Thermal shielding apparatus or radiositor for a gas turbine engine
US5176495A · kind A · utility
15Cited by
12References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 9, 1991 |
| Grant date | Jan 5, 1993 |
| Priority date | — |
| Expiry date | Jul 9, 2011 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D25/145
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thermal shielding apparatus for use in the low pressure stage of a turbine engine having a plurality of tubular honeycomb cells which are axially aligned and arranged perpendicularly to a radially outwardly directed heat flux. The cells are layered and are housed by an inner and outer liner. The outer liner and an outer casing form a space between them, the outer casing being located radially outward from the outer liner. The layers of honeycomb cells reduce radiant heat flow to the outer casing.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.