A gas turbine, in particular an aircraft engine, having a housing in which at least one guide blade (12) is situated, the guide blade (12) including at least one shroud configuration (21) having a radially outer shroud (16) and having a shroud holding device (23) with the aid of which the shroud (16) is secured on the housing, as well as including a turbine blade (18) extending radially inward from the shroud configuration (21). The shroud holding device (23) or parts thereof include(s) at least one air passage channel (28), which permits a flow passage through the shroud holding device (23). The invention also relates to a guide blade (12) for placement on a housing of a gas turbine as well as a method for manufacturing such a guide blade (12).