CN-224230061-U - Combustion chamber for solving difficult starting of high-altitude large incoming flow of turbojet engine

CN224230061UCN 224230061 UCN224230061 UCN 224230061UCN-224230061-U

Abstract

The utility model discloses a combustion chamber for solving the problem of difficult starting of high altitude large incoming flow of a turbojet engine, which belongs to the technical field of engines and comprises a combustion chamber shell, two ignition heads, two nozzles and two nozzles, wherein the two ends of the combustion chamber shell are respectively provided with an inlet and an outlet, the two ignition heads are arranged at the inlet end of the combustion chamber shell, the ignition ends of the ignition heads extend into the combustion chamber shell, the two nozzles are arranged on the side wall of the combustion chamber shell, the injection ends of the nozzles extend into the combustion chamber shell and face the ignition heads, the two nozzles are respectively positioned at two sides of the ignition heads, and the two nozzles are arranged in an eight shape, so that one nozzle is arranged in the forward direction along the rotation direction of air flow in the combustion chamber shell, and the other nozzle is arranged in the reverse direction along the rotation direction of the air flow in the combustion chamber shell. The two nozzles of the utility model, one of which is ignited under the action of air flow, and the other of which is ignited after being diffused under the action of air flow, realize the action of oiling, prevent the ignited flame from being impacted, increase the combustion degree and improve the ignition effect.

Inventors

Ye Sijuan
CHEN GANG
WU CHAO
JIA SHENGXI
WANG DONG
WANG LIN
Huo Xianglong

Assignees

保定市玄云涡喷动力设备研发有限公司

Dates

Publication Date: 20260512
Application Date: 20250521

Claims (5)

1. A combustion chamber for solving the problem of difficult starting of high altitude large incoming flow of a turbojet engine, comprising: the combustion chamber comprises a combustion chamber shell (1), wherein an inlet (2) and an outlet are respectively formed in two opposite ends of the combustion chamber shell (1); The two ignition heads are arranged at the inlet end of the combustion chamber shell (1), and the ignition ends of the ignition heads extend into the combustion chamber shell (1); Two nozzles (3), two nozzle (3) are installed on the lateral wall of combustion chamber shell (1), the injection end of nozzle (3) stretches into in combustion chamber shell (1) and towards the ignition head, two nozzle (3) are located respectively the both sides of ignition head, two nozzle (3) are "eight style of calligraphy" setting, thereby make one of them nozzle (3) follow the direction of rotation forward arrangement of air current in combustion chamber shell (1), another nozzle (3) are followed the direction of rotation reverse arrangement of air current in combustion chamber shell (1).
2. The combustion chamber for solving the problem of difficult starting of high-altitude large incoming flow of a turbojet engine according to claim 1, wherein the axis of the ignition head is parallel to the axis of the combustion chamber shell (1), and the axis of the nozzle (3) is perpendicular to the axis of the combustion chamber shell (1).
3. The combustion chamber for solving the problem of difficult starting of high-altitude large incoming flow of a turbojet engine according to claim 1, wherein two first mounting holes (4) are formed in the inlet end face of the combustion chamber shell (1), and two ignition heads penetrate through the two first mounting holes (4) respectively and are fixedly connected with the combustion chamber shell (1).
4. The combustion chamber for solving the problem of difficult starting of high-altitude large incoming flow of a turbojet engine according to claim 1, wherein two second mounting holes are formed in the side wall of the combustion chamber shell (1), and two nozzles (3) penetrate through the two second mounting holes respectively and are fixedly connected with the side wall of the combustion chamber shell (1).
5. The combustion chamber for solving the problem of difficult starting of high altitude large incoming flow of a turbojet engine according to claim 3, wherein the connection of the center points of the two first mounting holes (4) is a symmetrical line, and the two nozzles (3) are symmetrically arranged at two sides of the symmetrical line.

Description

Combustion chamber for solving difficult starting of high-altitude large incoming flow of turbojet engine Technical Field The utility model relates to the technical field of engines, in particular to a combustion chamber for solving the problem of difficult starting of high-altitude large incoming flow of a turbojet engine. Background When the aircraft is used, the aircraft needs to be started after being brought to the high altitude, and the turbojet engine generates high-temperature and high-pressure gas through compressed air and combustion to drive the turbine to rotate so as to generate thrust to drive the aircraft to move forward. However, the high-altitude low-temperature environment and the large incoming flow caused by high speed lead to that the fuel sprayed by the fuel spray nozzle in the original combustion chamber can not reach the position of the ignition head, and the ignition can not be successfully performed. Therefore, a combustion chamber for solving the problem of difficult starting of large incoming flow at high altitude of the turbojet engine is provided. Disclosure of utility model The utility model aims to provide a combustion chamber for solving the problem of difficult starting of high altitude large incoming flow of a turbojet engine, and aims to solve or improve at least one of the technical problems. In order to achieve the purpose, the utility model provides a combustion chamber for solving the problem of difficult starting of high altitude large incoming flow of a turbojet engine, comprising: the combustion chamber comprises a combustion chamber shell, wherein an inlet and an outlet are respectively formed in two opposite ends of the combustion chamber shell; the ignition heads are arranged at the inlet end of the combustion chamber shell, and the ignition ends of the ignition heads extend into the combustion chamber shell; The two nozzles are arranged on the side wall of the combustion chamber shell, the injection ends of the nozzles extend into the combustion chamber shell and face the ignition head, the two nozzles are respectively positioned on two sides of the ignition head, and the two nozzles are arranged in an eight shape, so that one of the nozzles is arranged along the rotating direction of the air flow in the combustion chamber shell in a forward direction, and the other nozzle is arranged along the rotating direction of the air flow in the combustion chamber shell in a reverse direction. Preferably, the axis of the ignition head is parallel to the axis of the combustion chamber housing, and the axis of the nozzle is perpendicular to the axis of the combustion chamber housing. Preferably, two first mounting holes are formed in the inlet end face of the combustion chamber shell, and the two ignition heads penetrate through the two first mounting holes respectively and are fixedly connected with the combustion chamber shell. Preferably, two second mounting holes are formed in the side wall of the combustion chamber shell, and the two nozzles penetrate through the two second mounting holes respectively and are fixedly connected with the side wall of the combustion chamber shell. Preferably, the connection of the center points of the two first mounting holes is a symmetrical line, and the two nozzles are symmetrically arranged at two sides of the symmetrical line. The utility model discloses the following technical effects that air flow enters the combustion chamber shell from the inlet of the combustion chamber shell, and flows forwards towards the outlet end in a rotating way, after fuel oil sprayed from nozzles arranged in the forward direction of the air flow is atomized, the contact point fire head is ignited under the assistance of spraying force and the air flow, and the fuel oil sprayed from the nozzles arranged in the reverse direction of the air flow in the rotating direction of the air flow is impacted and atomized by the air flow flowing at high speed to be highly diffused, so that the ignited fuel oil is contacted for combustion, the oiling effect is realized, the ignited flame is prevented from being impacted, the combustion degree is increased, and the ignition effect is improved. Drawings The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings: FIG. 1 is a schematic diagram of the structure of the present utility model; FIG. 2 is a schematic view of a nozzle arrangement structure according to the present utility model. In the figure, 1, a combustion chamber shell, 2, an inlet, 3, a nozzle and 4, and a first mounting hole. Detailed Description The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent t