| 发明名称 | Aircraft fuel system cooling flow device | ||
| 摘要 | A cooling system includes a housing having an aperture intersecting a passage that includes first and second passage portions. A plug is arranged in the aperture in an interference fit in a first position at a first temperature condition to block the passage and fluidly separate the first and second passage portions. A biasing element is arranged in the housing and is configured to move the plug from the first position to a second position at a second temperature condition to fluidly connect the first and second passage portions. | ||
| 申请公布号 | US8950170(B2) | 申请公布日期 | 2015.02.10 |
| 申请号 | US201113042538 | 申请日期 | 2011.03.08 |
| 申请人 | Hamilton Sundstrand Corporation | 发明人 | Paradise Bruce |
| 分类号 | F02C7/12;F01D25/08;F16K17/38;F16K99/00;F02C7/22;F16K31/00;F02C7/232 | 主分类号 | F02C7/12 |
| 代理机构 | Carlson, Gaskey & Olds, P.C. | 代理人 | Carlson, Gaskey & Olds, P.C. |
| 主权项 | 1. A cooling system comprising: a housing including an aperture intersecting a passage having first and second passage portions; a plug arranged in the aperture in an interference fit in a first position at a first temperature condition to block the passage and fluidly separate the first and second passage portions; a biasing element arranged in the housing and configured to move the plug from the first position to a second position at a second temperature condition and fluidly connect the first and second passage portions; and a first fuel system component providing the passage, and a second fuel system component in fluid communication with the first fuel system component, wherein the first fuel system component is a fueldraulic actuator. | ||
| 地址 | Windsor Locks CT US | ||