An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a first end of the wiper arm, and an output shaft coupled to a second end of the wiper arm. The wiper blade includes a fluid dispensing system including nozzles, a fluid control unit, fluid lines, fluid source, and a user interface. The wiper blade with the fluid dispensing system is configured to dispense a variety of fluids directly from the wiper blade onto the windshield of an aircraft.

An anti-icing system is provided for an inlet lip annularly extending about a nacelle of an aircraft engine assembly. The anti-icing system includes an interior wall structure at least partially forming an annular anti-icing chamber with the inlet lip and an annular shield with a first end coupled to the interior wall structure and a second end extending into the annular anti-icing chamber. The annular shield divides the annular anti-icing chamber into first and second chamber portions fluidly coupled together by a passage formed between the second end and the internal surface of the inlet lip. The anti-icing system further includes a nozzle at an inwardly radial position relative to the first end of the annular shield such that the heated air exits the nozzle into the first chamber portion in which the annular shield blocks direct impingement on the internal surface of the inlet lip.

The supercritical CO.sub.2 turbine in an embodiment includes: a rotary body; a stationary body housing the rotary body inside; and a turbine stage including a stator blade cascade in which a plurality of stator blades are supported inside the stationary body, and a rotor blade cascade in which a plurality of rotor blades are supported by the rotary body inside the stationary body, in which a supercritical CO.sub.2 working medium is introduced into the inside of the stationary body and flows via the turbine stage in an axial direction of the rotary body to thereby rotate the rotary body. Here, a thermal conductivity k1 and a specific heat c1 of a material constituting the rotary body and a thermal conductivity k2 and a specific heat c2 of a material constituting the stationary body satisfy a relationship represented by the following formula (A).

k1/c1≤k2/c2  formula (A)

A turbine-cooling system of a gas turbine system includes a first intra-vane flow passage defined in a first stator vane so as to penetrate the first stator vane in a radial direction, a second intra-vane flow passage defined in a second stator vane so as to penetrate the second stator vane in the radial direction, an intra-rotation-shaft flow passage connecting the first intra-vane flow passage and the second intra-vane flow passage in a rotation shaft, an extra-turbine flow passage connecting the first intra-vane flow passage and the second intra-vane flow passage, a boost compressor configured to make cooling air flow sequentially through the first intra-vane flow passage, the intra-rotation-shaft flow passage, the second intra-vane flow passage, and the extra-turbine flow passage, and a cooling unit configured to cool the cooling air.

A turbine-cooling system of a gas turbine system includes a first intra-vane flow passage defined in a first stator vane so as to penetrate the first stator vane in a radial direction, a second intra-vane flow passage defined in a second stator vane so as to penetrate the second stator vane in the radial direction, an intra-rotation-shaft flow passage connecting the first intra-vane flow passage and the second intra-vane flow passage in a rotation shaft, an extra-turbine flow passage connecting the first intra-vane flow passage and the second intra-vane flow passage, a boost compressor configured to make cooling air flow sequentially through the first intra-vane flow passage, the intra-rotation-shaft flow passage, the second intra-vane flow passage, and the extra-turbine flow passage, and a cooling unit configured to cool the cooling air.

A turbine wheel (100) for a turbocharger includes a hub (110) and blades (120). The hub includes a primary outer surface (116), a back wall surface (115), a peripheral edge (119) extending between the primary outer surface and the back wall surface, and a central axis (111). The hub has a back wall thickness measured parallel to the central axis from the primary outer surface to the back wall surface. The blades (120) extend from the primary outer surface of the hub and are integrally formed with the hub by casting. Each blade has a blade thickness measured tangential to the central axis between opposed surfaces of the blade. A maximum diameter of the peripheral edge is 60 mm or more. Over a majority of a radially outer region (117), a thickness ratio of the blade thickness to the back wall thickness varies by 25% or less. The radially outer region extends from the peripheral edge to a 25% meridional.

A turbine wheel (100) for a turbocharger includes a hub (110) and blades (120). The hub includes a primary outer surface (116), a back wall surface (115), a peripheral edge (119) extending between the primary outer surface and the back wall surface, and a central axis (111). The hub has a back wall thickness measured parallel to the central axis from the primary outer surface to the back wall surface. The blades (120) extend from the primary outer surface of the hub and are integrally formed with the hub by casting. Each blade has a blade thickness measured tangential to the central axis between opposed surfaces of the blade. A maximum diameter of the peripheral edge is 60 mm or more. Over a majority of a radially outer region (117), a thickness ratio of the blade thickness to the back wall thickness varies by 25% or less. The radially outer region extends from the peripheral edge to a 25% meridional.

A system and method for supplying compressed air from an auxiliary power unit to a main engine starter motor. The inlet guide vanes are controlled using either first or second inlet guide vane control logic and the surge control valve is controlled using either first or second surge control valve control logic. When the first inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand signal, when the second inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand schedule, when the first surge control valve logic is used, the surge control valve can be commanded to repeatedly move to only a fully-closed position and a fully-open position, and when the second surge control valve logic is used, the surge control valve can be commanded to the fully-closed position only when maximum flow is commanded.

A waste heat recovery system including a drive unit, the drive unit having a drive shaft, a compressor, the compressor operably coupled to the drive shaft, wherein operation of the drive unit drives the compressor, and a waste heat recovery cycle, the waste heat recovery cycle coupled to the drive unit and the compressor, wherein a waste heat of the drive unit powers the waste heat recovery cycle, such that the waste heat recovery cycle transmits a mechanical power to the compressor, is provided. Furthermore, an associated method is also provided.

A waste heat recovery system including a drive unit, the drive unit having a drive shaft, a compressor, the compressor operably coupled to the drive shaft, wherein operation of the drive unit drives the compressor, and a waste heat recovery cycle, the waste heat recovery cycle coupled to the drive unit and the compressor, wherein a waste heat of the drive unit powers the waste heat recovery cycle, such that the waste heat recovery cycle transmits a mechanical power to the compressor, is provided. Furthermore, an associated method is also provided.