| 发明名称 |
SYSTEM AND METHOD FOR COORDINATED CONTROL OF A POWER SYSTEM |
| 摘要 |
An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application includes a first motor/generator coupled to a low pressure (LP) shaft of the gas turbine engine, a second motor/generator coupled to a high pressure (HP) shaft of the gas turbine engine, and a system controller coupled to each of the gas turbine engine, a first motor generator and a second motor/generator, wherein the controller receives engine thrust demand and electrical power demand and is programmed to determine total system power demand and the amount of power sharing between the first motor/generator and the second motor/generator to meet thrust and electrical power demand. |
| 申请公布号 |
US2015191252(A1) |
申请公布日期 |
2015.07.09 |
| 申请号 |
US201414585888 |
申请日期 |
2014.12.30 |
| 申请人 |
Rolls-Royce Corporation ;Rolls-Royce North American Technologies, Inc. |
发明人 |
Cline Curtis H.;Armstrong Michael J. |
| 分类号 |
B64D31/12;F02C7/36;F02C9/00 |
主分类号 |
B64D31/12 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application, comprising:
a first motor/generator coupled to a low pressure (LP) shaft of the gas turbine engine; a second motor/generator coupled to a high pressure (HP) shaft of the gas turbine engine; and a system controller coupled to each of the gas turbine engine, the first motor/generator, and the second motor/generator, wherein the controller is programmed to determine an amount of power sharing between the first motor/generator and the second motor/generator to meet a power demand and control a gas generator portion of the gas turbine engine using a total system power demand as a control variable. |
| 地址 |
Indianapolis IN US |
