A liquid fuel engine thrust chamber pintle head regenerative cooling structure
By designing a concave structure and a swirling tangential hole cooling channel on the injector housing of a liquid fuel engine, the thermal protection problem of the needle plug head is solved, improving combustion efficiency and engine performance.
CN121184261BActive Publication Date: 2026-06-23SHAANXI TIANHUI AEROSPACE TECH CO LTD +1
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Patent Information
- Application Number
- CN202511424538.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-30
- Publication Date
- 2026-06-23
- Estimated Expiration
- 2045-09-30
AI Technical Summary
Technical Problem
In existing liquid fuel engines, the needle plug has a complex thermal environment due to thermal protection requirements, which leads to reduced combustion efficiency using traditional methods.
Method used
The system employs a cooling channel with a concave structure and swirling tangential holes on the injector housing. It utilizes liquid propellant to form a cooling oil film and swirling atomization, thereby reducing the number of auxiliary nozzles and improving combustion efficiency.
Benefits of technology
By designing swirl tangential holes and cooling channels, the cooling efficiency of the needle plug head is improved, the flow rate of the main injection hole is increased, and the combustion efficiency and specific impulse of the engine are enhanced.
✦ Generated by Eureka AI based on patent content.
Abstract
The present application relates to the technical field of aerospace engine, in particular to a liquid fuel engine thrust chamber needle bolt head regenerative cooling structure, comprising: a thrust chamber and a needle injection injector, the injector shell of the needle injection injector is arranged in the thrust chamber from the top of the thrust chamber, and the injector shell is located in the thrust chamber, at least one week main injection hole is arranged on the radial of the injector shell, the annular gap is formed between the injector shell and the top shell of the thrust chamber, and the end of the injector shell is provided with an inner recess structure in the thrust chamber; The first cooling flow channel and the second cooling flow channel are arranged in the injector shell above and below the main injection hole, and the outlet of the second cooling flow channel is connected with the rotational flow tangential hole; wherein, the liquid propellant in the propellant combination is injected into the injector shell, and the annular gap between the injector shell and the top shell of the thrust chamber is used for injecting another propellant in the propellant combination. The present application improves the combustion efficiency of the thrust chamber, and improves the specific impulse and the thrust-to-weight ratio of the engine.
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