Abstract: A stage for a compressor or a turbine in a turbine engine can include an annular row of airfoils radially extending from corresponding platforms, where each platform can include a fore edge and aft edge and each airfoil can include a leading edge and trailing edge. At least one of the platforms can have a scalloped flow surface including a bulge and a trough.

Abstract: A stage for a compressor or a turbine in a turbine engine can include an annular row of airfoils radially extending from corresponding platforms, where each platform can include a fore edge and aft edge and each airfoil can include a leading edge and trailing edge. At least one of the platforms can have a scalloped flow surface including a bulge and a trough.

Abstract: A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.

Abstract: A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.

Abstract: A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.