| 发明名称 | Method of forming an aerofoil with a damping filler | ||
| 摘要 | A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels. | ||
| 申请公布号 | US8857054(B2) | 申请公布日期 | 2014.10.14 |
| 申请号 | US200812216497 | 申请日期 | 2008.07.07 |
| 申请人 | Rolls-Royce PLC | 发明人 | Goldfinch Keith C.;Strother Oliver M.;MacKechnie-Jarvis Julian |
| 分类号 | B21D53/78;F01D5/14;F04D29/02;F04D29/66;F04D29/32;F01D5/26;B23P15/04 | 主分类号 | B21D53/78 |
| 代理机构 | Oliff PLC | 代理人 | Oliff PLC |
| 主权项 | 1. A method of manufacturing an aerofoil for a gas turbine engine with a first panel, a second panel and a pattern of ribs on a web, the method comprising the steps of: bonding the ribs to a first surface of at least one of the first panel and the second panel in selected regions, and deforming the first panel and the second panel by applying internal pressure between the first panel and the second panel so as to form an internal cavity, and wherein at least one rib forming a protrusion extends from the first surface partially across, but not completely across, the internal cavity between the first panel and the second panel. | ||
| 地址 | London GB | ||