Ge Aviation Systems Limited

Manish Ashvinkumar Dalal

Arthur Vorwerk Radun

Xiaochuan Jia

Paul Robert Gemin

A method and apparatus for generating electrical power, including providing a generator configured to generate a first voltage, providing a voltage converter configured to operably down-convert the first voltage output to a second voltage output to provide a first amount of power to a set of electrical loads, and changing a power demand for at least a subset of the set of electrical loads, wherein the changed power demand increases the power demanded. To meet the increased power demand, the voltage converter is controlled to operably down-convert the first voltage output to the second voltage output to provide a second amount of power to the set of electrical loads. The second amount of power is greater than the first amount of power. The power-generating capabilities of the generator are not modified between providing the first amount of power and providing the second amount of power.

Method and power distribution system for generating electrical power

Systems and method for an electrical system on an aircraft are provided. In example embodiments, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to a load. A hybrid electric propulsion system and a secondary aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the hybrid electric propulsion system, and the secondary aircraft systems bus.

Systems and methods of power allocation for hybrid electric architecture

Systems and method for an electrical system on an aircraft are provided. In example aspects, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to multiple high power demand loads. A propulsion system and a multiple aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the propulsion system, and the secondary aircraft systems bus.

Systems and methods of power allocation for turboprop and turboshaft aircraft

An electrical power system architecture and method for allocating power includes a power distribution bus configured to receive power generated by a first engine having a first generator and a second generator, a first set of electrical buses connected with the power distribution bus and associated with the first engine, and a second set of electrical buses configured to selectively connect with the power distribution bus.

Method for allocating power in an electrical power system architecture

One example aspect of the present disclosure is directed to a method for operating a gas turbine engine. One example aspect of the present disclosure is directed to a method for operating a gas turbine engine, the gas turbine engine including at least a high pressure spool and a low pressure spool. The method includes causing, by one or more control devices, electrical power to be drawn from the high pressure spool and the low pressure spool into a power distribution system. The method includes determining, by the one or more control devices, a power adjustment event associated with the high pressure spool. The method includes initiating, by the one or more control devices, a power assist operation to redirect electrical power to the high pressure spool based at least in part on the power adjustment event.

Engine core assistance

A power distribution system, includes a first current loop connected with a set of low voltage electrical loads, a second current loop connected with a set of high voltage electrical loads, at least two generator systems having respective power outputs, and a controller module configured to selectively connect the respective power outputs to at least one of the first or second current loops.

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Englewood, OH, United States of America

Manish Ashvinkumar Dalal