Fuel tank inerting system

Claim 2

A fuel tank inerting system for an enclosed volume in a helicopter having a turbine engine for producing bleed air, said system comprising: separating means including tubular membranes having walls within a housing, inlet means for feeding air into a first end of said tubular membranes, first outlet means for passing gas from a second end of said tubular membranes, and second outlet means for passing gas passed through said tubular membrane walls; means for feeding engine bleed air to said inlet means such that oxygen depleted gas is passed from said first outlet means and oxygen enriched gas is passed from said second outlet means; means for feeding oxygen depleted gas from said first outlet means to said enclosed volume for preventing gas in said enclosed volume from attaining an oxygen concentration greater than about 9%; jet pump means; means for feeding engine bleed air to said jet pump for creating a low pressure stream exhausted overboard; and means for connecting said jet pump low pressure stream to said second outlet means for exhausting said oxygen enriched gas overboard and maintaining a predetermined pressure differential across said tubular membrane walls.

Claim 3

The system of claim 1 additionally including wash means for feeding engine bleed air into said separating means housing outside said tubular membrane walls to help propel said oxygen enriched gas through said second means.

Claim 6

An inerting system for an enclosed volume in an aircraft having a limited supply pressure of pressurized air, said system comprising: a source of pressurized air; separating means for receiving the pressurized air and producing an oxygen depleted portion and an other portion in relation to a pressure differential across said separating means, said separating means comprising a housing containing tubular membranes having walls for receiving pressurized air therein and passing said other portion through said walls; means for feeding the oxygen depleted portion to said enclosed volume; jet pump means receiving pressurized air and withdrawing the other portion of air from said separating means to be exhausted for increasing said pressure differential and maintaining a predetermined pressure differential across said tubular membrane walls; and means for controlling temperature of the pressurized air received by said separating means, comprising: a first flow path for said pressurized air; a second flow path for said pressurized air including heat exchanger means; sensor means for producing an output corresponding to the temperature of air received by said separating means; and valve means receiving air from said first and second flow paths and mixing said air in proportion responsive to said sensor means output.

Claim 7

An inerting system for an enclosed volume in an aircraft having a limited supply pressure of pressurized air, said system comprising: a source of pressurized air; separating means for receiving the pressurized air and producing an oxygen depleted portion and an other portion in relation to a pressure differential across said separating means, said separating means comprising a housing containing tubular membranes having walls for receiving pressurized air therein and passing said other portion through said walls; means for feeding the oxygen depleted portion to said enclosed volume; jet pump means receiving pressurized air and withdrawing the other portion of air from said separating means to be exhausted for increasing said pressure differential and maintaining a predetermined pressure differential across said tubular membrane walls; and means for controlling temperature of the pressurized air received by said separating means, comprising: a first flow path for said pressurized air; a second flow path for said pressurized air including heat exchanger means; sensor means for producing an output corresponding to the temperature of air received by said separating means; and valve means receiving air from said first and second flow paths and mixing said air in proportion responsive to said sensor means output.

Claim 8

The system of claim 4 additionally including wash means for feeding pressurized air into said housing outside said tubular membranes.

Claim 9

The system of claim 4 wherein said oxygen depleted portion contains less than 9% oxygen.

Claim 10

The system of claim 4 wherein said aircraft has environmental control means for producing cooled air and including means for supplying cooled air from said environmental control means for removing heat from said heat exchanger.

Claim 11

The system of claim 7 wherein said aircraft is a helicopter.

Claim 12

The system of claim 8 wherein said helicopter has a turbine engine and said source of pressurized air comprises bleed air from said engine.

Claim 13

The system of claim 4 wherein said aircraft is an airplane and including means for supplying ram air for removing heat from said heat exchanger.