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发明公开
CN105189938A 用于燃气涡轮发动机的带喷嘴注射的涡轮发动机停机温度控制系统 失效 - 权利终止

用于燃气涡轮发动机的带喷嘴注射的涡轮发动机停机温度控制系统
摘要：
公开了一种涡轮发动机停机温度控制系统(10)，其被配置成在燃气涡轮发动机(16)停机期间，限制在包围涡轮叶片组件(14)的外壳(12)内产生的热梯度。通过减少在所述外壳(12)的中间区域空腔(18)内由热空气浮力所造成的热梯度，可以防止所述外壳(12)的拱形和背凹弯曲，从而减少所述燃气涡轮发动机(16)的热重启动期间，叶片尖端摩擦以及潜在的叶片损坏的可能性。所述涡轮发动机停机温度控制系统(10)可在其中所述转子(26)仍然由燃烧气体供给动力的所述停机过程期间或在所述燃气涡轮发动机(16)停机后转动齿轮系统操作期间，或在两个期间操作，以允许外壳(12)均匀地从上到下冷却。
摘要（英）：

A turbine engine shutdown temperature control system (10) configured to limit thermal gradients from being created within an outer casing (12) surrounding a turbine blade assembly (14) during shutdown of a gas turbine engine (16) is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities (18) in the outer casing (12), arched and sway-back bending of the outer casing (12) is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine (16). The turbine engine shutdown temperature control system (10) may operate during the shutdown process where the rotor (26) is still powered by combustion gases or during turning gear system operation after shutdown of the gas turbine engine, or both, to allow the outer casing (12) to uniformly, from top to bottom, cool down.

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