Aircraft
AssigneeMitsubishi Aircraft Corporation
InventorJingo Tateiwa
Life of this patent
Estimating the term…
Abstract
An aircraft including a turbofan engine provided with an engine body and a fan located anterior to the engine body, further includes: an engine oil cooler that is a heat exchanger for cooling engine oil used in the engine body by using, as a heat source, a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl; and a pre-cooler that is a heat exchanger for cooling bleed air from the engine body by using the fan stream as a heat source, wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle, and the engine oil cooler is located anterior to the pre-cooler.
Claims18
An aircraft comprising a turbofan engine provided with an engine body, a core cowl surrounding the engine body, a fan located anterior to the engine body, and a nacelle surrounding the core cowl and the fan, the fan producing a fan stream flowing from the fan into a gap between the core cowl and the nacelle, the fan stream dividing into at least a first fan stream portion and a second fan stream portion, the aircraft further comprising:
- an engine oil cooler that is a first heat exchanger for cooling engine oil used in the engine body by using the first fan stream portion as a first cooling source, the engine oil cooler defining a first passageway that the first fan stream portion flows through;
- and
- a pre-cooler that is a second heat exchanger for cooling bleed air from the engine body by using the second fan stream portion as a second cooling source, the pre-cooler defining a second passageway that the second fan stream portion flows through,
- wherein the engine oil cooler and the pre-cooler are in one position in a circumferential direction of the nacelle,
- the engine oil cooler and the pre-cooler are longitudinally arranged along an axial direction of the engine body such that the engine oil cooler is located anterior to the pre-cooler along the axial direction of the engine body, and
- a duct wall separates the first fan stream portion from the second fan stream portion, the duct wall having a first portion that defines an intake port of the engine oil cooler, a second portion that defines an exhaust port of the engine oil cooler, and an intermediate portion between the first portion and second portion that extends oblique to the axial direction.
An aircraft comprising a turbofan engine provided with an engine body and a fan located anterior to the engine body, the fan producing a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl, the fan stream dividing into at least a first fan stream portion and a second fan stream portion, the aircraft further comprising:
- an engine oil cooler that is a first heat exchanger for cooling engine oil used in the engine body by using the first fan stream portion as a first cooling source, the engine oil cooler defining a first passageway that the first fan stream portion flows through;
- and
- a pre-cooler that is a second heat exchanger for cooling bleed air from the engine body by using the second fan stream portion as a second cooling source, the pre-cooler defining a second passageway that the second fan stream portion flows through,
- wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle,
- the engine oil cooler is located anterior to the pre-cooler,
- the engine oil cooler and the pre-cooler are configured in such a manner that an exhaust port of the engine oil cooler and an intake port of the pre-cooler are each in direct communication with a space within the nacelle, and
- a duct wall separates the first fan stream portion from the second fan stream portion, the duct wall having a first portion that defines an intake port of the engine oil cooler, a second portion that defines the exhaust port of the engine oil cooler, and an intermediate portion between the first portion and the second portion that extends oblique to an axial direction of the engine body.
An aircraft comprising a turbofan engine provided with an engine body and a fan located anterior to the engine body, the fan producing a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl, the fan stream dividing into at least a first fan stream portion and a second fan stream portion, the aircraft further comprising:
- an engine oil cooler that is a first heat exchanger for cooling engine oil used in the engine body by using the first fan stream portion as a first cooling source, the engine oil cooler defining a first passageway that the first fan stream portion flows through;
- and
- a pre-cooler that is a second heat exchanger for cooling bleed air from the engine body by using the second fan stream portion as a second cooling source, the pre-cooler defining a second passageway that the second fan stream portion flows through,
- wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle,
- the engine oil cooler is located anterior to the pre-cooler,
- the engine oil cooler and the pre-cooler are supported by a lower portion of a pylon, and
- a duct wall separates the first fan stream portion from the second fan stream portion, the duct wall having a first portion that defines an intake port of the engine oil cooler, a second portion that defines an exhaust port of the engine oil cooler, and an intermediate portion between the first portion and the second portion that extends oblique to an axial direction of the engine body.
Dependencies are inferred from the claim text.