平衡寿命与推力的喷管喉道面积调节计划确定方法及装置
By optimizing the nozzle throat area adjustment plan and adjusting the inlet airflow of the aero-engine, the problem of high thermal load on hot-end components in the intermediate state was solved, and the engine life was extended under the target thrust.
CN117329019BActive Publication Date: 2026-07-17AECC SHENYANG ENGINE RES INST
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AECC SHENYANG ENGINE RES INST
- Filing Date
- 2023-11-03
- Publication Date
- 2026-07-17
AI Technical Summary
Technical Problem
When existing aero engines fly in the intermediate state, the nozzle throat area is not adjusted and optimized, which leads to an increase in the thermal load of hot-end components and reduces the service life of the engine.
Method used
By optimizing the nozzle throat area adjustment plan, adjusting the overall inlet airflow, and reducing the turbine inlet temperature, the turbine base temperature is ensured to be the lowest under the target thrust conditions. The nozzle throat area optimization design is adopted to balance life and thrust.
Benefits of technology
While maintaining constant thrust, the thermal load on the engine's hot-end components was reduced, thus improving the engine's service life.
✦ Generated by Eureka AI based on patent content.
Smart Images
Figure CN117329019B_ABST
Abstract
本申请属于发动机控制技术领域，具体涉及一种平衡寿命与推力的喷管喉道面积调节计划确定方法及装置。该方法包括步骤S1、确定指定高度及马赫数下的飞行包线右边界的推力目标值；步骤S2、以地面台架设计点喷管喉道面积作为初始值至达到机械面积最大值，形成多个喷管喉道面积设计点；步骤S3、在保持推力目标值不变的条件下，确定各喷管喉道面积设计点对应的控制计划值参数、压气机出口截面参数及涡轮进口截面参数；步骤S4、根据压气机出口截面参数及涡轮进口截面参数确定涡轮基体温度；步骤S5、选取涡轮基体温度最低值所对应的喷管喉道面积设计点，作为发动机中间状态的控制计划值。本申请降低了热端部件的热负荷，提高了发动机使用寿命。
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