Gas turbine engines and compression systems therefor
OwnerRayne Sunginventor
Life of this patent
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Abstract
A gas turbine engine, with a conical screw integrated compression system, that utilizes at least one conical screw as an intermediary fluid transport device to facilitate the multi-staging of non-axial compressors, such as centrifugal and diagonal compressors, as well as or alternatively to combine non-axial compressors to axial compressors and to the fan. The conical screw in the compression system applies axial flow translation and funnels, as necessary, the exit flow of the impeller, fan or compressor into the next impeller or compressor.
Claims14
A non-axial compression system for a gas turbine engine for positioning upstream of a combustor of the gas turbine engine, the non-axial compression system comprising:
- a longitudinal axis;
- a first radial impeller having a first body for rotating about the longitudinal axis;
- a second radial impeller positioned on the longitudinal axis downstream of the first radial impeller and upstream of the combustor, the second radial impeller having a second body for rotating about the longitudinal axis;
- and
- a conical screw positioned on the longitudinal axis between the first radial impeller and the second radial impeller, the conical screw for rotating about the longitudinal axis, the conical screw having:
- a first radius adjacent to the first radial impeller and a second radius adjacent to the second radial impeller, the second radius smaller than the first radius;
- a hub;
- and
- at least one conveyor blade extending outwardly from the hub and positioned between the first radius and the second radius, the first body adjacent to the first radius and the at least one conveyor blade being spaced apart from one another along the longitudinal axis;
- wherein a fluid downstream of the first radial impeller is directed axially by the conical screw towards the second radial impeller.
Dependencies are inferred from the claim text.