Abstract: An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.

Abstract: An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.

Abstract: A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis.

Abstract: A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.

Abstract: A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.

Abstract: A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, and in turn radial position of the shroud supported therefrom.

Abstract: A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, and in turn radial position of the shroud supported therefrom.

Abstract: A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.