一种多级旋流雾化的航空发动机喷油嘴结构
By using a multi-stage swirling atomization structure, the problem of reduced fuel atomization uniformity under high-temperature conditions is solved, achieving efficient mixing of fuel and air and structural stability of the nozzle, thereby improving the reliability of the combustion system.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- JIANGSU YUZHUANG TECHNOLOGY CO LTD
- Filing Date
- 2025-06-09
- Publication Date
- 2026-07-17
AI Technical Summary
Existing fuel injectors are unable to adapt to changes in engine load under high-temperature conditions, resulting in reduced fuel atomization uniformity, which affects the fuel-air mixing efficiency, and they lack an airflow-assisted atomization mechanism.
It adopts a multi-stage swirling atomization structure, including a cooling component and an atomizing component. The spiral tube generates a spiral force, and the main blade and the secondary blade guide the airflow. It works in conjunction with the blowing pipe for secondary guidance and shearing to form a complementary swirling flow field, which increases the kinetic energy of fuel mixing. The heat exchange efficiency is improved by using heat dissipation plates and heat dissipation fins, ensuring fuel refinement and nozzle structure stability.
It improves fuel atomization uniformity and mixing efficiency, ensures combustion stability under different operating conditions, reduces nozzle temperature, avoids material performance degradation, and improves the structural stability of the nozzle in high-temperature environments.
Smart Images
Figure CN224516839U_ABST
Abstract
Claims
1. A multi-stage rotational flow atomizing aeroengine fuel nozzle structure comprising: The mounting ring (1) is characterized in that it further includes a cooling component (2), the top of which is fixedly connected to the bottom of the mounting ring (1), and an atomizing component (3) is fixedly connected to the bottom of the cooling component (2). The atomizing component (3) includes an outer tube (31), the inner wall of the outer tube (31) is fixedly connected to a spiral tube (33) through an air inlet pipe (32), and the outer wall of the air inlet pipe (32) is fixedly connected to the inner wall of the outer tube (31). The inner wall of the outer tube (31) is fixedly connected to a main blade (34), and the main blade (34) is arranged in a ring array along the central axis of the outer tube (31). The inner wall of the top of the outer tube (31) is fixedly connected to an inner tube (35), and the inner wall of the inner tube (35) is fixedly connected to an air blowing pipe (36), and the air blowing pipe (36) is arranged in a ring array along the central axis of the inner tube (35).
2. A multi-stage rotational flow atomizing aeroengine fuel nozzle structure according to claim 1, characterized in that: The outer wall of the inner tube (35) is fixedly connected to the auxiliary blades (37), and the auxiliary blades (37) are arranged in a ring array along the central axis of the inner tube (35). The top of the blowing pipe (36) is fixedly connected to the inner wall of the spiral tube (33), and the outer wall of the air inlet pipe (32) is fixedly connected to the top of the spiral tube (33).
3. The multi-stage rotational flow atomizing aeroengine fuel nozzle structure of claim 1, wherein: The cooling component (2) includes an inner tube (21), the inner wall of which is fixedly connected to a heat sink (22) via a guide ring (23), and the outer wall of the guide ring (23) is fixedly connected to the outer wall of the heat sink (22). The outer wall of the heat sink (22) is fixedly connected to a heat sink fin (24), and the heat sink fin (24) is arranged in a linear array along the outer wall of the heat sink (22).
4. The multi-stage swirling atomizing fuel injector structure for an aircraft engine according to claim 3, characterized in that: The outer wall of the guide ring (23) is fixedly connected to the guide vane (25), and the guide vane (25) is arranged in a ring array along the central axis of the guide ring (23). The outer wall of the guide ring (23) is fixedly connected to the inner wall of the inner tube (21).
5. A multi-stage rotational flow atomizing aeroengine fuel nozzle structure according to claim 4, characterized in that: The top of the inner tube (21) is fixedly connected to the bottom of the mounting ring (1), and the bottom of the inner tube (21) is fixedly connected to the top of the outer tube (31).