Abstract: A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform. The airfoil body includes opposed pressure and suction sidewalls extending between a leading edge and a trailing edge of the airfoil body. The airfoil body includes a first trailing edge fillet blending into the inner platform at a trailing edge of the airfoil body.

Abstract: A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform. The airfoil body includes opposed pressure and suction sidewalls extending between a leading edge and a trailing edge of the airfoil body. The airfoil body includes a first trailing edge fillet blending into the inner platform at a trailing edge of the airfoil body.

Abstract: The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.

Abstract: The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.

Abstract: A turbomachine nozzle segment includes a vane having a first end extending to a second end through an airfoil portion. An outer member is positioned at the first end of the vane. The outer member includes a mounting element configured and disposed to secure the turbomachine nozzle segment to a turbomachine. An inner member is positioned at the second end of the vane. The inner member includes an upstream section and a downstream section. An upstream diaphragm member extends substantially radially outwardly from the inner member at the upstream section, and a downstream diaphragm member extends substantially radially outwardly from the inner member at the downstream section. Each of the upstream diaphragm member and down stream member includes an outer surface and an inner surface. One of the outer surface and inner surface of each of the upstream diaphragm member and downstream diaphragm member includes a cartridge mounting member.

Abstract: A jet pump for a nuclear reactor includes a riser and an inlet mixer having a set of nozzles and a mixing section for receiving coolant flow from the nozzles and suction flow from an annular space between the reactor vessel and the shroud core. To minimize or eliminate electrostatic deposition of charged particulates carried by the coolant on interior wall surface of the inlet-mixer of the jet pump, and also to inhibit stress corrosion cracking, the interior wall surfaces of the nozzles and mixing section are coated with a ceramic oxide such as TiO2 and Ta2O5 to thicknesses of about 0.5-1.5 microns.

Abstract: A jet pump for a nuclear reactor includes a riser and an inlet mixer having a set of nozzles and a mixing section for receiving coolant flow from the nozzles and suction flow from an annular space between the reactor vessel and the shroud core. To minimize or eliminate electrostatic deposition of charged particulates carried by the coolant on interior wall surface of the inlet-mixer of the jet pump, and also to inhibit stress corrosion cracking, the interior wall surfaces of the nozzles and mixing section are coated with a ceramic oxide such as TiO2 and Ta2O5 to thicknesses of about 0.5-1.5 microns.