Remy Paul Charles Ritt

Bio: Remy Paul Charles Ritt is an academic researcher. The author has contributed to research in topics: Turbine & Casing. The author has an hindex of 5, co-authored 9 publications receiving 174 citations.

Turbine ring for a gas turbine engine

Abstract: A turbine ring has an annular metallic carrier which is mounted within the inside of the turbine casing and within the carrier there is provided a ceramic abradable ring. A cooling air circuit is provided to regulate the temperature of only the annular carrier such that the latter always exerts a centripetal compression force on the ring under all operational conditions of the gas turbine to clamp the abradable ring.

Turbine ring incorporating elements of a ceramic composition divided into sectors

Abstract: 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 rings of gas turbine plant

Abstract: 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.

Tip-sealing shroud for a gas turbine

Abstract: L'invention concerne un anneau de turbine. A turbine ring. Cet anneau comprend un support annulaire, metallique (6) qui est monte a l'interieur du carter (1), a l'interieur duquel est monte un anneau (5) en materiau ceramique abradable; This ring comprises an annular support, metal (6) which is mounted within the housing (1), inside which is mounted a ring (5) made of abradable ceramic material; selon la presente invention, des moyens, tels qu'un circuit d'air de refroidissement (7-11-9a-9b-12-13) sont prevus pour regler seulement la temperature du support annulaire (6) de facon que celui-ci exerce toujours une compression axipete appropriee sur l'anneau (5), a tous les regimes de fonctionnement de la turbine, c'est-a-dire que le support annulaire (6) se comporte comme une frette pour l'anneau (5). according to the present invention, means such as a cooling air circuit (7-11-9a-9b-12-13) are provided only for adjusting the temperature of the annular support (6) so that it always exercises appropriate axipete compression on the ring (5) at all operating speeds of the turbine, that is to say that the annular support (6) behaves like a hoop to the ring (5) .

Gas turbine shroud

Abstract: 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.

Ceramic matrix composite component for a gas turbine engine

Abstract: 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.

Low-pressure turbine shroud

Abstract: 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.

Cooling joint connection for abutting segments in a gas turbine engine

Abstract: 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.

Mounting apparatus for low-ductility turbine shroud

Abstract: 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).

Polymer conjugates of interferon beta-1a and their uses

Abstract: 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.