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Control system and method for reducing low-temperature starting load of aero-engine

An aero-engine and control system technology, which is applied in the direction of engine lubrication, engine components, and turbine/propulsion lubrication. , the effect of reducing the impact of acceleration performance

Active Publication Date: 2019-03-19
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The present invention provides a control system and method for reducing the load of an aero-engine starting at low temperature, so as to solve the technical problem that the existing aero-engine has poor starting acceleration or even unsuccessful starting when it is started at low temperature.

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  • Control system and method for reducing low-temperature starting load of aero-engine

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Embodiment Construction

[0027] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.

[0028] Such as figure 1 As shown, the preferred embodiment of the present invention provides a control system for alleviating the low-temperature start-up load of an aero-engine, which is used to reduce the start-up load of an aero-engine in a low-temperature environment, so as to ensure that the aero-engine has good acceleration in a low-temperature environment thereby Can be started smoothly. Aeroengines include a fuel system, a lubricating oil system and an oil supply system for supplying lubricating oil to the lubricating oil system. The fuel system and the lubricating oil system are under the same working environment. The control system for alleviating the low-temperature start-up load of the aeroengine includes an electronically controlled switch element 11...

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Abstract

The invention discloses a control system for reducing the low-temperature starting load of an aero-engine. The aero-engine comprises a fuel system, a lubricating oil system and an oil supply system used for supplying lubricating oil to the lubricating oil system, and the control system comprises an electric control switch element which is arranged in the oil supply system and is in a normally closed state, a lubricating oil temperature sensor used for detecting the lubricating oil temperature, a fuel temperature sensor used for detecting the fuel temperature, a pressure sensor used for detecting the flight height of an aircraft, and a controller used for controlling a working state of the electric control switch element according to the detecting result of at least one of the lubricating oil temperature sensor, the fuel temperature sensor and the pressure sensor; and the electric control switch element, the lubricating oil temperature sensor, the fuel temperature sensor and the pressure sensor are all connected with the controller. According to the control system and method for reducing the low-temperature starting load of the aero-engine, the success rate of low-temperature starting of the aero-engine is increased, and meanwhile the time of low-temperature starting of the aero-engine is shortened.

Description

technical field [0001] The invention relates to the technical field of low-temperature starting of aero-engines, in particular to a control system and method for reducing the load of low-temperature starting of aero-engines. Background technique [0002] Lubricating oil pump load size is affected by temperature. In a low temperature environment, the viscosity of lubricating oil increases, resulting in a greater demand for power extracted by the lubricating oil pump from the engine starting system, which will lead to poor starting acceleration of the aeroengine, and even lead to unsuccessful starting. Existing aero-engines have not considered how to reduce the low-temperature starting load of aero-engines. Contents of the invention [0003] The invention provides a control system and method for lightening the low-temperature starting load of an aero-engine, so as to solve the technical problem that the existing aero-engine has poor starting acceleration or even unsuccessfu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/06
CPCF02C7/06
Inventor 翦玲玲向立军袁细传
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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