A space filler for forming a fibrous preform may comprise an additively manufactured ceramic material. The additively manufactured ceramic material may define a plurality of pores. A shape of the additively manufactured ceramic material may complement a shape of a void formed by fibrous regions of the fibrous preform.

The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.

The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.

The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.

A pillar-shaped honeycomb structure including an outer peripheral side wall, a plurality of first cells provided on an inner peripheral side of the outer peripheral side wall, the first cells extending from a first end surface to a second end surface, each opening on the first end surface and having a sealing portion with an average void ratio of 4% or less on the second end surface, and a plurality of second cells provided on the inner peripheral side of the outer peripheral side wall, the second cells extending from the first end surface to the second end surface, each having a sealing portion with an average void ratio of 4% or less on the first end surface and opening on the second end surface, the first cells and the second cells being alternately arranged adjacent to each other with a partition wall interposed therebetween.

A pillar-shaped honeycomb structure including an outer peripheral side wall, a plurality of first cells provided on an inner peripheral side of the outer peripheral side wall, the first cells extending from a first end surface to a second end surface, each opening on the first end surface and having a sealing portion with an average void ratio of 4% or less on the second end surface, and a plurality of second cells provided on the inner peripheral side of the outer peripheral side wall, the second cells extending from the first end surface to the second end surface, each having a sealing portion with an average void ratio of 4% or less on the first end surface and opening on the second end surface, the first cells and the second cells being alternately arranged adjacent to each other with a partition wall interposed therebetween.

A ceramic filter having a pillar-shaped honeycomb structure, wherein when observing a plurality of pores from a surface of partition walls with a laser microscope and plotting an equivalent circle diameter (μm) of each pore on an X-axis and a pore depth (μm) of each pore on a Y-axis on a two-dimensional coordinate system, a slope of a regression line (y/x) obtained by a least squares method in a range of 20≤x≤40 is 0 to 0.20, an average value of the pore depth of the plurality of pores is 2.5 μm to 5.0 μm, and a number density of the plurality of pores is 600/mm.sup.2 to 2450/mm.sup.2.

A ceramic filter having a pillar-shaped honeycomb structure, wherein when observing a plurality of pores from a surface of partition walls with a laser microscope and plotting an equivalent circle diameter (μm) of each pore on an X-axis and a pore depth (μm) of each pore on a Y-axis on a two-dimensional coordinate system, a slope of a regression line (y/x) obtained by a least squares method in a range of 20≤x≤40 is 0 to 0.20, an average value of the pore depth of the plurality of pores is 2.5 μm to 5.0 μm, and a number density of the plurality of pores is 600/mm.sup.2 to 2450/mm.sup.2.

A method of slowing an aircraft overrunning a runway, including covering an area adjacent a runway with irregular foamed glass bodies having aspect ratios of about 1:1.9 and diameters of about 10 mm to about 80 mm to define a bed, pouring liquid cement over the foamed glass bodies such that the cement infiltrates at least through the bed, curing the liquid cement to define a composite material of foamed glass bodies in a cementitious matrix, and crushing at least a portion of the composite material with an oncoming aircraft, slowing the aircraft. The composite material is at least 85 volume percent foamed glass bodies. When pouring the cement, the liquid cement flows over and around the foamed glass bodies. The aggregate bodies crush and break up before slip failure occurs when being overrun by an aircraft. The aggregate bodies intersect to define stacking angles of about 35 degrees. The cementitious matrix has a cementitious surface.

A method of slowing an aircraft overrunning a runway, including covering an area adjacent a runway with irregular foamed glass bodies having aspect ratios of about 1:1.9 and diameters of about 10 mm to about 80 mm to define a bed, pouring liquid cement over the foamed glass bodies such that the cement infiltrates at least through the bed, curing the liquid cement to define a composite material of foamed glass bodies in a cementitious matrix, and crushing at least a portion of the composite material with an oncoming aircraft, slowing the aircraft. The composite material is at least 85 volume percent foamed glass bodies. When pouring the cement, the liquid cement flows over and around the foamed glass bodies. The aggregate bodies crush and break up before slip failure occurs when being overrun by an aircraft. The aggregate bodies intersect to define stacking angles of about 35 degrees. The cementitious matrix has a cementitious surface.