Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.

Abstract: A support ring for a gas turbine engine includes a main body portion extending circumferentially about a center axis, a radially extending portion extending radially inward from the main body portion and having a plurality of openings, and a plurality of anti-rotation tabs extending radially inward from the main body portion and axially spaced from the radially extending portion.

Abstract: A debris separator for a gas turbine engine component includes a first body section along an axis, the first body section comprising a first orifice, a neck section adjacent to the first body section along the axis, and a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.

Abstract: A debris separator for a gas turbine engine component includes a first body section along an axis, the first body section comprising a first orifice, a neck section adjacent to the first body section along the axis, and a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.

Abstract: A gas turbine engine includes an engine static structure that provides a flow path. A metering hole is provided in the engine static structure. A strainer is arranged over the metering hole. The strainer includes multiple holes that have a total area that is greater than a metering hole area.

Abstract: A blade outer air seal support includes, at least one arc body having a first portion and a second portion, a blade outer air seal mounting region defined at least partially between the first portion and the second portion, and an interface feature interfacing the first portion and the second portion. The interface feature is configured such that axially aligned forces are communicated between the first and second portions through the interface feature, bypassing the blade outer air seal mounting region.

Abstract: A gas turbine engine assembly includes a shield that has a first portion and a second portion. The first portion extends radially from an axial end portion of the shield and includes a blade outer air seal contact surface. The second portion extends axially from a radially outer end of the first portion and includes a vane contact surface.

Abstract: A blades outer air seal includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A manifold is disposed at least partially in the pocket. The manifold subdivides the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface. The manifold includes at least one inlet and a plurality of outlets.

Abstract: A support ring for a gas turbine engine includes a main body portion extending circumferentially about a center axis, a radially extending portion extending radially inward from the main body portion and having a plurality of openings, and a plurality of anti-rotation tabs extending radially inward from the main body portion and axially spaced from the radially extending portion.

Abstract: A chamfered stator vane rail is provided. The chamfered stator vane rail may comprise a forward rail and an aft rail axially opposite the forward rail. The aft rail may comprise a leading edge and a trailing edge located axially opposite and aft of the leading edge. The aft rail may comprise a chamfered edge on a radially outer surface. The chamfered edge may be oriented at an angle relative to an axis.

Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.

Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.

Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides with the radially outer side including radially-extending sidewalls. A radially inner surface joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A rail shield has radially-extending walls lines the radially-extending sidewalls.

Abstract: A gas turbine engine includes an engine static structure that provides a flow path. A metering hole is provided in the engine static structure. A strainer is arranged over the metering hole. The strainer includes multiple holes that have a total area that is greater than a metering hole area.

Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.

Abstract: A chamfered stator vane rail is provided. The chamfered stator vane rail may comprise a forward rail and an aft rail axially opposite the forward rail. The aft rail may comprise a leading edge and a trailing edge located axially opposite and aft of the leading edge. The aft rail may comprise a chamfered edge on a radially outer surface. The chamfered edge may be oriented at an angle relative to an axis.

Abstract: A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.

Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.

Abstract: A blades outer air seal includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A manifold is disposed at least partially in the pocket. The manifold subdivides the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface. The manifold includes at least one inlet and a plurality of outlets.

Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.