The present disclosure provides systems and apparatuses for use in turbine systems that integrate structural frame elements into a variable-vectoring flow control configuration in order to reduce the weight and length of such turbine systems. In one exemplary embodiment, an apparatus for directing a gas flow includes an annular outer structural casing, an annular central hub disposed within the outer structural casing, and a plurality of structural support elements extending radially between the central hub and the outer structural casing. The apparatus further includes a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the central hub and the outer structural casing and positioned circumferentially along the central hub between ones of the plurality of structural support elements.

A system for preventing icing on an aircraft surface includes a plasma actuator which is applied onto an aircraft surface operationally exposed to air and which is arranged for generating at least one plasma discharge (D) for inducing a flow (F) of ionized hot-air particles towards the surface.

The present disclosure provides systems and apparatuses for use in turbine systems that integrate structural frame elements into a variable-vectoring flow control configuration in order to reduce the weight and length of such turbine systems. In one exemplary embodiment, an apparatus for directing a gas flow includes an annular outer structural casing, an annular central hub disposed within the outer structural casing, and a plurality of structural support elements extending radially between the central hub and the outer structural casing. The apparatus further includes a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the central hub and the outer structural casing and positioned circumferentially along the central hub between ones of the plurality of structural support elements.

A system and method for aerodynamically sealing rotating and fixed components of a gas turbine engine. The system includes a gas turbine engine having a casing and a rotating portion, a plasma actuator having a first and a second electrodes, the first electrode including at least one section of substantially flat conductive material encased in a dielectric material forming at least a portion of a cylinder disposed circumferentially on the casing. The system also includes the rotating portion operably configured as the second electrode, and an excitation source operably connected between the first electrode and the second electrode, the excitation source generating an excitation signal and applying it to the first and second electrodes to cause the actuator to form a plasma between the first and second electrodes, the plasma inducing an airflow between the casing and the rotating portion.

A blower having high efficiency and low noise by actively controlling airflow in the blower, and an air conditioner having the blower is provided. The air conditioner has a blower. The blower includes a fan having a hub and at least one blade provided on an outer circumferential surface of the hub, a motor to rotatably drive the hub, a shroud configured to surround the periphery of the fan and at least one actuator installed in the shroud and configured to form an airflow along an inner circumferential surface of the shroud.

The present application relates to an axial turbomachine gaseous flow-guiding element, such as a compressor inner shroud or vane. The element includes a plasma generator including: a layer of dielectric material with a guiding surface in contact with the gaseous flow, a first electrode placed in the guiding surface, and a second electrode electrically isolated from the first electrode by means of the dielectric layer. The plasma generator drives the gaseous flow along the guiding surface from the first electrode to the second electrode and includes a third electrode covered by the dielectric layer and electrically connected to the second electrode, so as to participate in the generation of the plasma in combination with the first electrode and the second electrode, the second electrode being closer to the guiding surface than the third electrode.

Disclosed is a method of manufacturing an airfoil structure. The airfoil structure includes a plurality of airfoils, a support for supporting the airfoils, and a case for covering the airfoils. Each airfoil includes an airfoil body, and an airflow generator for producing induced airflow by generating plasma. The method includes a process of forming the airflow generator that includes a first electrode forming step of forming a first electrode on the airfoil body, a dielectric layer forming step of forming a dielectric layer on the airfoil body by forming ceramic powder into a film to cover the first electrode through room temperature impact consolidation, and a second electrode forming step of forming a second electrode on a surface of the dielectric layer, such that the second electrode is electrically connected to the first electrode, and an alternating-current voltage is applied to the second electrode.

A surface plasma actuator includes a conducting wire attached to a surface of a target object and electrically insulated from the target object. Surface plasma is generated along a neighborhood of the conducting wire by applying a pulse voltage between the conducting wire and a conductive portion on a side of the target object. An induced gas flow is generated by the surface plasma.

An on-line wash system for a compressor including: a nozzle including a flow passage for wash liquid, wherein the flow passage is configured to be coupled to a source of a wash liquid and includes a discharge outlet arranged to project the wash liquid into a stream of working fluid for the turbomachine; an electrode proximate to the flow passage of the nozzle, wherein the electrode is configured to form an electrical field sufficient to charge the wash liquid flowing through the passage and the charge applied to the wash liquid is of a first polarity, and a surface of the compressor charged with the first polarity, wherein the surface is exposed to the stream of working fluid and downstream of the nozzle.

A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow.