Abstract: The present invention relates to multi-domain binding molecules.

Abstract: The present disclosure provides multi-domain molecules comprising, (i) a first binding domain that binds to PD-1, (ii) a second binding domain that binds to CD1a, and optionally, (iii) a half-life extending domain. Such multi-domain molecules are particularly useful in the development of soluble immunotherapeutic reagents for the treatment of autoimmune diseases, such as atopic dermatitis (AD).

Abstract: An airfoil device for a gas turbine has a root section mountable to an airfoil disc and an airfoil element. The root section has a platform at which the airfoil element is arranged. The root section has a cavity surrounded by an inner surface of the platform, a first and a second edge side of the root section. A seal strip is arranged at the inner surface, wherein the first edge side has a recess into which a first end section of the seal strip is arranged. The root section has a supporting lever extending from the second edge side into the cavity. The supporting lever is formed such that a further cavity is formed between the inner surface, the second edge side and the supporting lever, wherein the second end section of the seal strip is arranged inside the further cavity.

Abstract: A gas turbine rotor and blade include a root portion, a platform and airfoil portion arranged along a span direction of the rotor blade, the platform located between the root and airfoil portion. The platform has an upstream and downstream side, side faces which extend from upstream to downstream side, an axial groove in each side face extends perpendicular to the span direction with a minor component of extension in span direction. A radial groove in each side face extends towards the axial groove with a component of extension in span direction and a component of extension perpendicular to the span direction. The radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove. The second end is located a distance from the axial groove forming a groove free section between the second end and axial groove.

Abstract: A turbomachine rotor blade has a firtree shaped root, to be secured in a rotor disc rotatable around a rotor axis. In a plane perpendicular to the rotor axis, the root has a first, second, and third root lobe with a first, second, and third root contact face. Each of the first, second, and third root contact face is angled relative to a radial root bottom axis with a first, second, and third root angle, respectively. The first root angle is smaller than the second and the second root angle is substantially equal to the third. A turbomachine rotor disc has a firtree shaped slot having a first, second, and third slot angle, the first slot angle being smaller than the second and the second slot angle being substantially equal to the third. A gas turbine engine has the turbomachine rotor herein.

Abstract: An airfoil device for a gas turbine has a root section mountable to an airfoil disc and an airfoil element. The root section has a platform at which the airfoil element is arranged. The root section has a cavity surrounded by an inner surface of the platform, a first and a second edge side of the root section. A seal strip is arranged at the inner surface, wherein the first edge side has a recess into which a first end section of the seal strip is arranged. The root section has a supporting lever extending from the second edge side into the cavity. The supporting lever is formed such that a further cavity is formed between the inner surface, the second edge side and the supporting lever, wherein the second end section of the seal strip is arranged inside the further cavity.

Abstract: A gas turbine rotor and blade include a root portion, a platform and airfoil portion arranged along a span direction of the rotor blade, the platform located between the root and airfoil portion. The platform has an upstream and downstream side, side faces which extend from upstream to downstream side, an axial groove in each side face extends perpendicular to the span direction with a minor component of extension in span direction. A radial groove in each side face extends towards the axial groove with a component of extension in span direction and a component of extension perpendicular to the span direction. The radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove. The second end is located a distance from the axial groove forming a groove free section between the second end and axial groove.

Abstract: A turbomachine rotor blade has a firtree shaped root, to be secured in a rotor disc rotatable around a rotor axis. In a plane perpendicular to the rotor axis, the root has a first, second, and third root lobe with a first, second, and third root contact face. Each of the first, second, and third root contact face is angled relative to a radial root bottom axis with a first, second, and third root angle, respectively. The first root angle is smaller than the second and the second root angle is substantially equal to the third. A turbomachine rotor disc has a firtree shaped slot having a first, second, and third slot angle, the first slot angle being smaller than the second and the second slot angle being substantially equal to the third. A gas turbine engine has the turbomachine rotor herein.