
2,746,420.
It should be noted that it is the unique combination comprising the
composite coating that provides the coating endurance improvements
established by test. One of the incidents of the undesirable
coating-substrate interdiffusion, in addition to aluminum depletion
in the coating, is contamination of the substrate by the coating
constituents. The use of the chromium interlayer has been found not
only to prevent such detrimental contamination by the coating
elements but also to provide none of itself. In addition, the
chromium interlayer adjacent the FeCrAlY coating has appeared to
provide no observable detrimental effect on the coating alloy
itself nor on its adherence to the substrate.
Tests conducted on several nickel-base superalloy substrates,
including such superalloys as B-1900, MAR M200, and NX 188, and on
the cobalt-base superalloys such as MAR M302, have indicated that
coating life improvements on the order of 50 percent are achieved,
as graphically illustrated in the drawing.
EXAMPLE
Various nickel-base and cobalt-base superalloy parts to be coated
were embedded in a pack of blended powders composed of, by weight,
84.5 percent alumina, 15 percent chromium, and 0.5 percent ammonium
chloride. After purging with argon, the pack was sealed and the
parts were chromized at 2,100.degree. F. for 4 hours. In general,
surface buildups of 0.002-0.005 in. resulted from pack chromizing
under these conditions.
Subsequent to the chromizing operation, parts were mounted in the
vacuum chamber of electron beam melting apparatus, preheated, and
coated by vapor deposition from a molten pool of coating material
in a vacuum of 10.sup.-.sup.4 Torr or better to typical outer
coating thicknesses of 0.001-0.005 in.
Following deposition of the outer coating, the coated cobalt-base
substrates were heat treated at 1,900.degree. F. for about an hour
in vacuum with a cool in a nonoxidizing atmosphere at a rate
equivalent to air cool. The nickel-base superalloy substrates after
coating, and the cobalt-base superalloy substrates after coating
and heat treatment, as coated, were dry glass bead peened at 15N
for about 2 minutes in accordance with AMS 2,430. Subsequent to
peening the coated parts were heated to 1,975.degree. F. in dry
argon or hydrogen, or vacuum; held at heat for 4 hours; and cooled
at a rate equivalent to air cooling.
A variety of superalloy substrates were provided with several
composite coating combinations, particularly with respect to the
outer coating composition. After extensive testing, it was
determined that the preferred FeCrAlY outer coating chemistry
conformed to the following:
Component percent by weight chromium 25-29 aluminum 10.5-12.5
yttrium 0.4-0.9 oxygen 0.03 max. nitrogen 0.01 max. hydrogen 0.01
max. other elements, total 0.5 max. iron remainder
The most preferred CoCrAlY coating in the composite coating
consisted of:
Component percent by weight chromium 21-25 aluminum 12-14 yttrium
0.4-0.9 oxygen 0.03 nitrogen 0.01 hydrogen 0.01 other elements,
total 0.5 cobalt remainder
Although the invention has been described in detail, in its broader
aspects it is not limited to the exact details described, for
obvious modifications will occur to those skilled in the art.
* * * * *