A ceramic matrix composite (CMC) component for a combustion turbine engine ( 10 ). A blade shroud assembly ( 30 ) may be formed to include a CMC member ( 32 ) supported from a metal support member ( 32 ). The CMC member includes arcuate portions ( 50, 52 ) shaped to surround extending portions ( 46, 48 ) of the support member to insulate the metal support member from hot combustion gas ( 16 ). The use of a low thermal conductivity CMC material allows the metal support member to be in direct contact with the CMC material. The gap ( 42 ) between the CMC member and the support member is kept purposefully small to limit the stress developed in the CMC member when it is deflected against the support member by the force of a rubbing blade tip ( 14 ). Changes in the gap dimension resulting from differential thermal growth may be regulated by selecting an angle (A) of a tapered slot ( 76 ) defined by the arcuate portion.

Ceramic matrix composite component for a gas turbine engine

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 seal joint including a sealing member for sealing segmented components of a gas turbine engine is spaced from the gas path to provide more effective cooling. The segments include radial extension flanges spacing the seal joint from the gas path. Various cooling arrangements are adaptable to the modified segments to provide for open or closed circuit impingement or convection cooling plus film cooling. Excessive thermal gradients are avoided as the entire corner of the segment is evenly cooled. Moreover, air usage at the joint is bounded by seal leakage with no extra dedicated cooling air.

Cooling joint connection for abutting segments in a gas turbine engine

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

An interferon beta polypeptide comprising interferon-beta 1a coupled to a polymer containing a polyalkylene glycol moiety wherein the interferon-beta-1a and the polyalkylene glycol moiety are arranged such that the interferon-beta-1a has an enhanced activity relative to another therapeutic form of interferon beta (interferon-beta-1b) and exhibits no decrease in activity as compared to non-conjugated interferon-beta-1a. The conjugates of the invention are usefully employed in therapeutic as well as non-therapeutic, e.g., diagnostic, applications.

Polymer conjugates of interferon beta-1a and their uses

A turbine ring comprises an annular support in two parts and a ring of ceramic sectors for sealing purposes. The two parts of the support are interconnected by an axial groove and a sliding male part. Each part comprises an axial annular groove in which is engaged a respective axial edge portion of each sector. The cooperating internal radial faces respectively of the edge portion and of the groove are circumferential, while the radially outer radial face of each sector comprises at least one flat zone. The corresponding face of each groove may be polygonal.

Turbine ring incorporating elements of a ceramic composition divided into sectors

A turbine ring assembly is mounted on an annular carrier secured to the irior of the casing of a turbine and includes a succession of contiguous sectors of a ceramic abradable material. The sectors have grooves in which support fingers are engaged rigid with an annular member connected to the casing of the turbine. The sectors are thereby held in an annular configuration and the support fingers are so located in the grooves as to provide a screen to prevent reintroduction of hot gases.

Turbine rings of gas turbine plant

Anneau de turbine monte sur un support annulaire fixe a l'interieur du carter de turbine et constitue d'une succession de secteurs contigus en un materiau ceramique abradable. Turbine ring mounted on an annular support fixed inside the turbine housing and consisting of a succession of contiguous sectors in a ceramic abradable material. Les secteurs (1) representent des rainures axiales (1a, 1b) dans lesquelles s'engagent des doigts-supports (4) solidaires d'une virole (3) reliee au carter de turbine et assurant l'accrochage des secteurs (1) les uns a la suite des autres, ces doigts-supports d'accrochage (4) se trouvant loges dans les rainures (1a, 1b) a l'abri des reintroductions de ' gaz chauds. Sectors (1) are axial grooves (1a, 1b) into which engage the finger supports (4) integral with a ring (3) connected to the turbine housing and ensuring the attachment of the sectors (1) one after the other, these hooking finger supports (4) being housed in the grooves (1a, 1b) away from the "hot gas reintroduction. Application a la construction de turbines a gaz. Application to gas turbine construction.

Gas turbine shroud

Un anneau de turbine est constitue d'un support annulaire en deux parties (12,13) et d'un anneau (14) d'etancheite en secteurs ceramiques (14a). A turbine ring consists of an annular support in two parts (12,13) ​​and a ring (14) sealing ceramic sectors (14a). Les deux parties (12,13) de support cooperent par une gorge axiale (18) et une partie mâle coulissante (25). The two parts (12,13) ​​for supporting cooperate with an axial groove (18) and a male sliding part (25). Chacune comporte une rainure annulaire axiale (19,28) dans laquelle est engage le rebord axial (33,34) de chaque secteur (14a). Each includes an axial annular groove (19,28) in which is engaged the axial flange (33,34) of each sector (14a). Les faces cooperantes radialement interieures (33a,34a,21,30) respectivement du rebord et de la rainure sont circonferentielles alors que la face radialement exterieure (33b,34b) de chaque secteur (14a) comporte au moins une zone plate (33c,34c). The radially inner mating faces (33a, 34a, 21,30) respectively of the rim and groove are circumferential while the radially outer face (33b, 34b) of each sector (14a) comprises at least one flat area (33c, 34c ). Ladite face (21,30) de rainure peut etre polygonale. Said face (21,30) of groove may be polygonal.

Sectional turbine shroud

UN ANNEAU DE TURBINE EST CONSTITUE D'UN SUPPORT ANNULAIRE EN DEUX PARTIES 12, 13 ET D'UN ANNEAU 14 D'ETANCHEITE EN SECTEURS CERAMIQUE 14A LES DEUX PARTIES 12, 13 DE SUPPORT COOPERENT PAR UNE GORGE AXIALE 18 ET UNE PARTIE MALE COULISSANTE 25 CHACUNE COMPORTE UNE RAINURE ANNULAIRE AXIALE 19, 28 DANS LAQUELLE EST ENGAGE LE REBORD AXIAL 33, 34 DE CHAQUE SECTEUR 14A LES FACES COOPERANTES RADIALEMENT INTERIEURES 33A, 34A, 21, 30 RESPECTIVEMENT DU REBORD ET DE LA RAINURE SONT CIRCONFERENTIELLES ALORS QUE LA FACE RADIALEMENT EXTERIEURE 33B, 34B DE CHAQUE SECTEUR 14A COMPORTE AU MOINS UNE ZONE PLATE 33C, 34C LADITE FACE 21, 30 DE RAINURE PEUT ETRE POLYGONALE

Carmen Miraucourt

Papers

Turbine ring incorporating elements of a ceramic composition divided into sectors

Turbine rings of gas turbine plant

Gas turbine shroud

Sectional turbine shroud

Anneau de turbine sectorise