Vane ring for a turbomachine

The invention relates to a guide vane ring (10) with at least one Leitschaufelringsegment for a turbomachine comprising a plurality of radially arranged around a rotation axis guide vanes (12), a the guide vanes (12) radially outwardly disposed outer shroud (14) and one (the guide vanes 12 ) radially inward arranged inner shroud (16), said outer shroud (14) or the inner cover band (16) has at least one expansion gap (18), wherein the Leitschaufelringsegment (with vanes 12), the outer shroud (14) and the inner shroud (16) is formed in one piece and the at least one expansion gap (18) are sealed by means of at least one strain in the respective gap (18) respectively arranged sealing means (24). Furthermore, the invention relates to a gas turbine, in particular an aircraft engine with such a guide vane ring (10) and an additive manufacturing process of such a guide vane ring (10).