Structure for feeding air to an auxiliary power unit in an aircraft

Patent metadata

Field	Value
Publication number	US-10625874-B2
Application number	US-201414763796-A
Country	US
Kind code	B2
Filing date	Jan 23, 2014
Priority date	Jan 29, 2013
Publication date	Apr 21, 2020
Grant date	Apr 21, 2020

Abstract

The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the auxiliary power unit; a unit (4) for controlling the airflow fed to the auxiliary power unit; and a valve (31) for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (30), the opening of the valve being driven by the control unit (4). The structure is characterized in that it further comprises a circuit (32) for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

First claim

The invention claimed is:

1. An architecture for supplying air to an auxiliary power unit of an aircraft, comprising a pressurized cabin, a circuit for exhausting air from the cabin to the outside of the aircraft, and an auxiliary power unit of the type including a combustion chamber for fuel, the architecture including:
a supply duct for supplying air coming from outside the aircraft to the auxiliary power unit,
a unit for controlling the flow of air supplied to the auxiliary power unit via said supply duct,
a first valve for admitting air from outside the aircraft, positioned at the inlet to the supply duct, the opening of said first valve being controlled by the control unit,
a circuit for injecting air coming from the pressurized cabin into the supply duct,
wherein the circuit for injecting air is connected to the circuit for exhausting air toward the outside of the aircraft through a distribution valve, the opening whereof is controlled by the control unit to draw a proportion of a flow of air circulating in the exhaust circuit and to inject said proportion of the flow of air into the supply duct through a nozzle located at the exit of the of the injection circuit,
wherein the control unit controls the distribution valve to provide a continuously variable proportion of air between a first proportion wherein the entirety of the flow of air circulating in the exhaust circuit is drawn, and a second proportion wherein a zero proportion of air circulating in the exhaust circuit is drawn,
wherein said first valve and said distribution valve are each progressively controlled by said control unit so that the flow of air supplied to the auxiliary power unit is a determined variable mixture of air supplied from said air from outside the aircraft and said air from said pressurized cabin, said determined variable mixture determined by operation of said control unit.

2. The architecture according to claim 1 , wherein the control unit is designed to control the opening of the outside air admission valve and the opening of the distribution valve depending on a phase of operation of the auxiliary power unit.

3. The architecture according to claim 1 , wherein the control unit is designed to control the opening of the outside air admission valve and the opening of the distribution valve according to a rotation speed of a rotating shaft of the auxiliary power unit.

4. An aircraft comprising a pressurized cabin and an auxiliary power unit, wherein said aircraft further includes an architecture for supplying air to the auxiliary power unit according to claim 1 .

5. A method for supplying air to an auxiliary power unit of the type having a combustion chamber for fuel, in an aircraft comprising a pressurized cabin, an exhaust circuit for exhausting air from the cabin to the outside of the aircraft, an auxiliary power unit of the type including a combustion chamber for fuel, and an injection circuit for injecting air coming from the pressurized cabin into a supply duct of the auxiliary power unit, said method comprising steps of:
supplying a flow of air coming from outside the aircraft to the auxiliary power unit through the supply duct,
controlling the flow of air supplied to the auxiliary power unit via said supply duct by:
controlling opening of a first valve for admitting air from outside the aircraft, said first valve being positioned at an inlet to the supply duct,
injecting air coming from the pressurized cabin into the supply duct,
controlling an opening of a distribution valve to provide a continuously variable proportion of air between a first proportion wherein the entirety of the flow of air circulating in the exhaust circuit is drawn, and a second proportion wherein a zero proportion of air circulating in the exhaust circuit is drawn, wherein the distribution valve connects the circuit for injecting air is connected to the circuit for exhausting air toward the outside of the aircraft to draw a proportion of a flow of air circulating in the exhaust circuit and to inject said proportion of the flow of air into the supply duct through a nozzle located at the exit of the of the injection circuit,
wherein said controlling of said first valve and said distribution valve is progressive so that the flow of air supplied to the auxiliary power unit is determined variable mixture of air supplied from said air from outside the aircraft and said air from said pressurized cabin, said determined variable mixture determined by operation of a control unit.

6. The method according to claim 5 , wherein the proportion of flow of air circulating in the exhaust circuit and the proportion of flow of air into the supply duct are controlled according to a rotation speed of a rotating shaft of the auxiliary power unit.

7. The method according to claim 5 , wherein,
during a starting phase of the auxiliary power unit, the supply of air to said unit comes exclusively from the air recovered from the pressurized cabin, and
during a transitional phase between the starting phase and a stabilized operation phase, the supply of air to the auxiliary power unit includes an increasing flow of air coming from the outside and an increasing flow of air coming from the pressurized cabin.

8. The method according to claim 7 wherein, during a stabilized operation phase, the supply of air to the auxiliary power unit comes solely from the pressurized cabin, or comes partly from the cabin and partly from outside air.

Assignees

• Microturbo
• Safran Power Units

Inventors

• Rideau Jean-Francois
• Silet Fabien

Classifications

• B64D2033/0213

  specially adapted for auxiliary power units (APU's) · CPC title

• F02C7/08

  Heating air supply before combustion, e.g. by exhaust gases · CPC title

• F01D25/10

  Heating, e.g. warming-up before starting · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title