Design method of turboprop aircraft air inlet channel with bypass channel

Abstract

The invention discloses a method for designing a turboprop aircraft air inlet channel with a bypass channel, which comprises the following steps of: drawing section geometric molded lines of a main channel and the bypass channel by controlling the rotation angle between section discrete points and the length of a line segment between adjacent discrete points, rounding the intersection part of the main channel and the bypass channel, and finally forming a bypass channel molded surface. The design requirement for violent change of the cross section shape of the air inlet channel of the turboprop aircraft with the bypass channel is met, and meanwhile the aim of flexibly controlling parameters is achieved through design by controlling the offset distance, the length and the on-way cross section area change rule.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a design system and method for a turboprop aircraft air intake with a bypass channel. Background technique [0002] The development of aviation science and technology has higher and higher requirements on the performance of new aircraft. It is an important aspect that it can adapt to various flight environments and maintain good performance under harsh flight conditions. When turboprops perform missions, they will face various complex and severe flight environments. Once a foreign body is swallowed in the air intake, it may cause serious consequences to the engine and even the entire aircraft, ranging from a decrease in the propulsion efficiency of the engine, affecting the service life, and causing the engine to surge or stop, threatening flight safety. In order to prevent foreign matter from being sucked into the intake port into the engine, a foreign matter removal device is ad...

AI Technical Summary

Problems solved by technology

The design difficulty lies in: (1) the power output shaft passes through the main channel of the air inlet, which makes the surface complex and affects the flow quality of the aerodynamic interface; (2) the bypass channel has good rejection performance and high separation efficiency; (3) is affected by the engine room Restrictions such as size, offset distance, etc. can be well compatible with the geometry and structure of the gearbox and the cabin. The above restrictions make the design of the turboprop air intake / bypass more difficult.

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