Patent•
Turbine ring for a gas turbine engine
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.
Citations
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Patent•
09 Sep 2002TL;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.
146 citations
Patent•
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TL;DR: In this article, the authors describe a hollow section that defines an inlet (44) and an outlet (64, 66) for the passage of coolant through a turbine rotor.
Abstract: A ceramic seal segment (30) for a shroud ring (21) of a rotor (15) of a gas turbine engine (10), the ceramic seal segment (30) positioned radially adjacent the rotor (15) and characterised by being a hollow section that defines an inlet (44) and an outlet (64, 66) for the passage of coolant therethrough.
100 citations
Patent•
08 Apr 2005
TL;DR: The clearance between the tips of the rotor blades and the segmented shroud of a gas turbine engine is controlled by a passive clearance control that includes a support ring made from a low thermal expansion material supporting a retainer for the blade outer air seal as mentioned in this paper.
Abstract: The clearance between the tips of the rotor blades and the segmented shroud of a gas turbine engine is controlled by a passive clearance control that includes a support ring made from a low thermal expansion material supporting a retainer for the blade outer air seal that is slidable relative thereto so that the segments expand circumferentially and move radially to match the rate of change slope of the rotor during expansion and contraction for all engine operations. A leaf spring between the support ring and outer air seal biases the outer air seal in the radial direction and maintains the desired radial position during steady state operation of the gas turbine engine.
93 citations
Patent•
27 Oct 2000TL;DR: In this paper, a cold spray process is used to apply an abradable coating to a substrate material at a velocity sufficiently high to cause the particles to deform and to adhere to the surface.
Abstract: A cold spray process (20) for applying an abradable coating (16) to a substrate material (12). A bond coat layer (14) and/or an abradable coating material layer (16) are applied to a substrate (12) by directing particles of the material toward the substrate surface at a velocity sufficiently high to cause the particles to deform and to adhere to the surface. Particles of the bond coat material may first be directed toward the substrate surface at a velocity sufficiently high to clean the surface (24) but not sufficiently high to cause the particles to deform and to adhere to the surface.
84 citations
Patent•
17 Sep 2003TL;DR: In this article, a thermal barrier coating is applied to the front and back surfaces of a turbine wall and a network of flow channels is laminated between the substrate and the coating for carrying an air coolant there between for cooling the thermal barrier.
Abstract: A turbine wall includes a metal substrate having front and back surfaces. A thermal barrier coating is bonded atop the front surface. A network of flow channels is laminated between the substrate and the coating for carrying an air coolant therebetween for cooling the thermal barrier coating.
79 citations
References
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Patent•
22 Nov 1976TL;DR: In this article, a high temperature turbine shroud assembly for an aircraft gas turbine engine comprising a plurality of arcuate ceramic blocks arranged in a ring is presented, supported by a pair of annular support members which retain the blocks in the assembly.
Abstract: 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.
118 citations
Patent•
02 Oct 1969TL;DR: In this paper, a perforated baffle is used for impinging a pressurized fluid against the external surface of the shroud, which is mounted by a support structure defining a chamber outwardly of a shroud which is compartmentalized by the baffle Passageways are formed through the support structure to first direct the pressurised fluid into the outer compartment and toward a compartment wall defined by the support support structure before transit through the impingement baffle so as to provide effective temperature control for the shroud and shroud support during transient and steady-state operation.
Abstract: A shroud for a turbine or the like having an inner surface for defining a flow passage and carrying a perforated baffle for impinging a pressurized fluid against the external surface of the shroud The shroud is mounted by a support structure defining a chamber outwardly of the shroud which is compartmentalized by the baffle Passageways are formed through the support structure to first direct the pressurized fluid into the outer compartment and toward a compartment wall defined by the support structure before transit through the impingement baffle so as to provide effective temperature control for the shroud and shroud support during transient and steady-state operation
92 citations
Patent•
24 May 1985TL;DR: In this paper, a gas turbine rotor blade is mounted and cooled such that they are thrust outwards against seatings on surrounding high strength support structure by the gas pressure in the turbine passage, the shroud segments being provided with strengthening ribs or the like so that the outward thrust is transferred to the support structure through a plurality of load paths distributed over the outer sides of the shroud segment as necessary to avoid overstressing.
Abstract: To enable shroud segments in a gas turbine rotor blade stage to operate at high temperatures with an adequate margin of safety, the shroud segments are mounted and cooled such that they are thrust outwards against seatings on surrounding high strength support structure by the gas pressure in the turbine passage, the shroud segments being provided with strengthening ribs or the like so that the outward thrust is transferred to the support structure through a plurality of load paths distributed over the outer sides of the shroud segments as necessary to avoid overstressing.
62 citations
Patent•
16 Feb 1983TL;DR: In this paper, the use of a thin metal sheet with a ceramic coating promotes favorable temperature gradients in the skin enabling the coating to run at optimum conditions for maximum cooling effect.
Abstract: A shroud assembly for a gas turbine engine consists of a housing having a boundary wall and a gas contacting skin, the wall and skin being in segmented form. The skin consists of a thin metal sheet attached to the boundary wall, and a ceramic gas contacting coating. The skin is impingement cooled by cooling air flowing through apertures in the boundary wall, and the cooling air exhausts into the gas flow through passages. The use of a thin metal sheet with a ceramic coating promotes favorable temperature gradients in the skin enabling the coating to run at optimum conditions for maximum cooling effect.
59 citations
Patent•
05 Oct 1979
TL;DR: In this paper, a flexible annular wall member embedded in a turbine casing was proposed for aviation turbojets, which is applicable to aviation turboturbine engines, but not to aircraft.
Abstract: A portion of the stator of a gas turbine known as turbine shroud, which isituated radially opposite the mobile vanes of a turbine stage includes an "abradable" member supported by a first shell braced by a second shell and connected with turbine casing 2 by a thin, i.e. flexible, annular wall member embedded in a casing. Cooling air inflates the second shell so as to brace the exterior shell and circulates between the two shells so as to cool them and also cools the "abradable" member by impingement. The present invention is applicable to aviation turbojets.
26 citations