Thermal shielding apparatus or radiositor for a gas turbine engine
AssigneeGeneral Electric Company
InventorsMark S. Honkomp, Allewis A. Greninger
Life of this patent
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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.
Claims6
A thermal insulation assembly for protecting an outer casing from a high temperature working medium gas flow, the assembly being located radially inward from an annular space formed by the outer casing, said thermal insulation assembly comprising:
- (a) a plurality of honeycomb cells wherein
- (i) said plurality of honeycomb cells comprises a plurality of layers of honeycomb cells for controlling radiant heat flow, said plurality of layers aligned parallel to a radially outwardly directed heat flux, and
- (ii) each of said plurality of honeycomb cells includes a longitudinal axis arranged perpendicularly to said radially outwardly directed heat flux;
- and
- (b) housing means connected to the plurality of honeycomb cells for housing the plurality of honeycomb cells.
Dependencies are inferred from the claim text.