Independent power generator

Claim 2

An aircraft auxiliary power system comprising a gas turbine engine having a combustion chamber, a pressurizable aircraft cabin, a plurality of intake air compressor means, wherein the first of said intake air compressor means discharges to said pressurizable aircraft cabin and the second intake air compressor means receives intake air from said pressurizable aircraft cabin, and a ram air duct having an inlet and outlet open to the ambient atmosphere, and connected to said first intake air compressor means in order to convey air thereto; a gas turbine exhaust duct for conveying exhaust gases from said gas turbine engine to the atmosphere having an exhaust gas exit nozzle located within said ram air duct and facing downstream with respect to the air flow through said ram air duct.

Claim 3

An aircraft auxiliary power system as in claim 1 further comprising compressor inlet air duct means for conveying ambient air to the intake of the first of said plurality of intake air compressor means: cabin inlet duct means for conveying the compressed air discharge of the first of said plurality of intake air compressor means to said pressurizable aircraft cabin; cabin exhaust duct means for conveying pressurized cabin discharge air to the intake of the second of said plurality of intake air compressor means; combustion chamber inlet duct means for conveying the compressed air discharge of the last of said plurality of air compressor means to the combustion chamber of said gas turbine engine.

Claim 4

An aircraft auxiliary power system comprising: a gas turbine engine having a combustion chamber; a pressurizable aircraft cabin; a plurality of intake air compressor means for providing compressed cabin ventilation air to said pressurizable aircraft cabin and compressed intake air to said gas turbine engine; compressor inlet air duct means for conveying ambient air to the intake of the first of said plurality of intake air compressor means; cabin inlet duct means for conveying the compressed air discharge of the first of said plurality of intake air compressor means to said pressurizable aircraft cabin; cabin exhaust duct means for conveying pressurized cabin discharge air to the intake of the second of said plurality of intake air compressor means; combustion chamber inlet duct means for conveying the compressed air discharge of the last of said plurality of air compressor means to the combustion chamber of said gas turbine engine; a ram air duct having an inlet and outlet open to the ambient atmosphere, and connected to said compressor inlet air duct means in order to convey air thereto; a gas turbine exhaust duct for conveying exhaust gases from said gas turbine engine to the atmosphere having an exhaust gas exit nozzle located within said ram air duct and facing downstream with respect to the air flow through said ram air duct; means for generating electrical power; means for providing hydraulic fluid under pressure; and drive means drivingly connecting said means for generating electrical power and said means for providing hydraulic fluid under pressure to said gas turbine engine.

Claim 5

An aircraft auxiliary power system comprising: a gas turbine engine having a combustion chamber; a pressurizable aircraft cabin; a plurality of intake air compressor means for providing compressed cabin ventilation air to said pressurizable aircraft cabin and compressed intake air to said gas turbine engine; compressor inlet air duct means for conveying ambient air to the intake of the first of said plurality of intake air compressor means; cabin inlet duct means for conveying the compressed air discharge of the first of said plurality of intake air compressor means to said pressurizable aircraft cabin; cabin exhaust duct means for conveying pressurized cabin discharge air to the intake of the second of said plurality of intake air compressor means; combustion chamber inlet duct means for conveying the compressed air discharge of the last of said plurality of air compressor means to the combustion chamber of said gas turbine engine; a ram air duct having an inlet and outlet open to the ambient atmosphere, and connected to said compressor inlet air duct means in order to convey air thereto; a gas turbine exhaust duct for conveying exhaust gases from said gas turbine engine to the atmosphere having an exhaust gas exit nozzle located within said ram air duct and facing downstream with respect to the air flow through said ram air duct; means for generating electrical power; means for providing hydraulic fluid under pressure; and drive means drivingly connecting said means for generating electrical power and said means for providing hydraulic fluid under pressure to said gas turbine engine.

Claim 6

An aircraft auxiliary power system as in claim 2 further comprising; a ram air duct having an inlet and outlet open to the ambient atmosphere, and connected to said compressor inlet air duct means in order to convey air thereto.

Claim 7

An aircraft auxiliary power system as in claim 3 further comprising an air conditioning system including an air conditioning compressor drivingly connected to said gas turbine engine.

Claim 8

An aircraft auxiliary power system as in claim 3 further comprising: gas turbine means for providing aircraft main propulsion, and main engine bleed air means for conveying a portion of the compressed air discharge of a portion of the plurality of intake air compressor means to the compressor stages of said main propulsion gas turbine means for supplying compressed starting air to said main propulsion gas turbine means and further, subsequent to starting main propulsion means for conveying compressed main engine bleed air from the compressor stages of said main propulsion gas turbine means to the combustion chamber of said gas turbine engine and to said cabin inlet duct means for purpose of ventilation.

Claim 9

An aircraft auxiliary power system as in claim 6 wherein said main engine bleed air means further comprises valve means for isolating said main engine bleed air means from said cabin inlet duct means and said combustion inlet duct means.

Claim 10

An aircraft auxiliary power system as in claim 3 wherein said cabin inlet duct means further comprises a cabin pressurization heat exchanger exposed to the ambient airstream, a bypass duct around said cabin pressurization heat exchanger, and a control valve for purposes of regulating the temperature of the compressed air discharge of the first of said plurality of intake air compressor means.

Claim 11

An aircraft auxiliary power system as in claim 3 wherein said plurality of intake air compressor means consists of two shaft mounted axial flow air compressors.

Claim 12

An aircraft auxiliary power system as in claim 3 wherein said compressor inlet air duct means further comprises means for varying the inlet geometry thereof for purposes of regulating the discharge air pressure of the first of said plurality of intake air compressor means.

Claim 13

An aircraft auxiliary power system as in claim 4 wherein said combustion chamber inlet duct means further comprises; a heat exchanger located within said gas turbine exhaust duct.

Claim 14

An aircraft auxiliary power system as in claim 5 wherein said air conditioning system comprises a freon cycle air conditioning unit having a refrigerant compressor drivingly connected to the shaft of said gas turbine engine, a compressed refrigerant heat exchanger exposed to the ambient airstream and a refrigerant expansion heat exchanger located within said pressurizable aircraft cabin.

Claim 15

An aircraft auxiliary power system as in claim 7 further comprising: a freon cycle air conditioning system having a refrigerant compressor drivingly connected to the shaft of said gas turbine engine, a compressed refrigerant heat exchanger exposed to the ambient airstream and a refrigerant expansion heat exchanger located within said pressurizable aircraft cabin; and wherein said cabin inlet duct means further comprises a cabin pressurization heat exchanger exposed to the ambient airstream, a bypass duct around said cabin pressurization heat exchanger and a control valve for purposes of regulating the temperature of the compressed air contained within said cabin inlet duct means; said plurality of intake air compressor means comprises a first and a second stage axial flow air compressor drivingly connected to the shaft of said turbine engine; said compressor inlet air duct means includes a valve means for varying the inlet geometry thereof for purposes of regulating the discharge air pressure of said first stage air compressor; and said combustion chamber inlet duct means further comprises a heat exchanger located within said gas turbine exhaust duct.

Claim 16

An aircraft auxiliary power system as in claim 13 further comprising clutch means for disconnecting said plurality of intake air compressor means from the turbine of said gas turbine engine.