A turbine impeller includes: a hub portion coupled to an end of a rotational shaft; a plurality of main blades disposed at intervals on a peripheral surface of the hub portion; and a short blade disposed between two adjacent main blades among the plurality of main blades. An inter-blade flow channel is formed between the two adjacent main blades so that a fluid flows through the inter-blade flow channel from an outer side toward an inner side of the turbine impeller in a radial direction. In a meridional plane, a hub-side end of a leading edge of the short blade is disposed on an inner side, in the radial direction, of a hub-side end of a leading edge of the main blade.

A centrifugal compressor includes: a rotational shaft; a main casing surrounding at least a part of the rotational shaft, the main casing having an inlet and an outlet separated from each other in an axial direction of the rotational shaft and an annular space surrounding a section of the rotational shaft at a side of the inlet and communicating with the inlet; at least one impeller disposed in a fixed state to the rotational shaft inside the main casing; a flow guide member disposed inside the annular space and extending along the axial direction of the rotational shaft; a plurality of injection holes disposed along the flow guide member and separated from one another along the axial direction of the rotational shaft; and a flow path which extends inside the annular space and through which a cleaning fluid to be supplied to the plurality of injection holes is capable of flowing.

A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction.

A turbine wheel for a turbine of an exhaust gas turbocharger. The turbine wheel has a base body comprising a back wall and a plurality of turbine blades, connected to the base body, which each comprise a leading edge. The leading edges are designed to be wave shaped.

A variable guide vane control system comprises an actuator and a rolling contact joint. The joint includes a drive ring rotatable about a drive axis and at least one roller rotatable about a roller axis parallel to the drive axis and drivingly connectable to a vane. A first flexible member and a second flexible member connect the drive ring and the roller to one another. The first flexible member and the second flexible member are respectively tensioned when the drive ring rotates about the drive axis in a first direction and in a second direction opposite the first direction.

A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the compressor, combustion section, turbine, and the exhaust section are in fluid communication. The inlet duct is positioned upstream of the compressor and defines an inlet portion of the air flowpath. The inlet duct is generally radially oriented. A variable inlet guide vane extends at least partially through the inlet duct.

A radial inflow turbine includes a turbine wheel having a blade, in which a hub-side end of a leading edge of the blade is located radially inward relative to a shroud-side end of the leading edge, and a housing having a scroll part and a bend part deflecting a flow of a working fluid flowing radially inward from the scroll part, along an axial direction. The turbine wheel has at least one through hole bypassing the blade.

An engine comprises an air inlet configured to receive air; a first heat exchanger arrangement arranged downstream of the air inlet, having a first heat exchanger inlet configured to receive at least a portion of the air received by the air inlet, and being configured to cool the air received by the first heat exchanger inlet; one or more turbomachinery components arranged downstream of an outlet of the first heat exchanger arrangement, and being configured to receive air; a first flow path arranged to extend from the air inlet to the first heat exchanger inlet; a second flow path arranged to extend from the air inlet to the one or more turbomachinery components, the second flow path bypassing the first heat exchanger inlet; and a flow control arrangement comprising a first portion and a second portion, the first and second portions being configured to be movable relative to one another to selectively obstruct the second flow path.

A combustion chamber arrangement comprises an annular combustion chamber, a plurality of circumferentially arranged vanes and a radially inner sealing ring. The vanes are arranged at the axially downstream end of the annular combustion chamber. Each of the vanes comprises an aerofoil extending radially between a radially inner platform and a radially outer platform. The radially inner sealing ring forms a seal between a downstream end of a radially inner annular wall structure of the combustion chamber and the radially inner platforms of the vanes. A portion of the axial length of the radially inner sealing ring comprises a radially inner wall and a radially outer wall spaced radially from the radially inner wall to define a chamber. The radially inner wall has apertures to supply coolant into the chamber and the radially outer wall has effusion cooling apertures to supply coolant onto the surface of the radially outer wall.

An intake structure of a compressor includes an intake duct forming an intake port opening in a direction away from a central axis of the compressor and a bellmouth forming an annular channel expanding from an inlet of the compressor toward an inner space of the intake duct. The bellmouth includes a plurality of struts connecting an inner casing positioned inside the annular channel and an outer casing positioned outside the annular channel. At least one of a plurality of transverse struts, of the plurality of struts, which are located on both sides of a center plane passing through the central axis of the compressor and the center of the intake port has a trailing edge positioned on a virtual plane passing through the central axis of the compressor and a leading edge positioned on a side of the intake port with respect to the virtual plane.