A turbine shroud is formed by a ring of butted shroud segments. Each turbine shroud segment has a radially inwardly projecting annular flange which is seated on a radially outwardly facing surface of an annular tip of the outer shroud of the downstream nozzle stage. This flange is free to slide axially relative to the annular tip during thermal expansion of the nozzle outer shroud in the axial direction. Each turbine shroud segment has a spring seated thereon which urges the radially inwardly projecting flange toward the annular tip of the nozzle outer shroud. Honeycomb material attached to the turbine shroud segment discourages the flow of hot gases through the gap betwen the flange and annular tip of the outer shroud of the downstream nozzle stage attributable to seam chording, thereby reducing the leakage of hot gas into the spaces between the shrouds and the outer casing.

Low-pressure turbine shroud

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

A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising an annular ceramic shroud ring, a plurality of arcuate shroud support segments, and a plurality of inwardly biased resilient members The annular ceramic shroud ring is circumferentially disposed about radially extending blades of a turbine rotor and partially defines an annular hot gas passage of the turbine portion The plurality of arcuate shroud support segments are radially disposed outwardly of the ceramic shroud ring and are contiguous therewith The plurality of inwardly biased resilient members are each engaged between one of the shroud support segments and an outer annular turbine support case composed of a material having a different thermal expansion coefficient than the ceramic shroud ring The resilient members maintain contact between the shroud support segments and the ceramic shroud ring The shroud supporting segments and the resilient members are adapted to deflect to compensate for relative thermal growth differences between the ceramic shroud ring and the turbine support case

Attachment of a ceramic shroud in a metal housing

An electrical assembly for use in various operating environments such as a casing of a combustion turbine 10 is provided. The assembly may include an electrical energy-harvesting device 51 disposed in a component within the casing of the turbine to convert a form of energy present within the casing to electrical energy. The harvesting device is configured to generate sufficient electrical power for powering one or more electrical devices therein without assistance from an external power source. One example of electrical devices wholly powered by the energy harvesting device may be a sensor 50 connected for sensing a condition of the component within the casing during operation of the combustion turbine. Another example of electrical devices wholly powered by the energy harvesting device may be a transmitter in communication with the sensor for wirelessly transmitting the data signal outside the casing.

Electrical assembly for monitoring conditions in a combustion turbine operating environment

A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

Turbine ring assembly

A high temperature turbine shroud assembly for an aircraft gas turbine engine comprising a plurality of arcuate ceramic blocks arranged in a ring. The blocks are supported by a pair of annular support members which retain the blocks in the assembly. Spring-like fingers associated with the support members apply a preloaded force against a pair of slanted dovetail surfaces on the blocks to force the blocks against rigid stops formed upon the annular support members, thereby establishing their proper radial position within the assembly. The preload applied by the fingers accommodates the thermal expansion differences between the ceramic blocks and the metallic support members. In an alternative embodiment, the blocks are retained between cooperating rigid legs extending from the annular support members and wedged radially inwardly into position by a preloaded spring contacting the back side of the blocks. Heat transfer between the blocks and metallic support members is minimized by providing point or line contact between components, thus reducing the contact area available for heat conduction.

Ceramic turbine shroud assembly

Structure de virole comportant une virole en ceramique. Elle comprend des blocs en ceramique 40 disposes en anneau qui ont, vus en plan, une forme rectangulaire, ont une surface interieure arquee 42 qui delimite une partie du passage 38 d'ecoulement des gaz chauds et sont munis sur leurs cotes amont et aval de surfaces en queue d'aronde 44, 46 obliques par rapport a la face 42, les blocs etant maintenus en position par des organes de support annulaires 54, 56 qui appliquent aux blocs une composante de force radiale en les repoussant contre des butees fixes. L'invention est applicable, notamment, aux moteurs a turbine a gaz d'avions.

Hemsworth Martin Carl

Papers

Ceramic turbine shroud assembly

Structure de virole de turbine a gaz