CN-121976881-A - Injection device for air inlet channel of aeroengine, air inlet channel and aeroengine

CN121976881ACN 121976881 ACN121976881 ACN 121976881ACN-121976881-A

Abstract

The application provides an ejector device for an air inlet channel of an aeroengine, the air inlet channel and the aeroengine. The injection device comprises an injection pipeline, an injection pipe and an injection pipe, wherein the injection pipeline comprises a first pipeline and a second pipeline which are connected, the first pipeline is used for being connected with a particulate matter collecting part of an air inlet channel, the injection pipe is arranged in the second pipeline and comprises an air inlet section and an air injection section which are connected, the air inlet section is connected with the inner wall of the second pipeline and forms an air inlet channel with the outer wall of the second pipeline, the air injection section is parallel to the axis of the second pipeline, the outlet of the air injection section faces one end, far away from the first pipeline, of the second pipeline, and the air inlet channel is used for introducing air flow compressed and heated by a compressor of an aeroengine into the injection pipe and injecting air flow from the outlet of the air injection section so as to form negative pressure in the first pipeline and suck out particulate matters of the particulate matter collecting part.

Inventors

LI JICHAO
ZHANG XIAOYU
WANG WENTAO
Fan Boning
ZHANG HONGWU
DU QIANG

Assignees

中国科学院工程热物理研究所

Dates

Publication Date: 20260505
Application Date: 20260303

Claims (10)

1. An ejector for an aircraft engine inlet, comprising: the injection pipeline comprises a first pipeline and a second pipeline which are connected, wherein the first pipeline is used for being connected with the particulate matter collecting part of the air inlet channel; The jet pipe is arranged in the second pipeline and comprises an air inlet section and an air jet section which are connected, an air inlet channel is formed between the air inlet section and the inner wall of the second pipeline and between the air inlet section and the outer wall of the second pipeline, the air jet section is parallel to the axis of the second pipeline, and the outlet of the air jet section faces to one end, far away from the first pipeline, of the second pipeline; the air inlet channel is used for introducing air flow compressed and heated by a compressor of the aeroengine into the jet pipe and jetting the air flow from an outlet of the jet section so as to form jet air flow in the second pipeline, so that negative pressure is formed in the first pipeline and particulate matters of the particulate matter collecting component are sucked out.
2. The injection device of claim 1 wherein said injection tube comprises a plurality of said injection tubes disposed within said second conduit at circumferentially spaced intervals along said second conduit.
3. An ejector according to claim 1 or claim 2, wherein the cross-section of the second conduit is shaped as a racetrack formed by a combination of two semi-circles of the same radius and a rectangle located between the two semi-circles.
4. An ejector according to claim 3, wherein the plurality of air jets are symmetrically distributed about a line between the centers of the two semicircles.
5. The ejector according to claim 4, wherein a ratio of a distance between a center of the outlet of the air injection section and an inner wall of the second duct to a distance between the center of the outlet of the air injection section and the center of the second duct is in a range of 0.3 to 0.5.
6. An ejector according to any one of claims 1 to 5, wherein the ejector tube is configured as a rahal nozzle arrangement.
7. An ejector according to claims 1 to 5, further comprising: The outer shell is sleeved outside the second pipeline, a closed pressure stabilizing cavity is formed between the outer shell and the outer wall of the second pipeline, and the pressure stabilizing cavity is communicated with the air inlet channel; the induced draft tube is arranged on the outer shell and communicated with the pressure stabilizing cavity, and the induced draft tube is used for introducing air flow compressed and heated by the air compressor of the aeroengine into the pressure stabilizing cavity.
8. An air intake duct for an aircraft engine, comprising: The air inlet channel body comprises a first flow channel and a second flow channel which are communicated, a transition channel is further arranged between the first flow channel and the second flow channel, and the transition channel is used for centrifugally accelerating gas and particulate matters flowing in from the first flow channel and flowing to the second flow channel; A particulate collection member having a cavity for containing particulate matter and a lip extending into the second flow passage for separating the particulate matter from the gas and guiding the particulate matter into the cavity, and An ejector according to any one of claims 1 to 7.
9. The inlet of claim 1, wherein the first and second flow channels are each configured in an arc, and wherein the curvature of the first flow channel is greater than the curvature of the second flow channel.
10. An aircraft engine comprising an inlet duct according to claim 8 or 9.

Description

Injection device for air inlet channel of aeroengine, air inlet channel and aeroengine The application relates to the technical field of aeroengines, in particular to an injection device for an air inlet channel of an aeroengine, the air inlet channel and the aeroengine. Background During the operation of an aeroengine, extremely high requirements are placed on the quality of air in the air inlet channel. However, in complex operating environments, the air inevitably contains many solid particulates that enter the engine with the air, posing a serious threat to the performance, life, and even safety of the engine. At present, the conventional air inlet duct particulate matter separation equipment has the problems of large volume, complex structure and low energy efficiency, and how to realize the particulate matter separation equipment which has compact structure, high efficiency and energy conservation and is suitable for complex working conditions of aeroengines is a current urgent problem to be solved. Disclosure of Invention In view of the above, the application provides an ejector device for an air inlet of an aeroengine, the air inlet and the aeroengine. The application provides an ejector device for an air inlet channel of an aeroengine, which comprises an ejector pipeline, an ejector pipe and an ejector pipe, wherein the ejector pipeline comprises a first pipeline and a second pipeline which are connected, the first pipeline is used for being connected with a particulate matter collecting part of the air inlet channel, the ejector pipe is arranged in the second pipeline and comprises an air inlet section and an air outlet section which are connected, the air inlet section is connected with the inner wall of the second pipeline and forms an air inlet channel with the outer wall of the second pipeline, the air outlet section is parallel to the axis of the second pipeline, the outlet of the air outlet section faces to one end, far away from the first pipeline, of the second pipeline, and the air inlet channel is used for introducing air flow compressed and heated by a compressor of the aeroengine into the ejector pipe and ejecting the air flow from the outlet of the air outlet section to form ejector air flow in the second pipeline, so that negative pressure is formed in the first pipeline and particulate matters of the particulate matter collecting part are sucked out. According to an embodiment of the present application, the injection pipe includes a plurality of injection pipes, and the plurality of injection pipes are disposed in the second pipe at intervals along a circumferential direction of the second pipe. According to an embodiment of the application, the shape of the cross section of the second pipe is configured as a racetrack-shaped structure consisting of a combination of two semi-circles of the same radius and a rectangle located between the two semi-circles. According to the embodiment of the application, the plurality of air injection pipes are symmetrically distributed by taking a straight line between the circle centers of the two semicircles as a symmetrical axis. According to the embodiment of the application, the ratio of the distance between the center of the outlet of the air injection section and the inner wall of the second pipeline to the distance between the center of the outlet of the air injection section and the center of the second pipeline is 0.3-0.5. According to an embodiment of the application, the injection tube is constructed as a Laval nozzle structure. The air-entraining pipe is arranged on the outer shell and is communicated with the pressure-stabilizing cavity, and the air-entraining pipe is used for introducing air flow compressed and heated by the air compressor of the aeroengine into the pressure-stabilizing cavity. Another aspect of the present application provides an air intake duct for an aircraft engine, characterized by comprising: The air inlet channel body comprises a first flow channel and a second flow channel which are communicated, a transition channel is further arranged between the first flow channel and the second flow channel, and the transition channel is used for centrifugally accelerating gas and particulate matters flowing in from the first flow channel and flowing to the second flow channel; The particle collecting component is provided with a cavity for containing particles, a lip extending into the second flow channel, the lip is used for separating the particles and the gas and guiding the particles to enter the cavity, and the injection device is provided with a nozzle. According to an embodiment of the present application, the first flow passage and the second flow passage are each configured in an arc shape, and the curvature of the first flow passage is greater than the curvature of the second flow passage. In another aspect, the application provides an aeroengine comprising an air inlet duct as described above. According to the t