Abstract: An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.

Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

Abstract: A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.

Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.

Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.

Abstract: A combustor for use in a gas turbine engine including: a radially inward heat shield panel; and a radially outward heat shield panel located radially outward of the radially inward heat shield panel, the radially inward heat shield panel and the radially outward heat shield panel being in a facing spaced relationship defining a combustion chamber therebetween, wherein at least one of the radially inward heat shield panel and the radially outward heat shield panel has a non-axisymmetric shape.

Abstract: A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.

Abstract: An inlet guide vane is disclosed. The inlet guide vane includes a strut and a flap having a radial length in a radial direction. The flap includes a radially inner portion having a first angular orientation with respect to the strut, a radially outer portion having a second angular orientation with respect to the strut, and a transition portion intermediate the radially inner portion and the radially outer portion, wherein the first angular orientation transitions to the second angular orientation along a portion of the radial length.

Abstract: An inlet guide vane is disclosed. The inlet guide vane includes a strut and a flap having a radial length in a radial direction. The flap includes a radially inner portion having a first angular orientation with respect to the strut, a radially outer portion having a second angular orientation with respect to the strut, and a transition portion intermediate the radially inner portion and the radially outer portion, wherein the first angular orientation transitions to the second angular orientation along a portion of the radial length.

Abstract: A technique that improves large-eddy simulation consists in replacing the instantaneous sub-grid scale eddy-viscosity (such as the dynamic Smagorinsky model eddy-viscosity) in the near-wall region with an eddy-viscosity computed from Reynolds Averaged Navier-Stokes eddy-viscosity and corrected dynamically using the resolved turbulent stress. The near-wall eddy-viscosity formulation is applied either with a wall stress model on coarse grids that do not resolve the wall or with wall-resolved grids coarsened in the wall-parallel directions. Reynolds averaged Navier-Stokes eddy-viscosity is computed either from a look-up table or from a simultaneous solution of a Reynolds Averaged Navier-Stokes turbulence model.

Abstract: A technique that improves large-eddy simulation consists in replacing the instantaneous sub-grid scale eddy-viscosity (such as the dynamic Smagorinsky model eddy-viscosity) in the near-wall region with an eddy-viscosity computed from Reynolds Averaged Navier-Stokes eddy-viscosity and corrected dynamically using the resolved turbulent stress. The near-wall eddy-viscosity formulation is applied either with a wall stress model on coarse grids that do not resolve the wall or with wall-resolved grids coarsened in the wall-parallel directions. Reynolds averaged Navier-Stokes eddy-viscosity is computed either from a look-up table or from a simultaneous solution of a Reynolds Averaged Navier-Stokes turbulence model.