Abstract: A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.

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 vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.

Abstract: A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.

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 seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.

Abstract: A support assembly for a gas turbine engine includes an outer support that extends about a circumferential axis and includes at least one engagement member. An inner support forms a cavity. A control ring is located within the cavity and includes at least one tab for engaging at least one engagement member on the outer support.

Abstract: A support assembly for a gas turbine engine includes a control ring that extends about a circumferential axis. A plurality of first supports has a cavity that receives the control ring. A plurality of cover plates are attached to the first plurality of supports and enclose the cavity.

Abstract: A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.

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 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 seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.

Abstract: A support assembly for a gas turbine engine includes an outer support that extends about a circumferential axis and includes at least one engagement member. An inner support forms a cavity. A control ring is located within the cavity and includes at least one tab for engaging at least one engagement member on the outer support.

Abstract: A support assembly for a gas turbine engine includes a control ring that extends about a circumferential axis. A plurality of first supports has a cavity that receives the control ring. A plurality of cover plates are attached to the first plurality of supports and enclose the cavity.

Abstract: A gas turbine engine includes a containment ring to contain liberated compressor and turbine blades and blade fragments within a core assembly. The combination of a containment gap between the core case and the containment ring and a containment layer disposed in the gap helps dissipate the energy generated by loose body impacts on the core assembly. The containment layer deforms, deflects, and/or redirects the impact energy acting in a radial direction, thereby to improve containment.

Abstract: A gas turbine engine includes a core assembly with a core case having a containment section for containing liberated compressor and turbine blades and blade fragments. The containment section includes first and second containment layers and the containment section is configured to have a non-linear rate of energy dissipation across the first and second containment layers, thereby to improve containment of blades and blade fragments.

Abstract: A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.

Abstract: A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.

Abstract: A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.