Abstract: A flow control system (24) comprises a fluidic control device (26) having a main fluid path (34, 38) for a flow of fluid through the device, and a control fluid path (30) for a control flow of fluid through the device (24). At least part of the control fluid path coincides with at least part of the main fluid path (34, 38) to control the flow of fluid out of the fluidic control device (24). A valve (28) is associated with the control fluid path. The value (28) is movable between an open condition to allow fluid to flow along the control fluid path to effect the aforesaid control of the fluid flow out of the fluidic control device, and a closed condition to inhibit or prevent fluid flow along the control fluid path (30).

Abstract: It is known there is ingestion of hot gas flow 35 from an annular flow 36 in gas turbine engines. This flow 35 is prevented from attaching to the disc by coolant flow 32 passing through gaps in lock plates 28, 29 by creation of a barrier layer. In order to regulate and enhance this effect spacer protrusions 31 are provided between ends of lock plates 28, 29. In such circumstances the gap 30 is controlled and therefore the rate of leakage flow 32 regulated for best cooling effect. This cooling effect and cooling flow 32 can be further enhanced by providing chutes 39 for presentation of the coolant flow 32.

Abstract: In gas turbine engines it is found that leaked coolant flow through the lock plates 28, 29, 50, 60 can be used to insulate the rotor surfaces 33, 34 from the effects of hot gas ingestion. In order to enhance this effect chutes 39, 59, 69 are provided to guide the leakage airflow adjacent to the lock plate such that the ingested hot gas flow is prevented from coming into contact with the surfaces of the lock plate and other cavity surfaces 33, 34 to improve cooling effect. The chutes 39, 59, 69 create apertures 40, 53 which can be of dimensions to ensure that there is a high ratio between width and depth of the coolant flow 32 again facilitating heat exchange and cooling efficiency.

Abstract: A seal arrangement 32 between a turbine shroud seal segments 38,40 in a gas turbine engine. The arrangement 32 comprises facing slots 34, 36 provided respectively in the segments 38,40 with offset spaces 42, 44 provided between the segments 38,40. A strip 46 is cemented into the slot 36 such that the flow path 50 passes through the space 42, around the free end of the strip 46, and out through the offset space 44, thereby providing a longer flow path.