CN-122014419-A - Turbofan engine core cabin

CN122014419ACN 122014419 ACN122014419 ACN 122014419ACN-122014419-A

Abstract

The core cabin of the turbofan engine is beneficial to improving the distribution uniformity of ventilation air flow in the core cabin and improving the heat exchange effect in the core cabin. The turbofan engine core compartment includes an intake portion that causes the gas of the outer duct to flow into the core compartment in a manner that the gas flows toward the radially inner side and the circumferential side, and an exhaust portion that causes the gas in the core compartment to flow out to the outside in a manner that the gas flows toward the circumferential side.

Inventors

WANG YAN
ZHU JIANJUN
LIANG JIAYI
DENG MING
XIA HEMING
XUE ZHANDONG

Assignees

中国商用飞机有限责任公司
中国商用飞机有限责任公司上海飞机设计研究院

Dates

Publication Date: 20260512
Application Date: 20260311

Claims (7)

1. A turbofan engine core nacelle comprising: An inlet portion for allowing the gas of the outer duct to flow into the core cabin so as to flow radially inward and circumferentially outward, and And an exhaust unit that causes the gas inside the core compartment to flow out to the outside so as to flow to one side in the circumferential direction.
2. The turbofan engine core of claim 1 wherein, The gas inlet portion forms a tubular flow path through which gas flows, and is open to the radially inner side and the circumferential side inside the core nacelle.
3. The turbofan engine core of claim 2 wherein, Comprises an outer wall of a core cabin, The air intake portion includes: An air inlet opening in the outer wall of the core compartment, and And an intake pipe extending from the intake port toward a radially inner side of the core compartment outer wall, and forming the tubular flow path.
4. A turbofan engine core compartment according to claim 3, wherein, The intake pipe is provided with a plurality of in the circumferential direction.
5. The turbofan engine core of any one of claims 1 to 4 wherein, Comprises a core cabin outer wall and a core casing positioned on the radial inner side of the core cabin outer wall, The exhaust section includes: an annular gap defined by a downstream end of the outer wall of the core nacelle and a downstream end of the core case, and And a partition portion that partitions the annular gap into a plurality of portions in a circumferential direction and that causes the airflow to flow toward one side in the circumferential direction.
6. The turbofan engine core of claim 5 wherein, The partition is a baffle.
7. The turbofan engine core of claim 6 wherein, The guide vane is provided with a plurality of guide vanes in the circumferential direction.

Description

Turbofan engine core cabin Technical Field The invention relates to the field of ventilation and cooling of aircraft power devices, in particular to a turbofan engine core cabin. Background When the turbofan engine of the civil aircraft runs, a large amount of heat can be accumulated in the core cabin, the temperature in the core cabin is increased by heat exchange activities such as radiation, convection and the like, and the system accessories in the core cabin are easily overheated due to long-time high temperature in the cabin, so that the reliability is influenced, and even the ignition risk exists. Thus, ventilation of the turbofan engine core compartment is required. In the past, the ventilation structure of turbofan engine core cabin mainly includes the air inlet that distributes at the face of upper reaches core bulkhead and the exhaust circumferential weld at low reaches core cabin end, and the air inlet is introduced cooling air current through the outer duct, and cooling air current carries out heat exchange and flows out through the exhaust circumferential weld under the differential pressure effect in the core cabin. In the ventilation structure, too many air inlets cannot be arranged in consideration of flow loss of the outer duct, so that the circumferential cooling effect of the core cabin is easily uneven, on the other hand, the cooling mechanism in the cabin is completely dependent on the stamping effect of air flow, the local cooling effect at the position close to the air inlet is obvious, but the downstream cooling effect is greatly reduced along with the axial movement of the air flow along the engine, and the cooling air flow is difficult to complete sufficient heat exchange with the wall surface of the core cabin and the high-temperature accessories and is discharged into the wake of the outer duct, so that the waste of part of the air-entraining of the outer duct is definitely caused. That is, in the past, there was an irreconcilable conflict between improving the uniformity of distribution of ventilation air flow in the core cabin and improving the ventilation and heat exchange effects in the cabin. Disclosure of Invention The present invention has been made in view of the above-mentioned problems, and an object of the present invention is to provide a turbofan engine core compartment that helps to improve the uniformity of the distribution of ventilation air flow in the core compartment and to enhance the heat exchange effect in the core compartment. In order to achieve the above object, the present invention provides a turbofan engine core nacelle including an intake portion that causes gas in an outer duct to flow into the core nacelle so as to flow radially inward and circumferentially outward, and an exhaust portion that causes gas in the core nacelle to flow out to the outside so as to flow circumferentially outward. According to the turbofan engine core cabin, the cooling air flow introduced from the outer duct through the air inlet part easily forms initial vortex in the core cabin, the air flow distribution uniformity of an air inlet area is improved, the vortex formed by the cooling air flow introduced from the outer duct into the core cabin is easily and stably developed in a spiral line mode along the axial direction of the core cabin through the cooperation of the air inlet part and the air outlet part, the inner layer energy is exchanged to the outer layer through interlayer heat exchange similar to free vortex in the core cabin, and the outer layer high-speed air flow carrying more energy is discharged to the outside under the suction effect of the air outlet part, so that the overall efficient cooling heat exchange of the core cabin is easily realized. Furthermore, in an embodiment of the turbofan engine core compartment of the invention, the air intake forms a tubular flow path for the flow of air, and is open inside the core compartment towards the radially inner side and towards one circumferential side. According to the turbofan engine core cabin, the cooling airflow introduced from the outer duct can be better guided by the air inlet part to form initial vortex in the core cabin. Further, in an embodiment of the turbofan engine core compartment of the present invention, the intake portion includes a core compartment outer wall, the intake port including an intake port that opens to the core compartment outer wall, and an intake pipe that extends from the intake port toward a radially inner side of the core compartment outer wall and forms the tubular flow path. According to the turbofan engine core cabin, the air inlet part is simple in structure, and manufacturing cost is reduced. Furthermore, in an embodiment of the turbofan engine core compartment of the invention, the intake duct is provided with a plurality of intake ducts in the circumferential direction. According to the turbofan engine core cabin, the initial vortex of cooling air flow introduced from