Abstract: An aircraft propulsor with a thrust reverser with a pressure relief system is disclosed herein. The aircraft propulsor can include a flow path and a blocker door configured to block the flow path to divert airflow within the flow path to generate reverse thrust. The blocker door can include a main door and a pressure relief door. The pressure relief door can be coupled to the main door and configured to move from a closed position to an open position in response to flow path pressure greater than a threshold pressure. Moving the pressure relief door to the open position can relieve flow path pressure.

Abstract: High-pressure fan duct bleed air is used to pressurize a cavity between the fan duct inner wall and the inner wall thermal insulation blankets. The cavity is pressurized to prevent hot air from the nacelle core compartment from flowing under the insulation blankets and degrading the fan duct inner wall. Pressure regulating valves (PRV) allow better control of the cavity pressure during different phases of the flight profile and under different levels of insulation blanket seal degradation by passively controlling exit area from the cavity based on an established pressure limit. Moreover, the pressurization system can be implemented as a passive cooling system by increasing the mass flow rate into the cavity and then the core compartment to a level suitable for core compartment cooling.

Abstract: Seal systems for aircraft are disclosed. An example seal system includes a first seal to couple to a first thrust reverser portion, the first seal having a first cross-sectional shape. A second seal is to couple to a second thrust reverser portion opposite the first seal. The second seal having a second cross-sectional shape different than the first cross-sectional shape. The second seal is to receive at least a portion of the first seal in response to the first seal engaging the second seal.

Abstract: In an example, method of inspecting a thermal protection apparatus is described. The apparatus comprises a composite wall and a thermal insulation blanket, where the thermal insulation blanket is coupled to the wall by way of a sealant disposed around, and offset from, a perimeter of the composite wall and disposed between the composite wall and the thermal insulation blanket, and where the wall, the thermal insulation blanket, and the sealant form a plenum chamber within the apparatus. The method includes pressurizing the plenum chamber with pressurized air, heating the pressurized air within the plenum chamber, and inserting a liquid crystal sheet between the wall and the thermal insulation blanket and proximate to a periphery of the sealant, where the liquid crystal sheet is configured to change color when heated pressurized air exits a gap in the apparatus and heats the liquid crystal sheet.

Abstract: Drainage devices intended to prevent the reentry of drained fluids, the devices including a base having a contact surface for mounting over a drainage opening in an aerodynamic surface, a mast portion connected to the base and extending away from the contact surface of the base, and a top portion connected to the end of the mast portion, the top portion having a periphery that is greater than the periphery of the mast portion and including an exit port. The top portion may include a cantilevered fence portion extending upstream relative to the aerodynamic surface, and the drainage devices may be part of a system including a first opening and a second opening in the aerodynamic surface, the second opening upstream from the first opening, where a drainage device is mounted over the first opening and the cantilevered fence portion of the drainage device extends upstream toward the second opening.

Abstract: In an example, method of inspecting a thermal protection apparatus is described. The apparatus comprises a composite wall and a thermal insulation blanket, where the thermal insulation blanket is coupled to the wall by way of a sealant disposed around, and offset from, a perimeter of the composite wall and disposed between the composite wall and the thermal insulation blanket, and where the wall, the thermal insulation blanket, and the sealant form a plenum chamber within the apparatus. The method includes pressurizing the plenum chamber with pressurized air, heating the pressurized air within the plenum chamber, and inserting a liquid crystal sheet between the wall and the thermal insulation blanket and proximate to a periphery of the sealant, where the liquid crystal sheet is configured to change color when heated pressurized air exits a gap in the apparatus and heats the liquid crystal sheet.

Abstract: An aircraft propulsor with a thrust reverser with a pressure relief system is disclosed herein. The aircraft propulsor can include a flow path and a blocker door configured to block the flow path to divert airflow within the flow path to generate reverse thrust. The blocker door can include a main door and a pressure relief door. The pressure relief door can be coupled to the main door and configured to move from a closed position to an open position in response to flow path pressure greater than a threshold pressure. Moving the pressure relief door to the open position can relieve flow path pressure.

Abstract: Seal systems for aircraft are disclosed. An example seal system includes a first seal to couple to a first thrust reverser portion, the first seal having a first cross-sectional shape. A second seal is to couple to a second thrust reverser portion opposite the first seal. The second seal having a second cross-sectional shape different than the first cross-sectional shape. The second seal is to receive at least a portion of the first seal in response to the first seal engaging the second seal.

Abstract: High-pressure fan duct bleed air is used to pressurize a cavity between the fan duct inner wall and the inner wall thermal insulation blankets. The cavity is pressurized to prevent hot air from the nacelle core compartment from flowing under the insulation blankets and degrading the fan duct inner wall. Pressure regulating valves (PRV) allow better control of the cavity pressure during different phases of the flight profile and under different levels of insulation blanket seal degradation by passively controlling exit area from the cavity based on an established pressure limit. Moreover, the pressurization system can be implemented as a passive cooling system by increasing the mass flow rate into the cavity and then the core compartment to a level suitable for core compartment cooling.

Abstract: Drainage devices intended to prevent the reentry of drained fluids, the devices including a base having a contact surface for mounting over a drainage opening in an aerodynamic surface, a mast portion connected to the base and extending away from the contact surface of the base, and a top portion connected to the end of the mast portion, the top portion having a periphery that is greater than the periphery of the mast portion and including an exit port. The top portion may include a cantilevered fence portion extending upstream relative to the aerodynamic surface, and the drainage devices may be part of a system including a first opening and a second opening in the aerodynamic surface, the second opening upstream from the first opening, where a drainage device is mounted over the first opening and the cantilevered fence portion of the drainage device extends upstream toward the second opening.