Abstract: A rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially around an axial centerline and include a first seal shoe. The first seal shoe includes a first seal shoe base and a first seal shoe rib that projects axially out from the first seal shoe base to an axial distal end of the first seal shoe rib. The seal base extends circumferentially around the axial centerline. The spring elements include a first spring element that connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. The secondary seal assembly includes a free floating seal plate that axially contacts and is configured to slide radially along the first seal shoe rib.

Abstract: A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.

Abstract: A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.

Abstract: A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a precooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the precooler into a core compartment.

Abstract: A core compartment aft vent is disclosed. The core compartment aft vent may include a flexible core engine cowl surrounding a core engine case. A plurality of circumferentially spaced bumpers may be disposed within the aft vent and in operative contact with the flexible core engine cowl.

Abstract: A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.

Abstract: A core compartment aft vent is disclosed. The core compartment aft vent may include a flexible core engine cowl surrounding a core engine case. A plurality of circumferentially spaced bumpers may be disposed within the aft vent and in operative contact with the flexible core engine cowl.