Self-cooled motor driven compressor

Patent metadata

Field	Value
Publication number	US-9457908-B2
Application number	US-201213623506-A
Country	US
Kind code	B2
Filing date	Sep 20, 2012
Priority date	Sep 20, 2012
Publication date	Oct 4, 2016
Grant date	Oct 4, 2016

Abstract

An nitrogen generation system for an aircraft is provided. The system includes a RAM air circuit, a motor driven compressor (MDC) having a rotor, a stator to drive rotor rotation and a compressor rotatably coupled to the rotor and a cooling system. The cooling system directs cooling air from the RAM air circuit to an inlet of the compressor and an alternative low pressure environment such that the cooling air removes heat from the stator.

First claim

The invention claimed is:

1. A nitrogen generation system for an aircraft, comprising:
a RAM air circuit;
a motor driven compressor (MDC) having a rotor, a stator to drive rotor rotation and a compressor rotatably coupled to the rotor; and
a cooling system to direct cooling air from the RAM air circuit to an inlet of the compressor and an alternative low pressure environment at an aircraft exterior such that the cooling air removes heat from the stator, the cooling system comprising a first duct extending from the RAM air circuit to the stator, a second duct extending from the stator to the aircraft exterior, a third duct extending from the second duct to the inlet and a valve arrangement configured to direct the cooling air from the second duct to the third duct,
wherein the valve arrangement comprises:
a first valve disposed along the third duct; and
a second valve disposed along the second duct, wherein
the first valve is opened and the second valve is closed when cabin air pressure and a RAM air circuit pressure are equal, and
the first valve is closed and the second valve is opened when cabin air pressure exceeds a RAM air circuit pressure.

2. The nitrogen generation system according to claim 1 , wherein the compressor is a first stage compressor and further comprising a second stage compressor rotatably coupled to the rotor.

3. The nitrogen generation system according to claim 2 , further comprising a heat exchanger fluidly disposed between the first and second stage compressors.

4. The nitrogen generation system according to claim 3 , wherein the heat exchanger is fluidly disposed between an inlet of the RAM air circuit and an aircraft exterior.

5. A nitrogen generation system for an aircraft, comprising:
a supply of cooling air;
a motor having a rotor and a stator configured to drive rotor rotation;
a compressor fluidly disposed between a cabin of the aircraft and a heat exchanger of the aircraft, the compressor having an inlet defined between the cabin and the compressor and being rotatably coupled to the rotor to form a pressure depression at the inlet; and
a cooling system disposed to provide a flow of cooling air from the supply of cooling air to the inlet and an alternative low pressure environment at an aircraft exterior such that the cooling air removes heat from the stator, wherein the cooling system comprises a first duct extending from the supply of cooling air to the stator, a second duct extending from the stator to the aircraft exterior, a third duct extending from the second duct to the inlet and a valve arrangement configured to direct the flow of cooling air from the second duct to the third duct,
wherein the valve arrangement comprises:
a first valve disposed along the third duct; and
a second valve disposed along the second duct, wherein the first valve is opened and the second valve is closed when cabin air pressure and a pressure of the supply of cooling air are equal, and
the first valve is closed and the second valve is opened when cabin air pressure exceeds a pressure of the supply of cooling air.

6. The nitrogen generation system according to claim 5 , wherein the compressor is a first stage compressor and further comprising a second stage compressor rotatably coupled to the rotor.

7. The nitrogen generation system according to claim 6 , wherein the heat exchanger is fluidly disposed between the first and second stage compressors.

8. The nitrogen generation system according to claim 5 , wherein the heat exchanger is fluidly disposed between an inlet of the supply of cooling air and an aircraft exterior.

Assignees

• Surawski Eric
• Hamilton Sundstrand Corp

Inventors

• Surawski Eric

Classifications

• B64D2013/0677

  comprising on board oxygen generator systems · CPC title

• B64D37/32 Primary

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title

• B64D13/08 Primary

  the air being heated or cooled · CPC title

• B64D2013/0618

  with arrangements for reducing or managing bleed air, using another air source, e.g. ram air · CPC title

• B64D2013/0659

  comprising provisions for cooling fuel systems · CPC title