Abstract: The present disclosure relates to novel compounds for use in therapeutic treatment of a disease associated with peptidylarginine deiminases (PADs), such as peptidylarginine deiminase type 4 (PAD4). The present disclosure also relates to processes and intermediates for the preparation of such compounds, methods of using such compounds and pharmaceutical compositions comprising the compounds described herein.

Abstract: The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.

Abstract: Methods and apparatuses for film cooling of one or more turbine components are provided. A cooling gas flow passage provides a cooling gas to an turbine component with the hot gas path of a turbine. The cooling gas flow passage includes at least one feed aperture operable to receive cooling gas from at least one cooling gas compartment associated with a turbine component. The cooling gas flow passage also includes at least one slot with a converging portion having a first opening and a second opening, where the first opening receives the cooling gas from the feed aperture, and the second opening provides the cooling gas to at least a portion of an outer surface of the turbine component.

Abstract: A bowed airfoil is provided which includes a plurality of passages disposed between a pressure side wall and a suction side wall. The pressure and suction side walls extend widthwise between a leading edge and a trailing edge, and spanwise between inner and outer platforms. Passages extend spanwise between the inner and outer platforms. Ribs, each having a rib end, separate adjacent passages. Passage turns, each having an end wall, connect the passages. The end wall of each passage turn acutely converges with one of the side walls, and a first fillet extends between the acutely converging side wall and end wall. According to one embodiment, each rib end acutely converges with the other of the side walls, and a second fillet extends between the acutely converging side wall and rib end.

Abstract: The wall of a hollow airfoil for a gas turbine engine includes a film cooling slot therein elongated in the longitudinal direction and having a base within the wall and an outlet at the external surface of the airfoil. A plurality of metering passages extend from inlets at the internal surface of the wall and intersect the slot near its base. The metering passages are angled to direct a metered flow of coolant fluid at a sharp angle against a surface of the slot to cause turbulence and diffusion of the coolant fluid within the slot in order that the coolant fluid fill the entire slot. The coolant fluid thereupon exits the slot as a thin film over the surface of the airfoil downstream of the slot outlet along the full length of the slot.

Abstract: The wall of a hollow turbine airfoil has a longitudinally extending coolant outlet slot in its external surface which intersects, along its length, a longitudinally extending cylindrical channel within the wall. Metering passages extend from the inside surface of the airfoil wall to the cylindrical channel and direct a metered amount of coolant into the channel in a manner which results in a swirling motion being imparted to the fluid as the fluid diffuses within the channel. The coolant is thereupon ejected from the channel through the slot in the external surface as a film on the external surface of the airfoil along the length of the slot. The swirling of the fluid within the cylindrical channel helps diffuse the fluid such that the outlet slot becomes completely filled with coolant, whereby a film of coolant is created on the airfoil surface downstream of the slot over the full length of the slot.