US3879831A - Nickle base high temperature abradable material - Google Patents

Nickle base high temperature abradable material Download PDF

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US3879831A
US3879831A US382597A US38259773A US3879831A US 3879831 A US3879831 A US 3879831A US 382597 A US382597 A US 382597A US 38259773 A US38259773 A US 38259773A US 3879831 A US3879831 A US 3879831A
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diatomaceous earth
approximately
gamma
oxide
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David V Rigney
Peter W Schilke
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Raytheon Technologies Corp
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United Aircraft Corp
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C22C32/0089—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with other, not previously mentioned inorganic compounds as the main non-metallic constituent, e.g. sulfides, glass
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S277/00—Seal for a joint or juncture
    • Y10S277/935—Seal made of a particular material
    • Y10S277/939—Containing metal
    • Y10S277/94—Alloy

Definitions

  • 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.
  • abradable type seals may be seen to ha e 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.
  • 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.(l(ltlF has not previously been provided.
  • 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 y y and B phases for sustained use at temperatures of l.8()(lF and up to 2.()()()F for short term operation.
  • the present invention also relates to a method for making such a material.
  • the present invention contemplates a homogeneous and porous abradable seal material structure comprising principally y y and ,3 phases for use in clevated temperatures operating apparatus consisting essentially of. by weight. 604409 Ni. 2-126? Cr. 1-109? Co. 4-209; Al. up to 3?? of a refractory metal selected from the group consisting of Y. Hf and La and 3-l 5% inert powder material selected from the group consist ing of diatomaceous earth (DE. boron nitride. silicon glass. mica. vermiculite asbestos. molybdenum disulfide. graphite. cobalt oxide. cerium oxide and zinc oxide.
  • the composition consists essentially of. by weight.
  • 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 consist ing of NiCoCrAl. NiCr and CoAl and ('oCr and MM 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. fill-80% Ni. 2-127: Cr.
  • l-IOQZ Co. 4-2071 Aland 3-l59 inert powder It is preferred to include small amounts of refractory metal selected from the Group 3h or 4h elements. preferably from the group consisting of yttrium. hafnium and lanthanum in order to retard oxide spallation.
  • the abradable coating is produced by blending a powder mixture of. by weight. l0 4t)'/r nickel-chromium alloy. 5-20'4 cobaltaluminumyttrium alloy and 35-65% coated inert material selected from the group consisting of diatomaceous earth. boron nitride. silicon glass. mica. ⁇ ermiculite 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.
  • seals of the above composition have been found to possess unique characteristics which are superior to the prior art ahradables as outlined above.
  • 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.
  • 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 holding member such as a conventional metal honeycomb of suitable material and configuration.
  • metals may be used depending on the specific requirements of the engine.
  • stainless steel such as A.l.S.l. type 321 and nickel or nickel-cobalt base alloys may be employed satisfactorily.
  • suitable means such as an alkali cleaner or conventional solvents.
  • alloy powders selected from the group consisting of NiCrCoAl. NiCr and COM. 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. 60440 nowadays Ni. 2-] 2% Cr. l-lU7r Co. 1-20% Al and 3-l5/r 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.
  • a suitable binder such as a cellulose nitrate solution
  • 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.
  • 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 y, y and [3 phases and having a total porosity of approximately 35-65%.
  • a refractory metal powder is preferably added in an amount of up to 3% by weight.
  • Refractory metals selected from the Group 3b and 41) 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 0.0] to [00%. by weight.
  • the refractory metals have been found to increase the adherence of oxide layers such as M 0 COAi O; and NlAlgO4 to the seal particles.
  • the inert materials serve primar ily 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.
  • the sintering step is me cuted 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:
  • silica glass (Eccospheres 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 nickelaluminum 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 1.8UUF and able to withstand temperatures up to 2.000F 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.
  • EXAMPLE 1 A powder mixture having the following composition was thoroughly dry blended and mixed together:
  • NiCr 80% Ni. 20% Cr
  • Metco 43 F NS CoAlY (30% Co. 69% Al. 1% Y) 325 mesh 55% Ni-coated DE. (85% Ni. 15% DE.)
  • the above mixture was mixed with a cellulose nitrate solution as a carrier and packed into a Nicraloy reinforcing honeycomb foil. After carrier evaporation, the material was sintered in argon at 2.140F 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 y 7 and B 'phases and had a composition consisting essentially of 70.7% Ni. 60% Cr. 4.5% Co. 10.3% A1. 0.2% Y and 8.3% diatomaceous earth.
  • the sintered seal composition of this example had a density of 2.6 grams/cm" and exhibited a mean coefficient of thermal expansion from 6.7 X 10 in./in. F at room temperature to 10.2 X 10 in./in. "F at 1.832F. 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.
  • NiCr 80% Ni. Cr
  • Metco 43 F NS 20% CoAlY (30% Co. 69% A1.
  • Example 111 The techniques of Example 1 were again duplicated on a powder mixture having the following composition:
  • Example W The techniques of Example 1 were duplicated on a powder mixture having the following composition:
  • the material was sintered in argon at l.850F for two hours and 1.950F 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% A1. 0.3% Y and 7.5% diatomaceous earth.
  • Example V The techniques of Example I were again duplicated on a powder mixture of:
  • NiCr 80% Ni. 20% Cr
  • Metco 43 F NS 10% CoAlY (30% Co. 69% Al. 1% Y) -325 mesh 55% Ni-coated DE. (85% Ni. 15% DE.)
  • the material was sintered in argon at 1.750F for two hours. 1.950F for two hours and 2.050F for two hours.
  • the product was similar to those above and consisted essentially of 74.7% Ni, 70% Cr. 3.0% Co. 6.9% A1. 0.1% Y and 8.3% diatomaceous earth.
  • 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.
  • a homogeneous and porous abradable seal structure consisting principally of'y y and B phases for use in elevated temperature apparatus consisting essentially of. by weight. 60-80% Ni. 2-l2% Cr. 1-10% Co. 4-20% Al. up to 3% ofa 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.
  • a homogeneous and porous abradable seal struc ture consisting principally ofy 'y' and [3 phases for use in elevated temperature operating apparatus consisting essentially of. by weight. 65-75% Ni. 3-9% Cr. 4-8% Co. 7l8% Al. up to 1.0% of a refractory metal selected from the group consisting of yttrium. hafnium and lanthanum and 510% inert powder material selected from the group consisting of diatomaceous earth. boron nitride. silicon glass. mica. vermiculite asbestos. molybdenum disulflde. graphite. cobalt oxide. cerium oxide and zinc oxide.

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.

Description

United States Patent;
Rigney et a1.
1 1 NICKLE BASE HIGH TEMPERATURE ABRADABLE MATERIAL 175] inventors: David V. Rigney. Portland; Peter W.
Schilke, Meridcn. both of Conn.
173] Assignee: United Aircraft Corporation. East Hartford Conn.
[22] Filed: July 25. 1973 [21] Appl. No.: 382,597
Related U.S. Application Data 163| Continuation-in-part of Scr. No. 199.023. Nov. 15.
197 l abandoned.
[52] U.S. Cl. 29/1825: 29/182129/197; 75/171; 415/174 [51} Int. Cl. B221" 3/00; B22f 1/00 [58} Field of Search ,1 75/171; 29/182 1825. 29/197; 415/174 156] References Cited UNITED STATES PATENTS 2.930521 3/1961) Kochring 415/174 3.051694 9/l9o2 Daunt ct a1. 117/95 3.545344 12/1970 Emannclson et a1. 29/197 3.622.234 11 1971 Seyholt v 4 a w a 7. 75/171 3.811719 6/1974 Schilke 29/182 Primary Exuminer-Benjamin R. Padgett Ass/sum! Exumim'r-B. Hunt Armrney, Agwm or FirmJohn D. Del Ponti 1571 ABSTRACT NICKLE BASE HIGH TEMPERATURE ABRADABLE MATERIAL This is a continuation-in-part of US. Pat. application Ser. No. H.013 filed Nov. I5. 19 1. now abandoned.
BACKGROUND OF THE lNVENTlON 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 pro ide 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.
ln 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 pene trate 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 clear ance. A typical abradable seal construction of this type is shown in the US. Fat. to Emanuelson et al No. ll7-83.4 I 3.136 and in copending U.S. Pat. application Ser. No. M1946 (Attorney-s Docket EH-358X) filed July 9. 1971. now abandoned by the present inventors. both being of common assignee ith the present invention.
While in theory abradable type seals may be seen to ha e 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. ln 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.(l(ltlF 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 y y and B phases for sustained use at temperatures of l.8()(lF and up to 2.()()()F for short term operation. The present invention also relates to a method for making such a material.
ln brief the present invention contemplates a homogeneous and porous abradable seal material structure comprising principally y y and ,3 phases for use in clevated temperatures operating apparatus consisting essentially of. by weight. 604409 Ni. 2-126? Cr. 1-109? Co. 4-209; Al. up to 3?? of a refractory metal selected from the group consisting of Y. Hf and La and 3-l 5% inert powder material selected from the group consist ing of diatomaceous earth (DE. 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. 3-9'7! Cr. 4-871 Co. 7-18 Al. up to l'/( Y. Hf or La and 5-1071 inert powder material. An optimum composition for such an abradable seal is approximately. by weight. 70.9% Ni. 4.4% Cr. b.07r Co. 10.47! Al. 0.10)? Y and 8.39% diatomaceous earth powder.
Investigations have shown that the total porosity should be established at approximately -65%. pref erably at approximately -60% and most preferably at approximately SO /1.
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 consist ing of NiCoCrAl. NiCr and CoAl and ('oCr and MM 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. fill-80% Ni. 2-127: Cr. l-IOQZ Co. 4-2071 Aland 3-l59 inert powder. It is preferred to include small amounts of refractory metal selected from the Group 3h or 4h 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. l0 4t)'/r nickel-chromium alloy. 5-20'4 cobaltaluminumyttrium alloy and 35-65% coated inert material selected from the group consisting of diatomaceous earth. boron nitride. silicon glass. mica. \ermiculite 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% cobaltaluminum-yttrium alloy and -60% nickel or nickelchromium coated diatomaceous earth material is blended and sintered. The most preferred technique requires the blending and sintering ofa powder mixture consisting essentially of approximately. by weight. 30% nickel-chromium alloy. I592 cobalt-aluminum-yttrium alloy and 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 ahradables 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.l.S.l. 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 COM. 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. 60440?! Ni. 2-] 2% Cr. l-lU7r Co. 1-20% Al and 3-l5/r 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 y, y and [3 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 41) 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 0.0] to [00%. by weight. The refractory metals have been found to increase the adherence of oxide layers such as M 0 COAi O; and NlAlgO4 to the seal particles.
It is to be noted that the inert materials serve primar ily 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 me cuted 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:
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/DE. being varied from 30-85% ofthc 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 \liCr 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 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 nickelaluminum 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 1.8UUF and able to withstand temperatures up to 2.000F 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 CoAlY (30% Co. 69% Al. 1% Y) 325 mesh 55% Ni-coated DE. (85% Ni. 15% DE.)
The above mixture was mixed with a cellulose nitrate solution as a carrier and packed into a Nicraloy reinforcing honeycomb foil. After carrier evaporation, the material was sintered in argon at 2.140F 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 y 7 and B 'phases and had a composition consisting essentially of 70.7% Ni. 60% Cr. 4.5% Co. 10.3% A1. 0.2% Y and 8.3% diatomaceous earth.
The sintered seal composition of this example had a density of 2.6 grams/cm" and exhibited a mean coefficient of thermal expansion from 6.7 X 10 in./in. F at room temperature to 10.2 X 10 in./in. "F at 1.832F. 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 ll The techniques of Example 1 were duplicated on a powder mixture having the following composition:
25% NiCr (80% Ni. Cr) Metco 43 F NS 20% CoAlY (30% Co. 69% A1. 1% Y1325 mesh 4% Al flake 51% Ni-coated DE. (85% Ni. 15% DE.)
After carrier evaporation. the material was sintered in argon at 2.140F for two hours. The resulting product was a porous homogeneous abradable structure consisting principally of'y y and B phases ofa composition consisting essentially of 63.5% Ni. 5.0% Cr. 6.0% Co. 17.8% A1. 0.2% Y and 7.5% diatomaceous earth and having properties similar to those set forth in Example 1.
Example 111 The techniques of Example 1 were again duplicated on a powder mixture having the following composition:
% NiCr (80% Ni. 20% Cr) Metco 43 F NS 20% CoAlY Co. 69% Al. 1% Y) -325 mesh 55% Nl-coated DE. (85% Ni. 15% DE.)
After carrier evaporation. the material was sintered in argon at l.850F for two hours and 1950F for three hours. The resulting product was a porous homogeneous abradable structure consisting principally of 'y y 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 W The techniques of Example 1 were duplicated on a powder mixture having the following composition:
25% NiCr Ni. 20% Cr) Metco 43 F NS 25% CoAlY (30% Co. 69% Al. 1% Y) -325 mesh 50% Ni-coated DE. Ni. 15% DE.)
After carrier evaporation. the material was sintered in argon at l.850F for two hours and 1.950F 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% A1. 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 DE. (85% Ni. 15% DE.)
After carrier evaporation. the material was sintered in argon at 1.750F for two hours. 1.950F for two hours and 2.050F for two hours. The product was similar to those above and consisted essentially of 74.7% Ni, 70% Cr. 3.0% Co. 6.9% A1. 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.
What is claimed is:
l. A homogeneous and porous abradable seal structure consisting principally of'y y and B phases for use in elevated temperature apparatus consisting essentially of. by weight. 60-80% Ni. 2-l2% Cr. 1-10% Co. 4-20% Al. up to 3% ofa 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 struc ture consisting principally ofy 'y' and [3 phases for use in elevated temperature operating apparatus consisting essentially of. by weight. 65-75% Ni. 3-9% Cr. 4-8% Co. 7l8% Al. up to 1.0% of a refractory metal selected from the group consisting of yttrium. hafnium and lanthanum and 510% inert powder material selected from the group consisting of diatomaceous earth. boron nitride. silicon glass. mica. vermiculite asbestos. molybdenum disulflde. 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 pnmus ubruduhlc scul mutcmuccuus curth.
y I 4 I I v cmmsung 7 7 B 6. The 1n\ cntmn ufclulm whcrcm sand structure has scs for use in elevated temperature apparatus cnnsisting essentially of upprmimutcl h weight. 70.99? Ni. 44% Cr. (MW: Cu, 10.4% Al. 0.10); Y and 8.39 diatoa total porosity of approximately 35-6571

Claims (6)

1. A HOMOGENEOUS AND POROUS ABRADABLE SEAL STRUCTURE CONSISTING PRINCIPALLY OF Y, Y'' AND B PHASES FOR USE IN ELEVATED TEMPERATURE APPARATUS CONSISTING ESSENTILLY 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 NITRID3, 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%.
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US3985513A (en) * 1975-06-02 1976-10-12 Alexandr Fedorovich Silaev Nickel-base metal-ceramic heat-resistant sealing material
JPS51144311A (en) * 1975-05-28 1976-12-11 Brunswick Corp Compressed metallic mat
US4055705A (en) * 1976-05-14 1977-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal barrier coating system
US4060250A (en) * 1976-11-04 1977-11-29 De Laval Turbine Inc. Rotor seal element with heat resistant alloy coating
US4094673A (en) * 1974-02-28 1978-06-13 Brunswick Corporation Abradable seal material and composition thereof
US4155755A (en) * 1977-09-21 1979-05-22 Union Carbide Corporation Oxidation resistant porous abradable seal member for high temperature service
DE3015867A1 (en) * 1979-05-11 1980-11-20 United Technologies Corp METHOD FOR PRODUCING AN OBJECT COVERED AND A CERAMIC COVERED OBJECT
FR2459879A1 (en) * 1979-06-27 1981-01-16 United Technologies Corp AIR-COOLED SEAL WITH CERAMIC MATERIAL FOR A GAS TURBINE ENGINE
US4247249A (en) * 1978-09-22 1981-01-27 General Electric Company Turbine engine shroud
US4274875A (en) * 1977-07-20 1981-06-23 Brico Engineering Limited Powder metallurgy process and product
US4336276A (en) * 1980-03-30 1982-06-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Fully plasma-sprayed compliant backed ceramic turbine seal
US4377371A (en) * 1981-03-11 1983-03-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Laser surface fusion of plasma sprayed ceramic turbine seals
DE3246303A1 (en) * 1981-12-14 1983-08-04 United Technologies Corp., 06101 Hartford, Conn. METHOD FOR APPLYING A CERAMIC COATING
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US4546047A (en) * 1981-01-14 1985-10-08 United Technologies Corporation Composite tape preform for abradable seals
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US5024884A (en) * 1984-12-24 1991-06-18 United Technologies Corporation Abradable seal having particulate erosion resistance
US5064727A (en) * 1990-01-19 1991-11-12 Avco Corporation Abradable hybrid ceramic wall structures
US5080934A (en) * 1990-01-19 1992-01-14 Avco Corporation Process for making abradable hybrid ceramic wall structures
USRE33876E (en) * 1975-09-11 1992-04-07 United Technologies Corporation Thermal barrier coating for nickel and cobalt base super alloys
US5196471A (en) * 1990-11-19 1993-03-23 Sulzer Plasma Technik, Inc. Thermal spray powders for abradable coatings, abradable coatings containing solid lubricants and methods of fabricating abradable coatings
US5326647A (en) * 1991-09-18 1994-07-05 Mtu Motoren- Und Turbinen-Union Abradable layer for a turbo-engine and a manufacturing process
US5536022A (en) * 1990-08-24 1996-07-16 United Technologies Corporation Plasma sprayed abradable seals for gas turbine engines
US5976695A (en) * 1996-10-02 1999-11-02 Westaim Technologies, Inc. Thermally sprayable powder materials having an alloyed metal phase and a solid lubricant ceramic phase and abradable seal assemblies manufactured therefrom
US5975845A (en) * 1995-10-07 1999-11-02 Holset Engineering Company, Ltd. Turbomachinery abradable seal
US6203021B1 (en) * 1996-12-10 2001-03-20 Chromalloy Gas Turbine Corporation Abradable seal having a cut pattern
WO2001044533A1 (en) * 1999-12-15 2001-06-21 Pratt & Whitney Canada Corp. Abradable coatings
US6533285B2 (en) 2001-02-05 2003-03-18 Caterpillar Inc Abradable coating and method of production
US6547522B2 (en) * 2001-06-18 2003-04-15 General Electric Company Spring-backed abradable seal for turbomachinery
US20040126225A1 (en) * 2002-12-31 2004-07-01 General Electric Grc Rotary machine sealing assembly
US20040239040A1 (en) * 2003-05-29 2004-12-02 Burdgick Steven Sebastian Nozzle interstage seal for steam turbines
US6916529B2 (en) * 2003-01-09 2005-07-12 General Electric Company High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same
US20050232757A1 (en) * 2003-05-27 2005-10-20 General Electric Company Wear resistant variable stator vane assemblies
US20050281668A1 (en) * 2004-06-21 2005-12-22 Nava Irene L Low-mid turbine temperature abradable coating
US20050281704A1 (en) * 2004-06-21 2005-12-22 Siemens Westinghouse Power Corporation Boron free joint for superalloy component
US20060029494A1 (en) * 2003-05-27 2006-02-09 General Electric Company High temperature ceramic lubricant
US20060162546A1 (en) * 2005-01-21 2006-07-27 Sanden Corporation Sealing member of a compressor
US20060245676A1 (en) * 2005-04-28 2006-11-02 General Electric Company High temperature rod end bearings
US20070044792A1 (en) * 2005-08-30 2007-03-01 Aerogen, Inc. Aerosol generators with enhanced corrosion resistance
US20080286459A1 (en) * 2007-05-17 2008-11-20 Pratt & Whitney Canada Corp. Method for applying abradable coating
US20090136740A1 (en) * 2007-11-28 2009-05-28 Reynolds George H Article having composite layer
US20110014035A1 (en) * 2009-06-29 2011-01-20 Yoshitaka Kojima High-reliability turbine metal sealing material
US20130140774A1 (en) * 2010-01-13 2013-06-06 Dresser-Rand Company Annular seal apparatus and method
WO2014095887A1 (en) 2012-12-18 2014-06-26 Commissariat à l'énergie atomique et aux énergies alternatives Process for coating a substrate with an abradable ceramic material, and coating thus obtained
US20160177971A1 (en) * 2014-03-31 2016-06-23 Rolls-Royce Plc Gas turbine engine
EP2075415B1 (en) * 2007-12-27 2016-10-19 Techspace Aero Lightened annular stator structure for aircraft turboshaft engine
US10247027B2 (en) 2016-03-23 2019-04-02 United Technologies Corporation Outer airseal insulated rub strip
US10267174B2 (en) 2016-04-28 2019-04-23 United Technologies Corporation Outer airseal abradable rub strip
CN110760781A (en) * 2019-09-27 2020-02-07 武汉钢铁有限公司 Gradient sealing coating structure resistant to gas corrosion and preparation method thereof
US10669878B2 (en) 2016-03-23 2020-06-02 Raytheon Technologies Corporation Outer airseal abradable rub strip
WO2020172034A1 (en) * 2019-02-20 2020-08-27 General Electric Company Honeycomb structure including abradable material
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Publication number Priority date Publication date Assignee Title
US4094673A (en) * 1974-02-28 1978-06-13 Brunswick Corporation Abradable seal material and composition thereof
JPS51144311A (en) * 1975-05-28 1976-12-11 Brunswick Corp Compressed metallic mat
JPS56481B2 (en) * 1975-05-28 1981-01-08
US3985513A (en) * 1975-06-02 1976-10-12 Alexandr Fedorovich Silaev Nickel-base metal-ceramic heat-resistant sealing material
USRE33876E (en) * 1975-09-11 1992-04-07 United Technologies Corporation Thermal barrier coating for nickel and cobalt base super alloys
US4055705A (en) * 1976-05-14 1977-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal barrier coating system
US4060250A (en) * 1976-11-04 1977-11-29 De Laval Turbine Inc. Rotor seal element with heat resistant alloy coating
US4274875A (en) * 1977-07-20 1981-06-23 Brico Engineering Limited Powder metallurgy process and product
US4155755A (en) * 1977-09-21 1979-05-22 Union Carbide Corporation Oxidation resistant porous abradable seal member for high temperature service
US4247249A (en) * 1978-09-22 1981-01-27 General Electric Company Turbine engine shroud
DE3015867A1 (en) * 1979-05-11 1980-11-20 United Technologies Corp METHOD FOR PRODUCING AN OBJECT COVERED AND A CERAMIC COVERED OBJECT
FR2459879A1 (en) * 1979-06-27 1981-01-16 United Technologies Corp AIR-COOLED SEAL WITH CERAMIC MATERIAL FOR A GAS TURBINE ENGINE
US4289446A (en) * 1979-06-27 1981-09-15 United Technologies Corporation Ceramic faced outer air seal for gas turbine engines
DE3023441A1 (en) * 1979-06-27 1981-01-22 United Technologies Corp OUTER AIR SEAL
US4336276A (en) * 1980-03-30 1982-06-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Fully plasma-sprayed compliant backed ceramic turbine seal
US4546047A (en) * 1981-01-14 1985-10-08 United Technologies Corporation Composite tape preform for abradable seals
US4377371A (en) * 1981-03-11 1983-03-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Laser surface fusion of plasma sprayed ceramic turbine seals
DE3246303A1 (en) * 1981-12-14 1983-08-04 United Technologies Corp., 06101 Hartford, Conn. METHOD FOR APPLYING A CERAMIC COATING
US4481237A (en) * 1981-12-14 1984-11-06 United Technologies Corporation Method of applying ceramic coatings on a metallic substrate
DE3326728A1 (en) * 1982-07-27 1984-02-02 Dunlop Ltd., London LOAD-BEARING HEAT ISOLATOR
US4505640A (en) * 1983-12-13 1985-03-19 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
DE3447470A1 (en) * 1983-12-27 1985-07-04 United Technologies Corp., Hartford, Conn. MATERIAL FOR A GRINDABLE SEAL, ITS USE IN TURBINES AND METHOD FOR THE PRODUCTION THEREOF
DE3537044A1 (en) * 1984-12-21 1986-06-26 United Technologies Corp., Hartford, Conn. ARC-SHAPED WALL AND SEALING SEGMENT FOR AN AXIAL FLOW MACHINE
US5024884A (en) * 1984-12-24 1991-06-18 United Technologies Corporation Abradable seal having particulate erosion resistance
EP0416954A1 (en) * 1989-09-08 1991-03-13 Toyota Jidosha Kabushiki Kaisha Abradable material for a turbo machine
US5185217A (en) * 1989-09-08 1993-02-09 Toyota Jidosha Kabushiki Kaisha Relatively displacing apparatus
US5080934A (en) * 1990-01-19 1992-01-14 Avco Corporation Process for making abradable hybrid ceramic wall structures
US5064727A (en) * 1990-01-19 1991-11-12 Avco Corporation Abradable hybrid ceramic wall structures
US5536022A (en) * 1990-08-24 1996-07-16 United Technologies Corporation Plasma sprayed abradable seals for gas turbine engines
US5196471A (en) * 1990-11-19 1993-03-23 Sulzer Plasma Technik, Inc. Thermal spray powders for abradable coatings, abradable coatings containing solid lubricants and methods of fabricating abradable coatings
US5434210A (en) * 1990-11-19 1995-07-18 Sulzer Plasma Technik, Inc. Thermal spray powders for abradable coatings, abradable coatings containing solid lubricants and methods of fabricating abradable coatings
US5326647A (en) * 1991-09-18 1994-07-05 Mtu Motoren- Und Turbinen-Union Abradable layer for a turbo-engine and a manufacturing process
US5975845A (en) * 1995-10-07 1999-11-02 Holset Engineering Company, Ltd. Turbomachinery abradable seal
US5976695A (en) * 1996-10-02 1999-11-02 Westaim Technologies, Inc. Thermally sprayable powder materials having an alloyed metal phase and a solid lubricant ceramic phase and abradable seal assemblies manufactured therefrom
US6203021B1 (en) * 1996-12-10 2001-03-20 Chromalloy Gas Turbine Corporation Abradable seal having a cut pattern
WO2001044533A1 (en) * 1999-12-15 2001-06-21 Pratt & Whitney Canada Corp. Abradable coatings
US6533285B2 (en) 2001-02-05 2003-03-18 Caterpillar Inc Abradable coating and method of production
US6547522B2 (en) * 2001-06-18 2003-04-15 General Electric Company Spring-backed abradable seal for turbomachinery
US6969231B2 (en) * 2002-12-31 2005-11-29 General Electric Company Rotary machine sealing assembly
US20040126225A1 (en) * 2002-12-31 2004-07-01 General Electric Grc Rotary machine sealing assembly
US6916529B2 (en) * 2003-01-09 2005-07-12 General Electric Company High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same
US7220098B2 (en) 2003-05-27 2007-05-22 General Electric Company Wear resistant variable stator vane assemblies
US20060029494A1 (en) * 2003-05-27 2006-02-09 General Electric Company High temperature ceramic lubricant
US20050232757A1 (en) * 2003-05-27 2005-10-20 General Electric Company Wear resistant variable stator vane assemblies
US20040239040A1 (en) * 2003-05-29 2004-12-02 Burdgick Steven Sebastian Nozzle interstage seal for steam turbines
US7641985B2 (en) * 2004-06-21 2010-01-05 Siemens Energy, Inc. Boron free joint for superalloy component
US20050281668A1 (en) * 2004-06-21 2005-12-22 Nava Irene L Low-mid turbine temperature abradable coating
US7165946B2 (en) 2004-06-21 2007-01-23 Solar Turbine Incorporated Low-mid turbine temperature abradable coating
US20050281704A1 (en) * 2004-06-21 2005-12-22 Siemens Westinghouse Power Corporation Boron free joint for superalloy component
US20060162546A1 (en) * 2005-01-21 2006-07-27 Sanden Corporation Sealing member of a compressor
US20060245676A1 (en) * 2005-04-28 2006-11-02 General Electric Company High temperature rod end bearings
US7543992B2 (en) 2005-04-28 2009-06-09 General Electric Company High temperature rod end bearings
US20070044792A1 (en) * 2005-08-30 2007-03-01 Aerogen, Inc. Aerosol generators with enhanced corrosion resistance
US20080286459A1 (en) * 2007-05-17 2008-11-20 Pratt & Whitney Canada Corp. Method for applying abradable coating
US7998604B2 (en) 2007-11-28 2011-08-16 United Technologies Corporation Article having composite layer
US20090136740A1 (en) * 2007-11-28 2009-05-28 Reynolds George H Article having composite layer
EP2075415B1 (en) * 2007-12-27 2016-10-19 Techspace Aero Lightened annular stator structure for aircraft turboshaft engine
US20110014035A1 (en) * 2009-06-29 2011-01-20 Yoshitaka Kojima High-reliability turbine metal sealing material
US8801373B2 (en) * 2009-06-29 2014-08-12 Hitachi Ltd. High-reliability turbine metal sealing material
US20130140774A1 (en) * 2010-01-13 2013-06-06 Dresser-Rand Company Annular seal apparatus and method
WO2014095887A1 (en) 2012-12-18 2014-06-26 Commissariat à l'énergie atomique et aux énergies alternatives Process for coating a substrate with an abradable ceramic material, and coating thus obtained
US20160177971A1 (en) * 2014-03-31 2016-06-23 Rolls-Royce Plc Gas turbine engine
US9752593B2 (en) * 2014-03-31 2017-09-05 Rolls-Royce Plc Method of manufacturing a gas turbine engine having a fan track liner with an abradable layer
US10247027B2 (en) 2016-03-23 2019-04-02 United Technologies Corporation Outer airseal insulated rub strip
US10669878B2 (en) 2016-03-23 2020-06-02 Raytheon Technologies Corporation Outer airseal abradable rub strip
US10267174B2 (en) 2016-04-28 2019-04-23 United Technologies Corporation Outer airseal abradable rub strip
WO2020172034A1 (en) * 2019-02-20 2020-08-27 General Electric Company Honeycomb structure including abradable material
US11149354B2 (en) 2019-02-20 2021-10-19 General Electric Company Dense abradable coating with brittle and abradable components
CN110760781A (en) * 2019-09-27 2020-02-07 武汉钢铁有限公司 Gradient sealing coating structure resistant to gas corrosion and preparation method thereof

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