Apparatus and method for shielding a thrust reverser structure from engine heat
AssigneeSpirit AeroSystems, Inc.
InventorJohn M. Welch
Life of this patent
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Abstract
A heat-resistant apparatus comprising a plurality of rigid, fireproof panels mounted to an inner surface of an inner fixed structure (IFS) of an aircraft thrust reverser. The plurality of panels may include fixed panels and floating panels, with the fixed panels fastened directly to the IFS and the floating panels fastened to the fixed panels in a substantially checkered arrangement along the inner surface of the IFS. The fixed and floating panels may each comprise a rigid core surrounded by various fireproof or heat resistant materials. The fixed and floating panels may be configured and affixed to the IFS such that air from an engine's fan may flow through a space between the panels and the IFS, providing additional cooling and heat resistance.
Claims18
A heat-resistant apparatus for an aircraft engine nacelle, the apparatus comprising:
- a plurality of fixed panels that are rigid and configured to be attached to an inner surface of an internal fixed structure (IFS) of a thrust reverser such that at least a portion of the fixed panels are spaced a distance away from the inner surface of the IFS such that air flows between the fixed panels and the IFS, each of the fixed panels having an inner surface and an outer surface, wherein at least one of the inner surface and the outer surface of each of the fixed panels is substantially fireproof;
- and
- a plurality of floating panels that are rigid and configured to be attached to the inner surface of at least one of the fixed panels, each of the floating panels having an inner surface and an outer surface, wherein at least one of the inner surface and the outer surface of each of the floating panels is substantially fireproof,
- wherein each of the floating panels is attached to at least one of the fixed panels,
- wherein the fixed panels and the floating panels each comprise a honeycomb core and layers of at least one of heat-resistant material and composite material.
A heat-resistant apparatus comprising
- a plurality of fixed panels that are rigid and each have an inner surface, an outer surface, a forward edge, and an aft edge, each of the fixed panels having a plurality of holes formed proximate the forward edge and the aft edge, wherein at least one of the inner surface and the outer surface of each of the fixed panels is substantially fireproof;
- and
- a plurality of floating panels that are rigid and each have an inner surface and an outer surface, wherein at least one of the inner surface and the outer surface of each of the floating panels is substantially fireproof,
- wherein the fixed panels are configured to be attached to an inner surface of an internal fixed structure (IFS) of a thrust reverser such that at least a portion of the fixed panels and the floating panels are spaced a distance away from the inner surface of the IFS, such that air flows between the panels and the IFS,
- wherein the floating panels are attached to the fixed panels in an alternating, checkered configuration proximate edges of the fixed and floating panels, such that at least a portion of the floating panels overlap at least a portion of the holes of the fixed panels, and such that the floating panels do not make physical contact with the IFS when the fixed panels are attached to the IFS,
- wherein the fixed panels and the floating panels each comprise a honeycomb core and layers of at least one of heat-resistant material and composite material.
A method of forming and installing a heat-shielding apparatus into an aircraft thrust reverser, the method comprising:
- forming a plurality of rigid honeycomb cores;
- bonding a plurality of layers of materials, including at least one heat-resistant material, onto the plurality of honeycomb cores to form a plurality of fixed panels and a plurality of floating panels;
- attaching the plurality of floating panels to a heat-resistant surface of the plurality of fixed panels;
- and
- attaching the plurality of fixed panels to an internal fixed structure of the thrust reverser between an engine and the internal fixed structure in a configuration such that air flows from a fan duct outward of the internal fixed structure into a space between the fixed panels and the floating panels and the internal fixed structure.
Dependencies are inferred from the claim text.