US3307616A - Method of protecting a heat-resistant element from hot media - Google Patents

Method of protecting a heat-resistant element from hot media Download PDF

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Publication number
US3307616A
US3307616A US414279A US41427964A US3307616A US 3307616 A US3307616 A US 3307616A US 414279 A US414279 A US 414279A US 41427964 A US41427964 A US 41427964A US 3307616 A US3307616 A US 3307616A
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Prior art keywords
wall
combustion chamber
air
heat
protecting
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US414279A
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English (en)
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Giger Johannes
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BBC Brown Boveri AG Germany
BBC Brown Boveri France SA
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BBC Brown Boveri France SA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/16—Making or repairing linings increasing the durability of linings or breaking away linings
    • F27D1/1678—Increasing the durability of linings; Means for protecting
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
    • C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
    • C04B41/5025—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials with ceramic materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/12—Casings; Linings; Walls; Roofs incorporating cooling arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/16—Making or repairing linings increasing the durability of linings or breaking away linings
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2111/00—Mortars, concrete or artificial stone or mixtures to prepare them, characterised by specific function, property or use
    • C04B2111/72—Repairing or restoring existing buildings or building materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2700/00—Constructional details of combustion chambers
    • F23M2700/005—Structures of combustion chambers or smoke ducts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/16—Making or repairing linings increasing the durability of linings or breaking away linings
    • F27D2001/1605—Repairing linings
    • F27D2001/1615—Repairing linings through a hole in the casing, e.g. injecting refractory from outside the vessel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D3/00—Charging; Discharging; Manipulation of charge
    • F27D3/16—Introducing a fluid jet or current into the charge
    • F27D2003/161—Introducing a fluid jet or current into the charge through a porous element

Definitions

  • Various cooling systems have been disclosed to prolong the life of combustion chambers or elements having walls swept by hot media.
  • the present invention is intended for this purpose.
  • the heat-resistant element according to the invention is characterized in that at least part of the element is gas-permeable so that a coolant fluid can be moved through said part for the purpose of cooling the element.
  • the method of protecting a heat-resistant element according to the invention is characterized in that a coolant fluid is blown through the gas-permeable part thereof transversely into the flow of hot medium.
  • FIG. 1 is a perspective view of a cooling system including a part of a combustion chamber wall
  • FIG. 2 is a section of the part of the combustion chamber wall on the line IIII in FIG. 1;
  • FIG. 3 is a perspective View of part of a cylindrical combustion chamber Wall
  • FIG. 4 is a perspective view of a porous heat-resistant element with a connection for cooling medium
  • FIG. 5 is a section through a combustion chamber structural element with a cooling system.
  • the combustion chamber wall 1 shown in FIGS. 1 and 2 comprises an inner wall element 3 and an outer wall element 5.
  • the inner wall element 3 consists of sintered-together fragments 7 while the outer wall element 5 is made up of shaped bricks 9 as will be apparent from FIG. 1.
  • Injection tubes 11 are disposed slidably in apertures 37 in the shaped bricks 9. These tubes 11 lead to a header 13 fed by an air supply pipe 31.
  • the pipe 31 branches into a T-piece which leads to valves 27 and 29 from each of which a pressure line 25 runs, said pressure lines 25 extending respectively directly to the header pipe 13 and indirectly to said pipe 13 via a mixing tank 15 and a feed line 23.
  • a perforate distributor element 17 above which is a layer of loose ceramic powder 21 is provided in the base 19 of the mixing tank 15.
  • a nozzle 33 is also shown on the inside of the combustion chamber with fuel emerging therefrom to produce a flame 35 on ignition. As a result of the flame 35 the jets of cooling medium emerging from the injection tubes 11 are deflected in the direction of the arrows 39.
  • the inner wall element 3 undergoes increasing wear with increasing temperatures in the combustion chamber.
  • cooling air is forced directly into the injection tubes 11 during operation via the compressed air supply pipe 31, the valve 29, the compressed air pipe 25 and the header 13.
  • the cooling air flows through the combustion chamber wall 1 and acts as a cooling screen for the inner surface of the wall. Because of its low temperature it protects the combustion chamber wall from the 3,307,616 Patented Mar. 7, 1967 influence of the flame 35.
  • the axes of the streams of cooling air flowing through tubes 11 are at least approximately perpendicular to the combustion chamber wall to be cooled.
  • valve 29 is closed and compressed air is fed from the air supply pipe 31, through the valve 27 and the compressed air pipe 25, to the perforate distributor element 17, where the air is divided up into fine streams which flow into the ceramic powder 21 and fluidize the same depending upon their speed of exit.
  • Some of the fluidized ceramic powder is entrained by the passing air and flows through the feed pipe 23 and the header 13 to the injection tubes 11 and then to the interior of the combustion chamber together with the cooling air.
  • the particles shoot much farther into the interior of the combustion chamber than the air transporting the particles, so that they reach the region of the flame 35 where at least their outer surfaces are so heated that when they subsequently meet the inner wall elements 3 they lodge thereon and thus form a coating of material on the wall.
  • the return of the ceramic particles, whose surfaces are softened by heat, to the surface of the wall element 3 is governed by the turbulent mixing movement and the spreading mixing zone of the flame jet and the air streams which emerge into the combustion chamber through the tubes 11.
  • the wear of the inner wall element 3 can thus be compensated and any such wear can be replaced by appropriate regulation of the amount of entrained ceramic powder.
  • the inner wall element 3 may, for example, be formed of porous shaped bodies of frag ments 7 of A1 0 and may be made in the following way:
  • Ceramic balls of A1 0 with a diameter of 6 mm. for example are shaken into a mold of ceramic material (A1 0 or graphite and joggled to form a compact mass.
  • the mold with the layer of balls is then sintered at about 1650 C. for 3 hours, for example, to form a block.
  • a ceramic mold is used the sintering can be effected in air while when the sintering is carried out in a graphite mold a protective gas, for example nitrogen is used.
  • a protective gas for example nitrogen is used.
  • the walls and base of the ceramic mold must be removed after firing. It is also possible to make porous wall elements by sintering together chromium or other metal cylinders, bal-ls or cubes at 1700 C.
  • chromium balls or other chromium elements can be assisted by previously vapor-coating the surfaces of these elements with another metal, for example nickel.
  • another metal for example nickel.
  • open tubes of MgO for example of a size of 12 x 9 mm. and a length of 100 mm., can be superimposed and, after pre-coating the contacting places with high-temperature cement, fired to form porous wall elements by sintering at l'0 C. in air.
  • Such shaped elements can be assembled in variou ways. 'For example, ceramic tiles are advantageously joined with high-temperature cement. Shaped metal or cement parts can be combined by arranging for the same to interlock by means of stepped portions or grooves on the prefabricated component assembly principle.
  • the apertures are so distributed in the combustion chamber wall that the inner wall element 3 is covered and protected by the cooling air streams throughout. It has been found advantageous to make the air flow between about 5 and 10 litres per second and per square dm. of inner wall area.
  • the porous inner wall element 3 as shown in FIGS. 1 and 2 may also be made from nOnmetallic materials (oxides), for example aluminum oxide,
  • carbides, nitrides, borides, silicides and sulphides are also suitable for the production of such inner wall parts, for example silicon carbide, boron carbide, boron nitrides, molybdenum disilicide, titanium bromide, cerium sulphide, etc.
  • the inner element 3 of a combustion chamber consists of silicon carbide, it is resistant to temperature of 1450 C. in air. In a damp atmosphere intensive oxidation results in its rapid destruction. The protective skin of silicon oxide forming on the surface is permeable at elevated temperatures and breaks down so that the protective effect of the silicon oxide is lost.
  • a pre-melted and subsequently pulverized mixture of K 0, A1 and Si0 for example is injected from the mixing tank 15 through the feed pipe 23 and the header 13 and the injection tubes 11 into the combustion chamber, so that the inner wall element is covered with a stable dense glass-like coating. Adjustment of the powder mixture as regards melting point and composition gives protection to above 2,000 C. in the case of silicon carbide. In this way, the Wear of the innermost layer of the inner wall element 3 can be compensated from time to time by the application of such a coating so that the life of the wall 1 and hence of the entire combustion chamber is quite considerably increased.
  • cermets i.e., ceramics-metals
  • oxide cermets l e-A1 0 Al O -Cr, Cr-W-Al O Cr-Mo-TiAl O or other oxide cermets in the form of A1 0 and BeO with Co, Ni, Fe, W-Cr; BeO-Nb, ThO -Mo and ZrO -Ni, CaO-Co.
  • the metallic materials which are suitable for injection into the combustion chamber and for the formation of a coating on the inner wall element 3 are, for example high-' chromium-content alloys and the metals, chromium, titanium, etc. Chromium has a melting point of 1900 C. and compared with compact-ceramic materials has a much better thermal conductivity.
  • the chromium oxide (Cr O forming on the chromium has the following very favorable properties as regards wall coating:
  • the transition from the metallic chromium to Cr O is rarely dense and has very good adhesion at the metaloxide transition layer.
  • the melting point of C-r O at 1900-2200 C. is relatively high.
  • a high-melting oxide such as MgO, ZrO etc.
  • a low-melting material such as SiO LiF, BaO, ZnO or mullite
  • the high-melting oxide, carbide, boride, etc. can first be coated in a low-melting flux and then be conveyed to the interior of the combustion chamber. Caking or sintering on the inner wall of the combustion chamber can be very considerably facilitated in this way in individual cases. The flux will evaporate during operation or form a new ceramic compound which can be controlled within predetermined limits.
  • a jacket or coating of LiF-l- 0.4 mol percent ZrO can be provided for the MgO particles with a melting point of 2800" C. before injection by the sintering and melting process.
  • the core of the particle still has a melting point of 2800 C. but the particle jacket has a melting point of only about 1600-1800 C.
  • the MgO particles melt very rapidly on the inner surface of the hot wall of the inner element 3.
  • the flux in the particle jacket very rapidly evaporates after the sintering on the wall and the total melting point of the surface which is sintered at operating temperature thus immediately rises again to 2800" C.
  • FIG. 3 shows a combustion chamber wall 44 for the construction of a cylindrical combustion chamber. It will comprises an inner wall element 46 and an outer wall element 48.
  • the inner wall element 46 is a sintered element made from cylinders 50 while the outer wall element 48 is made up of shaped bricks 52. Cooling is effected by the injection of cooling medium through the injection tubes 11, appropriate powders or powder mixtures being added to the cooling medium as explained above, in order to coat the inner wall element 46.
  • the size of the air passages and the number thereof can be controlled by the choice of diameter for the cylinders 50.
  • Combustion chamber element 60 (see FIG. 4) comprising an inner wall part 62 and an outer wall part 64 can also be so sintered that the inner wall part 62 remains porous and hence air-permeable while the outer wall part 64 is dense.
  • An injection tube 66 is introduced through the dense outside wall part 64 to the porous inner part 62 for the supply of cooling air and the powder to build up the inner wall of the combustion chamber.
  • the fine structure of the inner wall part 62 insures adequate and good distribution of the air and entrained powder so that the inner wall is very uniformly swept by air and powder on the inside of the combustion chamber.
  • FIG. 5 shows a construction in which a combustion chamber element 70 has an inner wall element 72 to whose outside an air chamber 74 is connected, such chamber being enclosed by a shaft wall 76.
  • Cooling air tubes 78 feed the cooling air to the chamber 74 while a ceramic dust feed pipe 80 supplies the required internal wall coating substance for the element 72, together with cooling air as a vehicle.
  • the mixture of dust and air is blown to the interior of the combustion chamber through the fine pores of the porous element 72 and serves to cool the combustion chamber wall and restore the material thereof as already described.
  • the inner wall element may in principle be constructed from sintered fragments, cylinders, balls or other regular or irregular shaped bodies.
  • the important feature is that the number of pores and width should be such that uniform cooling of the surface swept by the hot medium is insured with a minimum of air and a uniform coating is obtained by the appplica-tion or sintering of injected powder on the wall.
  • a method of protecting the surface of a gaspermeable heat-resistant element that is to be exposed to high temperature which comprises flowing a suspension of a finely divided solid in a cooling gas through said element to said surface.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Inorganic Chemistry (AREA)
  • Materials Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Powder Metallurgy (AREA)
  • Ceramic Products (AREA)
  • Compositions Of Oxide Ceramics (AREA)
  • Tunnel Furnaces (AREA)
US414279A 1963-11-28 1964-11-27 Method of protecting a heat-resistant element from hot media Expired - Lifetime US3307616A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1458163A CH427118A (de) 1963-11-28 1963-11-28 Verfahren zum Schützen von durch heisse Medien überstrichenen Oberflächenteilen eines hitzebeständigen Körpers

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US (1) US3307616A (de)
CH (1) CH427118A (de)
DE (1) DE1278319B (de)
GB (1) GB1035148A (de)
SE (1) SE306141B (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3373796A (en) * 1965-04-23 1968-03-19 Vallak Method and means for cooling a combustion chamber by means of a powderlike material
US3400754A (en) * 1965-10-04 1968-09-10 Commissariat Energie Atomique Method and device for providing protection against scale formation on a heat exchange surface
US3428114A (en) * 1967-03-27 1969-02-18 Us Interior Method and apparatus for preventing scale formation in heat exchangers
US3771442A (en) * 1972-01-11 1973-11-13 Penril Data Communications Inc Zero-lock print wheel apparatus
US20040245389A1 (en) * 2003-06-05 2004-12-09 Behrens William W. Cooled insulation surface temperature control system
US20070247812A1 (en) * 2006-04-20 2007-10-25 The Boeing Company Ceramic foam cold plate
US20090202717A1 (en) * 2008-02-11 2009-08-13 General Electric Company Anti-Fouling Coatings for Combustion System Components Exposed to Slag, Ash and/or Char
US20090246500A1 (en) * 2008-03-25 2009-10-01 General Electric Company Component in a combustion system, and process for preventing slag, ash, and char buildup
US20110133026A1 (en) * 2009-12-03 2011-06-09 The Boeing Company Extended plug cold plate
US8505616B2 (en) * 2006-04-20 2013-08-13 The Boeing Company Hybrid ceramic core cold plate

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4705563A (en) * 1986-10-23 1987-11-10 The United States Of America As Represented By The United States Department Of Energy Methods and apparatus for reducing corrosion in refractory linings
FR2647533B1 (fr) * 1989-05-29 1993-03-19 Europ Propulsion Chambre de statoreacteur a combustion supersonique
FR2647534B1 (fr) * 1989-05-29 1991-09-13 Europ Propulsion Chambre de reacteur et procede pour sa fabrication

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941759A (en) * 1957-01-14 1960-06-21 Gen Dynamics Corp Heat exchanger construction

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE924945C (de) * 1951-04-22 1955-03-10 Babcock & Wilcox Dampfkessel W Verfahren zur Herstellung gekuehlter feuerfester Waende fuer Schmelzkammerfeuerungen
US2767518A (en) * 1953-01-13 1956-10-23 Arthur W Schmid Forehearth structure
US3024514A (en) * 1957-06-24 1962-03-13 Edward E Davis Shuttle car kiln

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941759A (en) * 1957-01-14 1960-06-21 Gen Dynamics Corp Heat exchanger construction

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3373796A (en) * 1965-04-23 1968-03-19 Vallak Method and means for cooling a combustion chamber by means of a powderlike material
US3400754A (en) * 1965-10-04 1968-09-10 Commissariat Energie Atomique Method and device for providing protection against scale formation on a heat exchange surface
US3428114A (en) * 1967-03-27 1969-02-18 Us Interior Method and apparatus for preventing scale formation in heat exchangers
US3771442A (en) * 1972-01-11 1973-11-13 Penril Data Communications Inc Zero-lock print wheel apparatus
US20060060702A1 (en) * 2003-06-05 2006-03-23 The Boeing Company Cooled insulation surface temperature control system
WO2004108531A1 (en) * 2003-06-05 2004-12-16 The Boeing Company Surface temperature control system
US7055781B2 (en) 2003-06-05 2006-06-06 The Boeing Company Cooled insulation surface temperature control system
JP2006526540A (ja) * 2003-06-05 2006-11-24 ザ・ボーイング・カンパニー 表面温度制御システム
US7232093B2 (en) 2003-06-05 2007-06-19 The Boeing Company Cooled insulation surface temperature control system
CN100415607C (zh) * 2003-06-05 2008-09-03 波音公司 表面温度控制系统
US20040245389A1 (en) * 2003-06-05 2004-12-09 Behrens William W. Cooled insulation surface temperature control system
EP2108587A3 (de) * 2003-06-05 2017-12-13 The Boeing Company Oberflächentemperaturregelungssystem
US7905275B2 (en) * 2006-04-20 2011-03-15 The Boeing Company Ceramic foam cold plate
US20070247812A1 (en) * 2006-04-20 2007-10-25 The Boeing Company Ceramic foam cold plate
US8505616B2 (en) * 2006-04-20 2013-08-13 The Boeing Company Hybrid ceramic core cold plate
US20090202717A1 (en) * 2008-02-11 2009-08-13 General Electric Company Anti-Fouling Coatings for Combustion System Components Exposed to Slag, Ash and/or Char
US8227078B2 (en) * 2008-02-11 2012-07-24 General Electric Company Anti-fouling coatings for combustion system components exposed to slag, ash and/or char
US7914904B2 (en) 2008-03-25 2011-03-29 General Electric Company Component in a combustion system, and process for preventing slag, ash, and char buildup
US20110136654A1 (en) * 2008-03-25 2011-06-09 General Electric Company Component in a combustion system, and process for preventing slag, ash, and char buildup
WO2009142786A1 (en) * 2008-03-25 2009-11-26 General Electric Company Component in a combustion system, and process for preventing slag, ash, and char buildup
RU2510687C2 (ru) * 2008-03-25 2014-04-10 Дженерал Электрик Компани Компонент системы сгорания и способ предотвращения накопления шлака, золы и угля
CN101981377B (zh) * 2008-03-25 2015-05-20 通用电气公司 燃烧系统中的组件和防止熔渣、灰烬和烧焦物堆积的方法
US20090246500A1 (en) * 2008-03-25 2009-10-01 General Electric Company Component in a combustion system, and process for preventing slag, ash, and char buildup
US20110133026A1 (en) * 2009-12-03 2011-06-09 The Boeing Company Extended plug cold plate
US8720828B2 (en) 2009-12-03 2014-05-13 The Boeing Company Extended plug cold plate

Also Published As

Publication number Publication date
DE1278319B (de) 1969-04-17
SE306141B (de) 1968-11-18
CH427118A (de) 1966-12-31
GB1035148A (en) 1966-07-06

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