Method and assembly for reducing secondary heat in a gas turbine engine
US10378453B2 · kind B2 · utility
0Cited by
12References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 3, 2015 |
| Grant date | Aug 13, 2019 |
| Priority date | — |
| Expiry date | Dec 17, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.