Thrust balancing and cooling system
US4653267A · kind A · utility
33Cited by
12References
2Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 26, 1985 |
| Grant date | Mar 31, 1987 |
| Priority date | — |
| Expiry date | Apr 26, 2005 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Thrust balance in a gas turbine engine of the thrust balance seal is modulated by judiciously locating a seal between the inner diffuser case and the rear of the high compressor rotor shaft and bleeding air out of the cavity between both seals. The bled air is utilized to cool a portion of the high pressure turbine rotor. Cool air bled from mid-stage compressor is fed downstream of the second seal to cool the bearing compartment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.