A stator for a gas turbine engine includes a stator vane, a first cooling passage located at the stator to provide a cooling fluid flow to a first portion of the stator, and a second cooling passage located at the stator to provide a cooling fluid flow to a second portion of the stator. A connection passage extends at least partially through the stator to connect a first cooling passage inlet of the first cooling passage to a second cooling passage inlet of the second cooling passage. The cooling fluid flow is directed from a common cooling flow source into the first cooling passage and the second cooling passage via the first cooling passage inlet.

A stage (10) of stationary vanes (12) of a gas turbine engine, including: a plurality of stationary vanes disposed in an annular array (14); and an energy damping system (30) having a plurality of connection assemblies (32), each joining respective adjacent stationary vanes. A spring (34) is configured to circumferentially bias respective adjacent stationary vanes, and a damper (36) is configured to oppose relative circumferential movement between the respective adjacent stationary vanes. The connection of the overall assembly disclosed herein allows for the oscillating system to decrease its amplitude over the shortest time period no matter the conditions. This reduces wear compared to underdamped arrangements that do not decrease amplitude as quickly.

An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

An example airfoil vane according to the present disclosure includes an airfoil section including an outer wall that defines an internal cavity, and an insert situated in the internal cavity. A space is defined between the insert and the airfoil outer wall, the insert including an insert wall. A plurality of standoff features extend from the insert wall into the space and contact the airfoil outer wall at a contact area, whereby the standoff features are configured to block airflow in the space at the contact area and redirect the airflow to gaps between the standoff features. A gas turbine engine with the example airfoil vane and a method of assembling an airfoil vane are also disclosed.

An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.

A vane arc segment includes an airfoil fairing that has a fairing platform and a hollow airfoil section that extends there from. The hollow airfoil section defines an airfoil profile and surrounds an internal cavity. The fairing platform defines a gaspath side and a non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite comprised of fiber plies. The fiber plies include at least one cavity fiber ply that is arranged as a tube that circumscribes the internal cavity. The at least one cavity fiber ply extends through the fairing platform and defines at least a portion of an upstanding collar on the non-gaspath side of the fairing platform. The upstanding collar defines a collar profile. The tube necks down through a neck portion such that at least a portion of the collar profile is narrower than the airfoil profile.

A turbine shroud block removal apparatus. In one embodiment, the apparatus includes a first base plate including a first armature. The first base plate may be releasably coupled to a first shroud block. The apparatus also may also include a second base plate including a second armature. The second base plate may be releasably coupled to a second shroud block positioned adjacent the first shroud block. Additionally, the apparatus may include an actuator coupled to the first armature of the first base plate and the second armature of the second base plate. The actuator may change a distance between the first shroud block and the second shroud block.

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

A method to produce a ceramic matrix composite with controlled surface characteristics includes: applying a scrim ply to a surface of a fiber preform, where the fiber preform includes silicon carbide fibers coated with boron nitride; infiltrating the fiber preform and the scrim ply with a slurry, thereby forming an impregnated ply on an impregnated fiber preform; infiltrating the impregnated fiber preform and the impregnated ply with a melt comprising silicon, and then cooling, thereby forming a ceramic matrix composite having a ceramic surface layer thereon, where the ceramic surface layer has a predetermined thickness and is devoid of boron; machining or grit blasting the ceramic surface layer to form an intermediate layer suitable for coating; and depositing an environmental barrier coating on the intermediate layer. Thus, a ceramic matrix composite coated with the environmental barrier coating is formed with the intermediate layer in between.

A measurement system includes a stator-side unit and a rotor-side unit installed on the rotary machine. The stator-side unit includes a stator-side antenna, an oscillation unit that oscillates a microwave signal and outputs the oscillated microwave signal to the stator-side antenna, and a reception unit that demodulates the microwave signal and outputs a desired signal. The rotor-side unit includes a sensor, a rotor-side antenna that receives a microwave transmitted by the stator-side antenna and outputs the microwave signal, a power conversion unit that converts the received microwave signal into predetermined DC power and outputs the DC power, and a modulation unit that modulates a rotor output signal or a multiplication rotor output signal obtained by frequency multiplication of the rotor output signal, according to the output signal of the sensor, using the DC power output of the power conversion unit, and outputs the modulated rotor signal to the rotor-side antenna.