Gas turbine engine comprising an ejector
AssigneeROLLS-ROYCE plc
InventorZahid M. HUSSAIN
Life of this patent
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Abstract
A gas turbine engine including: a bypass duct, a compressor stage, a cooling duct and an ejector. The cooling duct has an inlet which opens into the bypass duct. The ejector extends continuously through the cooling duct along an extension direction. The ejector includes an aperture and an aerodynamic structure. The aperture is configured to discharge gas received from the compressor stage into the cooling duct. The aerodynamic structure is configured to generate a plurality of vortex pairs downstream of the aperture within a flow of gas conveyed through the cooling duct along a bulk flow direction.
Claims20
A gas turbine engine comprising:
- a bypass duct;
- a compressor stage;
- a cooling duct having an inlet which opens into the bypass duct;
- and
- an ejector extending continuously through the cooling duct along an extension direction, the ejector including:
- an aperture configured to discharge gas received from the compressor stage into the cooling duct;
- and
- an aerodynamic structure configured to generate a plurality of vortex pairs downstream of the aperture within a flow of gas conveyed through the cooling duct along a bulk flow direction.
Dependencies are inferred from the claim text.