| 发明名称 |
AIR SUPPLY DEVICE FOR AIRCRAFT ENGINE TURBINES |
| 摘要 |
An air supply device for an aircraft engine turbine, in which device the air is conveyed to at least one aircraft engine turbine after being conveyed through at least one connecting sleeve from a low pressure distributor to a space defined by at least one upstream side and one downstream side, the upstream side having at least one opening and each pierced opening receiving one end of one of the connecting sleeves, wherein the upstream side and the downstream side are secured by at least one fastener. A retaining plate is used for each fastener in order to position a securing element of the fastener, the retaining plate having a supporting surface that blocks each connecting sleeve axially in one direction. |
| 申请公布号 |
US2015226121(A1) |
申请公布日期 |
2015.08.13 |
| 申请号 |
US201314425534 |
申请日期 |
2013.09.03 |
| 申请人 |
SNECMA |
发明人 |
Cohin Arthur Lou Nicolas;Charrie Audrey;Soupizon Jean-Luc |
| 分类号 |
F02C7/04;F02C7/12;F02C7/20 |
主分类号 |
F02C7/04 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An air supply device for an aircraft engine turbine, comprising:
at least one connecting sleeve; at least one upstream side and one downstream side, wherein air is conveyed to at least one aircraft engine turbine after being conveyed through the at least one connecting sleeve from a low pressure distributor to a space defined by the at least one upstream side and the one downstream side, said upstream side having at least one opening, receiving one end of the connecting sleeve, wherein the upstream side and the downstream side are secured by at least one fastener, a retaining plate is used, for each fastener to position a securing element of the fastener, said retaining plate having a supporting surface that blocks each connecting sleeve axially in one direction. |
| 地址 |
Paris FR |
