A gas turbine engine comprising: a compressor section; a combustor fluidly connected to the compressor section; a turbine section fluidly connected to the combustor and mechanically connected to said compressor section via a shaft (240; 340; 440; 540); a plurality of rotors disposed in one of said compressor section and said turbine section, each of said rotors including a rotor disk portion including a radially inward bore (216, 226, 316, 326; 416, 426; 516, 526), and each of said rotors being static relative to said shaft (240; 340; 440; 540); each rotor in said plurality of rotors being axially adjacent at least one other of said rotors in said plurality of rotors and defining a gap (270; 370; 470; 570) between each of said rotors and said axially adjacent rotors; a cooling passage (250; 350; 450; 550) for a cooling flow defined between said shaft (240; 340; 440; 540) and said rotors; and a cooling flow redirection component (290; 390; 490; 590) disposed at said gap (270; 370; 470; 570) and operable to redirect said cooling flow in said cooling passage into said gap (270; 370; 470; 570)], wherein said cooling flow redirection component (290; 390; 490; 590) comprises: a cooling flow redirection portion (494; 594), said cooling flow redirection portion being angled relative to flow through said cooling passage (250; 30; 450; 550) such that coolant flow is redirected into said gap (270; 370; 470; 570); and a radially aligned portion (496; 596) extending radially outward from said cooling flow redirection portion (494; 594), relative to a radius of the engine, and wherein the radially aligned portion (496; 596) includes at least one through hole (498; 598), such that during operation a redirected cooling flow (454; 554) passes through the hole (498; 598), characterised in that the cooling flow redirection component (290; 390; 490; 590) is distinct from said rotors, wherein the through hole is a tapered through hole having an inlet with a first cross sectional area, and an outlet with a second cross sectional area, and wherein the second cross sectional area is smaller than the first cross sectional area. a compressor section; a combustor fluidly connected to the compressor section; a turbine section fluidly connected to the combustor and mechanically connected to said compressor section via a shaft (240; 340; 440; 540); a plurality of rotors disposed in one of said compressor section and said turbine section, each of said rotors including a rotor disk portion including a radially inward bore (216, 226, 316, 326; 416, 426; 516, 526), and each of said rotors being static relative to said shaft (240; 340; 440; 540); each rotor in said plurality of rotors being axially adjacent at least one other of said rotors in said plurality of rotors and defining a gap (270; 370; 470; 570) between each of said rotors and said axially adjacent rotors; a cooling passage (250; 350; 450; 550) for a cooling flow defined between said shaft (240; 340; 440; 540) and said rotors; and a cooling flow redirection component (290; 390; 490; 590) disposed at said gap (270; 370; 470; 570) and operable to redirect said cooling flow in said cooling passage into said gap (270; 370; 470; 570)], wherein said cooling flow redirection component (290; 390; 490; 590) comprises: a cooling flow redirection portion (494; 594), said cooling flow redirection portion being angled relative to flow through said cooling passage (250; 30; 450; 550) such that coolant flow is redirected into said gap (270; 370; 470; 570); and a radially aligned portion (496; 596) extending radially outward from said cooling flow redirection portion (494; 594), relative to a radius of the engine, and wherein the radially aligned portion (496; 596) includes at least one through hole (498; 598), such that during operation a redirected cooling flow (454; 554) passes through the hole (498; 598), a cooling flow redirection portion (494; 594), said cooling flow redirection portion being angled relative to flow through said cooling passage (250; 30; 450; 550) such that coolant flow is redirected into said gap (270; 370; 470; 570); and a radially aligned portion (496; 596) extending radially outward from said cooling flow redirection portion (494; 594), relative to a radius of the engine, and wherein the radially aligned portion (496; 596) includes at least one through hole (498; 598), such that during operation a redirected cooling flow (454; 554) passes through the hole (498; 598), characterised in that the cooling flow redirection component (290; 390; 490; 590) is distinct from said rotors, wherein the through hole is a tapered through hole having an inlet with a first cross sectional area, and an outlet with a second cross sectional area, and wherein the second cross sectional area is smaller than the first cross sectional area.