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US 9,810,082 B2Granted
Gas turbine engine for aircraft engine
AssigneeGE Avio S.r.l.
InventorPaolo Calza
Life of this patent
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Abstract
A gas turbine stator for aircraft engines has a blade array with a plurality of blades constituted by a series of first blades and a series of second blades with different geometries; the array is formed by a plurality of sectors, each having an inner portion, an outer portion, at least one first blade and a least one second blade, and each defined by a body made in one piece; a single first blade is alternated with a single second blade for the entire circumference of the stator.
Claims11
A stator for a gas turbine of an aircraft engine, the stator comprising:
- a blade array comprising a plurality of blades constituted by a series of first blades and a series of second blades, said first blades having a different geometry from said second blades,
- said first and second blades are arranged to alternate a single first blade with a single second blade for the entire circumference of the stator,
- said blade array is defined by a plurality of sectors, each comprising:
- i) an inner curved portion;
- ii) an outer curved portion;
- iii) at least one of said first blades and at least one of said second blades;
- each of said plurality of sectors is defined by a body made in one piece, wherein the inner curved portions of adjacent sectors form an inner annular end-wall, and wherein the outer curved portions of adjacent sectors form an outer annular end-wall,
- each of said first blades having a first radial generatrix and each of said second blades having a second radial generatrix, said first radial generatrix comprising at least one first curved segment and at least one first straight segment, and said second radial generatrix comprising at least one second curved segment and at least one second straight segment, wherein said first radial generatrix and said second radial generatrix are different from each other.
5 more elements
A stator comprising:
- a plurality of blades constituted by a series of first blades and a series of second blades, said first blades having a different geometry from said second blades, said first and second blades are arranged to alternate a single first blade with a single second blade for the entire circumference of the stator, said blade array is defined by a plurality of sectors, each comprising:
- i. an inner curved portion;
- ii. an outer curved portion;
- iii. at least one of said first blades and at least one of said second blades,
- each said sector is defined by a body made in one piece, wherein the inner curved portions of adjacent sectors form an inner annular end-wall, and wherein the outer curved portions of adjacent sectors form an outer annular end-wall,
- each first blade of said series of first blades having a first radial generatrix and each second blade of said series of second blades having a second radial generatrix, the first radial generatrix comprising at least one first curved segment, and the second radial generatrix comprising at least one a second curved segment, each first curved segment having a first curvature and each second curved segment having a second curvature that is different than the first curvature, and the first curvature and the second curvature each having at least a portion that curves in the same direction.
3 more elements
Dependencies are inferred from the claim text.