Ventilation system for nacelle |
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| 申请号 | JP28659188 | 申请日 | 1988-11-12 | 公开(公告)号 | JPH0223257A | 公开(公告)日 | 1990-01-25 |
| 申请人 |
United Technol Corp |
发明人 | ROBAATO BUBERO; JIEFURII IN RIIMU; | ||||
| 摘要 | PURPOSE: To improve exhaust efficiency by forming pressure relief holes in a nacelle surrounding a gas turbine engine, wherein a door for opening and closing the pressure relief hole as a pressure in the nacelle increases is pivotally supported by a hinge at the upstream of the hole. CONSTITUTION: A nacelle 14 surrounding a gas turbine engine 12 for aircrafts is composed of a fan nacelle 16 and a core nacelle 18. The core nacelle 18 has a nacelle wall 34 and the fan nacelle 16 has an inner wall 36. An annular fan bypass passage 38 is formed in a gap between the inner wall 36 and a fan chamber radially spaced from the inner side of the inner wall 36. Further, the core nacelle 18 is provided with a pair of pressure relief holes 48 in the nacelle wall 34. In this case, each of the relief holes 48 is provided with a relief door 50 pivotally supported by a hinge at the upstream of the hole 48. As the pressure in the nacelle 14 increases the door 50 is rotated from a fully closed position via a pressure equilibrium position to a fully opened position. COPYRIGHT: (C)1990,JPO |
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