Patent•
Ceramic matrix composite component for a gas turbine engine
09 Sep 2002-
TL;DR: In this article, the gap between the CMC member and the support member is kept purposefully small to limit the stress developed in the material when it is deflected against the support by the force of a rubbing blade tip.
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.
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02 Jan 2014TL;DR: A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors.
Abstract: A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors. At least one of the hooks comprises a second element through which a recess is formed which opens up at each of the transverse flanks of the second element and at the internal peripheral surface of the second element.
1 citations
Patent•
29 Aug 2019TL;DR: In this paper, an actively cooled assembly adapted for use in a gas turbine engine is described, and the assembly includes at least one ceramic matrix composite component with an attachment feature, and it is shown that the component can be attached to the turbine.
Abstract: An actively cooled assembly adapted for use in a gas turbine engine is disclosed herein. In illustrative embodiments, the assembly includes at least one ceramic matrix composite component with an attachment feature.
1 citations
Patent•
23 Oct 2014TL;DR: In this paper, a gas turbine engine having a turbine blade tip clearance control system for increasing the efficiency of the engine by reducing the gap between turbine blade tips (16) and radially outward ring segments (18) is disclosed.
Abstract: A gas turbine engine (10) having a turbine blade tip clearance control system (12) for increasing the efficiency of the engine (10) by reducing the gap (14) between turbine blade tips (16) and radially outward ring segments (18) is disclosed. The turbine blade tip clearance control system (12) may include one or more clearance control bands (20) positioned radially outward of inner surfaces (22) of ring segments (18) and bearing against at least one outer surface (24) of the ring segments (18) to limit radial movement of the ring segments (18). During operation, the clearance control band (20) limits radial movement of the ring segments (18), and the turbine blade tips (16) do not have a pinch point during start-up transient conditions. In addition, the smallest gap (14) during turbine engine operation may be found at steady state operation of the gas turbine engine (10). Thus, the clearance control system (12) can set the gap (14) between turbine blade tips (16) and ring segments (18) to be zero at steady state operation.
1 citations
Patent•
17 May 2018TL;DR: In this article, a turbine assembly for a gas turbine engine is described, which includes a turbine vane and an annular turbine shroud, which is adapted to extend around a bladed turbine wheel to resist gasses from passing over turbine blades.
Abstract: A turbine assembly for a gas turbine engine is disclosed herein. The turbine assembly includes a turbine vane and an annular turbine shroud. The turbine vane has an airfoil extending through a primary gas path and is formed to include cooling passages sized to conduct cooling air from an inlet aperture to a discharge aperture. The turbine shroud is adapted to extend around a bladed turbine wheel to resist gasses from passing over turbine blades without interacting with the turbine blades. The turbine shroud includes a ceramic matrix composite blade track having a radially-inwardly facing inner surface arranged in confronting relation with the primary gas path.
1 citations
References
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Patent•
11 Feb 1999TL;DR: In this article, a ceramic composition for insulating components, made of ceramic matrix composites, of gas turbines is provided, which comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the binder partially fills gaps between the spheres and the filler powders.
Abstract: A ceramic composition for insulating components, made of ceramic matrix composites, of gas turbines is provided. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere and the arrangement of spheres is such that the composition is dimensionally stable and chemically stable at a temperature of approximately 1600 °C. A stationary vane of a gas turbine comprising the composition of the present invention bonded to the outer surface of the vane is provided. A combustor comprising the composition bonded to the inner surface of the combustor is provided. A transition duct comprising the insulating coating bonded to the inner surface of the transition is provided. Because of abradable properties of the composition, a gas turbine blade tip seal comprising the composition also is provided. The composition is bonded to the inside surface of a shroud so that a blade tip carves grooves in the composition so as to create a customized seal for the turbine blade tip.
141 citations
Patent•
15 Nov 1985
TL;DR: 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 as mentioned in this paper, and 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.
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.
69 citations
Patent•
21 Apr 1987
TL;DR: In this paper, a turbine ring comprises an annular support in two parts and a ring of ceramic sectors for sealing purposes, which are interconnected by an axial groove and a sliding male part.
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.
61 citations
Patent•
26 May 1983
TL;DR: In this article, the ceramic facing material of an outer air seal (30) at the leading edge region (36) is densified by a plasma gun to produce a glazed area (52) which is resistant to erosion.
Abstract: Outer air seal structures of particular suitability for use in gas turbine engines are disclosed. Techniques for improving resistance to erosion while maintaining good abradability are discussed. In one particular structure the ceramic facing material of an outer air seal (30) at the leading edge region (36) is densified by a plasma gun to produce a glazed area (52) which is resistant to erosion.
61 citations
Patent•
14 Jan 1991TL;DR: In this paper, a turbine blade shroud assembly for a gas turbine engine includes a metal substrate ring on the engine, a continous ceramic barrier ring inside the substrate ring and exposed to hot gas in a hot gas flow path of the engine and a wire mesh compliant ring between the barrier and substrate rings.
Abstract: A turbine blade shroud assembly for a gas turbine engine includes a metal substrate ring on the engine, a continous ceramic barrier ring inside the substrate ring and exposed to hot gas in a hot gas flow path of the engine, and a wire mesh compliant ring between the barrier and substrate rings. The temperature of the barrier ring increases faster than the temperature of the substrate ring as the temperature in the hot gas flow path increases. The coefficient of thermal expansion of the substrate ring is less than the coefficient of thermal expansion of the barrier ring so that the barrier ring expands relative to the substrate ring with increasing temperature in the hot gas flow path and development of tensile hoop stress in the ceramic barrier ring is minimized.
60 citations