A rotor assembly for use in a turbofan engine is provided. The rotor assembly includes an annular spool including a first blade opening defined therein, a first rotor blade configured to be radially inserted through the first blade opening, and a fairing positioned on a radially outer side of the annular spool. The first rotor blade includes a blade portion and a flange portion that extends substantially perpendicularly relative to the blade portion such that the flange portion is positioned on a radially inner side of the annular spool. The fairing is configured to receive a fastener radially inserted through the flange portion and the annular spool such that the first rotor blade is secured to the annular spool.

A gas turbine engine endwall treatment includes a recirculation passages distributed circumferentially around and extending generally axially in an endwall or shroud, Venturi effect producing main throats between main inlet and outlet passages including main inlet and outlet ports respectively extending through the endwall or shroud, and main inlet ports axially aft and downstream of the main outlet ports. Second inlet passages may connect second inlet ports in endwall to main recirculation passages at or near main throats and second inlet ports. An annular groove in endwall may pass through and interconnect the second inlet ports. Two or more clustered inlet passages may extend from two or more clustered secondary inlet ports to two or more intersections of the two or more clustered inlet passages and the main recirculation passage. The main inlet and outlet ports may be spaced one or more stages apart.

A turbine engine system comprising a turbine engine component, such as a fan includes a fan casing and a fan blade rotatable within the fan casing. An abradable seal coupled to the fan casing proximate the fan blade. The abradable seal comprising an abradable composite layer including a MAX phase solid and a polymer based abradable composition.

A diffuser for a centrifugal compressor includes a diffuser pipe having an internal flow passage extending therethrough between an inlet and an outlet, a bend in the internal flow passage disposed between the inlet and the outlet, and a throat defined in the internal flow passage downstream of the inlet and upstream of the bend. One or more vortex generators project into the internal flow passage, and the vortex generators are disposed downstream of the throat and upstream of the bend. A method for diffusing fluid flow in a diffuser of a compressor is also described. In operation, the vortex generators engage fluid flow in the internal flow passage to generate downstream vortices.

A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.

A system and method for detecting the rotation breakaway of a spacer from a compressor rotor disk are disclosed herein. The method includes detecting a disk sensed feature and a spacer sensed feature on the compressor rotor disk and the spacer respectively. The method also includes comparing the timing between the two to a predetermined threshold to determine whether the relative position of the spacer to the compressor rotor disk exceeds a predetermined amount. The predetermined amount may be selected to determine whether an imbalance, rubbing, or binding can occur in the gas turbine engine or to determine whether anti-rotation features have been broken.

A method for accurately producing the drilled hole in a wall of a component fabricated by investment casting process, such as for use in a blade or steam turbine includes the following steps. The 3D data of actual component is obtained from the measurements or from the numerical simulation. The actual model and the ideal model are aligned and compared, a series of cutting planes are given to establish a series of 2D cross-sections of the actual and ideal models after registration. Each cross-section is dispersed into discrete points, the distance between each corresponding points are calculated and formed into 2D displacement. The accurate parametric model consisting of the depth, hole center, and the nominal vector is obtained on the basis of considering the deviations in geometrical and positional values. The drilled hole is then produced according to the corrected parametric drilled-hole geometrical and positional value.

A method for measuring air mass flow into a compressor section of a gas turbine engine is provided. Air is introduced into a chamber upstream from an inlet of the compressor section. The chamber includes filter packages with at least some of the filter packages including a flow sensor and a filter structure, the filter structure filtering the air. The flow sensors measure the velocity of the air flowing through the corresponding filter package. A controller uses the air flow sensor signal data to characterize a two dimensional flow field through the chamber. Additionally, a plurality of temperature, humidity, and static pressure sensors are disposed throughout the filter packages. The controller uses the temperature, humidity, and static pressure sensor signal data to characterize a two dimensional density field through the chamber. The controller combines the flow field with the density field to calculate a two dimensional air mass flow field.

A compressor diffuser for a gas turbine engine which includes at least one diffuser pipe having a tubular body with an inner surface defining an internal flow passage extending therethrough. The tubular body includes a first portion that extends in a first direction and defines a throat therein, a second portion that extends in a second direction different from the first direction, and a curved portion fluidly linking the first portion and the second portion. A plurality of vortex generators are disposed within the diffuser pipe and extend from the inner surface into the internal flow passage. The vortex generators are disposed downstream of the throat in the first portion of the diffuser pipe and upstream of the curved portion. In operation, the vortex generators engage fluid flow in the internal flow passage to generate downstream vortices.

A thermal barrier attachment seal for a gas turbine engine component includes a spine having a first surface and a second surface facing opposite the first surface. A first layer of insulation is provided on the first surface. A second layer of insulation is provided on the second surface to provide a thermal barrier seal between a first gas turbine engine component and a second gas turbine engine component. A fan section for a gas turbine engine is also disclosed.