Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.

Abstract: The present disclosure relates generally to a seal between two circumferential components. The seal comprises one or more rope seals retained within the seal cavity by a carrier.

Abstract: A gas turbine engine includes a circumferential array of vanes slidably supported in an inner case shroud segment. Multiple segments are secured to one another to provide an annular engine static structure section. The inner case shroud segment and the vanes have different material properties than one another.

Abstract: The present disclosure relates to advanced materials, particularly single crystal grain structures including the formation of single crystal grain structures. Single crystal grain structures offer improved mechanical properties when used with individual components. Improving mechanical properties is favorable for components that are used in applications with high temperature, pressure, and stress. In these applications, mechanical failure is extremely undesirable. Individual components, such as seals, can be designed with a single crystal grain structure in a preferred direction. By selecting a preferred direction, and orienting the single crystal grain structure accordingly, the single crystal grain structure can improve the component's mechanical properties. Single crystal grain structure seals and the method of forming the seals, therefore, offer various improvements to individual components, specifically when the components are designed for high temperature, pressure, and stress applications.

Abstract: A seal for a gas turbine engine comprises a seal body extending from a first end to a second end. A wrap extends at least partially around the first and second ends of the seal body. A gas turbine engine is also disclosed.

Abstract: The present disclosure relates generally to a seal between two circumferential components. The seal comprises one or more rope seals retained within the seal cavity by a carrier.

Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.

Abstract: A vane seal system includes a non-rotatable vane segment that has an airfoil with a pocket at one end thereof. The pocket spans in an axial direction between forward and trailing sides, with respect to the airfoil, and in a lateral direction between open lateral sides. A seal member extends in the pocket. The seal member includes a seal element and at least one spring portion that is configured to positively locate the seal member in the axial direction in the pocket. A method for positioning the seal member in a vane seal system includes positively locating the seal member in the axial direction in the pocket using the spring portion.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a carrier having one or more cavities formed therein. The one or more carriers may contain wave springs and/or compliant seals therein. Various embodiments provide loading of the seal in both the axial and radial directions, regardless of whether a pressure differential exists across the seal, by means of springs and/or ramped surfaces. Other combinations of carrier, wave springs, and compliant seals are also disclosed.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section including one or more first slots formed therein, a second seal section including one or more second slots formed therein and one or more frustoconical rings disposed in respective ones of the slots, such that the first and second seal sections and the frustoconical rings move relative to one another during relative movement between the two components. A wave spring disposed between the first and second seal sections biases the first and second seal sections away from one another.

Abstract: A seal assembly arrangement for a gas turbine engine includes first and second non-rotating structures respectively that provide first and second faces. A sealing assembly includes first and second sealing rings respectively that engage the first and second faces. The first and second sealing rings slideably engage one another at a sliding wedge interface.

Abstract: The present disclosure relates generally to a seal between two circumferential components. The seal comprises a first rope seal partially disposed within a first retainer, a second rope seal partially disposed within a second retainer, a carrier including a first end operatively coupled to the first retainer and a second end operatively coupled to the second retainer.

Abstract: The present disclosure relates generally to a seal between two circumferential components. The seal comprises a plurality of seal segments disposed adjacent one another by a retaining ring that is at least partially disposed within a cavity formed within each of the plurality of seal segments.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an adjacent second seal section, each including a base and two extending legs defining respective first and second ends of the seal. At least the first seal section includes a first plurality of slots extending from the first end to the base and a second plurality of slots extending from the second end to the base.

Abstract: A seal assembly extends along an axis and seals an axial (and/or radial) gap between a first component and a second component. The seal assembly includes a seal carrier and a seal element. The seal element extends axially (and/or radially) between a first portion and a second portion. The first portion of the seal element is slidingly arranged within a slot in an axial end (or a radial side) of the seal carrier. The second portion of the seal element is configured to axially (and/or radially) engage the second component.

Abstract: A sheath and seal assembly for protecting, containing and insulating a seal is provided. The seal may be installable within the sheath forming a seal-sheath assembly. The assembly may be capable of being installed in the hot section of a gas turbine. The sheath may be a woven, braided, and/or chain link structure. The sheath may be capable of allowing pressure to be conducted to a portion of the seal to load the seal against one or more portions of a housing.

Abstract: A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.

Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.

Abstract: An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.

Abstract: A turbine shroud for incorporation in a turbine of a gas turbine engine has a plurality of butted shroud segments circumferentially arrayed to form a ring. Each of the shroud segments has an arcuate main shroud body portion, a radially inward extending annular flange attached to a first end of the main body portion, and a radially outward extending flange with a plurality of mounting apertures attached to a second end of the main shroud body portion. A first mounting aperture is sized smaller than an adjacent second mounting aperture in the radially outward extending flange.