| 发明名称 |
METHOD AND ASSEMBLY FOR REDUCING SECONDARY HEAT IN A GAS TURBINE ENGINE |
| 摘要 |
A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly. |
| 申请公布号 |
US2016186666(A1) |
申请公布日期 |
2016.06.30 |
| 申请号 |
US201514844097 |
申请日期 |
2015.09.03 |
| 申请人 |
United Technologies Corporation |
发明人 |
Suciu Gabriel L.;Partyka Julian;Pack David R.;Hill James D. |
| 分类号 |
F02C9/18;F02C7/12 |
主分类号 |
F02C9/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A turbine section for a gas turbine engine comprising:
a first rotor assembly with a first rotor assembly bleed air source and an aft cavity in fluid communication with the first rotor assembly bleed air source; a second rotor assembly including a forward cavity; a vane bleed air source in fluid communication with the forward cavity; and a seal extending between the first rotor assembly and the second rotor assembly. |
| 地址 |
Hartford CT US |
