Gas turbine engine including a rectifierless electronic control unit and method for supplying power to same

Patent metadata

Field	Value
Publication number	US-10801414-B2
Application number	US-201715413681-A
Country	US
Kind code	B2
Filing date	Jan 24, 2017
Priority date	Jan 24, 2017
Publication date	Oct 13, 2020
Grant date	Oct 13, 2020

Abstract

A gas turbine engine comprises an electronic control unit adapted to control functions of the gas turbine engine and having a DC power input unit coupled to receive DC supply power and an ignition igniter coupled thereto. The ignition exciter includes an AC power input unit adapted to receive AC power from an AC power source within the gas turbine engine, a power rectification unit coupled to receive the AC power from the AC power source and configured, upon receipt thereof, to rectify the AC power into DC power, and a DC power output unit coupled to receive the DC power from the power rectification unit and configured to supply the DC power to the DC power input unit of the electronic control unit as DC supply power and/or the ignition igniter.

First claim

The invention claimed is:

1. A gas turbine engine including at least a compressor section, a combustion section, and a turbine section, the gas turbine engine comprising:
an electronic control unit adapted to control functions of each of the compressor section, the combustion section, and the turbine section of the gas turbine engine and having a DC power input unit coupled to receive DC supply power, the electronic control unit is devoid of any AC/DC power rectification;
an ignition exciter, the ignition exciter comprising:
an AC power input unit adapted to receive AC power from an AC power source within the gas turbine engine;
a power rectification unit coupled to receive the AC power from the AC power source and configured, upon receipt thereof, to rectify the AC power into DC power; and
a DC power output unit coupled to receive the DC power from the power rectification unit and configured to supply the DC power directly to the DC power input unit of the electronic control unit as DC supply power; and

an ignition igniter coupled to the DC power output unit of the ignition exciter to directly receive the DC power from the power rectification unit.

2. The gas turbine engine according to claim 1 , wherein the AC power source is constituted by a permanent magnet alternator of the gas turbine engine.

3. The gas turbine engine according to claim 1 , further comprising one or more electrical consumers coupled to the DC power output unit of the ignition exciter.

4. The gas turbine engine according to claim 1 , wherein the ignition exciter further includes a step-down circuit adapted to reduce the rectified DC power into a DC power of lower value.

5. The gas turbine engine according to claim 4 , wherein the step-down circuit comprises a transformer.

6. The gas turbine engine according to claim 1 , wherein the power rectification circuit comprises a half wave rectification unit.

7. The gas turbine engine according to claim 1 , wherein the power rectification circuit comprises a full wave rectification unit.

8. A method for supplying DC power to an electronic control unit of a gas turbine engine that includes at least a compressor section, a combustion section, and a turbine section, the gas turbine engine, the electronic control unit having a DC power input unit adapted to receive DC supply power and being devoid of any internal power rectification circuit, the electronic control unit further adapted to control functions of each of the compressor section, the combustion section, and the turbine section of the gas turbine engine, the method comprising the following steps:
generating AC power by an AC power source of the gas turbine engine;
supplying the generated AC power to an ignition exciter of the gas turbine engine;
rectifying said AC power in said ignition exciter into DC power;
supplying said DC power directly to the DC power input unit of said electronic control unit as DC supply power; and
supplying said DC power directly to an ignition igniter of said gas turbine engine.

9. The method according to claim 8 , further comprising the step of supplying the DC power rectified in said ignition exciter to one or more other electrical consumers.

10. The method according to claim 8 , further including the step of stepping down the rectified DC power into a DC power of lower value inside said ignition exciter.

Assignees

• Honeywell Int Inc

Inventors

• Kelly Jeff M

Classifications

• H02M1/0006

  Arrangements for supplying an adequate voltage to the control circuit of converters · CPC title

• F05D2220/768

  equipped with permanent magnets · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02P3/0884

  Closing the discharge circuit of the storage capacitor with semiconductor devices · CPC title

• F02P15/003

  Layout of ignition circuits for gas turbine plants (ignition of gas turbine plants per se F02C7/26) · CPC title