The Boeing Company

Jianmin Liao

Ty Aaby Larsen

Bruce Lee Drolen

Robert M Thomas

The present disclosure provides an aircraft thermal management system. The aircraft thermal management system includes a first hydraulic system for circulating a first hydraulic fluid, a second hydraulic system for circulating a second hydraulic fluid, and a third hydraulic system for circulating a third hydraulic fluid. The aircraft thermal management system also includes a controller configured to: (i) determine a temperature of the first hydraulic fluid, a temperature of the second hydraulic fluid, and a temperature of the third hydraulic fluid, and (ii) based on the determined temperature of the first hydraulic fluid, utilize the second hydraulic fluid and/or the third hydraulic fluid to modify an operational temperature of the first hydraulic fluid.

Thermal management for aircraft hydraulic systems

A thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature and a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature. The thermal management system also includes a sealed heat transfer device coupled between the first hydraulic system and the second hydraulic system. The sealed heat transfer device is not in flow communication with either of the first hydraulic system and the second hydraulic system. The sealed heat transfer device is configured to transfer heat from the second hydraulic fluid to the first hydraulic fluid.

Systems and methods for heat balance and transport for aircraft hydraulic systems

An aircraft hydraulic thermal management system utilizes fuel to cool hydraulic fluid by means of a heat exchanger. A hydraulic pump includes a case drain flow of hydraulic fluid at a first temperature to drive a hydraulic motor; the hydraulic motor circulates hydraulic fluid to a reservoir at a second temperature. The heat exchanger is positioned remotely of the fuel tank, and has first and second channels positioned in thermal communication to transfer heat from the hydraulic fluid to the fuel. The hydraulic motor is mechanically coupled to the fuel pump; the hydraulic motor, driven by case drain flow through the first channel, thus operates the fuel pump to move fuel through the second channel. The thermal management system is configured to assure that a) the hydraulic pump circulates hydraulic fluid to the reservoir at the second temperature, and b) the second temperature is always lower than the first temperature.

Aircraft hydraulic thermal management system

A thermal management system is provided. The thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature, a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature, and a heat exchanger coupling the first hydraulic system to the second hydraulic system, wherein the heat exchanger is configured to exchange heat between the first hydraulic fluid and the second hydraulic fluid.

There is provided in an embodiment a hydraulic fluid heat dissipation control assembly for an aircraft hydraulic system. The hydraulic fluid heat dissipation control assembly has one or more heat exchangers. The hydraulic fluid heat dissipation control assembly further has at least one flow control element coupled to the one or more heat exchangers to control flow and heat dissipation of a hydraulic fluid. There is also provided a method of controlling heat dissipation of a hydraulic fluid in an aircraft hydraulic system using the hydraulic fluid heat dissipation control assembly disclosed herein.

Growing community of inventors

Bothell, WA, United States of America

Jianmin Liao