Segmented convergence type double-S-curve binary mixed exhaust system

Abstract

The invention discloses a segmented convergence type double-S-curve binary mixed exhaust system which is used for infrared stealth of a turbofan engine. The contour of the segmented convergence type double-S-curve binary mixed exhaust system converges in an axial symmetry shape firstly and then converges in a double-S-curve shape. The segmented convergence type double-S-curve binary mixed exhaust system is composed of a pointed conical central cone, an outer culvert axial symmetry convergence section, an outer culvert double-S-curve binary convergence section, an inner culvert axial symmetry convergence section and an inner culvert S-curve convergence section. The pointed conical central cone and the inner culvert axial symmetry convergence section are connected to form an inner culvert wall surface, in this way, local expansion of an inner culvert channel can be prevented, and flow separation on the wall surface of the central cone is restrained. The outer culvert axial symmetry convergence section and the outer culvert double-S-curve binary convergence section are connected to form an outer culvert wall surface, and accordingly blockage on typical high-temperature components such as the central cone and the inner culvert inlet section can be formed more effectively. By the adoption of the segmented convergence type double-S-curve binary mixed exhaust system, compared with an existing double-S-curve binary mixed exhaust system, the infrared emanation characteristic of the exhaust system can be further restrained while the aerodynamic performance of the exhaust system is further improved.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to the technical field of infrared radiation characteristic suppression of aircraft. Background technique [0002] The research on the infrared characteristics of the aircraft shows that: (1) the main infrared radiation source of the jet aircraft comes from the exhaust system and the fuselage skin of the aircraft; (2) when the flight Mach number is less than 1.5, the exhaust system cavity and The infrared radiation of high-temperature components contributes more than 90% to the infrared radiation of the aircraft's medium-wave band. Therefore, studying the infrared radiation characteristics of the aero-engine exhaust system in the 3-5 μm band and developing the infrared suppression technology of the exhaust system is one of the key technologies to improve the survivability of aircraft on the battlefield. [0003] The infrared suppression measures for the exhaust system of aero-engines mainly...

AI Technical Summary

Problems solved by technology

[0005] Purpose of the invention: In order to overcome the deficiencies in the prior art, the present invention proposes a segmented and convergent double-S-curved binary hybrid exhaust system, which is used to solve the serious air separation in the center cone of the existing double-S-curved binary nozzle And the technical problem of large nozzle size

Images