Conformal heat shield for gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsJoon Ha, John P. Lucashu
Life of this patent
Estimating the term…
Abstract
A conformal heat shield for a gas turbine engine may comprise a first section including a first arcuate segment and a second arcuate segment circumferentially adjacent to the first arcuate segment. The first arcuate segment and the second arcuate segment may each comprise a distal metal layer including a plurality of loops extending radially outward from the distal metal layer. A proximal metal layer may be located radially inward of the distal metal layer. An insulating material may be located between the distal metal layer and the proximal metal layer. A first strap may be located through the loops.
Claims20
A conformal heat shield for a gas turbine engine, comprising:
- a first section including a first arcuate segment and a second arcuate segment circumferentially adjacent to the first arcuate segment, wherein the first arcuate segment of the first section and the second arcuate segment of the first section each comprises:
- a first distal metal layer including a plurality of loops extending radially outward from the first distal metal layer;
- a first proximal metal layer located radially inward of the first distal metal layer;
- and
- an insulating material located between the first distal metal layer and the first proximal metal layer;
- and
- a first strap located through the plurality of loops.
A compressor section of a gas turbine engine comprising:
- a compressor case comprising:
- a first case section including a first radially extending flange located at a forward end of the first case section and a second radially extending flange located at an aft end of the first case section;
- a second case section aft of the first case section and including a third radially extending flange located at a forward end of the second case section;
- a first fastener located through the first radially extending flange;
- and
- a second fastener located through the second radially extending flange of the first case section and the third radially extending flange of the second case section;
- a conformal heat shield located radially outward of the compressor case, the conformal heat shield including a first section comprising a first arcuate segment and a second arcuate segment circumferentially adjacent to the first arcuate segment, wherein the first arcuate segment of the first section and the second arcuate segment of the first section each comprises:
- a first distal metal layer including a plurality of loops extending radially outward from the first distal metal layer;
- a first proximal metal layer located radially inward of the first distal metal layer;
- and
- a first insulating material located between the first distal metal layer and the first proximal metal layer;
- and
- a first strap located through the plurality of loops.
A gas turbine engine, comprising
- a case structure disposed around a longitudinal axis of the gas turbine engine;
- a conformal heat shield located radially outward of the case structure, wherein a first section of the conformal heat shield comprises:
- a first distal metal layer including plurality of loops extending radially outward from the first distal metal layer;
- a first proximal metal layer located radially inward of the first distal metal layer;
- and
- a first insulating material located between the first distal metal layer and the first proximal metal layer;
- and
- a first strap located through the plurality of loops.
Dependencies are inferred from the claim text.