| 发明名称 | Gas turbine combustor endcover with adjustable flow restrictor and related method | ||
| 摘要 | An endcover for a turbine combustor adapted to support one or more combustor nozzles, includes a plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel cavity is formed in the plate; and a fuel restrictor insert is formed with at least one flow orifice located within the fuel cavity for supplying fuel to at least one combustor nozzle. The fuel restrictor insert is adjustable along a length dimension of the fuel cavity. | ||
| 申请公布号 | US9188340(B2) | 申请公布日期 | 2015.11.17 |
| 申请号 | US201113300396 | 申请日期 | 2011.11.18 |
| 申请人 | General Electric Company | 发明人 | Bailey Donald Mark;Khan Abdul Rafey |
| 分类号 | F02C1/00;F23R3/28;F23R3/10;F23M20/00 | 主分类号 | F02C1/00 |
| 代理机构 | Nixon & Vanderhye P.C. | 代理人 | Nixon & Vanderhye P.C. |
| 主权项 | 1. An endcover for a turbine combustor adapted to support one or more combustor nozzles, the endcover comprising: a plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber; at least one fuel cavity in said plate; a fuel restrictor insert formed with two or more flow orifices located within said at least one fuel cavity for supplying fuel to at least one combustor nozzle, said fuel restrictor insert adjustable along a length dimension of said at least one fuel cavity. | ||
| 地址 | Schenectady NY US | ||