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6191 results about "Thermal dilatation" patented technology

Coating inorganic fiber toughened MAX phase ceramic composite material, preparation method and uses thereof

ActiveCN103910532AAppropriate bonding interface strengthFree control of interface strengthNuclear energy generationContainmentAviationFiber
The present invention provides a coating inorganic fiber toughened MAX phase ceramic composite material and a preparation method thereof. The composite material adopts a MAX phase ceramic material as a matrix and adopts coating inorganic fibers as a toughening phase, wherein the coating inorganic fiber content is 0.5-90% (by volume), and the coating inorganic fibers are completely dispersed in the matrix and are inorganic fibers with the surface coated with the coating. Compared with the composite material in the prior art, the composite material of the present invention has the following characteristics that: the interface reaction between the inorganic fibers and the MAX phase ceramic can be effectively inhibited, the thermal expansion coefficient and elasticity modulus matching degree between the inorganic fibers and the MAX phase ceramic can be effective regulated, the effective improvement of the fracture toughness and the high temperature resistance of the MAX phase ceramic composite material can be achieved, the problems of high brittleness and insufficient use reliability of the MAX phase ceramic can be fundamentally solved, and the coating inorganic fiber toughened MAX phase ceramic composite material has potential application prospects in the high technology fields of civil use, aviation, aerospace, nuclear industry and the like, and is especially for the fission and fusion reactor nuclear power plant inner wall structure material.
Owner:NINGBO INST OF MATERIALS TECH & ENG CHINESE ACADEMY OF SCI

Gas turbine engine having a multi-variable closed loop controller for regulating tip clearance

A gas turbine engine has, in flow series, a compressor section, a combustor, and a turbine section. The gas turbine engine further has a system (i) for cooling the turbine section and (ii) for providing tip clearance control between turbine blades of the turbine section and a plurality of circumferentially distributed segments which form an annular shroud surrounding the outer tips of the turbine blades. The system includes a turbine section cooling sub-system which diverts a first cooling air flow received from the compressor section to a heat exchanger and then to the turbine section to cool components thereof. The first cooling air flow by-passes the combustor and is cooled in the heat exchanger. The turbine section cooling subsystem has a first valve arrangement which regulates the first cooling air flow. The system further includes a tip clearance control sub-system which supplies a second cooling air flow to an engine case to which the segments are mounted. The second cooling air flow regulates thermal expansion of the case and thereby controls the clearance between the segments and the outer tips. The tip clearance control sub-system has a second valve arrangement which regulates the second cooling air flow. The system further includes a closed-loop controller which issues first and second demand signals to respectively the first and the second valve arrangements. Each of the first and second demand signals are determined on the basis of: (i) a value of the first demand signal at a previous time step, and a measurement or estimate of turbine section component temperature, and (ii) a value of the second demand signal at a previous time step, and a measurement or estimate of tip clearance.
Owner:ROLLS ROYCE PLC
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