US 6,585,191 B2Granted

Air inlet cowl for a jet engine, provided with deicing means

AssigneeAirbus France

InventorsRobert Andre, Alain Porte

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Abstract

An air inlet cowl for a jet engine, particularly an aeroengine, includes a leading edge deicer, a hollow leading edge defining an internal peripheral chamber, closed by a first internal partition, and an exhaust orifice, in the leading edge, connecting the internal chamber with the outside. The cowl further includes a pressurized hot air feedpipe for being connected, at its rear end away from the leading edge and passing through a second internal partition, to a pressurized hot air circuit and, at its front end toward the leading edge, to an injector of pressurized hot air into the internal chamber, a protective internal casing functioning with the first and second internal partitions to define an isolation volume enclosing the feedpipe, and an air extraction opening, in the first partition, to place the isolation volume in communication with the internal peripheral chamber. The area of this extraction opening is such that, in the event of damage to the feedpipe, the elimination of pressurized hot air in the isolation volume does not impair the protective internal casing and the injector injects into the internal chamber a pressurized hot air flow rate at least equal to 50% of the hot air flow rate in the feedpipe.

Claims8

Dependent claims

An air inlet cowl for a jet engine, particularly an aeroengine, said air inlet cowl being provided with means for deicing its leading edge, and comprising:

a hollow leading edge delimiting an internal peripheral chamber, closed by a first internal partition;
at least one exhaust orifice placing said internal chamber in communication with the outside and made in said hollow leading edge;
a pressurized hot air feedpipe capable of being connected, at its rear end away from said leading edge and passing through a second internal partition, to a pressurized hot air circuit and, at its front end toward said leading edge, to an injector injecting said pressurized hot air into said internal chamber of the leading edge;
a protective internal casing collaborating with said first and second internal partitions to delimit an isolation volume enclosing said feedpipe;
and
an air extraction opening made in said first partition to place said isolation volume enclosing said feedpipe in communication with said internal peripheral chamber of said leading edge, the area of this extraction opening being chosen from a range of values such that, in the event of damage to said hot air feedpipe:
the elimination of pressurized hot air in said isolation volume is not detrimental to said protective internal casing;
and
the injector injects into said internal chamber a pressurized hot air flow rate at least equal to 50% of the hot air flow rate in said feedpipe.

6 more elements

Dependencies are inferred from the claim text.

Facts

Application: 10/103,716Filed 25 Mar 2002
Priority: FR 01 0519417 Apr 2001
Published: US 2002/0148929 A117 Oct 2002
Granted: 1 Jul 2003
Term ends: Not estimatedThe source records don’t support an estimate.

Classification9 codes

B64D 15/04
By ducted hot gas or liquid: hot gas application
B64D 33/02
Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for: of combustion air intakes
F02C 7/047
Air intakes for gas-turbine plants or jet-propulsion plants: heating to prevent icing
B64D 2033/0233
Of combustion air intakes: comprising de-icing means