Turbine rear support plate in novel oil-gas matching form and aero-engine
By designing the return zone in the turbine rear support plate and injecting cooling gas and fuel, the problem of unstable combustion of low oxygen content in the new generation of aircraft engines is solved, and the stability and efficiency of combustion are improved.
CN119641446AActive Publication Date: 2025-03-18BEIHANG UNIV
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Patent Information
- Application Number
- CN202411628235.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-14
- Publication Date
- 2025-03-18
- Estimated Expiration
- 2044-11-14
AI Technical Summary
Technical Problem
现有油气匹配形式无法满足新一代航空发动机对低氧含量来流燃烧的要求，导致燃烧不稳定。
Method used
A new type of turbine rear support plate with oil and gas matching form is designed. By forming a return zone in the support plate body and injecting cooling gas and fuel with the cavity, the fuel and cooling gas are fully blended, thereby improving the ignition speed and combustion stability.
Benefits of technology
It effectively improves the ignition speed and combustion stability of the turbine rear support plate return area, and meets the requirements of the wide-area afterburner combustion chamber of the new generation of aircraft engines for low oxygen content flow combustion.
✦ Generated by Eureka AI based on patent content.
Abstract
The invention relates to the technical field of engines, and provides a novel turbine rear support plate in an oil-gas matching form and an aero-engine. The novel turbine rear supporting plate in the oil-gas matching form comprises a supporting plate body, the supporting plate body is provided with a cavity, a part of the supporting plate body is sunken towards the interior of the cavity, a backflow area is formed in the sunken position, and the cavity is used for spraying cooling gas and fuel oil to the backflow area. According to the turbine rear supporting plate in the novel oil-gas matching form, the ignition speed and the combustion stability of a backflow area of the supporting plate body can be well improved by introducing high-oxygen-content cooling gas behind the core fan, and the oil-gas matching form meets the requirement of a wide-area afterburner of a new-generation aero-engine for low-oxygen-content incoming flow combustion.
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