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US 2026/0287174 A1Published application
Engine torsional frame for exhaust channel track selection
AssigneeRtx Corporation
InventorsGregory M. Chere, Simon W. Evans
Life of this patent
Estimating the term…
Abstract
An aircraft propulsion system includes a core engine and a heat exchanger assembly that is operable in a heat exchanger configuration where the exhaust gas flow is in thermal communication with a working fluid flow and a bypass configuration where the exhaust gas flow passes through the heat exchanger assembly without thermal communication with the working fluid flow.
Claims20
An aircraft propulsion system comprising:
- a core engine comprising a main compressor where an inlet airflow is compressed and communicated to a combustor to generate an exhaust gas flow that is expanded through a main turbine section to generate power used to drive the main compressor and a propulsive fan;
- a fuel system configured to provide a flow of fuel to the combustor for generating the exhaust gas flow;
- a heat exchanger assembly operable in a heat exchanger configuration where the exhaust gas flow is in thermal communication with a working fluid flow and a bypass configuration where the exhaust gas flow passes through the heat exchanger assembly without thermal communication with the working fluid flow;
- and
- a controller programmed to operate the heat exchanger assembly to switch between the heat exchanger configuration and the bypass configuration based on at least one of an engine operating condition or a predefined flight profile.
2 more elements
A bottoming cycle system for an aircraft propulsion system comprising:
- a heat exchanger assembly operable in a heat exchanger configuration where an exhaust gas flow is in thermal communication with a working fluid flow and a bypass configuration where the exhaust gas flow passes through the heat exchanger assembly without thermal communication;
- a bottoming turbine where a heated working fluid flow from the heat exchanger assembly expands to generate shaft power;
- a fuel/working fluid heat exchanger where heat from the working fluid flow is communicated to a flow of fuel;
- and
- a controller programmed to operate the heat exchanger assembly to switch between the heat exchanger configuration and the bypass configuration based on engine operating conditions.
2 more elements
A method of operating an aircraft propulsion system comprising:
- generating an exhaust gas flow within a combustor of a core engine by igniting a mixture of inlet air and a flow of fuel;
- generating power by expanding the exhaust gas flow through a main turbine section to drive a compressor section and a propulsive fan;
- and
- operating a heat exchanger assembly in one of a heat exchanger configuration where the exhaust gas flow is in thermal communication with a working fluid flow and a bypass configuration where the exhaust gas flow passes through the heat exchanger assembly without thermal communication with the working fluid flow based on at least on of an engine operating condition, a predefined flight profile, or a prompt from a pilot.
1 more element
Dependencies are inferred from the claim text.