A rear earth lutetium silicate composite environmental barrier coating and a preparing method thereof are disclosed. The composite environmental barrier coating includes a SiC/SiC matrix, a mullite layer and a composite surface layer consisting of Lu2Si2O7 and Lu2SiO5 in a mass ratio of 6:4. The preparing method combining plasma spraying and physical vapor deposition is adopted, and mullite powderhaving a particle size of 18-58 [mu]m and Lu2Si2O7-Lu2SiO5 composite powder having a particle size of 62-105 [mu]m are adopted as raw materials to prepare the mullite layer on the SiC/SiC matrix andthe composite surface layer on the mullite layer in order. The coating prepared by the method has good resistance to water oxygen corrosion at 1723 K, effectively retards generation of cracks and effectively avoids oxidation and performance degradation of the SiC/SiC matrix at high temperatures.

A rear earth lutetium silicate composite environmental barrier coating and a preparing method thereof

The invention discloses a preparation method for low-energy synthesis of one-dimensional SiAlON on diamond surface. The preparation method comprises the following steps: (1) uniformly stirring silicapowder and diamond powder according to a proper ratio and adding a composite binder and mixing; (2) pressurizing the mixed powder into a preform with high porosity and regular shape; (3) drying the preform, and heating the preform along with an aluminium block in a tubular furnace; (4) making the inside of the furnace to be communicated with the atmosphere, carrying out thermal insulation at normal pressure, and cooling to prepare the one-dimensional SiAlON on the diamond surface. The one-dimensional SiAlON is synthesized by a nitridation reaction method and a carbothermal reduction-nitridation method. Then, the high-purity one-dimensional SiAlON is synthesized with low cost and low energy.

Preparation method for low-energy synthesis of one-dimensional SiAlON on diamond surface

A turbine wheel assembly adapted for use in a gas turbine engine is disclosed. The turbine wheel assembly includes components optionally made from ceramic matrix composite such as turbine blades and/or heat shields.

Turbine wheel with circumferentially-installed inter-blade heat shields

The invention relates to an environment shield coating, in particular to a rare earth silicate environment shield coating with a multi-layer structure and a preparation method thereof, so that the problems that a coating material in the prior art is poor in heat match with a base material, is poor in thermal shock resistance, and cracks and comes off easily under the high-temperature condition. Asilicon layer is adopted as a bottom layer of the coating. A mullite layer is adopted as a middle layer of the coating. Rare earth silicate composite layers are adopted as a top layer of the coating.The number of the rare earth silicate composite layers is 3-10 layers. Rare earth silicate in the rare earth silicate composite layers comprises rare earth monosilicate and rare earth sorosilicate. The content of the rare earth sorosilicate is linearly increased layer by layer from the starting layer adjacent to the mullite layer to the direction away from the mullite layer, and increase between two adjacent layers is no more than 20% of the total content of the rare earth silicate. The content of the rare earth monosilicate is reduced linearly layer by layer correspondingly. The thickness ofthe bottom layer is 10-150 micrometers. The thickness of the middle layer is 10-300 micrometers. The thickness of the top layer is 10-300 micrometers. The total thickness of the coating is larger thanor equal to 100 micrometers. The coating can be prepared by adopting a method of spraying plasmas to a base body.

Rare earth silicate environment shield coating with multi-layer structure and preparation method thereof

An example article includes a substrate and a barrier coating on the substrate. The barrier coating includes a matrix including a rare-earth disilicate extending from an inner interface facing the substrate to an outer surface opposite the inner interface. The barrier coating includes a graded volumetric distribution of rare-earth oxide rich (REO-rich) phase regions in the matrix along a direction from the inner interface to the outer surface. The graded volumetric distribution defines a first volumetric density of the REO-rich phase regions at a first region of the matrix adjacent the outer surface. The graded volumetric distribution defines a second volumetric density of the REO-rich phase regions at a second region of the matrix adjacent the inner surface. The second volumetric density is different from the first volumetric density. An example technique includes forming the barrier coating on the substrate of a component.

Cmas-resistant barrier coatings

An environmental resistant coating member includes a SiC long fiber-reinforced ceramics substrate and an environmental barrier coating layer provided on the whole surface of the SiC long fiber-reinforced ceramics substrate The environmental barrier coating layer includes a SiAlON bonding layer laminated on the SiC long fiber-reinforced ceramics substrate, a mullite layer laminated on the SiAlON bonding layer, a reaction inhibition layer laminated on the mullite layer, and a gradient layer formed on the reaction inhibition layer that gradually changes from a rare-earth disilicate to a rare-earth monosilicate The reaction inhibition layer includes at least one of an alumina layer, a garnet layer, and a rare-earth (mono)silicate layer When the reaction inhibition layer includes two or more of these layers, the layers are formed in the order of the alumina layer, the garnet layer, and the rare-earth (mono)silicate layer from a mullite layer side toward a gradient layer side

Environmental resistant coating member

The shield member (30) is disposed over a gap between platform parts (20) of adjoining turbine rotor blades (10), is formed from a ceramic-based composite material, and shields the gap between the platform parts (20).

Shield member and jet engine using the same

FIELD: engines and pumps.SUBSTANCE: invention relates to the jet engine shielding elements. Shielding element (30) is located on above of the gaps between the turbine rotor adjacent blades (10) flange (20) sections and is made of a composite material with a ceramic matrix with possibility of the gap between the flange (20) sections shielding due to coming into contact along the flange sections bodies internal surfaces. From the airfoil input edge the shielding element section is made elongated and includes a second shielding surface located between the turbine rotor adjacent blades tail portions. Each of the flange sections includes a rear skirt, made on the flange section corresponding body output edge side. First contact areas are configured to come into contact with the turbine rotor adjacent blades tail sections side surfaces and with the rear skirts holding sections. Second contact areas are configured to come into contact with the turbine rotor adjacent blades tail sections side surfaces.EFFECT: technical result is the shielding of gaps between the turbine rotor adjacent blades flange sections.4 cl, 21 dwg

Takemoto Tsuyoshi

Papers

Environmental resistant coating member

Shield member and jet engine using the same

Shielding element and jet engine, in which such element is used