Abstract: This application discloses anti-CCR7 antibodies, antigen binding fragments thereof, and antibody drug conjugates of said antibodies or antigen binding fragments. The invention also relates to methods of treating or preventing cancer using the antibodies, antigen binding fragments, and antibody drug conjugates. Also disclosed herein are methods of making the antibodies, antigen binding fragments, and antibody drug conjugates, and methods of using the antibodies and antigen binding fragments as diagnostic reagents.

Abstract: A system for delivering an implant device to a vascular site in a patient a delivery pusher apparatus, an implant device detachably connected to the delivery pusher apparatus by a tether having a distal end connected to a proximal end of the implant device, wherein the tether is substantially non-tensioned when connecting the implant device to the delivery pusher, and an electrical heating element configured coaxially around at least a portion of the tether, wherein heat generated by the heating element severs the tether at a point near the proximal end of the implant device.

Abstract: A turbine airfoil including an airfoil body is disclosed. The airfoil includes a leading edge, a trailing edge, an exterior surface including a suction side extending from the leading edge to the trailing edge and a pressure side extending from the leading edge to a trailing end. The pressure side is located opposite to the suction side on the airfoil body. The complete pressure side of the exterior surface is coated by a thermal barrier coating with a thickness decreasing towards the trailing end.

Abstract: A turbine blade assembly, which can be used for a gas turbine is provided. The turbine blade assembly includes turbine blades with platforms, gaps between the platforms of adjacent turbine blades and seals. Each seal covers the gap between the platforms of two adjacent turbine blades wherein the platforms are provided with slots extending in the downstream flow direction. The turbine blades have root cavities, wherein the seal covers at least the whole length of the root cavities of two adjacent turbine blades. The seal is formed from a strip and the seal is placed in two opposed slots formed in each of the platforms of two adjacent turbine blades and open towards the respective downstream ends.

Abstract: A turbine airfoil including an airfoil body is disclosed. The airfoil includes a leading edge, a trailing edge, an exterior surface including a suction side extending from the leading edge to the trailing edge and a pressure side extending from the leading edge to a trailing end. The pressure side is located opposite to the suction side on the airfoil body. The complete pressure side of the exterior surface is coated by a thermal barrier coating with a thickness decreasing towards the trailing end.

Abstract: A turbine blade assembly, in particular of a gas turbine, is provided. The turbine blade assembly includes a turbine disc with rotor blades inserted into notches of the turbine disc and locking plates that are placed inside circular grooves with rims in the turbine disc and in the rotor blade. The edges of the locking plates that are oriented towards the center of the turbine disc are castellated by providing teeth and accordingly a part of the rim of the circular groove of the turbine disc is also castellated by providing gaps and whereby the gaps of the rim match the teeth of the locking plates. The locking plates have a spring-back force to provide both locking and sealing capabilities during engine operation.

Abstract: A turbine blade assembly, which can be used for a gas turbine is provided. The turbine blade assembly includes turbine blades with platforms, gaps between the platforms of adjacent turbine blades and seals. Each seal covers the gap between the platforms of two adjacent turbine blades wherein the platforms are provided with slots extending in the downstream flow direction. The turbine blades have root cavities, wherein the seal covers at least the whole length of the root cavities of two adjacent turbine blades. The seal is formed from a strip and the seal is placed in two opposed slots formed in each of the platforms of two adjacent turbine blades and open towards the respective downstream ends.

Abstract: A turbine blade assembly, in particular of a gas turbine, is provided. The turbine blade assembly includes a turbine disc with rotor blades inserted into notches of the turbine disc and locking plates that are placed inside circular grooves with rims in the turbine disc and in the rotor blade. The edges of the locking plates that are oriented towards the center of the turbine disc are castellated by providing teeth and accordingly a part of the rim of the circular groove of the turbine disc is also castellated by providing gaps and whereby the gaps of the rim match the teeth of the locking plates. The locking plates have a spring-back force to provide both locking and sealing capabilities during engine operation.

Abstract: An anatomical musculoskeletal therapeutic knee sleeve support especially adapted to be placed over the knee to provide support for the muscles and skeletal structure of the knee during physical activity, particularly sports activity. The sleeve comprises a single panel of flexible resilient material cut and joined in such a manner that there is a stitched seam at the upper half of the sleeve on one side of the knee posterior to the side of the knee and another stitched seam at the lower half of the sleeve on the other side of the knee posterior of the side of the knee and an open horizontal aperture at the rear flexure point of the knee between central points of the stitched seams.