A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.

Blade outer air seal for a gas turbine engine

One exemplary embodiment of this disclosure relates to a gas turbine engine including an engine case, a retention block attached to the engine case, and a blade outer air seal (BOAS). The BOAS includes a plurality of layers formed of a ceramic matrix composite (CMC) material. At least one of the plurality of layers provides a slot receiving a portion of the retention block.

Blade outer air seal made of ceramic matrix composite

An example blade outer air seal support assembly (50) includes a main support member (54) configured to support a blade outer air seal (60). The main support member (54) extends generally axially between a leading edge portion (56) and a trailing edge portion (58). The leading edge portion (56) is configured to be slidably received within a groove (62) established by the blade outer air seal (60). A support tab (68) extends radially from the support member (54) toward the blade outer air seal (60). The support tab (68) is configured to contact an extension of the blade outer air seal (60) to limit relative axial movement of the blade outer air seal (60). A gusset (72) spans between the support tab (68) and the support member (54). The blade outer air seal (60) has an inwardly facing surface (80). A blade path portion (102) of the inwardly facing surface is axially aligned with a tip (78) of a rotating blade (76). A peripheral portion (104) of the inwardly facing surface (80) is located axially in front of the blade path portion (102), axially behind the blade path portion, or both. The blade outer air seal establishes cooling paths that terminate at a plurality of apertures (110) established within the inwardly facing surface (80) and located exclusively within the blade path portion (102).

Blade outer air seal assembly and support

A gas turbine engine component (54) has a filter (86) mounted adjacent an impingement cavity (80) to filter particles out of a secondary cooling airflow outboard of a cooling channel (84) in communication with the secondary cooling airflow.

Filter system for blade outer air seal

A blade outer air seal (BOAS) support segment for supporting at least one BOAS segment of a static turbine shroud of a gas turbine engine, includes a radially and outwardly extending front leg for engagement with an outer case of the engine. The BOAS support segment further includes a pair of radially elongated rear prongs circumferentially spaced apart from each other and radially outwardly abutting the outer case.

Blade outer air seal support

A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions.

Blade outer air seal

A material (90) having a plurality of impurity collection spaces (96) has an outer face facing into a cooling air flow stream (70) for a gas turbine engine component. Impurities such as sand or dirt will collect in the plurality of spaces (96). In a disclosed embodiment, a honeycombed material is utilized.

Particle collector for gas turbine engine

A seal assembly includes a first component, a second component, a first seal, a first shelf, a second shelf, and a second seal. The second component is adjacent to the first component and forms a cavity between the first and second components. The first seal spans the cavity. The first shelf extends axially from the first component and is located between the first seal and a hot gas path. The second shelf extends axially from the second component and is located between the first shelf and the hot gas path; the second shelf together with the first shelf forms a flow channel. The second seal conforms to the first shelf, sealing the flow channel.

Seal ring for gas turbine engines

An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.

Turbine abradable air seal system

A component for a turbomachine includes an annular body (101) defining an inner diameter portion (102A) and an outer diameter portion (102B), and a crack guiding slot (105; 405; 505) defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter 5 portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure (151) of a turbomachine. The inner diameter portion can be mountable to a turbine vane (153).

Michael J. Bruskotter

Papers

Blade outer air seal

Particle collector for gas turbine engine

Seal ring for gas turbine engines

Turbine abradable air seal system

Slots for turbomachine structures