Passive internal compartment exhaust for an aircraft propulsion system
AssigneeRohr, Inc.
InventorBrian A. Sherman
Life of this patent
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Abstract
An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inner structure that extends axially along and circumferentially about an axial centerline. 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. An aft end portion of the cowl is also configured to form an outer radial periphery of a compartment exhaust to the internal compartment. The aft end portion of the cowl includes a plurality of axial fingers arranged circumferentially about the axial centerline in an array.
Claims16
An assembly for an aircraft propulsion system, comprising:
- a nacelle inner structure extending axially along and circumferentially about an axial centerline, the 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 an aft end portion of the cowl further configured to form an outer radial periphery of a compartment exhaust to the internal compartment;
- the aft end portion of the cowl comprising a plurality of first axial fingers arranged circumferentially about the axial centerline in a first array, and each of the plurality of first axial fingers configured to deflect radially outward when fluid pressure within the internal compartment rises over a predetermined value;
- the aft end portion of the cowl further comprising a plurality of second axial fingers arranged circumferentially about the axial centerline in a second array;
- the first array radially outboard of and overlapping the second array;
- and
- 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.
An assembly for an aircraft propulsion system, comprising:
- a nacelle inner structure comprising an internal compartment and an inner barrel;
- the internal compartment configured to house a core of a gas turbine engine;
- the inner barrel extending circumferentially about and axially along the internal compartment, and an aft end portion of the inner barrel configured to at least partially form a compartment exhaust for the internal compartment;
- the aft end portion of the inner barrel further configured to passively deform to increase a cross-sectional area of the compartment exhaust when fluid pressure within the internal compartment rises above a predetermined value;
- the aft end portion of the inner barrel comprising a plurality of first fingers and a plurality of second fingers;
- the plurality of first fingers arranged in a first array about an axial centerline;
- the plurality of second fingers arranged in a second array about the axial centerline;
- and
- a surface of a first of the plurality of first fingers configured to radially engage a surface of a first of the plurality of second fingers.
An assembly for an aircraft propulsion system, comprising:
- a nacelle inner structure comprising an internal compartment and an inner barrel, an aft end portion of the inner barrel configured to at least partially form a compartment exhaust for the internal compartment, the compartment exhaust configured to direct fluid out of the internal compartment into an environment outside of the aircraft propulsion system;
- and
- a gas turbine engine comprising an engine core housed within the internal compartment;
- wherein the aft end portion of the inner barrel comprises a plurality of slots arranged circumferentially about an axial centerline of the aircraft propulsion system, each of the plurality of slots extends partially axially into the inner barrel from an aft end of the inner barrel, and a first of the plurality of slots having a lateral width that is uniform along at least a portion of a length of the first of the plurality of slots.
Dependencies are inferred from the claim text.