US3844011A - Powder metal honeycomb - Google Patents
Powder metal honeycomb Download PDFInfo
- Publication number
- US3844011A US3844011A US00323371A US32337173A US3844011A US 3844011 A US3844011 A US 3844011A US 00323371 A US00323371 A US 00323371A US 32337173 A US32337173 A US 32337173A US 3844011 A US3844011 A US 3844011A
- Authority
- US
- United States
- Prior art keywords
- grid
- honeycomb
- density
- cavities
- powder metal
- 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 - Lifetime
Links
Images
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
- B22F3/1109—Inhomogenous pore distribution
-
- 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
- B22F7/06—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 composite workpieces or articles from parts, e.g. to form tipped tools
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/006—Pressing and sintering powders, granules or fibres
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
- F16D69/02—Compositions of linings; Methods of manufacturing
- F16D69/027—Compositions based on metals or inorganic oxides
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/14—Sealings between relatively-stationary surfaces by means of granular or plastic material, or fluid
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/20—Geometry three-dimensional
- F05B2250/28—Geometry three-dimensional patterned
- F05B2250/283—Honeycomb
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
- F16D2069/002—Combination of different friction materials
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12014—All metal or with adjacent metals having metal particles
- Y10T428/12021—All metal or with adjacent metals having metal particles having composition or density gradient or differential porosity
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12014—All metal or with adjacent metals having metal particles
- Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
- Y10T428/12042—Porous component
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/1234—Honeycomb, or with grain orientation or elongated elements in defined angular relationship in respective components [e.g., parallel, inter- secting, etc.]
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12639—Adjacent, identical composition, components
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12771—Transition metal-base component
- Y10T428/12778—Alternative base metals from diverse categories
Definitions
- ABSTRACT [52] US. Cl 29/1823, 29/1822, 29/1912, A labyrinth Seal, for turbine engines, disposed 75/208 R tween the rotary blades and the shroud, composed of CLf. 1322f 3/16 a powder metal honeycomb in which the Cavities 1 d 0 Search 29/1912 1823 thereof are also filled with a powder metal material.
- This invention relates generally to a honeycomb-like structure adapted to be employed as a high temperature and low friction abradable seal, particularly for turbine engines.
- a third type of seal which has heretofore been utilized involves abradable metal powders which are hot gas or plasma sprayed onto the shroud. Again, the materials are of the oxidation resistant type. Finally, efforts have been made to utilize a seal composed of oxidation resistant powder metal alloys with a varying density and thickness and secured on a backing member. These powder metal seals generally provide excellent abradability with, however, a relatively poor resistance to the erosive forces generated by the hot gases and the erosive particles which are present in the environment of the jet engine.
- felted matrix has been found to be troublesome in the areas of the brazed joint, i.e., between the material and the backup shroud. Aside from the problems arising with the joint, the felted fiber has found, so far, limited adjability due to its low abradability and high wear factors.
- the sprayed powder metal seals are characteristically deficient in bond strength between the particles and the substrate to which they are applied. This is due largely to the inability to apply finely divided powders in a high temperature environment without some degree of surface oxidation.
- the powder metal seals with or without randomly dispersed fibers establish properties comparable to those properties established by sprayed powder metal seals. While such seals tend to have a greater structural integrity than sprayed materials the mechanical strength is still inadequate, at the density levels necessary, to provide good abradability and resistance to erosion.
- a cellular surface such as a honeycomb
- the cellular powder metal structure can be used either in the open faced honeycomb form or in a mode in which the individual cells are filled with a powder metal having the desired characteristics.
- the objective of the invention is to provide a material wherein all elements of brazing and welding are eliminated and wherein the structure is a unitary totally solid state bonded components of high structural integrity incorporating in solid state association the erosion resistant and abradable metal elements; such provision enabling a wide degree of adjustment of the filler and honeycomb materials not readily possible in conventional honeycomb structures, through the variation of density of the powder metal material.
- the honeycomb in accordance with the invention eliminates not only the costly welding normally employed in joining of the honeycomb elements to each other but also the subsequent need for brazing the honeycomb to a backup strip. Since the honeycomb in accordance with the invention has a solid state bond throughout it will be appreciated that the strength of the powder metal honeycomb is significantly superior, on a comparable basis to those of the prior art components.
- Another significant advantage of the invention resides in the ability to provide a honeycomb structure having an extremely small cell configuration without any substantial increase in the cost of manufacture. Moreover, such small dimensional cell configurations can be accomplished with a reduction in weight over conventional small cell honeycomb.
- FIG. 1 is a fragmentary, perspective and sectional view of the shrouded section of a turbine engine embodying the present invention.
- FIG. 2 is an enlarged fragmentary perspective view of a powder metal honeycomb
- FIGS. 3 and 4 are views similar to FIG. 2 showing modified versions thereof.
- FIG. 1 a radially extending rotor blade of a turbine engine (not shown) the tip of which faces in close proximity an annular shroud 1.2 to which a seal in the form of a honeycomb-like structure 14 is secured.
- the honeycomb-like structure 14 provides a coherent and structurally continuous body of compacted metal powders in which by means of selectively impacted regions a net-work of cavities 16,18 is formed with the cavities being arranged and distributed uniformly in a repeating and predetennined manner substantially over the entire surface of the honeycomb.
- These cavities l6 and 18 may be of various geometric configurations such as diamonds, squares, circles, sinusoidal patterns, crescent or straight lines parallel to a single axis and the like.
- FIG. 1 wherein the impacted regions 16 are continuous and intersect each other at right angles as compared to the discontinuous cavities 18, shown in FIG. 3.
- the impacted regions provide a bottom surface, see 16 and 18, of metal powder particles densificd to a greater degree than adjacent nonimpacted or raised regions, see 20 and 22.
- honeycomb structures 14, 14a, 14b shown in FIGS. 1 to 3 can be utilized as a labyrinth seal when composed of material having suitable properties of oxidation resistance and selected abradability.
- the honeycomb may be used with or without a powder metal backup strip 24 composed of suitable and conventional high density material. Ordinarily, the backup strip 24 is fully dense.
- a bonding interlayer (not shown) interposed between the honeycomb 14 and the strip 24 is composed of a relatively fine powder metal material which may be of the same or similar to, or at least metallurgically compatible with the material used for the honeycomb-like structure, the term compatibility" being used herein to signify that the two metals will diffuse and alloy with each other.
- the continuous and discontinuous cavities 16, 18 are filled with compacted metal powders, see 26, metallurgically compatible with the basic honeycomb-like structure 14 so that a solid state bond can be readily established between the powders in the cavities and the metal powders of the adjacent regions.
- the metal powder filler material, see 26 is densified to a pre-determined level which may differ from the degree of density imparted into the honeycomb-like structure 14 and, more particularly, the raised regions 20, 22 and the impacted regions l6, 18.
- the total structure consisting, in this instance, of the filler material and the honeycomb may have three different levels of density. This multi-density body can be readily achieved by a method hereinafter further described.
- the honeycomb-like structure. 14, 14a and 1411, the tiller 26 and the backup layer 24 may all be composed of oxidation resistant material such as nickel, chromium, aluminum, iron, molybdenum, cobalt, tungsten or particular alloys thereof.
- the degree of desired abradability can be imparted to the powder metal structure by varying the density or composition.
- the abradable powder metal material e.g., for the tiller
- the abradable powder metal material will be comprised of relatively coarse particulants and consequently less dense in the gravity sintered state providing relatively lower mechanical properties than required for the honeycomb-like structure 10, as the case may be.
- the honeycomb-like structure 14 (or, alternatively, the filler 26) is comprised of comparatively fine metal powder particles having the capability to sinter to relatively high densities.
- the density of the higher density component will range from 35 to 95 percent of theoretical density of the base material.
- the density of the abradable filler material 26 will generally be within the range of 20 to 60 percent of theoretical.
- the materials for both the honeycomb and the tiller are prepared separately.
- a l00 mesh alloy metal powder of weight percent nickel and 20 weight percent chrome, including possibly 1 percent aluminum and produced by water atomization, is blended with 2 percent carbon pore formers of a specific size, not to exceed l0 microns per particle, in a twin shell blender.
- a controllable l to 2 percent alcohol is added to the mixture as a suspension vehicle.
- the material which forms the honeycomb-like structure 14 is prepared in the same fashion using a -325 mesh alloy of the same composition which is blended with a 1 percent carbon pore former. Again, prior to its application, a l to 2 percent addition of alcohol is added to this material to act as a suspension agent.
- a graphite die having a channel of width sufiicient to accommodate the desired strip plus trim and of sufiicient thickess to compensate for sinter shrinkage is prepared by pre-coating with a slurry of magnesium oxide which is subsequently dried.
- the foil backup strip 24 has a thickness of l to 5 mils and is composed of the same or similar alloy which is properly cleaned to render it devoid of surface contaminants.
- the strip 24 is then sprayed with a suitable volatile adhesive and, while still wet, a dusting of fine 400 mesh metal powder is applied over the strip 24 to provide a high density bonding interface to the strip 24. The excess material after the adhesive has dried is dusted off.
- the coated foil backup 24 is then placed in the die cavity. Following this step, the powder forming the honeycomb is placed upon the backup strip 24 and together they are placed into a furnace and sintered in vacuum for 1 hour at a suitable temperature. After cooling, the strip is compressed l to 3 percent between steel plates in a hydraulic press to flatten the same to uniform dimension.
- the network of continuous or discontinuous cavities which form the honey comb is imparted into the sintered structure by means of a tool which is pressed into the structure.
- the tool has a configuration complementary to the pattern desired.
- the punch or tool is pressed over the sintered material with a load sufficient to provide penetration to the depths desired, usually 80 thousandths of an inch.
- the punch is rotated in order to establish the desired configuration.
- the structure is then dusted to remove loose material and placed in a fixture for application of the filler 26 material.
- Metal powder composing the filler material is doctored into the cavities established by the tool and the excess is removed by standard blade strike-off techniques.
- the resulting honeycomb structure in which the cavities are filled is then re-sintered in vacuum under suitable conditions, for instance, at a maximum pressure of 1 micron and at a temperature of 2,100F for 1 hour. if desired, the filler material within the cavities is compacted before and after sintering to the desired degree.
- honeycomb-like structure may be made with or without a back-up plate 24 and with (as shown in FIG. 3) impacted regions constituting the bottom of the cavities or a honeycomb-like structure in which such impacted regions have been completely removed as shown in FIG. 4.
- the honeycomb-like structure Me of FIG. 4 is in all other respects identical to the embodiment described with the respect to FIG. 3.
- a grid-like structure of powder metal comprising:
- a coherent and continuous body of porous material of compacted metal powders providing a grid established by mechanical impacting of selective regions thereby forming a network of cavities arranged and distributed in a repeating and predetermined manner uniformly over substantially the entire surface of the grid with said body having a density of 35 to percent of theoretical, and sintered in situ material of compacted metal powders within and substantially filling said cavities and having a density of 20 to 60 percent of theoretical, with the area in said body of the grid below each cavity having a density substantially greater than the density of the wall areas defining said cavity.
- a grid-like structure according to claim 1 and a metal backing strip on said grid closing off one end face of said cavities.
Abstract
Description
Claims (5)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US00323371A US3844011A (en) | 1970-12-21 | 1973-01-15 | Powder metal honeycomb |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10014070A | 1970-12-21 | 1970-12-21 | |
US00323371A US3844011A (en) | 1970-12-21 | 1973-01-15 | Powder metal honeycomb |
Publications (1)
Publication Number | Publication Date |
---|---|
US3844011A true US3844011A (en) | 1974-10-29 |
Family
ID=26796837
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US00323371A Expired - Lifetime US3844011A (en) | 1970-12-21 | 1973-01-15 | Powder metal honeycomb |
Country Status (1)
Country | Link |
---|---|
US (1) | US3844011A (en) |
Cited By (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3948613A (en) * | 1972-12-07 | 1976-04-06 | Weill Theodore C | Process for applying a protective wear surface to a wear part |
US4052802A (en) * | 1976-02-23 | 1977-10-11 | Caterpillar Tractor Co. | Ground-engaging tool with wear-resistant insert |
US4278153A (en) * | 1978-11-24 | 1981-07-14 | Goodyear Aerospace Corporation | Brake friction material with reinforcement material |
DE3326535A1 (en) * | 1982-08-09 | 1984-03-01 | United Technologies Corp., 06101 Hartford, Conn. | DEVICE WITH A GASWEG SEALING SYSTEM BETWEEN RELATIVELY MOVING PARTS |
US4546028A (en) * | 1982-04-27 | 1985-10-08 | Compagnie D'informatique Militaire Spatiale & Aeronautique | Composite substrate with high heat conduction |
EP0223474A2 (en) * | 1985-11-04 | 1987-05-27 | De Beers Industrial Diamond Division (Proprietary) Limited | Method of making a drill blank |
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 |
WO1993006342A1 (en) * | 1991-09-23 | 1993-04-01 | Technetics Corporation | Impermeable, abradable seal and method for the production thereof |
US5342697A (en) * | 1991-09-19 | 1994-08-30 | Helle Richard D | Connected articles |
US5529645A (en) * | 1994-05-17 | 1996-06-25 | Northrop Grumman Corporation | Thin wall casting and process |
US5618633A (en) * | 1994-07-12 | 1997-04-08 | Precision Castparts Corporation | Honeycomb casting |
US5759400A (en) * | 1993-09-03 | 1998-06-02 | Advance Waste Reduction | Reticulated foam structured fluid treatment element |
US20030019914A1 (en) * | 2001-07-24 | 2003-01-30 | Schreiber Karl | Method for the production of a sealing element |
WO2003059623A1 (en) | 2002-01-14 | 2003-07-24 | Peter Sing | Merhod of making structural cellular cores suitable to use of wood |
US20070017817A1 (en) * | 2004-06-19 | 2007-01-25 | Claus Mueller | Method for manufacturing components of a gas turbine and a component of a gas turbine |
US20090041607A1 (en) * | 2006-03-03 | 2009-02-12 | Mtu Aero Engines Gmbh | Method for the production of a sealing segment, and sealing segment to be use in compressor and turbine components |
US20090041610A1 (en) * | 2002-12-20 | 2009-02-12 | Mtu Aero Engines Gmbh | Gas turbine honeycomb seal |
US20100032367A1 (en) * | 2005-02-11 | 2010-02-11 | Fluid Treatment Systems, Inc. | Flexible reticulated foam fluid treatment media and method of preparation |
US20100206799A1 (en) * | 2009-02-17 | 2010-08-19 | Fluid Treatments Systems, Inc. | Liquid Filter |
US20150111060A1 (en) * | 2013-10-22 | 2015-04-23 | General Electric Company | Cooled article and method of forming a cooled article |
US20150354393A1 (en) * | 2014-06-10 | 2015-12-10 | General Electric Company | Methods of manufacturing a shroud abradable coating |
US20160265367A1 (en) * | 2014-12-22 | 2016-09-15 | General Electric Company | Environmental barrier coating with abradable coating for ceramic matrix composites |
EP3135869A1 (en) | 2015-08-25 | 2017-03-01 | Rolls-Royce Deutschland Ltd & Co KG | Sealing element for a turbomachine, corresponding turbomachine and manufacturing process |
EP3284916A1 (en) * | 2016-08-17 | 2018-02-21 | Rolls-Royce plc | A component for a gas turbine engine and method of manufacture |
US20180050422A1 (en) * | 2016-08-19 | 2018-02-22 | Solar Turbines Incorporated | Method for manufacturing compressor components |
US20190017388A1 (en) * | 2017-07-14 | 2019-01-17 | United Technologies Corporation | Gas turbine engine fan blade, design, and fabrication |
EP3514333A1 (en) * | 2018-01-23 | 2019-07-24 | MTU Aero Engines GmbH | Rotor blade tip shroud for a turbo machine, rotor blade, method for producing a rotor blade cover strip and a rotor blade |
US10385783B2 (en) * | 2012-01-23 | 2019-08-20 | MTU Aero Engines AG | Turbomachine seal arrangement |
US10443958B2 (en) * | 2016-04-25 | 2019-10-15 | Raytheon Company | Powdered metal as a sacrificial material for ultrasonic additive manufacturing |
US20210018006A1 (en) * | 2019-07-15 | 2021-01-21 | Pratt & Whitney Canada Corp. | Centrifugal compressor and shroud therefore |
DE102021105287A1 (en) | 2021-03-04 | 2022-09-08 | Rolls-Royce Deutschland Ltd & Co Kg | Sealing element for a turbomachine, molded part for producing a sealing element, method for producing and arranging a sealing element and turbomachine with a sealing element |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2498873A (en) * | 1945-05-30 | 1950-02-28 | Chrysler Corp | Bearing and method of making the same |
US2652520A (en) * | 1949-12-24 | 1953-09-15 | Gen Electric | Composite sintered metal powder article |
US2691208A (en) * | 1948-08-14 | 1954-10-12 | Joseph B Brennan | Method of laminating strip metal |
US2747261A (en) * | 1952-05-28 | 1956-05-29 | Gen Motors Corp | Bearing and method of making same |
US2815567A (en) * | 1953-04-15 | 1957-12-10 | Federal Mogul Corp | Process for making bearings |
US2977673A (en) * | 1955-09-22 | 1961-04-04 | Gen Motors Corp | Method of forming composite metal bearings |
US3221392A (en) * | 1960-09-28 | 1965-12-07 | Federal Mogul Bower Bearings | Method of making bearings |
-
1973
- 1973-01-15 US US00323371A patent/US3844011A/en not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2498873A (en) * | 1945-05-30 | 1950-02-28 | Chrysler Corp | Bearing and method of making the same |
US2691208A (en) * | 1948-08-14 | 1954-10-12 | Joseph B Brennan | Method of laminating strip metal |
US2652520A (en) * | 1949-12-24 | 1953-09-15 | Gen Electric | Composite sintered metal powder article |
US2747261A (en) * | 1952-05-28 | 1956-05-29 | Gen Motors Corp | Bearing and method of making same |
US2815567A (en) * | 1953-04-15 | 1957-12-10 | Federal Mogul Corp | Process for making bearings |
US2977673A (en) * | 1955-09-22 | 1961-04-04 | Gen Motors Corp | Method of forming composite metal bearings |
US3221392A (en) * | 1960-09-28 | 1965-12-07 | Federal Mogul Bower Bearings | Method of making bearings |
Cited By (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3948613A (en) * | 1972-12-07 | 1976-04-06 | Weill Theodore C | Process for applying a protective wear surface to a wear part |
US4052802A (en) * | 1976-02-23 | 1977-10-11 | Caterpillar Tractor Co. | Ground-engaging tool with wear-resistant insert |
US4278153A (en) * | 1978-11-24 | 1981-07-14 | Goodyear Aerospace Corporation | Brake friction material with reinforcement material |
US4546028A (en) * | 1982-04-27 | 1985-10-08 | Compagnie D'informatique Militaire Spatiale & Aeronautique | Composite substrate with high heat conduction |
DE3326535A1 (en) * | 1982-08-09 | 1984-03-01 | United Technologies Corp., 06101 Hartford, Conn. | DEVICE WITH A GASWEG SEALING SYSTEM BETWEEN RELATIVELY MOVING PARTS |
EP0223474A2 (en) * | 1985-11-04 | 1987-05-27 | De Beers Industrial Diamond Division (Proprietary) Limited | Method of making a drill blank |
EP0223474A3 (en) * | 1985-11-04 | 1988-11-09 | De Beers Industrial Diamond Division (Proprietary) Limited | Drill blanks |
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 |
US5342697A (en) * | 1991-09-19 | 1994-08-30 | Helle Richard D | Connected articles |
WO1993006342A1 (en) * | 1991-09-23 | 1993-04-01 | Technetics Corporation | Impermeable, abradable seal and method for the production thereof |
US5759400A (en) * | 1993-09-03 | 1998-06-02 | Advance Waste Reduction | Reticulated foam structured fluid treatment element |
US5529645A (en) * | 1994-05-17 | 1996-06-25 | Northrop Grumman Corporation | Thin wall casting and process |
US5618633A (en) * | 1994-07-12 | 1997-04-08 | Precision Castparts Corporation | Honeycomb casting |
US20030019914A1 (en) * | 2001-07-24 | 2003-01-30 | Schreiber Karl | Method for the production of a sealing element |
US6745931B2 (en) * | 2001-07-24 | 2004-06-08 | Rolls-Royce Deutschland Ltd. & Co Kg | Method for the production of a sealing element |
WO2003059623A1 (en) | 2002-01-14 | 2003-07-24 | Peter Sing | Merhod of making structural cellular cores suitable to use of wood |
US20090041610A1 (en) * | 2002-12-20 | 2009-02-12 | Mtu Aero Engines Gmbh | Gas turbine honeycomb seal |
US20070017817A1 (en) * | 2004-06-19 | 2007-01-25 | Claus Mueller | Method for manufacturing components of a gas turbine and a component of a gas turbine |
US20100032367A1 (en) * | 2005-02-11 | 2010-02-11 | Fluid Treatment Systems, Inc. | Flexible reticulated foam fluid treatment media and method of preparation |
US20090041607A1 (en) * | 2006-03-03 | 2009-02-12 | Mtu Aero Engines Gmbh | Method for the production of a sealing segment, and sealing segment to be use in compressor and turbine components |
US20100206799A1 (en) * | 2009-02-17 | 2010-08-19 | Fluid Treatments Systems, Inc. | Liquid Filter |
US10385783B2 (en) * | 2012-01-23 | 2019-08-20 | MTU Aero Engines AG | Turbomachine seal arrangement |
US20150111060A1 (en) * | 2013-10-22 | 2015-04-23 | General Electric Company | Cooled article and method of forming a cooled article |
US10539041B2 (en) * | 2013-10-22 | 2020-01-21 | General Electric Company | Cooled article and method of forming a cooled article |
US20150354393A1 (en) * | 2014-06-10 | 2015-12-10 | General Electric Company | Methods of manufacturing a shroud abradable coating |
US20160265367A1 (en) * | 2014-12-22 | 2016-09-15 | General Electric Company | Environmental barrier coating with abradable coating for ceramic matrix composites |
DE102015216208A1 (en) | 2015-08-25 | 2017-03-02 | Rolls-Royce Deutschland Ltd & Co Kg | Sealing element for a turbomachine, turbomachine with a sealing element and method for producing a sealing element |
EP3135869A1 (en) | 2015-08-25 | 2017-03-01 | Rolls-Royce Deutschland Ltd & Co KG | Sealing element for a turbomachine, corresponding turbomachine and manufacturing process |
US10480340B2 (en) | 2015-08-25 | 2019-11-19 | Rolls-Royce Deutschland Ltd & Co Kg | Sealing element for a turbo-machine, turbo-machine comprising a sealing element and method for manufacturing a sealing element |
US10443958B2 (en) * | 2016-04-25 | 2019-10-15 | Raytheon Company | Powdered metal as a sacrificial material for ultrasonic additive manufacturing |
EP3284916A1 (en) * | 2016-08-17 | 2018-02-21 | Rolls-Royce plc | A component for a gas turbine engine and method of manufacture |
US20180050422A1 (en) * | 2016-08-19 | 2018-02-22 | Solar Turbines Incorporated | Method for manufacturing compressor components |
US10808545B2 (en) * | 2017-07-14 | 2020-10-20 | United Technologies Corporation | Gas turbine engine fan blade, design, and fabrication |
US20190017388A1 (en) * | 2017-07-14 | 2019-01-17 | United Technologies Corporation | Gas turbine engine fan blade, design, and fabrication |
EP3514333A1 (en) * | 2018-01-23 | 2019-07-24 | MTU Aero Engines GmbH | Rotor blade tip shroud for a turbo machine, rotor blade, method for producing a rotor blade cover strip and a rotor blade |
US11098609B2 (en) * | 2018-01-23 | 2021-08-24 | MTU Aero Engines AG | Rotor blade shroud for a turbomachine, rotor blade, method of making a rotor blade shroud and a rotor blade |
US20210018006A1 (en) * | 2019-07-15 | 2021-01-21 | Pratt & Whitney Canada Corp. | Centrifugal compressor and shroud therefore |
US10989203B2 (en) * | 2019-07-15 | 2021-04-27 | Pratt & Whitney Canada Corp. | Centrifugal compressor and shroud therefore |
DE102021105287A1 (en) | 2021-03-04 | 2022-09-08 | Rolls-Royce Deutschland Ltd & Co Kg | Sealing element for a turbomachine, molded part for producing a sealing element, method for producing and arranging a sealing element and turbomachine with a sealing element |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3844011A (en) | Powder metal honeycomb | |
US3693750A (en) | Composite metal structure useful in sound absorption | |
US3831258A (en) | Reinforced porous metal structure and manufacture thereof | |
DE2163068A1 (en) | Powder metal honeycomb | |
KR830001651B1 (en) | Manufacturing method of surface treated products with ceramic | |
CA1128866A (en) | Gas turbine engine seal and method for making same | |
EP0254667B1 (en) | Improved method for adhesion of grit to blade tips | |
EP1313932B1 (en) | Thermal barrier coating system | |
US3261576A (en) | Aircraft structure | |
US3608170A (en) | Metal impregnated composite casting method | |
US5662720A (en) | Composite polycrystalline diamond compact | |
KR930010150B1 (en) | Abrasive surface coating process for superalloys | |
US2359361A (en) | Composite metal element and method of making same | |
US5535857A (en) | Brake disc and method for its production | |
PL186317B1 (en) | Wearing seal | |
US3359623A (en) | Method for making refractory metal contacts having integral welding surfaces thereon | |
US3891398A (en) | Disc brake pads formed from two sintered metallic layers | |
GB2049735A (en) | Sintered porous metal plate and its production | |
US3350178A (en) | Sealing device | |
US4448591A (en) | Cutting insert having unique cross section | |
US3869259A (en) | Composite sliding member | |
US4576872A (en) | Friction element and method of manufacture thereof | |
EP0604625B1 (en) | Sintered brake pad for disc brakes | |
JP2540510B2 (en) | Abrasion resistant member and manufacturing method thereof | |
CA1051633A (en) | Composite metal article and method for the manufacture thereof |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: IMPERIAL CLEVITE INC., 2550 GOLF ROAD, ROLLING MEA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:GOULD INC., A CORP. OF DE;REEL/FRAME:003998/0236 Effective date: 19810928 Owner name: IMPERIAL CLEVITE INC., A CORP. OF PA,ILLINOIS Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GOULD INC., A CORP. OF DE;REEL/FRAME:003998/0236 Effective date: 19810928 |
|
AS | Assignment |
Owner name: GOULD, INC.; 10 GOULD CENTER, ROLLING MEADOWS, IL. Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:IMPERIAL CLEVITE INC.;REEL/FRAME:004079/0245 Effective date: 19821006 Owner name: GRID SEAL CORPORATION Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:GOULD, INC.;REEL/FRAME:004088/0604 Effective date: 19821026 |