Rolls-royce Corporation

Rolls-royce Singapore Pte. Ltd.

Vestas Wind Systems A/s

Rolls-royce North American Technologies Inc.

Michael Adam Zagrodnik

Krishnamoorthi Sivalingam

Chandana Jayampathi Gajanayake

Stephen Andrew Long

Stephen John Mountain

Teh Yee Siang

Mathivanan Anand Prabhu

Michael P Dougherty

Firman Sasongko

Satyanarayana Reddy Gajjela

Daniel Lorincz

István Örökös-tóth

Anand Prabhu Mathivanan

Tomasz Marek Lubecki

Xiong Liu

Amit Kumar Gupta

Peter Michael Schenk

Andrew Mark Bollman

Chandana Jayamapathi Gajanayake

Pradip Chatterjee

Vidor Veres-székely

Umesh Mahajan

Rakesh Murali

Vidor Veres-szekely

Melvin Yang Yueng Yap

A thermal management system for an energy storage system, the energy storage system comprising an energy storage device, an energy storage monitoring system including circuitry dedicated and configured to monitor a temperature of the energy storage device. The thermal management system comprises: a thermal management conditioning loop, a pump configured to circulate a thermal management fluid through the thermal management conditioning loop, a heat source, and a heat transfer hardware in thermal communication with the energy storage device. An energy storage controller of the energy storage monitoring system is configured to confirm that a temperature of the thermal management fluid and/or a temperature of the energy storage device is below an upper safety limit, between a lower control limit and an upper control limit, or both, and in response, to send an enable heater request indicating the heat source is to turn on.

Energy storage system heater control architecture

Methods of controlling an in-line heater for an energy storage device are provided. A determination is made that a pump is running. When running, the pump circulates a thermal management fluid through a thermal management conditioning loop, which includes the in-line heater and a heat transfer hardware configured to transfer heat between the thermal management fluid and the energy storage device, wherein the in-line heater is in thermal communication with the thermal management fluid. The in-line heater is turned on in response to the determination that the pump is running and a temperature of the thermal management fluid is below a lower control limit.

Energy storage system heater control methods

An aerospace battery may include a housing and a battery pack core. The housing may include a thin dual layer casing. The battery pack core is disposed in the housing and may include at least one cell district that includes a plurality of pouch cell batteries. A ceramic material may surround the at least one cell district and a closed cell foam may fill open space between the ceramic material and the housing.

Light weight thermal runaway and explosion resistant aerospace battery

A battery pack core may include a cold plate comprising a plurality of apertures defined between a first major surface and a second major surface of the cold plate; a plurality of battery cells, a single battery cell positioned in each aperture of the plurality of apertures such that a first end of the battery cell projects beyond the first major surface and a second end of the battery cell projects beyond the second major surface; and a plurality of silicone bushings, a silicone bushing surrounding each battery cell of the plurality of battery cells and contacting a wall of the aperture in which the battery cell is positioned.

Battery pack core for fire and explosion protection for battery module

Aircraft with battery thermal regulation systems, including: an aircraft air inlet and an aircraft air outlet; a battery pack including battery cells; and a battery thermal regulation system including a first air channel, a surface of which is in thermal communication with the battery cells so that air flowing through the first air channel exchanges heat with the cells through the surface; and an airflow device for driving an airflow. The battery thermal regulation system has a first and a second mode operation. In the first mode, the first air channel is fluidly connected with the aircraft air inlet and the aircraft air outlet whereby, during flight of the aircraft, air can enter the aircraft through the air inlet, flow through the first air channel and exit the aircraft through the air outlet. In the second mode, the airflow device drives an airflow through the first air channel.

VTOL aircraft including a reconfigurable battery thermal regulation system

An aircraft including a battery pack having a plurality of battery cells arranged to vent into a venting region of the battery pack. A path is defined between the venting region and an exterior of the aircraft, whereby thermal products vented by the cells can exit the aircraft via the path. In some embodiments, the venting region is or is in fluid communication with an air channel through which air flows from an aircraft air inlet to an aircraft air outlet. In other embodiments, the path joins the venting region and an opening in an external surface of the aircraft.

Aircraft battery system including a pressure-sensitive element sealing a battery venting region from a fluid channel

An aerospace battery may include a housing, a retaining seat disposed in the housing, and a battery pack core supported by the retaining seat in the housing. The battery pack core may include at least one cell district comprising a plurality of pouch cell batteries and at least one flexible cold plate disposed between at least two adjacent pouch cell batteries of the plurality of pouch cell batteries. The retaining seat may define a fluid delivery channel configured to couple to an inlet of a cooling channel of the flexible cold plate and a fluid return channel configured to couple to an outlet of the cooling channel of the flexible cold plate.

There is described a device for controlling an amount of current within a power distribution network by manipulating the amount of magnetic flux in the device and thus the impedance experienced by the power distribution network across the device. This is achieved by winding a plurality of coils about a magnetically permeable core and by providing the device with a magnetically permeable bridge element that is movable between a fully-open position at which the net magnetic flux generated in the core by alternating currents in each coil is zero, and a fully-closed position at which a net magnetic flux is present in the core.

Current controlling device

Energy storage systems for aircraft and methods of operating the same are provided. The energy storage system may include a main battery, a propulsion power bus, a non-critical bus, a critical bus, and an engine starter bus. The propulsion power bus may be configured to convey electricity, which is supplied by the main battery, to an electric propulsion machine configured to provide propulsion for the aircraft. The non-critical bus may be configured to convey electricity to a hotel load on the aircraft. The critical bus may be configured to convey electricity, which is supplied by the main battery, to a critical load on the aircraft. The engine starter bus may be configured to convey electricity, which is supplied by the main battery, to an electric starter for a gas turbine engine, where the gas turbine engine is configured to power the electric propulsion machine.

Energy storage system for a hybrid power system

An electrical system including a three phase AC input supply and three or more H-bridge converter cells. Each H-bridge converter cell has: an active front end rectifier for receiving the three phase AC input supply and transforming it into a DC supply, thereby providing a rectifier current i; a capacitor suitable to receive a capacitor current i, the capacitor smoothing the DC supply; and an inverter suitable to receive an inverter current i, wherein i=i&#x2212;i, said inverter transforming the received inverter current iinto a single phase AC supply. The system also including a control subsystem, which provides a signal to each active front end rectifier to vary its respective rectifier current isuch that the difference between the rectifier current i, provided by the active front end rectifier, and the inverter current i, received by the inverter, is substantially zero.

Control of an electrical converter

A method for compensating an inductance imbalance in a three-phase alternating current electrical system is provided. An inductance imbalance is determined in the three-phase electrical system, an induction compensation device is selected based on the determination and thereafter applied within the three-phase electrical system. The induction compensation device is applied onto a power cable within the electrical system. A three-phase electrical system wherein an inductance imbalance is addressed with an inductance compensation device is further provided. A wind turbine generator comprising such a three-phase AC electrical system.

Growing community of inventors

Singapore, Singapore

Michael Adam Zagrodnik