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AssigneeVolvo Aero Corporation
InventorsLinda Ström, Fredrik Wallin, Tomas Fernström
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A gas turbine engine component providing a gas flow passage is provided, which gas flow passage surrounds an inner passage surface, an outer passage surface forming an outer delimitation of said gas flow passage. In an aspect, the trace of the inner passage surface in a cross-section perpendicular to a central axis of the component presents at least one substantially straight portion. In another aspect, where a plurality of circumferentially spaced blades extends between the inner and outer passage surfaces, two portions of the trace, in a cross-section perpendicular to a central axis of the component, of the outer passage surface between two adjacent blades are substantially straight and oriented in an angle in relation to each other so as to form a concavity in the gas flow passage.
A gas turbine engine component comprising an inner passage surface (111) adapted to be surrounded by and to form a delimitation of a gas flow passage (13, 14), characterized in that the trace of the inner passage surface (111) in a cross-section perpendicular to a central axis of the component presents at least one substantially straight portion (113).
A gas turbine engine component according to any one of the preceding claims, comprising an inner part (11) and an outer part (12) forming between them the gas flow passage (13, 14), which gas flow passage (13, 14) surrounds the inner part, the inner part (11) presenting the inner passage surface (111).
A gas turbine engine component according to any one of the preceding claims, wherein the inner passage surface (111) presents in said cross-section a plurality of crests (112), and that said at least one substantially straight portion (113) of the trace is positioned between two adjacent crests.
A gas turbine engine component according to any one of the preceding claims, wherein the inner passage surface (111) forms an external surface of a hub for a propeller for a turboprop engine, or a hub for external blades for an unducted fan (UDF) or an open rotor.
A gas turbine engine component adapted to provide a gas flow passage (13, 14) for at least a part of a gas flow through the gas turbine engine, which gas flow passage (13, 14) surrounds an inner passage surface (111), an outer passage surface (121) forming an outer delimitation of said gas flow passage (13, 14), a plurality of circumferentially spaced blades (15, 16) extending between the inner and outer passage surfaces (111, 121), characterized in that two portions (123) of the trace, in a cross-section perpendicular to a central axis of the component, of the outer passage surface (121) between two adjacent blades are substantially straight and oriented in an angle (a3) in relation to each other so as to form a concavity in the gas flow passage (13, 14).
A gas turbine engine comprising at least one rotatable portion (2, 3) for the operation of a turbine assembly (6, 7) and a compressor assembly (8, 9), located, in relation to a gas flow through the engine, downstream and upstream, respectively, of a combustion chamber (4), characterized in that the engine comprises a gas turbine engine component according to any one of the preceding claims and wherein the central axis of the component coincides with an axis of rotation of said rotatable portion (2, 3).
Dependencies are inferred from the claim text.