An information input device includes a touch panel which is provided with a touch sensor capable of sensing a position in which a sensing target body is close to a sensing surface thereof. The touch sensor includes a scanning electrode and a detection electrode which faces and is spaced from the scanning electrode with a dielectric body being interposed therebetween, the touch sensor being configured so that electrostatic capacitance which is formed between the scanning electrode and the detection electrode is varied when the sensing target body is close to the detection electrode. The detection electrode is formed with a slit in a surface thereof which faces the scanning electrode, and a floating electrode is installed in the slit.

Information input device and display device

A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).

Mounting apparatus for low-ductility turbine shroud

The invention relates to a method for producing a turbomachine blade from a composite material, having an integrated platform and/or shroud. The method comprises the following steps: the three-dimensional weaving of a flexible fibrous blank as a single part comprising blade vane (220) and root (230) preform portions; the separate production of a blade platform (400) or blade shroud (500) element comprising a stiffened fibrous reinforcement, whereby at least one opening in the shape of the vane profile of the blade to be produced is formed in the platform or shroud element; the mounting of the platform or shroud element, by means of the opening therein, on the flexible fibrous blank, with deformation of the latter, for assembly with the fibrous blank; the forming of the fibrous blank with the assembled platform or shroud element in order to obtain a preform (200) having a shape similar to that of the blade to be produced; the setting of the shape of the preform in a former; and the introduction of a matrix in the preform in order to obtain a blade made from a composite material and having an integrated platform or shroud.

Method for producing a turbomachine blade made from a composite material

An engine has a blade stage (10) and a circumferential array of blade outer air seal segments (66). A support ring (70) carries the blade outer air seal segments (66). The support ring (70) has a low-CTE member (72) and a high-CTE member (90) intervening between the blade outer air seal segments (66) and the low-CTE member (72).

Blade clearance control using high-CTE and low-CTE ring members

A system includes a radiation sensor configured to direct a field of view toward at least one conduit along a fluid flow path into a heat exchanger. The radiation sensor is configured to output a signal indicative of a temperature of the at least one conduit. The system also includes a controller communicatively coupled to the radiation sensor. The controller is configured to determine the temperature based on the signal, to compare the temperature to a threshold range, and to adjust a fluid flow through the fluid flow path or the at least one conduit if the temperature deviates from the threshold range.

Thermal control system for fault detection and mitigation within a power generation system

A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion.

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Ceramic matrix composite turbine engine vane

A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.

Turbine shroud thermal distortion control

A ceramic shroud assembly suitable for use in a gas turbine engine comprises a metal clamp ring shrink fitted around a ceramic shroud ring and an insulating and compliant interlayer. The interlayer is positioned between the metal clamp ring and the ceramic shroud ring.

Ceramic shroud assembly

A turbine shroud (24) includes a ceramic shroud ring (30) configured to surround a plurality of turbine rotor blades, a plurality of slots (44) circumferentially distributed around the ceramic shroud ring, a forward metallic support ring (32), a plurality of tabs (40) attached to a forward edge of the forward metallic support ring configured to engage a turbine support case (26), and a plurality of tabs (42) attached to an aft edge of the forward metallic support ring received by the slots of the ceramic shroud ring. Only two axially extending radial surfaces (44a) of each of the tabs attached to the aft edge of the forward metallic support ring are configured to contact the slots of the ceramic shroud ring.

Ceramic turbine shroud support

A system for supporting a shroud (18) used in an engine (10) has a shroud (18) positioned radially outboard of a rotor (20), which shroud (18) has a plurality of circumferentially spaced slots (40); a forward support ring (26) for supporting the shroud (18); the forward support ring (26) having a plurality of spaced apart first tabs (36) on a first side for functioning as anti-rotation devices; the forward support ring (26) having a plurality of spaced apart second tabs (38) on a second side; the second tabs (38) engaging the slots (40) in the shroud (18) and circumferentially supporting the shroud (18).

Jun Shi

Papers

Ceramic matrix composite turbine engine vane

Turbine shroud thermal distortion control

Ceramic shroud assembly

Ceramic turbine shroud support

Gas turbine shroud arrangement