JPH0379523B2 - - Google Patents
Info
- Publication number
- JPH0379523B2 JPH0379523B2 JP60146912A JP14691285A JPH0379523B2 JP H0379523 B2 JPH0379523 B2 JP H0379523B2 JP 60146912 A JP60146912 A JP 60146912A JP 14691285 A JP14691285 A JP 14691285A JP H0379523 B2 JPH0379523 B2 JP H0379523B2
- Authority
- JP
- Japan
- Prior art keywords
- sintered
- lining
- inlet lining
- spherical particles
- inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000012798 spherical particle Substances 0.000 claims description 16
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 15
- 229910052759 nickel Inorganic materials 0.000 claims description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052804 chromium Inorganic materials 0.000 claims description 3
- 239000011651 chromium Substances 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 239000010949 copper Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 2
- 239000010410 layer Substances 0.000 description 9
- 239000000463 material Substances 0.000 description 8
- 239000000843 powder Substances 0.000 description 7
- 229910045601 alloy Inorganic materials 0.000 description 6
- 239000000956 alloy Substances 0.000 description 6
- 239000011248 coating agent Substances 0.000 description 5
- 238000000576 coating method Methods 0.000 description 5
- 239000011247 coating layer Substances 0.000 description 4
- 238000005245 sintering Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 230000003628 erosive effect Effects 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 229910018487 Ni—Cr Inorganic materials 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000002241 glass-ceramic Substances 0.000 description 2
- 238000003915 air pollution Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000005868 electrolysis reaction Methods 0.000 description 1
- 238000009713 electroplating Methods 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000013528 metallic particle Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000000053 physical method Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/10—Sintering only
- B22F3/11—Making porous workpieces or articles
- B22F3/1103—Making porous workpieces or articles with particular physical characteristics
- B22F3/1112—Making porous workpieces or articles with particular physical characteristics comprising hollow spheres or hollow fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/002—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of porous nature
-
- 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
- F01D11/125—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 with a reinforcing structure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Materials Engineering (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laminated Bodies (AREA)
- Powder Metallurgy (AREA)
Description
【発明の詳細な説明】
本発明は、ターボ機械、特にガスタービンのロ
ータ羽根とケーシングとの間の半径方向のクリア
ランスを減少させるための、焼結された入口ライ
ニングであつて、グラフアイトコアと、ニツケル
又はクローム、アルミニウム又は銅とのニツケル
合金から成る薄壁の被覆層とを有している球状粒
子から成る形式のものに関する。DETAILED DESCRIPTION OF THE INVENTION The present invention is a sintered inlet lining for reducing the radial clearance between the rotor blades and the casing of a turbomachine, particularly a gas turbine. , of the type consisting of spherical particles having a thin-walled covering layer of nickel or a nickel alloy with chromium, aluminum or copper.
ターボ機械においては効率と運転特性はロータ
羽根とケーシングとの間の半径方向のクリアラン
スをできるだけわずかに保つことに成功するか、
否かに関連する。半径方向のクリアランスを減少
させたい場合には、ケーシングをロータの羽根が
擦過する場合に該ケーシングライニングを摩滅さ
せることで前記クリアランスを形成することが可
能である。この場合にはロータの羽根の摩滅はで
きるだけわずかにしたい。 In turbomachinery, efficiency and operating characteristics are determined by success in keeping the radial clearance between the rotor blades and the casing as small as possible;
Related to whether or not. If it is desired to reduce the radial clearance, it is possible to create said clearance by abrading the casing lining when the rotor blades rub against the casing. In this case, it is desirable to minimize wear on the rotor blades.
DE−A2239840号によればターボ機械のロータ
の羽根とケーシングとの間の半径方向のクリアラ
ンスを減少させるために用いられる多孔質の入口
ライニングが公知である。この入口ライニングは
主として３つの成分から成り、そのうちの第１の
部分がNi−Cr合金粉末であり、第２の部分が
CoAlY合金粉末であり、第３の部分が球状粒子
から成る粉末である。前記球状粒子はグラフアイ
トコアとNi、Fe、Co、Cr又はそれらの合金から
成る被覆層とを有している。ライニングが、多孔
性であること及び金属製の粒子の割合が大きいこ
とに基づき、ライニングの摩滅粒子によつて、下
流側におかれた構成要素が侵蝕されるか又はギヤ
ツプ又は小さな冷却孔が閉塞する惧れがある。 From DE-A 2239840 a porous inlet lining is known which is used to reduce the radial clearance between the rotor blades and the casing of a turbomachine. This inlet lining mainly consists of three components, the first part is Ni-Cr alloy powder and the second part is Ni-Cr alloy powder.
It is a CoAlY alloy powder, and the third part is a powder consisting of spherical particles. The spherical particles have a graphite core and a coating layer made of Ni, Fe, Co, Cr, or an alloy thereof. Due to the porosity of the lining and the large proportion of metallic particles, abrasion particles of the lining can erode downstream components or block gaps or small cooling holes. There is a risk that this will happen.
さらにUS−Ａ−4291089号によれば粉末を炎射
することにより形成される入口ライニングが公知
である。この場合には粉末は滑り特性のよい非金
属材料から成るコアを有しかつニツケル又はニツ
ケル合金から成る被覆層を有している。このよう
にして形成されたライニングも多孔質である。 Furthermore, according to US Pat. No. 4,291,089, an inlet lining is known which is produced by flame bombarding a powder. In this case, the powder has a core made of a non-metallic material with good sliding properties and a cover layer made of nickel or a nickel alloy. The lining formed in this way is also porous.
さらにDE−Ａ−2421504号によればガラス−セ
ラミツクコアと該ガラス−セラミツクコアを取囲
む金属製被覆層とから成る粒子から成る焼結材料
が公知である。このような材料はその硬度及び耐
摩滅性に基づき、ブレーキライニング、電気的な
接点及び集電子には適しているが、入口ライニン
グには適していない。 Furthermore, DE-A-2421504 discloses a sintered material consisting of particles consisting of a glass-ceramic core and a metallic coating surrounding the glass-ceramic core. Due to their hardness and abrasion resistance, such materials are suitable for brake linings, electrical contacts and current collectors, but not for inlet linings.
本発明の課題はターボ機械のケーシングとロー
タ羽根との間の半径方向のクリヤランスを減少さ
せると同時に温度及び侵蝕に対する影響を受けに
くい、比較的にやわらかい入口ライニングを提供
することである。 It is an object of the present invention to provide a relatively soft inlet lining that reduces the radial clearance between the casing of a turbomachine and the rotor blades and at the same time is less susceptible to temperature and erosion.
この課題は本発明によれば、入口ライニングが
密に閉じられた表面を有する層を成すように焼結
されていることによつて解決された。 This object is achieved according to the invention in that the inlet lining is sintered in layers with a tightly closed surface.
本発明の重要な利点は球状粒子の被覆層が金属
から成るために球状粒子の結合が容易でかつ圧縮
が容易であることである。他の利点は球状粒子の
コア及び被覆層の構成により複合材料における金
属製の割合を公知の入口ライニングの場合よりも
低く保つことができることである。これによつて
タービンにおける摩滅した材料の有害な影響（例
えば冷却孔の閉塞、後続のタービンの侵蝕、大気
汚染）が減少される。 An important advantage of the present invention is that since the coating layer of the spherical particles is made of metal, the spherical particles can be easily bonded and compressed. Another advantage is that the composition of the spherical particle core and the covering layer allows the proportion of metal in the composite to be kept lower than in the case of known inlet linings. This reduces the detrimental effects of worn material on the turbine (eg, cooling hole blockage, subsequent turbine erosion, air pollution).
最後に本発明による入口ライニングの別の利点
は、ロータにおける羽根先端の摩滅が小さくなる
と同時に温度の影響が小さくなることである。 Finally, another advantage of the inlet lining according to the invention is that the wear of the blade tips on the rotor is reduced and at the same time the influence of temperature is reduced.
次に図面について本発明を説明する：
第１図においてはグラフアイトコアとニツケル
又はニツケル合金から成る金属製の被覆層２とか
ら成る球状粒子が示されている。被覆層２はコア
を電気鍍金法（電気分解）で又はCVD法（化学
的に＝電流を用いずに）で形成される。又、他の
物理的な方法（PVD法）を使用することもでき
る。 The invention will now be explained with reference to the drawings: FIG. 1 shows spherical particles consisting of a graphite core and a metallic covering layer 2 of nickel or a nickel alloy. The covering layer 2 is formed on the core by electroplating (electrolysis) or by CVD (chemically = without electric current). Also, other physical methods (PVD method) can also be used.
被覆層の材料としてはニツケル又はニツケル合
金を使用することができる。なぜならば有害な酸
化を伴うことのない使用温度がきわめて高い（ほ
ぼ500°の範囲）からである。グラフアイトコアは
滑り特性が良いために使用される。第１図の球状
粒子はほぼ50μｍと150μｍとの間の直径を有する
ことができる。焼結法で製造されたライニングは
主としてコアの大きさとグラフアイトの量及び使
用された被覆材料ととその量もしくは厚さに関連
する。入口ライニングに高い耐温性が要求される
場合にはニツケルの含有量の多い合金を用いるこ
とができる。使用温度が低い場合にはニツケルは
電解法によつてアルミニウム又は銅と合金されて
被覆層として施される。球状粒子におけるコアの
体積分はほぼ75％であると有利である。コア１の
上の被覆層２の厚さほぼ1.5μｍであるが、ほぼ1/
３の重量分しか有していない。球状粒子は有利に
は真空炉内で≦10-MPaの低い圧力で、1000℃か
らほぼ1500℃までの温度で、数時間に亘つて焼結
される。 Nickel or a nickel alloy can be used as the material for the covering layer. This is because the operating temperatures are extremely high (approximately in the 500° range) without harmful oxidation. Graphite core is used because of its good sliding properties. The spherical particles of FIG. 1 can have a diameter of approximately between 50 and 150 μm. The lining produced by the sintering method depends primarily on the size of the core, the amount of graphite and the coating material used and its amount or thickness. If high temperature resistance is required for the inlet lining, alloys with a high nickel content can be used. At low operating temperatures, nickel is applied electrolytically alloyed with aluminum or copper as a coating. Advantageously, the volume fraction of the core in the spherical particles is approximately 75%. The thickness of the coating layer 2 on the core 1 is approximately 1.5 μm, but the thickness is approximately 1/1 μm.
It only has a weight of 3. The spherical particles are advantageously sintered in a vacuum furnace at low pressures of ≦10 − MPa and at temperatures of from 1000° C. to approximately 1500° C. over a period of several hours.
金属製の被覆材料の合金は、タービンの圧縮機
羽根又はタービン羽根により容易に削り取られ得
るように選択される。この場合にはたいていの羽
根材料は高温で、つまり羽根先端がケーシングを
擦つて回転するときに硬度を低下させることが考
慮されなければならない。 The alloy of the metallic coating material is selected so that it can be easily abraded by the compressor blades or turbine blades of the turbine. In this case it must be taken into account that most blade materials lose their hardness at high temperatures, ie when the blade tips rub against the casing and rotate.
さらに入口ライニングはローラ掛けすることに
より圧縮することもできる。 Furthermore, the inlet lining can also be compacted by rolling.
複合材料から成る焼結された入口ライニングの
研磨面を顕微鏡で見た組織像は第２図に示されて
いる。球状粒子が互いに緊密に結合されているこ
とにより、ガスタービンの攻撃性のガスに起因す
る侵蝕は起り得ない。第２図から判るように純然
たる形状の形態は出発材料（粉末）においてしか
見られない。焼結後には任意の粒状形をとること
ができる。さらに第２図から明らかであるように
焼結後の粒子相互間の良好な結合は被覆材料で得
られる。 A microscopic microscopic image of the polished surface of the composite sintered inlet lining is shown in FIG. Due to the tight bonding of the spherical particles to each other, erosion due to the aggressive gases of the gas turbine cannot occur. As can be seen from FIG. 2, pure shape morphology is only found in the starting material (powder). After sintering, it can take any desired granular shape. Furthermore, as is clear from FIG. 2, a good bond between the particles after sintering is obtained with the coating material.
ライニングは第３図に示されているように複合
材料から成る球状粒子を層状に重ねることで形成
することができる。この場合、組織構造には焼結
条件により所望される影響を与えることができ
る。第３図には担体としてのシート４、例えば
0.2mm厚の金属シートの上に焼結された層が示さ
れている。該層は良好に接着もしくはろう接可能
なバンドを形成している。 The lining can be formed by layering spherical particles of composite material as shown in FIG. In this case, the microstructure can be influenced as desired by the sintering conditions. FIG. 3 shows a sheet 4 as a carrier, e.g.
A sintered layer is shown on top of a 0.2 mm thick metal sheet. The layers form a band that can be easily glued or soldered.
図面は本発明の１実施例を示すものであつて、
第１図は入口ライニングの球状粒子を示した図、
第２図は入口ライニングの研磨面の組織像を示し
た図、第３図は片側に担体ベルト状の表面を有す
る入口ライニングを示した図である。
１……グラフアイトコア、２……被覆層、３…
…球状粒子、４……シート。
The drawings show one embodiment of the invention,
Figure 1 shows the spherical particles of the inlet lining;
FIG. 2 shows the texture of the polished surface of the inlet lining, and FIG. 3 shows the inlet lining with a carrier belt-like surface on one side. 1... graphite core, 2... coating layer, 3...
... Spherical particles, 4... Sheets.
Claims (1)
の半径方向のクリアランスを減少させるための、
焼結された入口ライニングであつて、グラフアイ
トコアと、ニツケル又はクローム、アルミニウム
又は銅とのニツケル合金から成る薄壁の被覆層と
を有している球状粒子から成る形式のものにおい
て、入口ライニングが密に閉じられた表面を有す
る層を成すように焼結された球状粒子だけから成
ることを特徴とする、ターボ機械のための焼結さ
れた入口ライニング。 ２ 焼結されたライニングがローラによりあとか
ら圧縮されている、特許請求の範囲第１項記載の
入口ライニング。 ３ 入口ライニングがケーシング側に担体ベルト
状の、平らな外面を有する連続した層を有してい
る、特許請求の範囲第１項又は第２項記載の入口
ライニング。[Claims] 1. A method for reducing the radial clearance between a rotor blade and a casing of a turbomachine.
sintered inlet lining of the type consisting of spherical particles having a graphite core and a thin-walled covering layer of nickel or a nickel alloy with chromium, aluminum or copper; Sintered inlet lining for turbomachines, characterized in that it consists exclusively of spherical particles sintered in layers with a tightly closed surface. 2. Inlet lining according to claim 1, wherein the sintered lining is subsequently compressed by rollers. 3. Inlet lining according to claim 1 or 2, characterized in that the inlet lining has on the casing side a continuous layer in the form of a carrier belt with a flat outer surface.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19843424661 DE3424661A1 (en) | 1984-07-05 | 1984-07-05 | INLET COVER OF A FLUID MACHINE |
| DE3424661.4 | 1984-07-05 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS6123805A JPS6123805A (en) | 1986-02-01 |
| JPH0379523B2 true JPH0379523B2 (en) | 1991-12-19 |
Family
ID=6239843
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14691285A Granted JPS6123805A (en) | 1984-07-05 | 1985-07-05 | Intake port lining of fluid machine |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP0166940B1 (en) |
| JP (1) | JPS6123805A (en) |
| DE (1) | DE3424661A1 (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL75564A (en) * | 1984-06-25 | 1988-02-29 | United Technologies Corp | Abrasive surfaced article for high temperature service |
| DE4130946C1 (en) * | 1991-09-18 | 1992-09-03 | Mtu Muenchen Gmbh | |
| US5250136A (en) * | 1992-02-12 | 1993-10-05 | General Motors Corporation | Method of making a core/pattern combination for producing a gas-turbine blade or component |
| DE10221114C1 (en) * | 2002-05-03 | 2003-09-11 | Glatt Systemtechnik Gmbh | Seal maintaining gap dimensions under varying thermal stresses in turbo-machine, comprises joined assembly of hollow spheres |
| DE102006009054B4 (en) | 2006-02-27 | 2007-11-22 | Woco Industrietechnik Gmbh | Housing for centrifugal compressor |
| DE102006016147A1 (en) * | 2006-04-06 | 2007-10-11 | Mtu Aero Engines Gmbh | Method for producing a honeycomb seal |
| DE102007009781B4 (en) | 2007-02-27 | 2009-09-17 | Woco Industrietechnik Gmbh | Plastic compressor housing and method for its production |
| DE102007019476A1 (en) * | 2007-04-25 | 2008-11-06 | Mtu Aero Engines Gmbh | Method of producing a scuffing pad |
| DE102007027282B3 (en) | 2007-06-11 | 2008-11-13 | Woco Industrietechnik Gmbh | Plastic compressor housing and method for producing a plastic compressor housing |
| DE102009009389B4 (en) | 2009-02-18 | 2011-03-24 | Woco Industrietechnik Gmbh | Compressor housing, compressor comprising such a compressor housing and method for producing a compressor housing |
| DE102009016803A1 (en) * | 2009-04-09 | 2010-10-14 | Rolls-Royce Deutschland Ltd & Co Kg | Labyrinth rubbing seal for a turbomachine |
| DE102009018801A1 (en) | 2009-04-24 | 2009-11-05 | Daimler Ag | Turbocharger arrangement has turbocharger shaft and turbocharger wheel, where turbocharger shaft with turbocharger wheel is made in single piece from material from group comprising metal matrix and ceramic matrix composites |
| US9719176B2 (en) * | 2013-09-20 | 2017-08-01 | Hrl Laboratories, Llc | Thermal barrier materials and coatings with low heat capacity and low thermal conductivity |
| FR3058457B1 (en) * | 2016-11-10 | 2018-12-07 | Safran Helicopter Engines | PROCESS FOR PRODUCING A TURBOMACHINE BLADE |
| KR20230113275A (en) * | 2020-12-03 | 2023-07-28 | 오를리콘 메트코 (유에스) 아이엔씨. | Electrically conductive filler with improved corrosion resistance |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1089613B (en) * | 1956-04-23 | 1960-09-22 | Siemens Ag | Process for making materials solderable through firmly adhering layers of metal from the iron-nickel-cobalt group |
| US3594216A (en) * | 1969-06-19 | 1971-07-20 | Westinghouse Electric Corp | Vapor phase deposition of metal from a metal-organic beta-ketoamine chelate |
| CA901892A (en) * | 1970-03-20 | 1972-06-06 | Sherritt Gordon Mines Limited | Method of preparing metal alloy coated composite powders |
| US3879830A (en) * | 1971-06-30 | 1975-04-29 | Gte Sylvania Inc | Cathode for electron discharge device having highly adherent emissive coating of nickel and nickel coated carbonates |
| FR2160358B3 (en) * | 1971-11-15 | 1975-08-29 | United Aircraft Corp | |
| CH589221A5 (en) * | 1973-06-29 | 1977-06-30 | Bbc Brown Boveri & Cie | |
| US3975165A (en) * | 1973-12-26 | 1976-08-17 | Union Carbide Corporation | Graded metal-to-ceramic structure for high temperature abradable seal applications and a method of producing said |
| FR2401310A1 (en) * | 1977-08-26 | 1979-03-23 | Snecma | REACTION ENGINE TURBINE CASE |
| JPS5553017A (en) * | 1978-10-16 | 1980-04-18 | Nippon Mining Co | Method of manufacturing multiple coating composite powder |
| US4251272A (en) * | 1978-12-26 | 1981-02-17 | Union Carbide Corporation | Oxidation resistant porous abradable seal member for high temperature service |
| US4291089A (en) * | 1979-11-06 | 1981-09-22 | Sherritt Gordon Mines Limited | Composite powders sprayable to form abradable seal coatings |
| DE3019920C2 (en) * | 1980-05-24 | 1982-12-30 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Device for the outer casing of the rotor blades of axial turbines for gas turbine engines |
| FR2507729B1 (en) * | 1981-06-12 | 1986-08-22 | Snecma | SEAL LIKELY TO BE USED BY ABRASION AND ITS MANUFACTURING METHOD |
-
1984
- 1984-07-05 DE DE19843424661 patent/DE3424661A1/en active Granted
-
1985
- 1985-05-22 EP EP85106255A patent/EP0166940B1/en not_active Expired
- 1985-07-05 JP JP14691285A patent/JPS6123805A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6123805A (en) | 1986-02-01 |
| EP0166940A2 (en) | 1986-01-08 |
| DE3424661A1 (en) | 1986-01-16 |
| EP0166940A3 (en) | 1986-05-21 |
| EP0166940B1 (en) | 1989-03-29 |
| DE3424661C2 (en) | 1988-02-18 |
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