Provided is a polycrystalline ceramic substrate to be bonded to a compound semiconductor substrate with a bonding layer interposed therebetween, wherein at least one of relational expression (1) 0.7<α.sub.1/α.sub.2<0.9 and relational expression (2) 0.7<α.sub.3/α.sub.4<0.9 holds, where α.sub.1 represents a linear expansion coefficient of the polycrystalline ceramic substrate at 30° C. to 300° C. and α.sub.2 represents a linear expansion coefficient of the compound semiconductor substrate at 30° C. to 300° C., and α.sub.3 represents a linear expansion coefficient of the polycrystalline ceramic substrate at 30° C. to 1000° C. and α.sub.4 represents a linear expansion coefficient of the compound semiconductor substrate at 30° C. to 1000° C.

A porous refractory cast material contains a closed refractory aggregate fraction having a minimum particle size and a maximum particle size; the ratio of maximum particle size to minimum particle size is 10:1 or less. This closed refractory aggregate fraction comprises all of the porous refractory cast material having a particle diameter greater than 0.1 mm. The porous refractory cast material also contains a binder phase containing refractory selected from calcium aluminate cement, alumina phosphate, hydratable alumina, colloidal silica and combinations thereof. Also disclosed is a metallurgical vessel with an interior lining incorporating the porous refractory cast material.

A porous refractory cast material contains a closed refractory aggregate fraction having a minimum particle size and a maximum particle size; the ratio of maximum particle size to minimum particle size is 10:1 or less. This closed refractory aggregate fraction comprises all of the porous refractory cast material having a particle diameter greater than 0.1 mm. The porous refractory cast material also contains a binder phase containing refractory selected from calcium aluminate cement, alumina phosphate, hydratable alumina, colloidal silica and combinations thereof. Also disclosed is a metallurgical vessel with an interior lining incorporating the porous refractory cast material.

An extrudable ceramic precursor mixture and method of use includes: an inorganic ceramic-forming component, a first siloxane prepolymer, a second siloxane prepolymer with a different composition than the first siloxane prepolymer, a catalyst adapted to catalyze polymerization of the first siloxane prepolymer with the second siloxane prepolymer into a siloxane-based polymer, and a thermally curable siloxane-based cross-linking agent adapted to crosslink the siloxane-based polymer. Comprised is a polydimethylsiloxane having a vinyl functional group and a polydimethylsiloxane having a silicon hydride functional group.

An extrudable ceramic precursor mixture and method of use includes: an inorganic ceramic-forming component, a first siloxane prepolymer, a second siloxane prepolymer with a different composition than the first siloxane prepolymer, a catalyst adapted to catalyze polymerization of the first siloxane prepolymer with the second siloxane prepolymer into a siloxane-based polymer, and a thermally curable siloxane-based cross-linking agent adapted to crosslink the siloxane-based polymer. Comprised is a polydimethylsiloxane having a vinyl functional group and a polydimethylsiloxane having a silicon hydride functional group.

A pillar shaped honeycomb structure for induction heating, the honeycomb structure being made of ceramics and including: an outer peripheral wall; and a partition wall disposed on an inner side of the outer peripheral wall, the partition wall defining a plurality of cells, each of the cells penetrating from one end face to other end face to form a flow path, wherein a composite material containing a conductor and a non-conductor is provided in the cells in a region of 50% or less of the total length of the honeycomb structure from one end face, and wherein the conductor is a conductor that generates heat in response to a change in a magnetic field.

A pillar shaped honeycomb structure for induction heating, the honeycomb structure being made of ceramics and including: an outer peripheral wall; and a partition wall disposed on an inner side of the outer peripheral wall, the partition wall defining a plurality of cells, each of the cells penetrating from one end face to other end face to form a flow path, wherein a composite material containing a conductor and a non-conductor is provided in the cells in a region of 50% or less of the total length of the honeycomb structure from one end face, and wherein the conductor is a conductor that generates heat in response to a change in a magnetic field.

A honeycomb filter includes a honeycomb structure having a porous partition wall disposed to surround a plurality of cells; and a plugging portion provided at one end of the cell, wherein the honeycomb structure has an inflow side region including a range of up to at least 30% with respect to the total length of the honeycomb structure with the inflow end face as the starting point and an outflow side region including a range of up to at least 20% with respect to the total length of the honeycomb structure with the outflow end face as the starting point, in the extending direction of the cell of the honeycomb structure, an average pore diameter of the partition wall in the inflow side region is 9 to 14 μm and an average pore diameter of the partition wall in the outflow side region is 15 to 20 μm.

A turbine engine has: a first member (22) having a surface bearing an abradable coating, the abradable coating (36) being at least 90% by weight ceramic; and a second member (24) having a surface bearing an abrasive coating. The abrasive coating (56) has a metallic matrix (64) and a ceramic oxide abrasive (66) held by the metallic matrix, the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating. At least 50% by weight of the ceramic abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.

A turbine engine has: a first member (22) having a surface bearing an abradable coating, the abradable coating (36) being at least 90% by weight ceramic; and a second member (24) having a surface bearing an abrasive coating. The abrasive coating (56) has a metallic matrix (64) and a ceramic oxide abrasive (66) held by the metallic matrix, the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating. At least 50% by weight of the ceramic abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.