An intermediate-casing structure for a compressor in a gas turbine engine, in particular an aircraft engine, having a plurality of components including at least one static blade row for deflecting at least one airflow entering the intermediate-casing structure, and at least one ring, on which the blade rows are radially arranged, characterized in that at least one first component of the intermediate-casing structure is formed from composite material, in particular fiber-composite material, or exhibits composite material, and at least one second component of the intermediate-casing structure is formed from metal or exhibits metal. Furthermore, the invention relates to a gas turbine device.