US 6,595,742 B2Granted

Aircraft engine air filter and method

AssigneeWestar Corporation

InventorMichael J. Scimone

Life of this patent

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Abstract

A barrier filter for use in an helicopter to remove contaminants from intake air prior to delivery to an engine. The helicopter has an intake and a peripheral external surface adjacent to the intake. The filter includes a pleated filter element mounted flush across the intake such as to meet the contour of the peripheral external surface. The filter element comprises a porous filter media and having a surface area such that a calculated speed of air flowing through the filter, when the engine is operating at take off power (TOP) or military intermediate rated power (IRP), is less than about 30 ft/sec. The filter may be retrofit into helicopters having other contaminant removal systems. Preferably, the filter is positioned such that intake air is delivered to the engine at a pressure which is substantially independent of whether the helicopter is moving in a forward direction or hovering with no forward motion.

Claims20

Dependent claims

An air induction system for a helicopter to receive intake air, remove contaminants from said intake air, and provide said intake air for delivery to an engine at a pressure which is substantially independent of whether the helicopter is moving in a forward direction or hovering with no forward motion, the helicopter having a longitudinal axis and a generally horizontal rotor, the system comprising:

a first entryway for receiving intake air, the first entryway positioned on the helicopter generally facing said forward direction and perpendicular to said longitudinal axis such that forward motion of the helicopter directs intake air to flow directly into said first entryway with an elevated pressure due to said forward motion;
a first barrier filter mounted across said first entryway, the first filter having a porous media and positioned such that all air received in said first entryway flows to said first filter;
a second entryway for receiving intake air, the second entryway positioned below said rotor and facing generally upwardly such that during hovering flight, said rotor directs intake air downwardly to flow directly into said second entryway with an elevated pressure due to downward motion;
and
a second barrier filter mounted across said second entryway, the second filter having a porous media and positioned such that all air received in said second entryway flows to said second filter.

2 more elements

Dependencies are inferred from the claim text.

Facts

Application: 09/968,762Filed 2 Oct 2001 · us provisional application
Priority: 2 Oct 2000
Published: US 2002/0182062 A15 Dec 2002
Granted: 22 Jul 2003
Term ends: Not estimatedThe source records don’t support an estimate.

Classification7 codes

B64D 33/02
Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for: of combustion air intakes
F02C 7/052
Having provisions for obviating the penetration of damaging objects or particles: with dust-separation devices
B64D 2033/0246
Of combustion air intakes: comprising particle separators
Y02T 50/60
Aeronautics or air transport: efficient propulsion technologies, e.g. for aircraft