Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the airfoil having a fillet at the trailing edge proximate the at least one endwall.

A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.

An electric blower includes: an electric motor portion including a rotation shaft; a centrifugal impeller; and a heat dissipating portion connecting the centrifugal impeller and the rotation shaft. A boss portion of the centrifugal impeller is provided with a first hole extending in an extending direction of the rotation shaft. The heat dissipating portion includes a first portion connected to an inner circumferential surface of the first hole, and a second portion connected to the first portion in the extending direction and located outside the first hole. A length of the heat dissipating portion in the extending direction is longer than a length of the first hole in the extending direction.

An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.

Systems and methods axe disclosed herein that generally involve a double pinch criterion for optimization of regenerative Rankine cycles. In some embodiments, operating variables such as bleed extraction pressure and bleed flow rate are selected such that a double pinch is obtained in a feedwater heater, thereby improving the efficiency of the Rankine cycle. In particular, a first pinch point is obtained at the onset of condensation of the bleed and a second pinch point is obtained at the exit of the bleed from the feedwater heater. The minimal approach temperature at the first pinch point can be approximately equal to the minimal approach temperature at the second pinch point. Systems that employ regenerative Rankine cycles, methods of operating such systems, and methods of optimizing the operation of such systems are disclosed herein in connection with the double pinch criterion.

An airfoil includes an airfoil wall that defines a leading end, a trailing end, a first side, and a second side. Radially-extending ribs partition the interior cavity of the airfoil into first and second cooling channels and a radial cooling passage that is situated between the first and second cooling channels. The cooling channels extend to respective first and second channel ends. A turn channel connects the first and second channel ends. The turn channel splits at the first channel end into first and second channel legs such that there is a region between the first and second channel legs. The channels legs merge at the second channel end. The radial cooling passage extends through the region between the first and second channel legs.

A gas turbine engine including an engine core and a cooling air system is disclosed herein. The cooling air system is fluidly coupled between a compressor section of the engine core and a turbine section of the engine core to conduct pressurized air from the compressor section to the turbine section to cool components of the turbine section.

A turbine includes an inner casing to which at least a stator vane of a turbine section is mountable, and an outer casing arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing. The outer cooling channel includes a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel. The cooling channel includes a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine. The fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel includes a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine.

Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.

A gas turbine engine defines a working air flowpath and includes an electrical system having an electric machine coupled to the rotary component at least partially inward of the working air flowpath along the radial direction and an electric bus electrically coupled to the electric machine. The electric bus includes an electric line extending through the working air flowpath within or downstream of a turbine section. The engine further includes a cooling system including a cooling fluid supply line and a cooling fluid return line, wherein a portion of the electric line extending though the working air flowpath is substantially embedded within the cooling fluid supply line, and wherein a portion of the cooling fluid supply line extending though the working air flowpath is substantially embedded within the cooling fluid return line.