Methods for processing a vessel, for example to provide a gas barrier or lubricity, are disclosed. First and second PECVD or other vessel processing stations or devices and a vessel holder comprising a vessel port are provided. An opening of the vessel can be seated on the vessel port. The interior surface of the seated vessel can be processed via the vessel port by the first and second processing stations or devices. Vessel barrier, lubricity and hydrophobic coatings and coated vessels, for example syringes and medical sample collection tubes are disclosed. A vessel processing system and vessel inspection apparatus and methods are also disclosed.

Vessel, coating, inspection and processing apparatus

The invention pertains to components (1) with a thermal barrier coating (2-6) on the surface thereof, wherein the thermal barrier coating comprises at least one layer (3) comprising chemically stabilised zirconia, and wherein at least indirectly adjacent to the layer (3) comprising chemically stabilised zirconia and on its surface facing side there is provided a protective layer (4) and/or a infiltration zone (5) which is not reacting with environmental contaminant compositions that contain oxides of calcium and which is not reacting with the material of the layer (3) comprising chemically stabilised zirconia. It furthermore relates to methods for making such components as well as to uses of specific systems for coating thermal barrier coatings for the prevention of CMAS.

Multilayer thermal barrier coating

Disclosed is a novel heat-resistant superalloy for turbine disks having a chemical composition consisting of, in mass%, 19.5-55% of cobalt, 2-25% of chromium, 0.2-7% of aluminum, 3-15% of titanium and the balance of nickel and inevitable impurities.

Heat-resistant superalloy

Methods for processing a vessel, for example to provide a gas barrier or lubricity, are disclosed. First and second PECVD or other vessel processing stations or devices and a vessel holder comprising a vessel port are provided. An opening of the vessel can be seated on the vessel port. The interior surface of the seated vessel can be processed via the vessel port by the first and second processing stations or devices. Vessel barrier, lubricity and hydrophobic coatings and coated vessels, for example syringes and medical sample collection tubes are disclosed. A vessel processing system and vessel inspection apparatus and methods are also disclosed, for example using material outgassed from a surface to inspect the properties of a surface coating.

Vessel inspection apparatus and methods

A method for providing a passivation layer or pH protective coating on a substrate surface by PECVD is provided, the method comprising generating a plasma from a gaseous reactant comprising polymerizing gases, for example an organosilicon precursor and optionally O2. The lubricity, passivation, pH protective, hydrophobicity, and/or barrier properties of the passivation layer or pH protective coating are set by setting the ratio of the O2 to the organosilicon precursor in the precursor feed, and/or by setting the electric power used for generating the plasma. In particular, a lubricity and/or passivation layer or pH protective coating made by said method is provided.

Passivation, ph protective or lubricity coating for pharmaceutical package, coating process and apparatus

PROBLEM TO BE SOLVED: To provide a thermal insulating coating material which can prevent peeling of the coating in use at a high temperature, and to provide a turbine member and a gas turbine coated with the thermal insulating coating material. SOLUTION: The thermal insulating coating material comprises a ceramic layer 23 formed on of a heat resistant alloy substrate 21 at a high temperature, in order to improve heat resistance of the substrate 21, wherein the ceramic layer 23 is layered through a metallic bonding layer 22, and is composed of ZrO 2 added with Yb 2 O 3 of a stabilizing agent. In the ceramic layer 23, several longitudinal cracks 23A are preferably introduced. The surfaces of the turbine member and gas turbine are coated with the thermal barrier coating material. COPYRIGHT: (C)2003,JPO

Thermal insulating coating material, manufacturing method therefor, turbine member and gas turbine

PROBLEM TO BE SOLVED: To rapidly perform re-coating or the like by correctly diagnosing degradation of thermal barrier coating executed on a high-temperature member for a gas turbine such as a gas turbine blade, and discovering damages such as peeling and wear of the coating. SOLUTION: Internal peeling of the thermal barrier coating is firstly inspected by the infrared ray thermography method. If a peeling pattern portion is detected as a result, a surface element analysis inspection by the fluorescent X-ray method and the film thickness measurement inspection by the eddy current flaw detection method are carried out on the peeling pattern portion. Presence/absence of peeling/wear of the thermal barrier coating is detected from the result of inspection, and degradation diagnosis is determined. If no peeling pattern portion is detected as a result of the internal peeling inspection by the infrared ray thermography method, the surface element analysis inspection by the fluorescent X-ray method is eliminated, and the film thickness measurement inspection by the eddy current flaw detection method is carried out for confirmation. COPYRIGHT: (C)2004,JPO

Thermal barrier coating degradation diagnosing method

PROBLEM TO BE SOLVED: To improve the durability at higher temperatures in a thermal barrier coasting material coating a gas turbine member. SOLUTION: In a thermal barrier coating film, on a base material 21 composing the moving blade, or the like, of a gas turbine, a metallic bonding layer 22 excellent in corrosion resistance and oxidation resistance and a high strength and high toughness ceramics layer 23 whose physical properties change by the occurance of phase transformation and sintering at ≥1,100°C in spite of its high strength and toughness are successively laminated, and on the outermost layer, a high temperature phase stabilized ceramics layer 24 excellent in phase stability at high temperature in spite of its low strength and toughness is laminated. The metallic bonding phase 22 is composed of MCrAlY alloy series, the high strength and high toughness ceramics layer 23 is composed of ZrO2.6 to 12 wt.%Y2O3 or ZrO2.8 to 16 wt.%Dy2O3, and the high temperature phase stabilized ceramics layer 24 is composed of ZrO2.15 to 20 wt.%Y2O3 or ZrO2.16 to 20 wt.%Dy2O3. COPYRIGHT: (C)2001,JPO

Thermal barrier coating material, gas turbine member applied with the same and gas turbine

PROBLEM TO BE SOLVED: To provide a coating material for shielding heat, coating a gas-turbine member, whereby a higher heat-shielding property and a higher stripping resistance are obtained. SOLUTION: As the first embodiment, a metallic bond layer 22 and a porous ZeO2 based ceramic layer 23 are laminated in turn, on a base material 21, while a fine crack 24, expanding (growing) in the thickness direction of the ceramic layer 23, is formed. This crack 24 is formed by laminating the ceramic layer 23 on the metallic bond layer 22 by spraying method, and the like, and thereafter by heating the surface of the ceramic layer 23 to 1,000 deg.C-1,700 deg.C by radiating a laser beam on the surface of the same while cooling the back side of the base material 21.

Coating material for shielding heat, its production method, gas-turbine member applied with the same material, and gas turbine

PROBLEM TO BE SOLVED: To provide a heat-shielding ceramic coating parts which is for use in such equipment as an electricity-generating gas turbine utilized in the region of elevated temperatures and which has an extremely excellent thermal-shock resistance and is manufactured easily. SOLUTION: The heat-shielding ceramic coating parts comprises a metal substrate 1, an undercoat flame spray coating film 2 which is formed of an alloy of MCrAlY (M is Co or Ni) on the surface of the substrate 1 and a heat-shielding ceramic flame spray coating film 3 which is formed of ZrO 2 as a main body on the film 2. The heat-shielding ceramic coating film 3 has a large number of vertical cracks 5 towards the thickness direction from the surface and the average depth of the vertical cracks 5 is made to be in the range of 30-80 % of the thickness of the heat-shielding ceramic flame spray coating film. COPYRIGHT: (C)2004,JPO

孝二高橋

Papers

Thermal insulating coating material, manufacturing method therefor, turbine member and gas turbine

Thermal barrier coating degradation diagnosing method

Thermal barrier coating material, gas turbine member applied with the same and gas turbine

Coating material for shielding heat, its production method, gas-turbine member applied with the same material, and gas turbine

Heat-shielding ceramic coating parts and manufacturing method thereof

孝二 高橋

Papers

Thermal insulating coating material, manufacturing method therefor, turbine member and gas turbine

Thermal barrier coating degradation diagnosing method

Thermal barrier coating material, gas turbine member applied with the same and gas turbine

Coating material for shielding heat, its production method, gas-turbine member applied with the same material, and gas turbine

Heat-shielding ceramic coating parts and manufacturing method thereof

孝二高橋