Abstract: The invention provides a modular system and method of use for the storage of energy subsea. The modular system comprises an energy management system and a rechargeable energy storage system. The energy management system is configured to control a transfer of electrical energy between the rechargeable energy storage system and at least one energy source and/or at least one electrical load.

Abstract: The invention provides a modular system and method of use for the storage of energy subsea. The modular system comprises an energy management system and a rechargeable energy storage system. The energy management system is configured to control a transfer of electrical energy between the rechargeable energy storage system and at least one energy source and/or at least one electrical load.

Abstract: A method of connecting three-dimensional structured meshes to form a conformal mesh, for solutions of flow problems, including: forming an interface by overlaying surfaces of two structured meshes; defining an interface set of mesh points in the interface; merging mesh points in the interface set that are within a predetermined distance of each other and projecting mesh points of one mesh in the interface that are within a predetermined distance of a line of the other mesh; generating an interface layer in the form of an unstructured mesh; and inserting a node at the center of each hexahedra, and producing an unstructured layer of cells between the two structured meshes by joining the nodes to the mesh points of the interface layer.

Abstract: A casing treatment for a fan or compressor stage 10 of a gas turbine engine comprises circumferential grooves 16A, 16B, 16C, 16D and 16E which extend in a series disposed between the leading edges 20 and trailing edges 22 of blades 6 of a fan or compressor stage 10. The grooves 16 vary in depth d in order to optimise the stall margin of the fan or compressor stage 10 while preserving peak efficiency.

Abstract: A method of connecting three-dimensional structured meshes to form a conformal mesh, for solutions of flow problems, including: forming an interface by overlaying surfaces of two structured meshes; defining an interface set of mesh points in the interface; merging mesh points in the interface set that are within a predetermined distance of each other and projecting mesh points of one mesh in the interface that are within a predetermined distance of a line of the other mesh; generating an interface layer in the form of an unstructured mesh; and inserting a node at the centre of each hexahedra, and producing an unstructured layer of cells between the two structured meshes by joining the nodes to the mesh points of the interface layer.

Abstract: A casing treatment for a fan or compressor stage 10 of a gas turbine engine comprises circumferential grooves 16A, 16B, 16C, 16D and 16E which extend in a series disposed between the leading edges 20 and trailing edges 22 of blades 6 of a fan or compressor stage 10. The grooves 16 vary in depth d in order to optimise the stall margin of the fan or compressor stage 10 while preserving peak efficiency.