Abstract: A blade outer air seal arc segment includes a ceramic matrix composite body that defines a core gaspath side, a non-core gaspath side opposite the core gaspath side, a forward end, an aft end, and circumferential sides. The ceramic matrix composite body has first and second flanges on the non-core gaspath side. The ceramic matrix composite body is comprised of fiber plies disposed in a ceramic matrix. The fiber plies include flange fiber plies that have a +/?15-75 degree ply layup arrangement.

Abstract: A gas turbine engine includes a turbine section that has a ceramic matrix composite body that defines a core gaspath side that a row of blades, a forward end, an aft end, and circumferential sides. The forward end abuts at least one vane of a first row of vanes, and the aft end including a seal channel. A compliant seal is disposed in the seal channel and seals against at least one vane of a second row of vanes.

Abstract: A gas turbine engine includes a turbine section that has a retainer ring, a first vane that bears against the retainer ring to prevent movement of the first vane in a first axial direction, a second vane axially spaced from the first vane, and a blade axially between the first vane and the second vane. A blade outer air seal is situated radially outwardly of the blade. The blade outer air seal includes a ceramic matrix composite body that defines a core gaspath side that faces the blade, a forward end, an aft end, and circumferential sides. There is a spring seal at the aft end of the blade outer air seal that seals against the second vane. The spring seal provides a preload that biases the blade outer air seal against the first vane and thereby biases the first vane against the retainer ring.

Abstract: There is a blade outer air seal positioned to be radially outward of blades in the rotating blade row relative to the rotational axis. There is at least one brush seal having bristles extending from a mount location radially inward to contact a sealing surface on the blade outer air seal. An angle is defined between the bristles and relative to the sealing surface having a radially inward extending component, and with an axial component in a direction toward a leading edge attachment feature and a trailing edge attachment feature, and the angle is less than 90° on a side of the brush seal opposite the leading edge and trailing edge mount hooks. A gas turbine engine component is also disclosed.

Abstract: Apparatus and a method for separating elongate elements one at a time from a batch of elements. The apparatus comprises a batch receiver means having an inclined support face to support the leading element of the batch, and element ejector means including at least one finger engageable with the trailing element of said batch to lift said trailing element in an upwardly forward direction to separate said element from said batch.