CN-119460084-B - Aircraft nose vortex generator device of making an uproar falls

CN119460084BCN 119460084 BCN119460084 BCN 119460084BCN-119460084-B

Abstract

The invention belongs to the technical field of aircraft aerodynamic design, and relates to an aircraft nose noise-reduction vortex generator device. The device comprises 13 vortex generators, wherein the 7 th vortex generator is positioned right behind a central circular light window of the spherical head nacelle, the 13 vortex generators are arranged towards two sides along the rear edge of the central circular light window of the spherical head nacelle by taking the 7 th vortex generator as the center, the two symmetrically arranged vortex generators are identical in appearance, and are sequentially a first vortex generator, a second vortex generator, a third vortex generator, a fourth vortex generator, a fifth vortex generator, a sixth vortex generator and a seventh vortex generator from two sides to the middle, wherein the seventh vortex generator is shortest in length, the vortex generators arranged at two sides of the seventh vortex generator are sequentially increased, a gap exists between the front end of each vortex generator and the central circular light window, and each vortex generator is arranged along the course.

Inventors

XU LU
MA LONGFEI
DING FAN
WANG YUANBO
ZHANG XIAO
LIU WENPING
WANG CHAO
ZOU YULONG
DU ZHONGRUI
ZHANG SHENGRUI

Assignees

陕西飞机工业有限责任公司

Dates

Publication Date: 20260505
Application Date: 20241129

Claims (1)

1. The noise-reducing vortex generator device for the aircraft nose is characterized by comprising 13 vortex generators; the 7 th vortex generator is positioned right behind the central circular light window of the spherical head nacelle; The two vortex generators which are symmetrically arranged are identical in appearance, and a first vortex generator, a second vortex generator, a third vortex generator, a fourth vortex generator, a fifth vortex generator, a sixth vortex generator and a seventh vortex generator are sequentially arranged from two sides to the middle; The seventh vortex generator is shortest in length, and vortex generators arranged on two sides of the seventh vortex generator are sequentially increased, and an interval exists between the front end of each vortex generator and the central circular optical window; the profile of the top of the first vortex generator is consistent with the curvature change of the profile of the spherical head nacelle, the profile of the front edge is an arc smooth curve, and the included angle of the front edge is 57 degrees; the shape of the top of the second vortex generator is consistent with the curvature change of the shape of the spherical head nacelle, the section of the front edge is an arc smooth curve, and the included angle of the front edge is 52 degrees; the top shape of the third vortex generator is consistent with the curvature change of the spherical head nacelle shape, the section of the front edge is an arc smooth curve, and the included angle of the front edge is 62 degrees; the top appearance of the fourth vortex generator is consistent with the curvature change of the appearance of the spherical head nacelle, the section of the front edge is an arc smooth curve, and the included angle of the front edge is 71 degrees; the top appearance of the fifth vortex generator is consistent with the curvature change of the appearance of the spherical head nacelle, the section of the front edge is an arc smooth curve, and the included angle of the front edge is 74 degrees; The top appearance of the sixth vortex generator is consistent with the curvature change of the appearance of the spherical head nacelle, the section of the front edge is an arc smooth curve, and the included angle of the front edge is 72 degrees; the top appearance of the seventh vortex generator is consistent with the curvature change of the appearance of the spherical head nacelle, the section of the front edge is an arc smooth curve, the included angle of the front edge is 57 degrees, the length of the bottom of the seventh vortex generator is 80mm, the height of the tail is 30mm, the thickness is designed to be 2mm, and the thickness is uniform along the course.

Description

Aircraft nose vortex generator device of making an uproar falls Technical Field The invention belongs to the technical field of aircraft aerodynamic design, and relates to an aircraft nose noise-reduction vortex generator device. Background Aircraft noise is mainly the result of high-speed airflow and turbulence and relative motion to objects in the airflow, and noise sources can be categorized into power plant noise, aircraft system noise, airframe aerodynamic noise, and the like. The aerodynamic noise of the airframe is that when the aircraft flies at a high speed, air flows around the aircraft to generate a boundary layer, and the higher the speed is, the larger the boundary layer transition and separation phenomena are, and the higher the sound pressure level of the generated noise is. When the air flow passes through the cavity, self-oscillation is generated in the cavity, and the pneumatic noise generated by the mutual coupling of the flow field and the acoustic field can cause vibration and fatigue damage of the structure, even affect the service life of the structure, so how to control and reduce the pneumatic noise of the cavity has become the focus problem of research of domestic and foreign students. Disclosure of Invention Aiming at the aerodynamic noise influence caused by the spherical head nacelle with the complex cavity of the airplane, the invention provides the vortex generator device capable of effectively reducing the noise level of the spherical head nacelle with the complex cavity. The technical scheme is as follows: a noise-reducing vortex generator device for aircraft nose comprises 13 vortex generators; the 7 th vortex generator is positioned right behind the central circular light window of the spherical head nacelle; The two vortex generators which are symmetrically arranged are identical in appearance, and a first vortex generator, a second vortex generator, a third vortex generator, a fourth vortex generator, a fifth vortex generator, a sixth vortex generator and a seventh vortex generator are sequentially arranged from two sides to the middle; The length of the seventh vortex generator is shortest, the vortex generators arranged on two sides of the seventh vortex generator are sequentially increased, an interval exists between the front end of each vortex generator and the central circular optical window, and each vortex generator is arranged along the course. Further, the top shape of the first vortex generator is consistent with the curvature change of the spherical head nacelle shape, the section of the front edge is an arc smooth curve, the included angle of the front edge is 57 degrees, the length of the bottom of the first vortex generator is 216mm, the height of the tail of the first vortex generator is 30mm, the thickness of the first vortex generator is designed to be 2mm, and the first vortex generator is uniform in thickness along the course. Further, the top shape of the second vortex generator is consistent with the curvature change of the spherical head nacelle shape, the section of the front edge is an arc smooth curve, the included angle of the front edge is 52 degrees, the bottom length of the second vortex generator is 208mm, the tail height is 30mm, the thickness is designed to be 2mm, and the thickness is uniform and equal along the course. Further, the top shape of the third vortex generator is consistent with the curvature change of the spherical head nacelle shape, the section of the front edge is an arc smooth curve, the included angle of the front edge is 62 degrees, the length of the bottom of the third vortex generator is 196mm, the height of the tail of the third vortex generator is 30mm, the thickness of the third vortex generator is designed to be 2mm, and the third vortex generator is uniform in thickness along the course. Further, the top shape of the fourth vortex generator is consistent with the curvature change of the spherical head nacelle shape, the section of the front edge is an arc smooth curve, the included angle of the front edge is 71 degrees, the length of the bottom of the fourth vortex generator is 160mm, the height of the tail is 30mm, the thickness is designed to be 2mm, and the thickness is uniform along the course. Further, the top shape of the fifth vortex generator is consistent with the curvature change of the spherical head nacelle shape, the section of the front edge is an arc smooth curve, the included angle of the front edge is 74 degrees, the bottom length of the fifth vortex generator is 110mm, the tail height is 30mm, the thickness is designed to be 2mm, and the thickness is uniform and equal along the course. Further, the top shape of the sixth vortex generator is consistent with the curvature change of the spherical head nacelle shape, the section of the front edge is an arc smooth curve, the included angle of the front edge is 72 degrees, the length of the bottom of the sixth vortex generator is 87mm, the height of