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12A high temperature gas turbine component includes an inner core made of a monolithic ceramic material embedded within an outer CMC shell. The inner core may be formed with a through hole, blind hole, wear pads and the like. A method of making the bushing includes the steps of a) forming an inner c

12A high temperature gas turbine component includes an inner core made of a monolithic ceramic material embedded within an outer CMC shell. The inner core may be formed with a through hole, blind hole, wear pads and the like. A method of making the bushing includes the steps of a) forming an inner core of silicon nitride or silicon carbide; and b) applying a ceramic matrix composite material over substantially all of the inner core.

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12A high temperature gas turbine component includes an inner core made of a monolithic ceramic material embedded within an outer CMC shell. The inner core may be formed with a through hole, blind hole, wear pads and the like. A method of making the bushing includes the steps of a) forming an inner c

12A high temperature gas turbine component includes an inner core made of a monolithic ceramic material embedded within an outer CMC shell. The inner core may be formed with a through hole, blind hole, wear pads and the like. A method of making the bushing includes the steps of a) forming an inner core of silicon nitride or silicon carbide; and b) applying a ceramic matrix composite material over substantially all of the inner core. ring temperature to provide on cooling an abrasive product which includes a sintered matrix bonded to shaped abrasive particles with abrading ends exposed; and i) cooling said abrasive product. 2. The method of claim 1, wherein each of the contact and mating surfaces of said tools correspond to the surface of a roller. 3. The method of claim 1, wherein said sinterable particles comprise metal particles. 4. The method of claim 3, wherein said layer provides on heating to the sintering temperature a liquidus phase in a volume sufficient to wet the base ends of said abrasive particles during the heating step and on cooling sufficient to bond the base ends of said abrasive particles within said sintered matrix. 5. The method of claim 4, wherein said volume is at least 20% based on the total volume of metal particles in the layer. 6. The method of claim 1, wherein in step e) orienting comprises vibrating. 7. The method of claim 1, wherein said abrasive particles are selected from cuboctahedral diamond crystals or cuboctahedral cubic boron nitride crystals. 8. The method of claim 3, wherein said metal particles are at least partially comprised of a brazing composition. 9. The method of claim 8, wherein said brazing composition comprises an active metal braze. 10. The method of claim 8, wherein said brazing composition is selected from Ni--Cr--Si, Cu--Su, Ag--Cu, Ni--Cr--P, Ni--Cr--Si--B, Ni--Cr--B or Ni--Si--B alloys. 11. The method of claim 1, further comprising the step of solvent softening the organic binder prior to deploying the abrasive particles. 12. An abrasive article comprising: a) a multiplicity of shaped abrasive particles wherein each abrasive particle has a shaped base end and an opposite shaped abrading end; b) a sintered matrix having the form of a sheet or strip, the matrix having a top surface which includes depressions wherein each depression contains and binds therein a shaped base end of an abrasive particle while the opposite abrading end of said abrasive particle is exposed and aligned in an optimal orientation; and c) a metal foil sinter bonded to the matrix providing a bottom surface to said abrasive article. 13. The abrasive article of claim 12, wherein said abrasive particles are cuboctahedral diamond crystals. 14. The abrasive article of claim 12, wherein said abrasive particles are cuboctahedral cubic boron nitride. 15. The abrasive article of claim 12, wherein said sintered matrix comprises a metal alloy braze. 16. A method of making an abrasive article comprised of a matrix having the form of a sheet or strip, the matrix having deployed therein a multiplicity of optimally oriented shaped abrasive particles, each abrasive particle having a shaped base end and an opposite shaped abrading end, said method comprising the following steps: a) providing a substrate forming apparatus including a first tool having a contact surface including a multiplicity of projections and a second tool having a mating surface; b) providing an embossable, perforatable, substrate having the form of a sheet or strip; c) contacting the substrate with the contact and mating surfaces of said first and second tools to provide an embossed, perforated, sheet having back surface and an opposite top surface characterized by having a multiplicity of tapered depressions and a perforation through the substrate within said depression; d) deploying one abrasive particle within each of said depressions; e) orienting each abrasive particle in the depression containing the abrasive particle, such that the abrading ends of the abrasive particles are exposed; f) creating a pressure differential between the top surface and the back surface of said embossed, perforated sheet wherein a lower pressure is applied to the back surface to hold each oriented abrasive particle within its depression while removing at least a major portion of the abrasive particles not within said depressions from the top surface of said embossed, perforat