A nozzle segment for a gas turbine engine includes an arcuate outer vane platform segment. An arcuate inner vane platform segment spaced from the arcuate outer vane platform segment. A multiple of airfoils between the arcuate inner vane platform segment and the arcuate outer vane platform segment, the arcuate outer vane platform segment includes a scallop slot and a seal that seals the scallop slot.

A blade includes an airfoil, a stationary portion coupled to a radially inner end of the airfoil, and a leakage flow guide vane assembly coupled to the stationary portion. The leakage flow guide vane assembly includes a plurality of passages defined therein. The passages are oriented to induce a swirl velocity to a working fluid flowing through the passages.

A liner assembly includes a core and a septum coupled to the core. The liner assembly also includes a facesheet coupled to the septum. The facesheet includes a plurality of slots defined therethrough. Each slot of the plurality of slots is substantially continuous over a selected portion of a surface and perpendicular to or parallel to a centerline of the liner assembly.

A turbine section for a gas turbine engine includes a variable reaction free wheel downstream of the first static vane structure and a turbine rotor downstream of the variable reaction free wheel. A method of generating thrust for a gas turbine engine, includes rotating a variable reaction free wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.

A flow guide structure for a casing flange, and a casing and a turbomachine having the same, include a flange portion connecting an upper casing and a lower casing and a flow guide positioned at the flange portion to guide fluid to flow close to the flange portion, whereby steam flow resistance is reduced around an inner casing flange of a turbine and the steam flow is smoothed.

A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.

A fan rotor module for a gas turbine engine, the fan rotor module comprising a drive arm, a fan disc and a windage shield attached at one or more points to a rear portion of the fan disc, wherein the fan rotor module comprises at least one balancing weight disposed at one or more of the points where the windage shield is attached to the rear portion of the fan disc.

A turbomachine airfoil element has a substrate. The substrate defines an airfoil having a pressure side and a suction side. A plurality of fiber composite ribs are along the pressure side.

A component is provided for an aircraft. This aircraft component includes an object and a multi-layer coating. The object includes an object surface. The multi-layer coating includes a barrier layer and a laminar flow layer. The covers at least a portion of the object surface. The barrier layer a fluoropolyether, a silicon rubber and/or a polyurethane. The laminar flow layer covers the barrier layer and forms an exterior surface of the component. The laminar flow layer includes a sol-gel siloxane, a rare-earth oxide and/or a phosphate.

A turbulent air reducer assembly for a gas turbine engine includes a windage cover attached to a first standoff and a second standoff, the windage cover tuned to a particular vibration response. A method of managing air within a turbine of a gas turbine engine includes reducing turbulence from a multiple of recesses within a tangential on-board injector with a turbulent air reducer assembly within each of the multiple of recesses, the turbulent air reducer assembly tuned to a particular vibration response from a turbine rotor.