Nacelle cowl deflection limiter
An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inner structure and a deflection limiter. The nacelle inner structure includes an internal compartment and a cowl. The internal compartment is configured to house a core of a gas turbine engine. The cowl is configured to form an outer radial periphery of the internal compartment. The cowl is also configured to form an outer radial periphery of a compartment exhaust to the internal compartment at an aft end of the cowl. The deflection limiter is attached to the cowl. The deflection limiter is configured to limit radial outward movement of the cowl.
1. An assembly for an aircraft propulsion system, comprising:
a nacelle inner structure comprising an internal compartment and a cowl;
the internal compartment configured to house a core of a gas turbine engine;
the cowl configured to form an outer radial periphery of the internal compartment, and the cowl further configured to form an outer radial periphery of a compartment exhaust to the internal compartment at an aft end of the cowl;
a deflection limiter attached to the cowl, the deflection limiter configured to limit radial outward movement of the cowl, the deflection limiter extending radially between an inner end and an outer end, the deflection limiter comprising a mounting aperture at the outer end, and the mounting aperture comprising a slot; and
a fastener mated with the mounting aperture to attach the deflection limiter to the cowl, and the fastener configured to move laterally within the slot.
2. The assembly of claim 1 , wherein the deflection limiter is configured to limit radial outward movement of the cowl at the aft end of the cowl.
3. The assembly of claim 1 , wherein the deflection limiter is further configured to enable a predefined amount of radial movement of the cowl.
4. The assembly of claim 1 , further comprising:
the gas turbine engine;
the deflection limiter attached to and extending radially between the cowl and a case of the core of the gas turbine engine.
5. The assembly of claim 1 , wherein the deflection limiter comprises a damper.
6. The assembly of claim 1 , wherein the compartment exhaust is configured to direct fluid out of the internal compartment into an environment outside of the nacelle inner structure.
7. The assembly of claim 1 , further comprising a core nozzle configured to form an inner radial periphery of the compartment exhaust and to form an outer radial periphery of a core exhaust.
8. The assembly of claim 1 , wherein the cowl is further configured to form an inner radial periphery of a bypass flowpath within the aircraft propulsion system.
9. The assembly of claim 1 , wherein the deflection limiter comprises a turnbuckle.
10. An assembly for an aircraft propulsion system, comprising:
a nacelle inner structure comprising an internal compartment and a cowl;
the internal compartment configured to house a core of a gas turbine engine;
the cowl configured to form an outer radial periphery of the internal compartment, and the cowl further configured to form an outer radial periphery of a compartment exhaust to the internal compartment at an aft end of the cowl;
a deflection limiter attached to the cowl, the deflection limiter configured to limit radial outward movement of the cowl, the deflection limiter extending radially between an inner end and an outer end, the deflection limiter comprising a slot; and
a fastener mated with the slot, the fastener configured to attach the deflection limiter to a fixed structure located radially inboard of the cowl, and the fastener configured to move laterally within the slot.
11. The assembly of claim 10 , wherein the deflection limiter comprises a turnbuckle.
12. The assembly of claim 10 , wherein the deflection limiter comprises a damper.
13. The assembly of claim 10 , wherein the deflection limiter is configured to limit radial outward movement of the cowl at the aft end of the cowl.
14. An assembly for an aircraft propulsion system, comprising:
a nacelle inner structure comprising an internal compartment and a cowl;
the internal compartment configured to house a core of a gas turbine engine;
the cowl configured to form an outer radial periphery of the internal compartment, and the cowl further configured to form an outer radial periphery of a compartment exhaust to the internal compartment at an aft end of the cowl; and
a deflection limiter attached to the cowl, the deflection limiter configured to limit radial outward movement of the cowl, and comprising a turnbuckle.
15. The assembly of claim 14 , wherein the deflection limiter is configured to limit radial outward movement of the cowl at the aft end of the cowl.
16. The assembly of claim 14 , wherein the deflection limiter is configured to enable a predefined amount of radial movement of the cowl.
17. The assembly of claim 14 , further comprising:
the gas turbine engine;
the deflection limiter attached to and extending radially between the cowl and a case of the core of the gas turbine engine.
18. The assembly of claim 14 , wherein the compartment exhaust is configured to direct fluid out of the internal compartment into an environment outside of the nacelle inner structure.
19. The assembly of claim 14 , further comprising a core nozzle configured to form an inner radial periphery of the compartment exhaust and to form an outer radial periphery of a core exhaust.
20. The assembly of claim 14 , wherein the cowl is further configured to form an inner radial periphery of a bypass flowpath within the aircraft propulsion system.