Rolls-royce Corporation

Vestas Wind Systems A/s

Rolls-royce Singapore Pte. Ltd.

United Test and Assembly Center Limited

Krishnamoorthi Sivalingam

Jesper Nyvad

Michael Adam Zagrodnik

Anand Bahuguni

Srikanth Narasimalu

Ravi Kandasamy

John K Grevsen

Stephen John Mountain

Mathivanan Anand Prabhu

Paul T Tietze

Teh Yee Siang

Chandana Jayampathi Gajanayake

Poul Torben Tietze

Satyanarayana Reddy Gajjela

Palanisamy Mohan Kumar

Daniel Lorincz

István Örökös-tóth

Anand Prabhu Mathivanan

Peter Michael Schenk

Hien Boon Tan

Ravi Kanth Kolan

Anthony Yi Sheng Sun

Vidor Veres-szekely

Melvin Yang Yueng Yap

Govind Pandey

Divya Bharathi Perumal

Yunzhe Zhai

Jeyaraman Kumaravel

Beng Kuan Lim

Rakesh Murali

John P E Forsdike

Vidor Veres-székely

Umesh Mahajan

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

A propulsion system for use with an aircraft includes a gas turbine engine, an electric power system, and at least one propulsor. The gas turbine engine includes a compressor, a combustor, and a turbine. The electric power system includes a generator coupled to the gas turbine engine to generate electrical energy, power electronics connected to the generator to receive the electrical energy from the generator, and a motor configured to produce rotational energy in response to receiving electric energy from the power electronics. The propulsor is configured to use rotational energy received from the motor of the electric power system to generate thrust for propelling the aircraft.

Electrical current converter/rectifier with integrated features

A hybrid propulsion system for use with an aircraft includes a gas turbine engine, at least one propulsor, and an electric power system. The electric power system is coupled to the gas turbine engine to generate electrical energy and the propulsor to provide electrical energy to drive the propulsor. The electric power system includes a thermal management system configured to cool a heat load generated by the electric power system.

Aircraft hybrid propulsion system including cold plate for a high density power converter

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.

The present invention relates to a wind turbine nacelle having a top face with a longitudinal extension in a wind direction. The nacelle comprises a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face and at least a front edge facing the wind direction. The cooling device is enclosed by the first face of the nacelle and the inner face of the cover and is arranged in a front distance of at least 440 mm from the front edge of the cover.

Wind turbine nacelle with cooler top

The present invention relates to a wind turbine nacelle having a first face with a longitudinal extension in a wind direction, comprising a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face, the cooling device being enclosed by the first face of the nacelle and the inner face of the cover. A first distance between at least one of the faces and the cooling area is at least 30 mm.

The present invention relates to a wind turbine nacelle having a top face with a longitudinal extension in a wind direction, comprising a cooling device extending from the top face of the nacelle and a cover having at least one inner face. The cooling device is enclosed by the top face of the nacelle and the inner face of the cover.

A wind turbine having a cooling system, which wind turbine includes a nacelle in connection with which one or more wind turbine components are arranged, is disclosed. The cooling system includes at least one cooling circuit arranged to lead a heat transfer medium to and from one or more of the wind turbine components, at least one cooling device arranged to cool the heat transfer medium, at least one pump arranged in connection with the at least one cooling circuit to circulate the heat transfer medium in the cooling circuit, and at least one medium tank arranged in connection with the cooling circuit. The at least one medium tank is arranged inside the nacelle.

Cooling system for a wind turbine

The invention provides a wind turbine wind turbine with two vessels, each being interchangeably in thermal communication with a heating medium which transfers heat from a heat generating structure to the vessel, and with a cooling medium which transfers heat from the vessel to an ambient space. The vessels form a compression structure which form part of a refrigerating circuit which can circulate a working fluid between the compression structure, a condenser and an evaporator. At the evaporator, cooling effect is obtained based on evaporation of a working fluid, and the cooling can be utilized for cooling a heat generating component in the wind turbine.

Wind turbine with a refrigeration system and a method of providing cooling of a heat generating component in a nacelle for a wind turbine

A chip scale integrated circuit package includes an integrated circuit chip which has a first face and a second face. A plurality of pillar bumps are formed on the first face of the integrated circuit chip. An encapsulant material encapsulates the sides and the first face of the integrated circuit chip, and the pillar bumps. Upper ends of the pillar bumps remain free from encapsulant material and a substantially planar surface is formed by an upper surface of the encapsulant material and the upper ends of the pillar bumps. A plurality of solder balls are mounted on the substantially planar surface in locations corresponding to the upper ends of the pillar bumps.

Growing community of inventors

Singapore, Singapore

Krishnamoorthi Sivalingam