A hydrostatic seal configured to be disposed between relatively rotatable components includes a seal carrier. The seal also includes a beam extending axially from a forward end to an aft end, the beam cantilevered to the seal carrier at one of the forward end and the aft end, the beam free at the other end. The seal further includes a brush seal operatively coupled to the seal carrier and in contact with the beam.

A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.

A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.

The present disclosure pertains to electric machines such as electric propulsion systems for aircraft that integrated cooling systems, and methods of cooling such an electric machine. Exemplary electric machines include an electric motor that has a stator, a rotor, and a drive shaft operably coupled to the rotor. Exemplary electric machines further include a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, a casing assembly that circumferentially surrounds at least a portion of the electric motor, a casing assembly conduit integrally formed within at least a portion of the casing assembly which defines a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, and a pump or compressor operably coupled to the drive shaft and configured to circulate the cooling fluid through the motor cooling conduit and the casing assembly conduit.

The present disclosure pertains to electric machines such as electric propulsion systems for aircraft that integrated cooling systems, and methods of cooling such an electric machine. Exemplary electric machines include an electric motor that has a stator, a rotor, and a drive shaft operably coupled to the rotor. Exemplary electric machines further include a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, a casing assembly that circumferentially surrounds at least a portion of the electric motor, a casing assembly conduit integrally formed within at least a portion of the casing assembly which defines a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, and a pump or compressor operably coupled to the drive shaft and configured to circulate the cooling fluid through the motor cooling conduit and the casing assembly conduit.

A compressor includes a compressor screen mounted on the outer circumferential surface of a compressor disk or the inner wall of a compressor casing. The compressor screen is positioned between a row of compressor blades and a row of compressor vanes to stabilize airflow by regulating the amount of air flowing in the compressor. The compressor screen is formed of annular plate having openings through which the compressed air flows, arranged in a pattern to smoothly regulate the flow of air. The compressor screen may be variously configured, for example, to facilitate installation or to guide the flow of air using a tapered surface or a directionality of the openings or a flow guide. A gas turbine includes a combustor, a turbine, and a compressor employing the compressor screen.

A compressor includes a compressor screen mounted on the outer circumferential surface of a compressor disk or the inner wall of a compressor casing. The compressor screen is positioned between a row of compressor blades and a row of compressor vanes to stabilize airflow by regulating the amount of air flowing in the compressor. The compressor screen is formed of annular plate having openings through which the compressed air flows, arranged in a pattern to smoothly regulate the flow of air. The compressor screen may be variously configured, for example, to facilitate installation or to guide the flow of air using a tapered surface or a directionality of the openings or a flow guide. A gas turbine includes a combustor, a turbine, and a compressor employing the compressor screen.

A steam turbine (ST) includes a rotor (11) which is rotatable around an axis (Ar), an inner casing (21) surrounding the rotor (11) from an outer peripheral side, an outer casino (30) surrounding the rotor (11) and the inner casing (21) and defining an exhaust chamber between the inner casing (21) and the outer casing (30), the steam being exhausted to the exhaust chamber (30s), and a flow guide (27) which has a tubular shape and is installed on one end portion of the inner casing 21 in an axial direction (Da) in the exhaust chamber (30s) to guide the steam discharged from the rotor (11). The flow guide (27) has a turning surface (RA) which is connected to an outer peripheral surface (27A) and turns a fluid flowing along the outer peripheral surface (27A) toward the other side in the axial direction (Da).

A steam turbine (ST) includes a rotor (11) which is rotatable around an axis (Ar), an inner casing (21) surrounding the rotor (11) from an outer peripheral side, an outer casino (30) surrounding the rotor (11) and the inner casing (21) and defining an exhaust chamber between the inner casing (21) and the outer casing (30), the steam being exhausted to the exhaust chamber (30s), and a flow guide (27) which has a tubular shape and is installed on one end portion of the inner casing 21 in an axial direction (Da) in the exhaust chamber (30s) to guide the steam discharged from the rotor (11). The flow guide (27) has a turning surface (RA) which is connected to an outer peripheral surface (27A) and turns a fluid flowing along the outer peripheral surface (27A) toward the other side in the axial direction (Da).

A control valve for a fluid flow includes: a valve body that defines an inlet and an outlet for the fluid, an obstructer inserted in the valve body, and an actuator system configured for reversibly translating the obstructer between a first position, in which the obstructer allows the passage of the fluid between the inlet and the outlet, and a second position, in which the obstructer prevents the passage of the fluid between the inlet and the outlet; the control valve further includes a turbine rotor housed inside the valve body, wherein the rotor includes a plurality of blades and is configured for continuously rotating under the action of the fluid flowing between the inlet and the outlet, the rotor rotating about an axis of rotation substantially aligned with the direction of translation of the obstructer.