Abstract: A gas turbine engine valve assembly having an oil shut-off valve and a compensating valve fluidly connected thereto. The compensating valve, in a first position, restricts access to a pressure-reducing oil flow path leading to an oil reservoir, and in a second position, provides access to the pressure-reducing oil flow path. The pressure-reducing oil flow path is defined by fluid flow between housing apertures, a laminar hole and an orifice. The valve assembly is operable between a first configuration, wherein the oil shut-off valve is in a fluid transfer position and a piston of the compensating valve is in a closed position to direct oil toward the engine component, and a second configuration, wherein the oil shut-off valve is in the shut-off position and the piston is in a open position to direct oil toward the oil reservoir via the pressure-reducing oil flow path.

Abstract: A gas turbine engine valve assembly having an oil shut-off valve and a compensating valve fluidly connected thereto. The compensating valve, in a first position, restricts access to a pressure-reducing oil flow path leading to an oil reservoir, and in a second position, provides access to the pressure-reducing oil flow path. The pressure-reducing oil flow path is defined by fluid flow between housing apertures, a laminar hole and an orifice. The valve assembly is operable between a first configuration, wherein the oil shut-off valve is in a fluid transfer position and a piston of the compensating valve is in a closed position to direct oil toward the engine component, and a second configuration, wherein the oil shut-off valve is in the shut-off position and the piston is in a open position to direct oil toward the oil reservoir via the pressure-reducing oil flow path.

Abstract: A gas turbine engine valve assembly having an oil shut-off valve and a compensating valve fluidly connected thereto. The compensating valve, in a first position, restricts access to a pressure-reducing oil flow path leading to an oil reservoir, and in a second position, provides access to the pressure-reducing oil flow path. The pressure-reducing oil flow path is defined by fluid flow between housing apertures, a laminar hole and an orifice. The valve assembly is operable between a first configuration, wherein the oil shut-off valve is in a fluid transfer position and a piston of the compensating valve is in a closed position to direct oil toward the engine component, and a second configuration, wherein the oil shut-off valve is in the shut-off position and the piston is in a open position to direct oil toward the oil reservoir via the pressure-reducing oil flow path.

Abstract: A gas turbine engine valve assembly having an oil shut-off valve and a compensating valve fluidly connected thereto. The compensating valve, in a first position, restricts access to a pressure-reducing oil flow path leading to an oil reservoir, and in a second position, provides access to the pressure-reducing oil flow path. The pressure-reducing oil flow path is defined by fluid flow between housing apertures, a laminar hole and an orifice. The valve assembly is operable between a first configuration, wherein the oil shut-off valve is in a fluid transfer position and a piston of the compensating valve is in a closed position to direct oil toward the engine component, and a second configuration, wherein the oil shut-off valve is in the shut-off position and the piston is in a open position to direct oil toward the oil reservoir via the pressure-reducing oil flow path.

Abstract: A damping system for a gas turbine engine comprises a bearing mounted to a rotor shaft and a support connected to an outer race of the bearing. The support has a wall secured to a casing of the gas turbine engine at a connection portion. The wall has a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft. A cavity is defined in the first surface by a narrowing of a thickness of the wall. The cavity contains a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft. An abutment is provided to limit an amplitude of the elastic deformation of the wall.

Abstract: A damping system for a gas turbine engine comprises a bearing mounted to a rotor shaft and a support connected to an outer race of the bearing. The support has a wall secured to a casing of the gas turbine engine at a connection portion. The wall has a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft. A cavity is defined in the first surface by a narrowing of a thickness of the wall. The cavity contains a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft. An abutment is provided to limit an amplitude of the elastic deformation of the wall.