Abstract: A nozzle tip includes a nozzle tip body defining an upstream surface and an opposed downstream surface. An outlet orifice is defined through the nozzle tip body for fluid communication from a space upstream of the upstream surface to a space downstream of the downstream surface. The outlet orifice includes a cylindrical outlet portion defining an outlet axis, and a tapered inlet portion upstream of the outlet portion. The tapered inlet portion converges down towards the outlet axis in a direction from the upstream surface toward the downstream surface.

Abstract: A dynamic seal assembly is disclosed for use in a valve having an upstream pressure side and a downstream pressure side, the dynamic seal assembly including an annular seal member having a generally C-shaped cross-section and including opposed upstream and downstream legs defining an internal cavity with an opening facing toward the upstream pressure side of the valve, wherein the upstream leg has a radial length that is greater than a radial length of the downstream leg and includes a retaining foot that extends angularly away from the upstream leg in an upstream direction at an angle of between about 0° and 90°, and a metallic spring is disposed within the internal cavity of the seal member for providing a constant sealing force to the seal member.

Abstract: A fluid nozzle includes, a body having an annular cavity that extends out one axial end of the fluid nozzle. At least one port fluidically connects to an annular chamber of the annular cavity and the annular cavity is defined between a radially inner surface of the body and a radially outer surface of the body. A first portion of the radially outer surface has a first radial dimension smaller than a greatest radial dimension of the at least one port and a second portion of the radially outer surface further from the annular chamber than the first portion has a second radial dimension greater than the first radial dimension and so forth.

Abstract: A combustion system for a gas turbine engine includes a housing defining a pressure vessel. A master injector is mounted to the housing for injecting fuel along a central axis defined through the pressure vessel. A plurality of slave injectors is included. Each slave injector is disposed radially outward of and substantially parallel to the master injector for injecting fuel and air in an injection plume radially outward of fuel injected through the master injector. The master injector and slave injectors are configured and adapted so the injection plume of the master injector intersects with the injection plumes of the slave injectors. The slave injectors can be staged for reduced power operation.

Abstract: A combustion system for a gas turbine engine includes a housing defining a pressure vessel. A master injector is mounted to the housing for injecting fuel along a central axis defined through the pressure vessel. A plurality of slave injectors is included. Each slave injector is disposed radially outward of and substantially parallel to the master injector for injecting fuel and air in an injection plume radially outward of fuel injected through the master injector. The master injector and slave injectors are configured and adapted so the injection plume of the master injector intersects with the injection plumes of the slave injectors. The slave injectors can be staged for reduced power operation.