| 发明名称 |
MIXED FLOW TURBOCORE |
| 摘要 |
A gas turbine engine is provided having a compressor section, a combustion section located downstream of the compressor section, and a turbine section located downstream of the combustion section. A structural member extends from the compressor section to the turbine section for strengthening one or more components of the gas turbine engine. The structural member also defines a flowpath extending between an inlet in airflow communication with the compressor section and an outlet in airflow communication with the turbine section. The flowpath is configured to provide bleed air from the compressor section to the turbine section to capture at least a portion of the energy in such bleed air. |
| 申请公布号 |
US2017051678(A1) |
申请公布日期 |
2017.02.23 |
| 申请号 |
US201514828541 |
申请日期 |
2015.08.18 |
| 申请人 |
General Electric Company |
发明人 |
BECKER, JR. Thomas Lee |
| 分类号 |
F02C9/18;F02C7/20;F02C3/04 |
主分类号 |
F02C9/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a compressor section; a combustion section located downstream of the compressor section; a turbine section located downstream of the combustion section; and a structural member extending from the compressor section to the turbine section, the structural member defining a flowpath extending between an inlet in airflow communication with the compressor section and an outlet in airflow communication with the turbine section, the flowpath configured to provide bleed air from the compressor section to the turbine section. |
| 地址 |
Schenectady NY US |
