Turbine casing made of two materials
View Patent ↗The invention proposes a casing ( 30 ) of an aircraft turbine ( 16 ), intended to support a set of ring sectors ( 28 ) which partly delimits a channel for the passage of a gas stream through the turbine ( 16 ), where the casing ( 30 ) includes means for dynamic adjustment of the radial position of the ring sectors ( 28 ) by controlled injection of an air stream on to portions ( 36 ) of an annular wall ( 34 ) of the casing ( 30 ), where the casing ( 30 ) includes an upstream radial tab ( 38 ) which connects an upstream end of each ring sector ( 28 ), in the flow direction of the gas stream, to the casing ( 30 ), and a downstream radial tab ( 40 ) which connects a downstream end of each ring sector ( 28 ) to the casing ( 30 ), where both upstream and downstream radial tabs ( 38, 40 ) are made from a single piece with the casing ( 30 ), characterized in that each radial tab ( 38, 40 ) is made as two portions ( 42, 44 ) from different materials.
1. A casing of an aircraft turbine, configured to support a set of ring sectors which partly delimits a channel for the passage of a gas stream through the turbine,
where the casing includes an adjustment device for dynamic adjustment of a radial position of the ring sectors by controlled injection of an air stream on to portions of an annular wall of the casing,
where the casing includes an upstream radial tab which connects an upstream end of each ring sector, in a flow direction of the gas stream, to the casing, and a downstream radial tab which connects a downstream end of each ring sector to the casing, where both upstream and downstream radial tabs are made from a single piece with the casing,
wherein each radial tab is made as two portions from different materials, and includes a radially internal portion made of a first material and a radially external portion made of a second material, and
wherein the first material is a heat-resistant material, and the second material is a material with a high linear expansion coefficient.
2. A casing according to claim 1 , wherein the annular wall of the casing is made from the second material.
3. A casing according to claim 1 , wherein both portions of each radial tab are coupled to one another by welding.
4. A casing according to claim 3 , wherein a welding bead of both portions of each radial tab is circular and coaxial with a main axis of the casing.
5. A casing according to claim 1 , wherein the first material is an alloy of aluminium and titanium.
6. A casing according to claim 1 , wherein the second material is an alloy made from nickel and chromium.
7. A turbine of an aircraft turbomachine comprising a stator assembly including the casing according to claim 1 , and including multiple ring sectors which are attached directly at least to the upstream radial tab of the casing.
8. An aircraft turbomachine including the turbine according to claim 7 .