United Technologies Corporation

Raytheon Technologies Corporation

Simon Pickford

Gabriel L Suciu

Nathan A Snape

William K Ackermann

Frederick M Schwarz

Wendell V Twelves

James D Hill

Harold W Hipsky

Stephen Karl Kramer

Allan R Penda

Steven J Laporte

A method of sizing a heat exchanger for a geared architecture gas turbine engine includes sizing a minimum frontal area of at least one heat exchanger located in communication with a fan bypass airflow such that a ratio of waste heat area to horsepower generation characteristic area is between 1.6 to 8.75.

Geared architecture turbofan engine thermal management system and method

A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger, wherein the second lubricant circuit is fluidly separate from the first lubricant circuit. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second turbine engine component includes a bearing. The shaft is supported by the bearing and connected to one of the engine stages.

Multi-circuit lubrication system for a turbine engine

An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.

Turbomachine thermal management

A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources.

Gas turbine engine oil tank with integrated packaging configuration

A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the heat exchanger via a fuel pipe and toward a fuel nozzle of the combustor. An airflow inlet directs a cooling airflow through the heat exchanger to reduce an airflow temperature via thermal energy exchange between the cooling airflow and the flow of fuel. An airflow outlet directs the cooling airflow from the heat exchanger toward one or more of components of the turbine to cool the one or more components.

Diffuser mounted fuel-air heat exchanger

A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger. The second lubricant circuit is fluidly coupled with the first lubricant circuit, and the second turbine engine component includes a bearing. The shaft is supported by the bearing, and connected to one of the engine stages.

The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a fuel circuit, comprising a burn line and a recirculation line, and a burn line fuel-oil cooler, coupled to the burn line and an oil circuit. The oil circuit comprises a sending portion, configured to carry oil from the burn line fuel-oil cooler to an engine lube system, and a returning portion, configured to carry oil from the engine lube system to the burn line fuel-oil cooler. The thermal management system further comprises a recirculation fuel-oil cooler, coupled to the recirculation line and the returning portion, and an air-fuel cooler coupled to the recirculation line.

Fuel recirculation thermal management system

An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

Low profile compressor bleed air-oil coolers

An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump that is selectively driven by a motor or a shaft to communicate air to an interior of the nose cone. The pump shaft is driven by a dedicated geared architecture.

An example turbomachine assembly includes, among other things, a nose cone of a turbomachine. The nose cone provides an aperture that communicates air to an interior of the nose cone.

Growing community of inventors

Amston, CT, United States of America

Simon Pickford