System for controlling heat expansion and thermal stress in a gas turbine disk
US4741153A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 14, 1982 |
| Grant date | May 3, 1988 |
| Priority date | — |
| Expiry date | Oct 14, 2002 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention concerns a system for controlling heat expansion and thermal stress in a gas turbine disk. The system includes perforated plates mounted close to and facing at least one surface of the disk, particularly opposite its rim and around its thick inner bored section. Conduits are provided for bleeding cold air and hot air from various stages of the compressor or from the turbine and for injecting cold air toward the rim of the disk and hot air toward its thick inner bored section through the corresponding perforated plates at the beginning of each acceleration, and, preferentially, during deceleration, for injecting hot air toward the said rim and cold air toward said inner bored section. The invention applies particularly to gas turbines used to propel aircraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.