Abstract: A bioprocessing system comprising a series of processing stations for performing operations for bioprocessing is disclosed. The bioprocessing system includes an automated system comprising means for manipulating a fluid connection between a first container and a separable second container whereby to create an aseptic connection that enables a controlled transfer of fluid or cell material between the first container and the second container, wherein the means for manipulating a fluid connection is configured to create an aseptic connection that can be disconnected after the transfer of fluid or cell material is complete to enable a further such fluid connection to be manipulated between the first container and a separable third container, and means for controlling an automated sequence of operation of the processing stations.

Abstract: A component for a gas turbine engine, comprising: a first wall defining an exterior surface of the component; a second wall, arranged such that a coolant channel is defined by the space between the first and second walls; and a plurality of apertures provided through the first wall to connect the coolant channel to the exterior surface of the component; wherein adjacent at least one aperture the coolant channel comprises a flow modifier, configured to locally change the pressure of the coolant flowing in the coolant channel in the region of the aperture relative to a region of the coolant channel adjacent another aperture.

Abstract: A blade has a root portion and elongate portion extending from the root portion to a tip. The elongate portion has an aerofoil-shaped cross section having leading and trailing edges and suction and pressure sides. The tip may include a gutter defining squealer. The squealer has a wall extending from the trailing edge and along a substantial portion of the tip perimeter. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exiting into the gutter. A gallery channel is arranged just behind the gutter and extends from an open end intersecting the main trailing edge cooling channel to a closed end located just behind a trailing edge apogee. Cooling channels extend from the gallery channel and through the squealer wall. The gallery channel diameter is greater at the open end than the closed end.

Abstract: A turbine blade having a body enclosing a plurality of internal channels for the passage of coolant gas received through an inlet formed in the blade root, including a gas flow separator, configured to separate coolant gas into first and second gas flows. The gas flow separator is configured to separate the first and second gas flows such that the level of contaminants in the first gas flow is lower than the level of contaminants in the second gas flow.

Abstract: A component for a gas turbine engine, comprising: a first wall defining an exterior surface of the component; a second wall, arranged such that a coolant channel is defined by the space between the first and second walls; and a plurality of apertures provided through the first wall to connect the coolant channel to the exterior surface of the component; wherein adjacent at least one aperture the coolant channel comprises a flow modifier, configured to locally change the pressure of the coolant flowing in the coolant channel in the region of the aperture relative to a region of the coolant channel adjacent another aperture.

Abstract: A component for a gas turbine engine, comprising: first and second walls; a coolant channel defined by the space between the first and second walls; and a plurality of ribs extending between the first and second walls, subdividing the coolant channel and configured such that the spaces between the ribs define the direction of flow of coolant through the coolant channel; wherein the ribs are arranged in first and second groups; and the second group of ribs is arranged downstream of the first group of ribs in the direction of the flow of coolant such that the ribs of the second group are aligned with the spaces between the ribs of the first group.

Abstract: A core (300) for an investment casting process in which a component to be cast has an internal passageway, the internal passageway being provided by the core (300), the core (300) comprising: a chimney portion (301); and a core passage (302), the chimney portion (301) extending away from the core passage (302); wherein the chimney portion (301) comprises at least one indent, groove or recess (306).

Abstract: A core for an investment casting process in which a component to be cast has an internal passageway, the internal passageway being provided by the core. A first core passage having a first point and a second point and including no straight path between the first point and the second point; a first core bridge which extends away from the first core passage between the first and second points, and has a first pillar and a second pillar which connect to the first and second points respectively, and a bridge portion which extends between the first and second pillars; wherein the first pillar has a core inlet portion having a thickness at the first point and the second pillar has a thickness at the second point, the thickness of the core inlet portion at the first point being less than the thickness of the second pillar at the second point.

Abstract: A blade has a root portion and elongate portion extending from the root portion to a tip. The elongate portion has an aerofoil-shaped cross section having leading and trailing edges and suction and pressure sides. The tip may include a gutter defining squealer. The squealer has a wall extending from the trailing edge and along a substantial portion of the tip perimeter. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exiting into the gutter. A gallery channel is arranged just behind the gutter and extends from an open end intersecting the main trailing edge cooling channel to a closed end located just behind a trailing edge apogee. Cooling channels extend from the gallery channel and through the squealer wall. The gallery channel diameter is greater at the open end than the closed end.

Abstract: A blade includes a root and an elongate portion extending to a tip, the elongate portion having an aerofoil-shaped cross-section. The aerofoil has leading and trailing edges, and suction and pressure sides. The tip includes a squealer defining a gutter at the tip, the squealer extending from the trailing edge along the entirety of a first of the suction and pressure sides, around the leading edge and partly along a second of the suction and pressure sides leaving a gap between the trailing edge and an end of the wall. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exits into the gutter. The main trailing edge cooling channel includes a bend just downstream of the exit, the exit displaced from a camber line of the blade elongated portion towards the second side.

Abstract: An aerofoil for a gas turbine engine including a pressure wall and a suction wall and defining leading and trailing edge, the walls define a passage into which is supplied a cooling fluid, an array of cooling holes is provided through at least one of the walls to allow the cooling fluid to flow from an interior surface to an exterior surface. The array of holes include two groups, the holes of each group are angled to intersect the holes of the other group and are characterised in that the holes of at least one of the groups includes two or more holes at different angles to one another to vary the porosity of the wall to account for otherwise varying wall temperatures. This arrangement also allows either less coolant mass flow to maintain a constant metal temperature, or a lower metal temperature for a given coolant mass flow.