Honeywell International Inc.

Alliedsignal Inc.

Ray McGinley

Cristian E Anghel

Rocco DiVito

Wayne T Pearson

Randy Fuller

Mingzhou Xu

Nicolae Morcov

John K Harvell

David Chandu-Lall

Robert C Wagner

Alan B Luebs

An aircraft engine starting system may comprise a starter motor, a start controller for controlling the starter motor to operate with a desired torque output, and a processor for determining torque profiles for the starter motor. The processor may provide an initial torque profile responsively to ambient condition of the engine. The processor may also provide modifications to the initial torque profile responsively to temperature of the start controller.

Control methodology for an AC starter-generator system

A starting system for aircraft engines employs power from multiple power sources. Each engine is started with a starter motor that is driven by the same multiple power sources which collectively provide starting power. As engine speed increases during each starting cycle a voltage boost is progressively provided by a boost converter. The starting system allows use of voltages higher than output voltage of the power sources while allowing the power sources to remain connected to a main aircraft power distribution bus.

Enhanced DC electric main engine start system

A method and apparatuses are implemented for electric power systems. An apparatus for power conversion according to one embodiment comprises: a multiple function power converter (), the multiple function power converter () being capable of performing functions of a static inverter, and being capable of at least one of performing functions of a motor controller, and performing functions of a start converter to use a generator as a starter. An architecture system for aircraft according to another embodiment comprises: one or more rectifiers (), wherein the one or more rectifiers () receive at least one high frequency AC power input; and a plurality of power conversion devices () optionally connectable to drive at least one high frequency generator () as a starter and at least one load, the input of each power conversion device () being connected to at least one rectifier ().

Architecture and a multiple function power converter for aircraft

A starter-generator system is configured to supply power to an aircraft electrical bus having a rated AC voltage magnitude, or receive power from a start converter, and includes a rotor and a stator. The stator is disposed at least partially around at least a portion of the rotor and has at least one multi-phase stator winding set wound thereon that has an increased number of turns per phase that is greater than a least number of turns per phase needed to supply power to an aircraft electrical bus at the rated AC voltage magnitude. The increased number of stator turns results in reduced current drawn by the starter-generator during the motor mode, which improves the efficiency and introduces other benefits to the overall starting system.

Engine starter-generator optimized for start function

A method and apparatus for executing a no-break power transfer between an electrical power generator powered by an auxiliary power unit (APU) and an electrical power generator powered by an aircraft main engine. The method comprises sending a power transfer command, a load/unload amplitude signal, and a target frequency signal from a bus power control unit to an APU electronic control unit; deriving a calculated load range for the APU at a new load and frequency operating point; and determining if the new load and frequency operating point falls within the calculated APU load range. If within range, a no-break power transfer is initiated; if not within range, a power transfer with momentary interruption is initiated.

No-break-power-transfer control system for variable frequency electrical power systems

An apparatus () controls a synchronous machine () used to start an engine () during an engine start operation. The apparatus comprises: an exciter current control unit () for controlling exciter current output to the synchronous machine () during the engine start operation; and a main current control unit () for controlling main current output to the synchronous machine () during the engine start operation as a function of machine speed. In one implementation, the main current control unit () controls main current output to the synchronous machine () so that the synchronous machine () exhibits a reduced output torque during an initial torque application stage. The reduced viscous drag effects and reduced impact torque are beneficial to the engine system ().

Method and apparatus for controlling an engine start system

Two spool gas turbine engines are often used to drive variable speed loads, such as an electric generator, or the fan/propeller of aircraft engines. The gas turbine engine must be designed to withstand transient speed and temperature conditions which are encountered when sudden changes to the load on the generator, fan, or propeller occur. By adding a relatively small motor/generator to the gas generator spool of the gas turbine engine, the compressor speed and airflow can be quickly adjusted to compensate for external load changes. This reduces the severity and duration of the transient conditions, resulting in decreased operation and reliability problems such as overspeed, compressor surge, and high turbine temperature. The motor/generator may also be used as an engine starting device.

Starting and controlling speed of a two spool gas turbine engine

A start circuit controlled by an electronic control unit for providing power from one or both of a battery and TRU in parallel to a starter motor coupled to a gas turbine engine. The circuit includes contactors between the TRU and battery and a junction where the current from the TRU and battery combine. The circuit further includes two additional contactors in series between the junction and the starter motor. Voltage sensors and contactor position sensors are employed for diagnostics. A novel method of starting the engine using the start circuit contemplated by the present invention is also descibed. In this method, the start is initiated with power only from the battery. After a period of time power from the TRU is added. This method reduces the amplitude of the start motor inrush current, which has a beneficial reliability effect on the components of the start circuit.

Growing community of inventors

Fountain Hills, AZ, United States of America

Ray McGinley