Combustor liner cooling system
USH1380H · kind H · statutory invention registration
5Cited by
0References
5Claims
0Family size
Inventors
Key dates
| Filing date | — |
| Grant date | Dec 6, 1994 |
| Priority date | — |
| Expiry date | — |
Classification
- Technology area (CPC —)General
Abstract
A gas turbine engine combustor cooling system for imperforate non-metallic combustor liners has a wall positioned adjacent to the liners forming therewith a cavity. The wall has a plurality of inlets for admitting cooling air into the cavity and a plurality of outlets for exhausting the cooling air into a separate passageway after it impinges the liners. The exhausted cooling air is transferred upstream of the liner where it is combined with fuel for burning rather than discharged downstream as cooling film.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.