Gas turbine engine shroud ring mounting

A turbine for a gas turbine engine, said turbine having a turbine casing, means cooperating with said turbine casing to define an annular gas passage, a stage of rotary aerofoil blades positioned within said annular passage and having an axis of rotation, a shroud ring made from a ceramic material surrounding and spaced from said aerofoil blades, said shroud ring being capable of floating radially with respect to said axis of rotation, said turbine casing being axially divided radially outwardly of said stage to define a circumferentially extending housing accommodating said shroud ring and additionally defining an annular chamber with an outer wall spaced radially outwardly of said shroud ring, and means radially supporting and radially spacing apart said shroud ring from said turbine casing, the improvement in said last-mentioned means comprising:

• a pair of axially spaced apart flanges extending radially inwardly from said outer wall toward said shroud ring and defining an annular space surrounding said shroud ring;
• and a woven wire mesh array located within and filling said space between said outer wall and said shroud ring and between said axially spaced apart flanges, said flanges being capable of restraining said woven wire mesh array from axial movement.