Abstract: A multiple banknote and/or check deposit transaction at a Self-Service Terminal (SST) permits visual customer feedback during the transaction for depicting categories and denominations associated with the transaction. Moreover, an interface rendered with the visual customer feedback permits the customer to review, edit, accept, or abort the transaction.

Abstract: A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer. The first intermediate layer has at least one first elongated through hole, wherein a cooling fluid is flowable through the first elongated through hole.

Abstract: A seal of a turbomachine reduces a leakage flow between a first and second component of the turbomachine. The first component has a first surface and the second component has a second surface, wherein the first component is stiff with regard to a first force exerted perpendicularly thereto and the second component is stiff with regard to a second force exerted perpendicularly thereto. The first surface is opposite the second surface, together defining boundaries of a fluid passage for the leakage flow. The first surface has a first surface riffle. A turbomachine has a seal described above, wherein the turbomachine is a gas turbine engine. A method of manufacturing a first component of a turbomachine with a reduced leakage flow between the first component and a second component of the turbomachine includes fabrication of a first surface riffle, in particular by grinding and/or by electrical discharge machining.

Abstract: A blade system for a gas turbine has a blade device and a further blade device. The blade device has a shroud, an airfoil extending from the shroud along the radial direction, the shroud has at a circumferential end a wedge face having a recess extending with a component along the axial direction, and a damping wire arranged within the recess such that the damping wire is adapted for contacting the shroud and a further wedge face of a further shroud of a further blade device arranged adjacent to the shroud along the circumferential direction. The recess includes an inclining side surface which has a normal, non-parallel with the radial direction, the further wedge face has a plane surface onto which the damping wire is abuttable. A method of manufacturing a blade system includes arranging the further shroud adjacent to the shroud and arranging a damping wire within the recess.

Abstract: A seal of a turbomachine reduces a leakage flow between a first and second component of the turbomachine. The first component has a first surface and the second component has a second surface, wherein the first component is stiff with regard to a first force exerted perpendicularly thereto and the second component is stiff with regard to a second force exerted perpendicularly thereto. The first surface is opposite the second surface, together defining boundaries of a fluid passage for the leakage flow. The first surface has a first surface riffle. A turbomachine has a seal described above, wherein the turbomachine is a gas turbine engine. A method of manufacturing a first component of a turbomachine with a reduced leakage flow between the first component and a second component of the turbomachine includes fabrication of a first surface riffle, in particular by grinding and/or by electrical discharge machining.

Abstract: A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer. The first intermediate layer has at least one first elongated through hole, wherein a cooling fluid is flowable through the first elongated through hole.

Abstract: A multiple banknote and/or check deposit transaction at a Self-Service Terminal (SST) permits visual customer feedback during the transaction for depicting categories and denominations associated with the transaction. Moreover, an interface rendered with the visual customer feedback permits the customer to review, edit, accept, or abort the transaction.

Abstract: The present invention relates to a stator stage (100) for a gas turbine and a method of adjusting a relative position between a vane segment (110) and a centre section (101) of the stator stage. A groove (102) is formed between a first rim (103) and a second rim (104) of a radially outer edge of the centre section, wherein the groove, the first rim and the second rim run along a circumferential direction (131). The vane segment comprises a radially inner shroud (111) from which a protrusion (112) protrudes radially inwards. The protrusion is inserted into the groove. An adjusting pin (120) comprises a first end section (121), a second end section (122) and an eccentric section (123) which runs between the first end section and the second end section.

Abstract: A method and apparatus are provided for the extraction and collection of coelomic fluid of sea stars. The method includes feeding sea stars, one at a time, from storage into the mouth of a longitudinally-moving gripper. The method includes moving the sea stars in a downstream direction by means of the longitudinally-moving gripper. The method includes severing the tip of the arm of the sea star. The method includes allowing the coelomic fluid to drain out of the severed arm of the sea star; The method includes accumulating the drained coelomic fluid. The method includes collecting the accumulated drained coelomic fluid. Finally, the method includes discharging the sea stars from the longitudinally-moving gripper.