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US 12,654,871 B2Granted
Framed heat exchanger for aircraft propulsion system
AssigneeRtx Corporation
InventorsJon Erik Sobanski, Jeffrey T. Morton
Life of this patent
Estimating the term…
Abstract
An assembly for an aircraft includes an airframe structure, a turbine engine and a heat exchanger. The turbine engine is mounted to the airframe structure. The heat exchanger is mounted to the airframe structure independent of the turbine engine. The heat exchanger extends axially along and circumferentially about the turbine engine.
Claims18
An assembly for an aircraft, comprising:
- an airframe structure;
- a turbine engine mounted to the airframe structure;
- and
- a heat exchanger mounted to the airframe structure independent of the turbine engine, the heat exchanger extending axially along and circumferentially about the turbine engine;
- wherein the turbine engine is fixedly mounted to the airframe structure;
- and
- wherein the heat exchanger is movably mounted to the airframe structure.
4 more elements
An assembly for an aircraft, comprising:
- an airframe structure;
- a turbine engine mounted to the airframe structure;
- and
- a heat exchanger mounted to the airframe structure independent of the turbine engine, the heat exchanger extending axially along and circumferentially about the turbine engine;
- and
- a nacelle housing the turbine engine;
- the heat exchanger disposed in a cavity radially between a case of the turbine engine and a wall of the nacelle.
4 more elements
An assembly for an aircraft, comprising:
- an airframe structure;
- a turbine engine mounted to the airframe structure;
- and
- a heat exchanger mounted to the airframe structure independent of the turbine engine, the heat exchanger extending axially along and circumferentially about the turbine engine,
- wherein the heat exchanger includes
- a frame mounted to the airframe structure;
- and
- a plurality of heat exchanger cores arranged circumferentially about an axis, each of the plurality of heat exchanger cores attached to and supported by the frame,
- wherein the frame includes a first support ring, a second support ring and a backbone;
- wherein the first support ring and the second support ring each extend circumferentially around the turbine engine;
- wherein the backbone extends axially between and is connected to the first support ring and the second ring;
- and
- wherein the plurality of heat exchanger cores are arranged axially between and mounted to the first support ring and the second support ring.
10 more elements
An assembly for an aircraft, comprising:
- a frame including a first support ring, a second support ring, a backbone and an aperture, the first support ring and the second support ring each extending circumferentially around an axis, the backbone extending axially between and connected to the first support ring and the second ring, the aperture extending radially through the frame, the aperture extending axially within the frame between the first support ring and the second support ring, and the aperture extending circumferentially about the axis within the frame between opposing sides of the backbone;
- and
- a plurality of heat exchanger cores arranged circumferentially about the axis in an array, the array of the plurality of heat exchanger cores arranged in the aperture axially between the first support ring and the second support ring, and each of the plurality of heat exchanger cores mounted to the first support ring and the second support ring.
Dependencies are inferred from the claim text.