Ceramic centerbody and method of making
A ceramic centerbody ( 120 ) for an aircraft gas turbine engine. The ceramic centerbody ( 120 ) comprises an interlaced fiber structure having fibers oriented in a substantially transverse directions and a ceramic matrix surrounding the ceramic fiber structure. The ceramic fiber and matrix are formed into a conical shape having a fore end ( 128 ) and an aft end ( 126 ). The centerbody includes a means for mechanical attachment ( 130 ) circumferentially oriented around the fore end of the centerbody. The fore end further includes additional plies oriented in a third preselected direction, thereby providing additional strength to for mechanical attachment.
1. A green ceramic centerbody ( 120 ) for an aircraft gas turbine engine, comprising:
an interlaced fiber structure having fibers oriented in a substantially transverse direction;
a ceramic matrix surrounding the interlaced fiber structure; and
wherein the ceramic fibers and ceramic matrix surrounding the fibers are formed into a conical shape having a fore end ( 128 ) and an aft end ( 124 ), and wherein
a plurality of Y-brackets are circumferentially oriented around the fore end to form mechanical attachment and to provide restraint in the tangential direction while allowing for kinematic growth in the radial direction.
2. The ceramic centerbody ( 120 ) of claim 1 wherein the fore end ( 128 ) further includes additional plies of ceramic material oriented in a third preselected direction.
3. The ceramic centerbody ( 120 ) of claim 1 wherein the fibers of the interlaced fiber structure further comprise a first ceramic material and the ceramic matrix comprises a second ceramic material.
4. The ceramic centerbody ( 120 ) of claim 1 wherein the fibers of the interlaced fiber structure further comprise aluminosilicate fibers.
5. The ceramic centerbody ( 120 ) of claim 4 wherein the aluminosilicate fibers comprise polycrystalline α-alumina fibers.
6. The ceramic centerbody ( 120 ) of claim 1 wherein the ceramic matrix comprises aluminosilicate material.
7. The ceramic centerbody ( 120 ) of claim 1 wherein the interlaced fiber structure and matrix further comprise at least one ply of ceramic material, the fibers interlaced within the ply oriented in substantially transverse directions and surrounded by the ceramic matrix.
8. The centerbody ( 120 ) of claim 1 further including plies of ceramic matrix composite material reinforcing the fore end ( 128 ) of the centerbody, the plies oriented in a preselected third direction at an angle between the substantially transverse oriented plies.
9. The centerbody ( 120 ) of claim 8 wherein the preselected third direction is an angle oriented at ±45° to the substantially transverse oriented plies.
10. The centerbody ( 120 ) of claim 1 further including an aperture ( 126 ) at the aft end, the aft end further including reinforcing plies of ceramic matrix composite material, the plies oriented in a preselected third direction at an angle between the substantially transverse oriented plies.
11. The centerbody ( 120 ) of claim 1 further including a corrosion resistant, oxidation resistant metallic strip ( 134 ) overlying a fore edge of the fore end ( 128 ).
12. The centerbody ( 120 ) of claim 1 wherein the metallic strip ( 134 ) is selected from the group consisting of stainless steel and superalloys.