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Airborne generator cooling device

A cooling device and generator technology, applied in the aviation field, can solve problems such as engine performance and adverse effects of engine compartment shape design, and achieve the effects of reducing size, strengthening convection heat transfer, and simplifying design

Active Publication Date: 2018-12-14
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
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Problems solved by technology

[0003] The purpose of the present invention is to provide a cooling method for an airborne generator, to solve the cooling problem of the generator in the full flight envelope of the aircraft, especially at low speeds, and to avoid adverse effects on the performance of the engine and the shape design of the engine compartment influences

Method used

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  • Airborne generator cooling device

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Embodiment Construction

[0012] The present invention will be described in further detail below. see figure 1 , an airborne generator cooling device is characterized in that it includes: a generator set 1, an oil pump 2, a pressure relief valve 3, a first filter 4, a lubricating oil air cooling system, a temperature bypass valve 6, a one-way valve 7 and the second filter 8; there are casing oil inlet 1a, casing oil outlet 1b and casing oil return port 1c on the casing of the generator set 1, and the casing oil outlet 1b and the oil inlet of the oil pump 2 The oil outlet of the oil pump 2 is connected with the oil inlet of the pressure relief valve 3 and the oil inlet of the first filter 4 at the same time, and the oil outlet of the pressure relief valve 3 is connected with the oil return port 1c of the casing; the first filter The oil outlet of device 4 is connected with the oil inlet of lubricating oil air cooling system and the oil inlet of temperature bypass valve 6 at the same time; the oil outle...

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Abstract

The invention belongs to the aviation field, and relates to an airborne power generator cooling device, which is characterized by comprising a power generator set (1), an oil pump (2), a pressure relief valve (3), a first filter (4), a lubricating oil air cooling system, a temperature bypass valve (6), a non-return valve (7) and a second filter (8). The invention provides an airborne power generator cooling device, which solves the problem of cooling of the power generator in an aircraft full flight envelope range, particularly, in a low-speed condition, and avoids bad influences on the performance of the engine and the engine compartment appearance design.

Description

technical field [0001] The invention belongs to the aviation field and relates to an airborne generator cooling device. Background technique [0002] For turboprop aircraft, due to its small fuel consumption, if aircraft fuel is used to cool the generator, the heat sink brought to the aircraft fuel system is often unacceptable; if external air is used to cool the generator, in In low-speed conditions such as ground idle, take-off and landing, the amount of air that enters the engine compartment only by ramming is very limited, which cannot meet the cooling requirements of the generator; if the high-speed airflow is drawn from the engine, it is expected to increase the cooling air volume of the generator through ejection , will cause a decline in engine performance. Contents of the invention [0003] The purpose of the present invention is to provide a cooling method for an airborne generator, to solve the cooling problem of the generator in the full flight envelope of the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H02K9/04H02K9/19
CPCH02K9/04H02K9/19
Inventor 周红钟剑龙吴宇
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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