U.S. patent number 3,879,831 [Application Number 05/382,597] was granted by the patent office on 1975-04-29 for nickle base high temperature abradable material.
This patent grant is currently assigned to United Aircraft Corporation. Invention is credited to David V. Rigney, Peter W. Schilke.
United States Patent |
3,879,831 |
Rigney , et al. |
April 29, 1975 |
Nickle base high temperature abradable material
Abstract
A homogeneous and porous abradable seal material structure
comprising principally .gamma., .gamma.' and/or .beta. phases for
use in elevated temperature operating apparatus consisting
essentially of, by weight, 60-80% Ni, 2-12% Cr, 1-10% Co, 4-20% Al,
up to 3% of a refractory metal selected from the group consisting
of yttrium, hafnium and lanthanum and 3-15% inert powder material
selected from the group consisting of diatomaceous earth (D.E.),
boron nitride, silicon glass, mica, vermiculite asbestos,
molybdenum disulfide, graphite, cobalt oxide, cerium oxide and zinc
oxide.
Inventors: |
Rigney; David V. (Portland,
CT), Schilke; Peter W. (Meriden, CT) |
Assignee: |
United Aircraft Corporation
(East Hartford, CT)
|
Family
ID: |
26894385 |
Appl.
No.: |
05/382,597 |
Filed: |
July 25, 1973 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
|
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199023 |
Nov 15, 1971 |
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|
Current U.S.
Class: |
415/173.4;
420/446; 277/940; 277/415 |
Current CPC
Class: |
C22C
32/0089 (20130101); C22C 32/00 (20130101); F01D
11/122 (20130101); Y10S 277/94 (20130101) |
Current International
Class: |
F01D
11/08 (20060101); F01D 11/12 (20060101); C22C
32/00 (20060101); B22f 003/00 (); B22f
001/00 () |
Field of
Search: |
;75/171
;29/182,182.5,197 ;415/174 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Padgett; Benjamin R.
Assistant Examiner: Hunt; B.
Attorney, Agent or Firm: Del Ponti; John D.
Parent Case Text
This is a continuation-in-part of U.S. Pat. application Ser. No.
199,023 filed Nov. 15, 1971, now abandoned.
Claims
What is claimed is:
1. A homogeneous and porous abradable seal structure consisting
principally of .gamma. , .gamma.' and .beta. phases for use in
elevated temperature apparatus consisting essentially of, by
weight, 60-80% Ni, 2-12% Cr, 1-10% Co, 4-20% Al, up to 3% of a
refractory metal selected from the group consisting of yttrium,
hafnium and lanthanum and 3-15% inert powder material selected from
the group consisting of diatomaceous earth, boron nitride, silicon
glass, mica, vermiculite asbestos, molybdenum disulfide, graphite,
cobalt oxide, cerium oxide and zinc oxide.
2. The invention of claim 1 wherein said structure has a total
porosity of approximately 35-65%.
3. A homogeneous and porous abradable seal structure consisting
principally of .gamma. , .gamma.' and .beta. phases for use in
elevated temperature operating apparatus consisting essentially of,
by weight, 65-75% Ni, 3-9% Cr, 4-8% Co, 7-18% Al, up to 1.0% of a
refractory metal selected from the group consisting of yttrium,
hafnium and lanthanum and 5-10% inert powder material selected from
the group consisting of diatomaceous earth, boron nitride, silicon
glass, mica, vermiculite asbestos, molybdenum disulfide, graphite,
cobalt oxide, cerium oxide and zinc oxide.
4. The invention of claim 3 wherein said structure has a total
porosity of approximately 35-65%.
5. A homogeneous and porous abradable seal material structure
consisting principally of .gamma. , .gamma.' and .beta. phases for
use in elevated temperature apparatus consisting essentially of
approximately, by weight, 70.9% Ni, 4.4% Cr, 6.0% Co, 10.4% Al,
0.10% Y and 8.3% diatomaceous earth.
6. The invention of claim 5 wherein said structure has a total
porosity of approximately 35-65%.
Description
BACKGROUND OF THE INVENTION
The present invention relates to abradable materials and more
particularly relates to a low friction abradable material which is
resistant to oxidation at elevated temperatures and is especially
suitable for gas turbine engines.
It is known that the efficiency of a gas turbine engine is
dependent in part upon the control of gas leakage between stages in
both the compressor and turbine sections of the engine. Although
the engine is typically designed and manufactured to very precise
dimensional tolerances, it is necessary to provide a sufficient
cold clearance between the tips of the rotating elements and the
surrounding stator assembly to accommodate the differential thermal
growth between the parts as the engine assumes its normal operating
temperature. To this cold clearance must be added the usual
manufacturing tolerances plus an additional safety factor to
provide for limited engine operation at temperatures in excess of
the design temperatures. The requisite clearances thus provided
are, however, generally not sufficiently close to permit the engine
to operate at its maximum theoretical efficiency.
In an effort to remedy this condition, it has been proposed to
utilize an abradable surface on the assembly surrounding the
rotating elements and to permit the knife-edge or squealer tips of
the rotor system to penetrate into the coating as a result of
thermal expansion, thereby permitting the rotor to seat itself
against the casing assembly with what is essentially a zero
clearance. A typical abradable seal construction of this type is
shown in the U.S. Pat. to Emanuelson et al No. 117-83,413,136 and
in copending U.S. Pat. application Ser. No. 161,946 (Attorney's
Docket EH-3588) filed July 9, 1971, now abandoned by the present
inventors, both being of common assignee with the present
invention.
While in theory abradable type seals may be seen to have great
potential in improving engine performance, current techniques and
abradable seal structures have not been entirely satisfactory in
their practical application to current high performance jet
engines. In particular, the requirement for seal material which has
a high thermal stability and melting point, a relatively constant
degree of abradability and good thermal shock characteristics while
possessing strong adherence to the metal substrate to which it is
applied as well as good structural integrity in an elevated
temperature environment up to 2,000.degree.F has not previously
been provided.
SUMMARY OF THE INVENTION
The present invention relates to an abradable seal facing material
for use in elevated temperature coating apparatus and more
particularly relates to a homogeneous and porous nickel-base
abradable seal material structure comprising principally .gamma. ,
.gamma.' and .beta. phases for sustained use at temperatures of
1,800.degree.F and up to 2,000.degree.F for short term operation.
The present invention also relates to a method for making such a
material.
In brief the present invention contemplates a homogeneous and
porous abradable seal material structure comprising principally
.gamma. , .gamma.' and .beta. phases for use in elevated
temperatures operating apparatus consisting essentially of, by
weight, 60-80% Ni, 2-12% Cr, 1-10% Co, 4-20% A1, up to 3% of a
refractory metal selected from the group consisting of Y, Hf and La
and 3-15% inert powder material selected from the group consisting
of diatomaceous earth (D.E.), boron nitride, silicon glass, mica,
vermiculite asbestos, molybdenum disulfide, graphite, cobalt oxide,
cerium oxide and zinc oxide. Preferably the composition consists
essentially of, by weight, 65-75% Ni, 3-9% Cr, 4-8% Co, 7-18% Al,
up to 1% Y, Hf or La and 5-10% inert powder material. An optimum
composition for such an abradable seal is approximately, by weight,
70.9% Ni, 4.4% Cr, 6.0% Co, 10.4% Al, 0.10% Y and 8.3% diatomaceous
earth powder.
Investigations have shown that the total porosity should be
established at approximately 35-65%, preferably at approximately
40-60% and most preferably at approximately 50%.
The present invention not only contemplates an abradable seal
product but also the process for making the same and more
particularly encompasses a method wherein alloy powders selected
from the group consisting of NiCoCrAl, NiCr and CoAl and CoCr and
NiAl are mixed with an inert powder or metal coated inert powder
selected from the group consisting of diatomaceous earth, boron
nitride, silicon glass, mica, vermiculite asbestos, molybdenum
disulfide, graphite, cobalt oxide, cerium oxide and zinc oxide
coated with Ni, Co, Cr, Al or alloys thereof and sintered to
produce a homogeneous and porous abradable material consisting
essentially of approximately, by weight, 60-80% Ni, 2-12% Cr, 1-10%
Co, 4-20% Al and 3-15% inert powder. It is preferred to include
small amounts of refractory metal selected from the Group 3b or 4b
elements, preferably from the group consisting of yttrium, hafnium
and lanthanum in order to retard oxide spallation.
In the preferred method, the abradable coating is produced by
blending a powder mixture of, by weight, 10-40% nickel-chromium
alloy, 5-20% cobalt-aluminumyttrium alloy and 35-65% coated inert
material selected from the group consisting of diatomaceous earth,
boron nitride, silicon glass, mica, vermiculite asbestos,
molybdenum disulfide, graphite, cobalt oxide, cerium oxide and zinc
oxide, said inert material being coated with nickel, cobalt,
chromium, aluminum or alloys thereof, and sintering. In a more
preferred method, a powder mixture consisting essentially of, by
weight, 25-35% nickel-chromium alloy, 12-20%
cobalt-aluminum-yttrium alloy and 45-60% nickel or nickel-chromium
coated diatomaceous earth material is blended and sintered. The
most preferred technique requires the blending and sintering of a
powder mixture consisting essentially of approximately, by weight,
30% nickel-chromium alloy, 15% cobalt-aluminum-yttrium alloy and
55% nickel or nickel-chromium coated diatomaceous earth
material.
Seals of the above composition have been found to possess unique
characteristics which are superior to the prior art abradables as
outlined above. In addition, the seals of the present invention
have a low thermal conductivity and act as insulators to allow the
maintenance of a steep thermal gradient between the hot gas path
and the outer diameter of the seal wall while minimizing thermal
losses.
DESCRIPTION OF THE PREFERRED EMBODIMENT
The seal material of the present invention is preferably used in
conjunction with a holding member such as a conventional metal
honeycomb of suitable material and configuration. A variety of
metals may be used depending on the specific requirements of the
engine. For example, stainless steel such as A.I.S.I. type 321 and
nickel or nickel-cobalt base alloys may be employed satisfactorily.
As will be appreciated, of course, prior to usage the holding
member must be cleaned and degreased by suitable means such as an
alkali cleaner or conventional solvents.
After cleaning, alloy powders selected from the group consisting of
NiCrCoAl, NiCr and CoAl, and CoCr and NiAl are thoroughly dry
blended and mixed together with inert material powder selected from
the group consisting of diatomaceous earth, boron nitride, silicon
glass, mica, vermiculite asbestos, molybdenum disulfide, graphite,
cobalt oxide, cerium oxide and zinc oxide and preferably having a
coating selected from the group consisting of nickel, cobalt,
chromium and aluminum and alloys thereof. The total composition of
the powders is selected so as to correspond to, by weight, 60-80%
Ni, 2-12% Cr, 1-10% Co, 4-20% Al and 3-15% inert material. The dry
powders are mixed with a suitable binder such as a cellulose
nitrate solution and packed, as by troweling, into the honeycomb.
The carrier is allowed to evaporate and the mixture is then
sintered in a nonoxidizing atmosphere, such as argon or a vacuum,
according to a schedule selected so as to limit the amount of
liquid phase present at any given time to an amount below that
which will cause the material to slump and thus lose its porosity.
As will be appreciated, a satisfactory sintering time-temperature
cycle can be varied and depends on the particular composition of
the material being treated and its intended application. The
resulting product is a homogeneous abradable seal material
comprising principally .gamma. , .gamma.' and .beta. phases and
having a total porosity of approximately 35-65%.
In order to further improve the properties of the above system, a
refractory metal powder is preferably added in an amount of up to
3% by weight. Refractory metals selected from the Group 3b and 4b
elements such as yttrium, hafnium and lanthanum are satisfactory.
The refractory metals should be uniformly distributed in the seal
material and are preferably present in an amount of 0.01 to 1.00%,
by weight, The refractory metals have been found to increase the
adherence of oxide layers such as Al.sub.2 O.sub.3, CoAl.sub.2
O.sub.4 and NiAl.sub.2 O.sub.4 to the seal particles.
It is to be noted that the inert materials serve primarily to
increase lubricity and provide an adjustable porosity and density.
The inert materials may have a particle size generally within the
range of 100 to 200 mesh.
It will be appreciated that the sintering step is executed in order
to form a bond between the particles themselves and between the
particles and the holding member, as well as to form oxidation
resistant alloys. The aluminum containing starting alloy powder,
whether it be CoAl, NiAl or CoAlY, NiAlY, etc., acts as an active
ingredient. With its inclusion in the pack, there results a liquid
phase sintering wherein the sintering process is accelerated with
resulting better diffusion and bonding than heretofore
experienced.
The abradable seal filler material is in a sense a free standing
sinter and is therefore quite porous, the porosity being in the
range of approximately 35-65%. It is also in a broad sense a cermet
since there is present both metal and oxide which contributes to
the structural and physical characteristics of the system.
Particle sizes of the components for the powder mix play an
important role in providing a satisfactory seal product in both
controlling green density and in controlling the sintering kinetics
of the materials system. If the particles are too small, a too
dense material is achieved which causes excessive blade wear and if
too large, the structural strength of the seal is lessened, the
number of bonds per unit volume becomes inadequate and erosion
resistance is diminished. The following table sets forth the
particle size distributions which have been found most
satisfactory:
Table I ______________________________________ ASTM % by weight
Component Sieve min max ______________________________________ NiCr
+170 -- 1 -230 95 -- +270 -- 20 -270 80 -- CoAlY +325 -- 5 -325 95
-- Ni or NiCr +150 -- 5 Coated D.E. -325 -- 30
______________________________________
Experiments were performed varying the relative proportions of
coated diatomaceous earth and NiCr to optimize the composition. It
was found that with Ni/D.E. or NiCr/D.E. being varied from 30-85%
of the total seal composition, an increase in the amount of coated
D.E. resulted in a softening of the sinter while a decrease caused
a hardening thereof. Experimentation also showed that increasing
amounts of NiCr resulted in increasing hardness values for the
sinter while decreasing amounts thereof caused a concomitant
decrease in hardness. The various ranges expressed hereinbefore as
being satisfactory were selected based on dynamic blade tip
interactions and erosion testing to match blade configurations and
gas velocities in the turbine environment. Other experiments
conducted using coated boron nitride, silica glass
(Eccospheres.sup.TM), mica and graphite gave results which were
satisfactory, although inferior to the coated diatomaceous earth.
Other inert, relatively soft materials which are stable and fairly
lubricious, such as cobalt oxide, cerium oxide, zinc oxide,
molybdenum disulfide or vermiculite asbestos or the like, may be
used. Suitable coatings for the inert powder material are nickel,
cobalt, chromium, aluminum or iron or alloys thereof such as
nickel-aluminum or nickel-chrome-aluminum.
The abradable seal material of the present invention has shown
itself to be suitable for use at sustained operating temperatures
up to 1,800.degree.F and able to withstand temperatures up to
2,000.degree.F for short term operation. The composition is
resistant to galling, is easily abraded and the utilization of the
coated inert diatomaceous earth particles provides insulating and
thermal stability characteristics.
In order that those skilled in the art will better understand how
the abradable seal of the present invention may be obtained, the
following specific examples are provided. All percentages are by
weight unless otherwise noted.
EXAMPLE 1
A powder mixture having the following composition was thoroughly
dry blended and mixed together:
30% NiCr (80% Ni, 20% Cr) Metco 43 F NS
15% coAlY (30% Co, 69% Al, 1% Y) --325 mesh
55% Ni-coated D.E. (85% Ni, 15% D.E.)
The above mixture was mixed with a cellulose nitrate solution as a
carrier and packed into a Nicraloy.sup.TM reinforcing honeycomb
foil. After carrier evaporation, the material was sintered in argon
at 2,140.degree.F for two hours. The resulting product was a porous
homogeneous abradable structure having an open porosity of
approximately 40% and a total porosity of approximately 50% with a
mean pore size of about 0.001 inch. The structure consisted
essentially of .gamma. , .gamma.' and .beta. phases and had a
composition consisting essentially of 70.7% Ni, 6.0% Cr, 4.5% Co,
10.3% Al, 0.2% Y and 8.3% diatomaceous earth.
The sintered seal composition of this example had a density of 2.6
grams/cm.sup.3 and exhibited a mean coefficient of thermal
expansion from 6.7 .times. 10 .sup..sup.-6 in./in. .degree.F at
room temperature to 10.2 .times. 10.sup..sup.-6 in./in. .degree.F
at 1,832.degree.F. After accumulating approximately 600 hours of
engine testing, the seal composition remained in good condition
with minimal erosion and no spalling from the substrate. In all, it
was found that the use of a honeycomb filled with the abradable
seal material of the present example, as compared to an unfilled
honeycomb, increased the life of the honeycomb by a factor of at
least 3. Further, primarily because of its excellent insulating
properties, the shroud of the gas turbine engine is rendered more
dimensionally stable and is thereby benefited.
EXAMPLE II
The techniques of Example I were duplicated on a powder mixture
having the following composition:
25% NiCr (80% Ni, 20% Cr) Metco 43 F NS
20% coAlY (30% Co, 69% Al, 1% Y) -325 mesh
4% Al flake
51% Ni-coated D.E. (85% Ni, 15% D.E.)
After carrier evaporation, the material was sintered in argon at
2,140.degree.F for two hours. The resulting product was a porous
homogeneous abradable structure consisting principally of .gamma. ,
.gamma.' and .beta. phases of a composition consisting essentially
of 63.5% Ni, 5.0% Cr, 6.0% Co, 17.8% Al, 0.2% Y and 7.5%
diatomaceous earth and having properties similar to those set forth
in Example I.
Example III
The techniques of Example I were again duplicated on a powder
mixture having the following composition:
25% NiCr (80% Ni, 20% Cr) Metco 43 F NS
20% coAlY (30% Co, 69% Al, 1% Y) -325 mesh
55% NI-coated D.E. (85% Ni, 15% D.E.)
After carrier evaporation, the material was sintered in argon at
1,850.degree.F for two hours and 1950.degree.F for three hours. The
resulting product was a porous homogeneous abradable structure
consisting principally of .gamma. , .gamma.' and ' phases of a
composition consisting essentially of 66.7% Ni, 5.0% Cr, 6.0% Co,
13.8% Al, 0.2% Y and 8.3% diatomaceous earth and having properties
similar to those set forth in Example I.
Example IV
The techniques of Example I were duplicated on a powder mixture
having the following composition:
25% NiCr (80% Ni, 20% Cr) Metco 43 F NS
25% coAlY (30% Co, 69% Al, 1% Y) -325 mesh
50% Ni-coated D.E. (85% Ni, 15% D.E.)
After carrier evaporation, the material was sintered in argon at
1,850.degree.F for two hours and 1,950.degree.F for three hours.
The product was similar to those above and consisted essentially of
62.5% Ni, 5.0% Cr, 7.5% Co, 17.2% Al, 0.3% Y and 7.5% diatomaceous
earth.
Example V
The techniques of Example I were again duplicated on a powder
mixture of:
35% NiCr (80% Ni, 20% Cr) Metco 43 F NS
10% coAlY (30% Co, 69% Al, 1% Y) -325 mesh
55% Ni-coated D.E. (85% Ni, 15% D.E.)
After carrier evaporation, the material was sintered in argon at
1,750.degree.F for two hours, 1,950.degree.F for two hours and
2,050.degree.F for two hours. The product was similar to those
above and consisted essentially of 74.7% Ni, 7.0% Cr, 3.0% Co, 6.9%
Al, 0.1% Y and 8.3% diatomaceous earth.
It is to be understood that various modifications may be made
without departing from the spirit of the present invention. It is
recognized, for example, that while the inert powder material is
preferably coated with nickel or an alloy thereof, it may also be
coated with cobalt, iron, chromium or aluminum or their alloys. The
invention contemplates the use of superalloy powders with a liquid
phase sintering and inert particles coated with a metal, as
described.
What has been set forth above is intended primarily as exemplary to
enable those skilled in the art in the practice of the invention
and it should therefor be understood that within the scope of the
appended claims, the invention may be practiced in other ways than
as specifically described.
* * * * *