Apparatus for aircraft with high peak power equipment

Patent metadata

Field	Value
Publication number	US-9328661-B2
Application number	US-201213667079-A
Country	US
Kind code	B2
Filing date	Nov 2, 2012
Priority date	Nov 3, 2011
Publication date	May 3, 2016
Grant date	May 3, 2016

Abstract

An apparatus is provided for supplying electrical power and cooling for an aircraft. The apparatus includes a cooling turbine coupled to a shaft, a compressor coupled to the shaft, and including an input for receiving engine bleed air or ambient air, and an output for discharging compressed air, a flywheel coupled to the shaft, a power turbine coupled to the shaft, and a starter generator coupled to the shaft between the compressor and the power turbine.

First claim

What is claimed is:

1. An apparatus for providing electrical power and cooling for an aircraft, the apparatus comprising:
a cooling turbine connected to a shaft;
a compressor connected to the shaft, and including an input for receiving engine bleed air or ambient air, and an output for discharging compressed air;
a flywheel connected to the shaft;
a power turbine connected to the shaft; and
a starter generator connected to the shaft between the compressor and the power turbine, wherein during periods of transient or peak power requirements, kinetic energy stored in the flywheel is converted into electrical power by the starter generator.

2. The apparatus of claim 1 , further comprising:
a combustion chamber coupled to the power turbine; and
a valve for connecting the combustion chamber to the output of the compressor.

3. The apparatus of claim 1 , wherein the starter generator is connected to an energy accumulator unit bus through an inverter control unit.

4. The apparatus of claim 3 , further comprising:
a power distribution system connected to receive electrical power from the energy accumulator unit bus.

5. An apparatus for providing electrical power and cooling for an aircraft, the apparatus comprising:
a cooling turbine coupled to a shaft;
a compressor coupled to the shaft, and including an input for receiving engine bleed air or ambient air, and an output for discharging compressed air;
a flywheel coupled to the shaft;
a power turbine coupled to the shaft; and
a starter generator coupled to the shaft between the compressor and the power turbine, wherein the power distribution system comprises:
a first generator configured to supply power to a first power distribution unit;
a second generator configured to supply power to a second power distribution unit;
a first switch for connecting an energy accumulator unit bus to the first power distribution unit; and
a second switch for connecting the energy accumulator unit bus to the second power distribution unit.

6. The apparatus of claim 5 , further comprising:
a solid state power controller connected between the first switch and the first power distribution unit.

7. The apparatus of claim 6 , further comprising:
an inverter control unit connected between the first generator and the first power distribution unit; and
a vehicle management computer configured to provide control signals to the inverter control unit and the solid state power controller.

8. The apparatus of claim 7 , further comprising:
a first permanent magnet generator coupled to the first generator; and
a first converter regulator unit connected to transmit electrical power from the first permanent magnet generator to the vehicle management computer.

9. The apparatus of claim 8 , further comprising:
a second permanent magnet generator coupled to the second generator; and
a second converter regulator unit connected to transmit electrical power from the first permanent magnet generator to a second vehicle management computer.

10. The apparatus of claim 5 , further comprising:
a first ultra capacitor; and
a third switch for connecting the first ultra capacitor to the first power distribution unit.

11. The apparatus of claim 10 , further comprising:
a second ultra capacitor connected to the energy accumulator unit bus.

Assignees

• Northrop Grumman Systems Corp

Inventors

• Ho Yuhang
• Knowles Jeffrey A

Classifications

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• B64D2013/0674

  comprising liquid subsystems · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02C3/13

  having variable working fluid interconnections between turbines or compressors or stages of different rotors {(controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075)} · CPC title

• Y02T50/56

  Cross-Sectional Technologies · mapped topic