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AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorsReyya Nitin RAO, Christoph KLAUS
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The disclosure relates to an annular component for an aircraft gas turbine, having a front flange structure in the direction of flight, a rear flange structure in the axial direction and an annulus structure arranged between the flange structures in the axial direction, wherein the annulus structure has a variable cross-sectional form and/or a variable material arrangement in the circumferential direction and/or perpendicularly to the circumferential direction and at least one of the flange structures has at least two annular portions in the circumferential direction, which are each arranged at a different angle relative to the annulus structure. The disclosure furthermore relates to an aircraft gas turbine having an annular component and a method for producing the annular component.
An annular component for an aircraft gas turbine, having a front flange structure in the direction of flight, a rear flange structure in the axial direction and an annulus structure arranged between the flange structures in the axial direction, wherein the annulus structure has a variable cross-sectional form and/or a variable material arrangement in the circumferential direction and/or perpendicularly to the circumferential direction and at least one of the flange structures has at least two annular portions in the circumferential direction, which are each arranged at a different angle relative to the annulus structure.
Dependencies are inferred from the claim text.