A component for the turbine of a gas turbine engine, the component including: two facing walls interconnected by one or more generally elongate divider members to partially define side-by-side, generally elongate, cooling fluid passage portions (138a, 138b, 138c, 138d, 138e) which form a multi-pass cooling passage within the component, the passage portions being connected in series fluid flow relationship by respective bends formed by joined ends of neighbouring passage portions; and one or more core tie linking passages (142, 142a, 142b) formed in the divider members, the or each core tie linking passage having an entrance at an upstream passage portion and an exit at a neighbouring downstream passage portion to allow cooling fluid to leak therethrough to bypass the bend formed by the joined ends of the neighbouring passage portions; and one or more differential pressure reducing arrangements formed in the multi-pass cooling passage facing a respective one of the core tie linking passages and the one or more differential pressure reducing arrangements extending at least partially across the entrance of the one of the core tie linking passages, the one or more differential pressure reducing arrangements being configured to reduce the difference in the static pressure of the cooling fluid between the entrance of the respective core tie linking passage and the exit of that core tie linking passage, the one or more differential pressure reducing arrangements including a flow deflector structure in the upstream passage portion, and the flow deflector structure being configured to substantially locally remove a dynamic component of the cooling fluid flow in the upstream passage portion at the entrance of the core tie linking passage, wherein: the flow deflector structure defines a cavity in the upstream passage portion at the entrance of the core tie linking passage, and the flow deflector structure is configured to define a hundred and eighty degree bend for flow of coolant air from the upstream passage portion to the cavity. two facing walls interconnected by one or more generally elongate divider members to partially define side-by-side, generally elongate, cooling fluid passage portions (138a, 138b, 138c, 138d, 138e) which form a multi-pass cooling passage within the component, the passage portions being connected in series fluid flow relationship by respective bends formed by joined ends of neighbouring passage portions; and one or more core tie linking passages (142, 142a, 142b) formed in the divider members, the or each core tie linking passage having an entrance at an upstream passage portion and an exit at a neighbouring downstream passage portion to allow cooling fluid to leak therethrough to bypass the bend formed by the joined ends of the neighbouring passage portions; and one or more differential pressure reducing arrangements formed in the multi-pass cooling passage facing a respective one of the core tie linking passages and the one or more differential pressure reducing arrangements extending at least partially across the entrance of the one of the core tie linking passages, the one or more differential pressure reducing arrangements being configured to reduce the difference in the static pressure of the cooling fluid between the entrance of the respective core tie linking passage and the exit of that core tie linking passage, the one or more differential pressure reducing arrangements including a flow deflector structure in the upstream passage portion, and the flow deflector structure being configured to substantially locally remove a dynamic component of the cooling fluid flow in the upstream passage portion at the entrance of the core tie linking passage, wherein: the flow deflector structure defines a cavity in the upstream passage portion at the entrance of the core tie linking passage, and the flow deflector structure is configured to define a hundred and eighty degree bend for flow of coolant air from the upstream passage portion to the cavity. the flow deflector structure defines a cavity in the upstream passage portion at the entrance of the core tie linking passage, and the flow deflector structure is configured to define a hundred and eighty degree bend for flow of coolant air from the upstream passage portion to the cavity.