Variable pneumatic output with constant electrical output driven by a single engine

Patent metadata

Field	Value
Publication number	US-10589874-B2
Application number	US-201816177313-A
Country	US
Kind code	B2
Filing date	Oct 31, 2018
Priority date	Jun 29, 2016
Publication date	Mar 17, 2020
Grant date	Mar 17, 2020

Abstract

In an embodiment, an integrated ground support system for an aircraft is described herein, the system including a frame on which the system is arranged as a singular assembly. An engine, drive train, alternator, bleed air unit, one or more electrical components, and air cycle machine are mounted on the frame. The engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.

First claim

What is claimed is:

1. An integrated ground support system for an aircraft, the system comprising:
a frame on which the system is arranged as a singular assembly;
an engine mounted on the frame and configured to power the system;
a drive train, an alternator, and a bleed air unit mounted on the frame, the drive train disposed between and interconnected to the engine and each of the alternator and the bleed air unit;
one or more electrical components mounted on the frame and electrically connected to the alternator, wherein the one or more electrical components is configured to produce electrical power for use by the aircraft; and
an air cycle machine mounted on the frame and connected to the bleed air unit, wherein the bleed air unit is configured to produce bleed air for use by the aircraft and the air cycle machine is configured to produce conditioned air for use by the aircraft,
wherein the engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with the electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with the bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.

2. The system of claim 1 , wherein the one or more electrical components comprises an rectifier and a power converter mounted on the frame, the rectifier disposed between and electrically connected to the alternator and the power converter, and wherein the power converter is configured to output the electrical power.

3. The system of claim 2 , wherein the alternator produces an alternating current (AC) output, the rectifier is configured to rectify the AC output to produce a direct current (DC) output, and the power converter is configured to convert the DC output to produce the electrical power.

4. The system of claim 3 , wherein a frequency of the AC output is in accordance with a rotational speed of the engine and a gear ratio of a gear mechanism associated with an output shaft included in the drive train and connected to the alternator.

5. The system of claim 2 , further comprising:
a first control loop connected to the power converter and configured to monitor and maintain the electrical power at a level required by the aircraft; and
a second control loop connected to the bleed air unit and the air cycle machine and configured to monitor and maintain the bleed air or conditioned air at a level required by the aircraft.

6. The system of claim 5 , wherein the first control loop includes a voltage sensor, a frequency sensor, and a controller, wherein the voltage and frequency sensors are configured to monitor voltage and frequency of the electrical power, and wherein the controller is configured to process the monitored voltage and frequency and determine adjustment to production of the electrical power by the power converter.

7. The system of claim 5 , wherein the second control loop includes a first pressure sensor, a second pressure sensor, and a controller, wherein the first pressure sensor is configured to monitor pressure of the bleed air and the second pressure sensor is configured to monitor pressure of the conditioned air, and wherein the controller is configured to process the monitored pressure and determine adjustment to a rotational speed of the engine.

8. The system of claim 5 , wherein the second control loop includes a first temperature sensor, a second temperature sensor, and a controller, wherein the first temperature sensor is configured to monitor temperature of the bleed air and the second temperature sensor is configured to monitor temperature of the conditioned air, and wherein the controller is configured to process the monitored temperature and determine adjustment to a heat exchange mechanism included in the bleed air unit or air cycle machine.

9. The system of claim 1 , wherein, if only the electrical power is to be used by the aircraft, the bleed air is exhausted to the ambient or output of the bleed air unit comprises an input to the air cycle machine to produce the conditioned air, and the conditioned air is provided to the bleed air unit.

10. The system of claim 1 , wherein the first rotational speed comprises fixed rotational speed and the second rotational speed comprises variable rotational speed.

11. The system of claim 1 , wherein the first rotational speed comprises a speed of the engine at which high fuel efficiency is realized, engine noise is minimized, engine lifetime is prolonged, or a speed associated with an output shaft of the drive train connected to the alternator is optimized for high power draw from the alternator.

12. The system of claim 1 , wherein the electrical power comprises alternating current (AC) power, AC power at a constant frequency and voltage, direct current (DC) power, DC power at a constant voltage, 400 Hertz (Hz) and 115 Volt (V) DC, 28 V DC, or 270 V DC.

13. The system of claim 1 , wherein the bleed air comprises high pressure and high temperature air or 35-50 pound-force per square inch gauge (psig) at 250-320° F., and wherein the conditioned air comprises lower pressure and low temperature air or 3-5 psig at 40-35° F.

14. An integrated ground support system for an aircraft, the system comprising:
a frame on which the system is arranged as a singular assembly;
an engine mounted on the frame and configured to power the system;
a drive train, an alternator, and a bleed air unit mounted on the frame, the drive train disposed between and interconnected to the engine and each of the alternator and the bleed air unit;
an rectifier and a power converter mounted on the frame, the rectifier disposed between and electrically connected to the alternator and the power converter, wherein the power converter is configured to produce electrical power for use by the aircraft;
a first control loop connected to the power converter and configured to monitor and maintain the electrical power at a level required by the aircraft;
an air cycle machine mounted on the frame and connected to the bleed air unit, wherein the bleed air unit is configured to produce bleed air for use by the aircraft and the air cycle machine is configured to produce conditioned air for use by the aircraft; and
a second control loop connected to the bleed air unit and the air cycle machine and configured to monitor and maintain the bleed air or conditioned air at a level required by the aircraft,
wherein the engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with the electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with the bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.

15. The system of claim 14 , wherein the alternator produces an alternating current (AC) output, the rectifier is configured to rectify the AC output to produce a direct current (DC) output, and the power converter is configured to convert the DC output to produce the electrical power.

16. The system of claim 14 , wherein the first control loop includes a voltage sensor

Assignees

• John Bean Technologies Corp

Inventors

• Nestel Steven U
• Carlson Brent Andrew
• Nelson Kirk Rodney

Classifications

• F02B63/047

  Movable engine-generator combinations on wheels · CPC title

• F02B2063/045

  Frames for generator-engine sets · CPC title

• F04B35/06

  Mobile combinations · CPC title

• F04C29/0085

  Prime movers · CPC title

• F04B35/04

  the means being electric · CPC title