Abstract: Disclosed is a turbine vane thermal barrier coating working condition simulation experiment test system, including: a working state simulation device, a service environment simulation device and a detection device. The working state simulation device is provided on one side of the turbine vane thermal barrier coating to be tested, is connected to the turbine vane thermal barrier coating to be tested, and is configured to simulate a high-speed rotation working state of the turbine vane thermal barrier coating to be tested. The service environment simulation device is provided on the other side of the turbine vane thermal barrier coating to be tested. The detection device is configured to detect damage generated when the turbine vane thermal barrier coating to be tested rotates at a high speed in the service environment.

Abstract: Disclosed is a turbine vane thermal barrier coating working condition simulation experiment test system, including: a working state simulation device, a service environment simulation device and a detection device. The working state simulation device is provided on one side of the turbine vane thermal barrier coating to be tested, is connected to the turbine vane thermal barrier coating to be tested, and is configured to simulate a high-speed rotation working state of the turbine vane thermal barrier coating to be tested. The service environment simulation device is provided on the other side of the turbine vane thermal barrier coating to be tested. The detection device is configured to detect damage generated when the turbine vane thermal barrier coating to be tested rotates at a high speed in the service environment.

Abstract: A method for evaluating an application effect of a thermal barrier coating for a turbine vane comprises: performing a preset program for calculation according to distribution of temperature fields of two computational domains for the thermal barrier coating and the turbine vane without the thermal barrier coating as well as maximum principal stress and maximum shear stress data of a stress field of the thermal barrier coating to obtain heat insulation efficiency of the thermal barrier coating, so as to obtain a local comprehensive evaluation factor and a global comprehensive evaluation factor of the thermal barrier coating. In the present invention, a simulation method of the thermal barrier coating for the three-dimensional turbine vane having a gas film hole is realized; and an evaluation parameter for the application effect of the thermal barrier coating is established.

Abstract: The invention relates to a compound having general formula I, wherein: X represents CH2, C?O, C?S or CHOH, R1 represents an amino acid optionally substituted by one or more halogen atoms, or by one or more CF3 groups and n=0.1 or 2, or R1 represents a peptide containing two amino acids, each amino acid being optionally substituted by one or more halogen atoms, or by one or more CF3 groups and n=0 or 1, or XR1 represent PO3H or SO3H and n=0.1 or 2; R2 represents H, XR1, an alkyl group at C1-C6, an aralkyl group at C1-C6 or an aryl group, whereby the alkyl, aralkyl and aryl groups can be substituted by an amine NH2, a carboxylic group COOH, one or more halogen atoms.

Abstract: The invention relates to a compound having general formula I, wherein: X represents CH2, C?O, C?S or CHOH, R1 represents an amino acid optionally substituted by one or more halogen atoms, or by one or more CF3 groups and n=0.1 or 2, or R1 represents a peptide containing two amino acids, each amino acid being optionally substituted by one or more halogen atoms, or by one or more CF3 groups and n=0 or 1, or XR1 represent PO3H or SO3H and n=0.1 or 2; R2 represents H, XR1, an alkyl group at C1-C6, an aralkyl group at C1-C6 or an aryl group, whereby the alkyl, aralkyl and aryl groups can be substituted by an amine NH2, a carboxylic group COOH, one or more halogen atoms.