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Multi-air source system flow balance controlling apparatus

A technology of balance control and system flow, applied in the direction of fluid pressure control, non-electric variable control, electric fluid pressure control, etc., can solve problems such as unbalanced bleed air flow, improve test performance, reduce false alarm rate, The effect of simplifying maintenance procedures

Active Publication Date: 2016-10-26
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a flow balance control device for a multi-engine air source system to at least solve the problem of unbalanced flow during the ground test bleed air of the aircraft air source system

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Embodiment Construction

[0023] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to design of ground testing apparatuses directed at airplane air source systems, and in particular to a multi-air source system flow balance controlling apparatus. The controlling apparatus is intended for controlling the air-entraining flow of each path air source in the multi-air-entraining system. The controlling apparatus includes: air source pressure-regulating valves each of which is arranged in each path air-entraining pipeline; precoolers each of which is arranged in each path air-entraining pipeline and is arranged upstream of the air source pressure-regulating valve; first pressure transducers and second pressure transducers each pair of which are separately arranged upstream and downstream of the precooler of each path air-entraining pipeline; and a flow balance controller. According to the invention, the flow balance controller can regulate the air source pressure-regulating valve of a corresponding path air source on the basis of the comparison result between real time flow and object flow so as to automatically regulate the flow of the multi-air-entraining system, and the apparatus allows relative balance of the air-entraining amount of each engine and eliminates the phenomenon of excessive air entraining of a single engine, so that the method reduces influence on engine power, increases safe flying of the airplane, and reduces rate of error alarm report of the air-entraining valve.

Description

technical field [0001] The invention relates to the design of a ground test device for an aircraft air source system, in particular to a flow balance control device for a multi-engine air source system. Background technique [0002] At present, the ground test of the air supply system of a large aircraft usually needs to simulate the configuration of multiple engines bleed air at the same time. The air flow is unbalanced, that is, under the premise of ensuring the total air consumption downstream, the bleed air volume of each engine varies greatly, resulting in the phenomenon that the air consumption of the engine may exceed the amount of bleed air of a single engine, which may affect the engine. The power of the aircraft will bring hidden dangers to the flight safety of the aircraft. At the same time, it will also affect the opening of the pneumatically adjusted valve, and false alarms of valve failure may occur. In addition, domestic transport aircraft do not have digita...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D16/20
CPCG05D16/2006
Inventor 郑旭洲杨丹闫海兵白晓秋杨霍燕韩小刚
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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