Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure, a thrust reverser and a fan cowl. The thrust reverser includes a forward portion and a translating sleeve. The fan cowl is axially between the nacelle inlet structure and the translating sleeve. The fan cowl axially covers the forward portion of the thrust reverser. The fan cowl is axially structurally tied to the nacelle inlet structure. The fan cowl is radially and circumferentially structurally tied to the forward portion of the thrust reverser.

Abstract: An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a first end configured to deliver heated gas to a plenum and a second end spaced from the first end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a seal system disposed proximate the second end, the seal system including a first annular seal having a radially inner end positioned proximate a flange disposed on the inner duct.

Abstract: An anti-icing system for an aircraft nacelle includes an inner duct and an outer duct. The inner duct extends through a first bulkhead between a gas turbine engine and a plenum of the nacelle. The inner duct is configured to deliver heated gases from the gas turbine engine to the plenum. The outer duct includes a first end and a second end. The outer duct circumferentially encompasses at least a portion of the inner duct on a first side of the bulkhead. At least one of the first end and the second end of the outer duct is mounted to at least one of the respective first bulkhead and a second bulkhead by a bellows forming an annular seal between the respective bulkhead and the outer duct.

Abstract: An exhaust assembly may include an exhaust body and a pivoting attachment feature. The exhaust body, such as a center body or a nozzle, may be configured to direct an annular exhaust stream exiting from a gas turbine engine. The pivoting attachment feature may be coupled the exhaust body and may be configured to pivotally couple the exhaust body to an engine flange. The pivoting attachment feature may be one of a plurality of attachment features circumferentially distributed around the exhaust body. The exhaust body may be a center body and the plurality of attachment features may be coupled to a radially inward surface the center body. The pivoting attachment feature may enable a degree of relative thermal expansion movement between the engine flange/turbine exhaust case and the exhaust body while mitigating detrimental thermal loads, according to various embodiments.

Abstract: An exhaust assembly may include an exhaust body and a pivoting attachment feature. The exhaust body, such as a center body or a nozzle, may be configured to direct an annular exhaust stream exiting from a gas turbine engine. The pivoting attachment feature may be coupled the exhaust body and may be configured to pivotally couple the exhaust body to an engine flange. The pivoting attachment feature may be one of a plurality of attachment features circumferentially distributed around the exhaust body. The exhaust body may be a center body and the plurality of attachment features may be coupled to a radially inward surface the center body. The pivoting attachment feature may enable a degree of relative thermal expansion movement between the engine flange/turbine exhaust case and the exhaust body while mitigating detrimental thermal loads, according to various embodiments.

Abstract: Sliding fastener systems can include a fastener configured to fixedly attach to a first component having a first thermal expansion coefficient, a tray configured to fixedly attach to a second component having a second thermal expansion coefficient different from the first thermal expansion coefficient, the tray defining a sliding surface, and at least a portion of a locking element configured to engage with the fastener, the locking element having a base with a contact surface that movably contacts the sliding surface of the tray when the tray, the fastener, and the locking element fasten the first component and the second component together. The fastener and the locking element are configured to move with the first component and the tray is configured to move relative to the fastener and the locking element with the second component when there is a differential thermal expansion between the first and second components.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure, a thrust reverser and a fan cowl. The thrust reverser includes a forward portion and a translating sleeve. The fan cowl is axially between the nacelle inlet structure and the translating sleeve. The fan cowl axially covers the forward portion of the thrust reverser. The fan cowl is axially structurally tied to the nacelle inlet structure. The fan cowl is radially and circumferentially structurally tied to the forward portion of the thrust reverser.

Abstract: Aspects of the disclosure are directed to a system for an aircraft comprising: a titanium bottle section that includes at least two sections configured to house an engine, and at least one bifurcation panel coupled to the bottle section, wherein the at least one bifurcation panel includes a material that is different from titanium.

Abstract: Sliding fastener systems can include a fastener configured to fixedly attach to a first component having a first thermal expansion coefficient, a tray configured to fixedly attach to a second component having a second thermal expansion coefficient different from the first thermal expansion coefficient, the tray defining a sliding surface, and at least a portion of a locking element configured to engage with the fastener, the locking element having a base with a contact surface that movably contacts the sliding surface of the tray when the tray, the fastener, and the locking element fasten the first component and the second component together. The fastener and the locking element are configured to move with the first component and the tray is configured to move relative to the fastener and the locking element with the second component when there is a differential thermal expansion between the first and second components.

Abstract: Aspects of the disclosure are directed to a system for an aircraft comprising: a titanium bottle section that includes at least two sections configured to house an engine, and at least one bifurcation panel coupled to the bottle section, wherein the at least one bifurcation panel includes a material that is different from titanium.