Aeroengine bleed valve
AssigneeROLLS-ROYCE plc
InventorStuart James Kirby
Life of this patent
Estimating the term…
Abstract
A bleed valve (30) for a gas turbine engine (10) comprises a diffuser (50), through which heated compressor bleed air flows (54) into a bypass duct (22) air stream (B), has a plurality of small holes (40). The plurality of holes (40) is divided into two or more arrays of holes (52p,q,r), each array of holes (52p,q,r) is angled (δ) away from one another so that their respective bleed flows (54p,q,r) do not coalesce. This separation improves mixing with the air stream (B) and helps prevent hot bleed air damaging nacelle and other engine components.
Claims17
A bleed valve for a gas turbine engine, the bleed valve comprises a diffuser having a plurality of holes through which a bleed fluid flows into a fluid stream,
- wherein the plurality of holes of the diffuser is divided into two or more arrays of holes, each array of holes being adjacent to another array of holes, and adjacent arrays of holes having an angle δ between respective bleed flows of the adjacent arrays of holes so that the respective bleed flows of the adjacent arrays of holes do not coalesce.
Dependencies are inferred from the claim text.