US 8,756,909 B2Granted

Aircraft engine protection device

AssigneeThe Ctfot Group LLC

InventorDonna Avery

Life of this patent

Estimating the term…

Loading patent…

Abstract

A jet engine intake guard includes an engine sleeve located within the nacelle of the engine; a primary deflection screen located at a front portion of the sleeve and having a first circular frame formed of a tubular fabric member and a plurality of fiber yarn strings disposed across the diameter of the primary frame and attached to one another in a tri-axel weave pattern. The guard also includes a secondary deflection screen located behind the primary deflection screen in the direction of air flow through the engine and having a second circular frame formed of a tubular fabric member and a plurality of fiber yarn strings disposed across the secondary frame and attached to one another in a tri-axel weave pattern. The guard further includes a capture basket located between the primary and secondary deflection screens. The capture basket has a first wall located toward the primary deflection screen, a center portion and a second wall located toward the secondary deflection screen. In a preferred embodiment the entire guard is made of woven carbon fiber.

Claims10

Dependent claims

A jet engine intake guard apparatus comprising:

an engine sleeve located within the nacelle of the engine;
a primary deflection screen located at a front portion of the sleeve, said primary deflection screen having a first frame formed of a tubular fabric member and a plurality of fiber yarn strings disposed across the width of the primary frame and attached to one another in a tri-axel weave pattern;
a secondary deflection screen located behind the primary deflection screen in the direction of air flow through the engine, said secondary deflection screen having a second frame formed of a tubular fabric member and a plurality of fiber yarn strings disposed across the secondary frame and attached to one another in a tri-axel weave pattern;
and
a capture basket located after the secondary deflection screen in the direction of air flow through the engine, said capture basket having a first wall located toward the secondary deflection screen, a center portion and a second wall located toward the engine, wherein the center portion has a proximal end and a distal end, wherein the proximal end is joined to the first wall, the distal end is joined to the second wall, the center portion being sized and configured to be placed against an interior surface of the nacelle.

2 more elements

Dependencies are inferred from the claim text.

Facts

Application: 12/840,935Filed 21 Jul 2010 · us provisional application
Priority: 22 Jul 2009
Published: US 2011/0016845 A127 Jan 2011
Granted: 24 Jun 2014
Term ends: Not estimatedThe source records don’t support an estimate.

Classification5 codes

B64D 33/02
Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for: of combustion air intakes
B64D 2033/022
Of combustion air intakes: comprising bird or foreign object protections
Y10T 137/0536
Fluid handling: highspeed fluid intake means [e.g., jet engine intake]
B64D
Equipment for fitting in or to aircraft