Concentric turbomachine with trailing edge
AssigneeROLLS-ROYCE plc
InventorGiles E Harvey
Life of this patent
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Abstract
An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. A swept area of the outer fan is from 2 to 20 times greater than a swept area of the inner fan.
Claims19
An axial flow turbomachine for producing thrust to propel an aircraft, the turbomachine comprising:
- an inner duct and an outer duct, both of the inner duct and the outer duct are annular and concentric with one another;
- an inner fan located in the inner duct, the inner fan being configured to produce a primary pressurized flow;
- and
- an outer fan located in the outer duct, the outer fan being configured to produce a secondary pressurized flow and having a hollow hub through which the inner duct passes;
- wherein a duct length is defined by a length of a trailing edge of the outer duct located axially downstream of the inner duct, a swept area of the outer fan is from 2 to 20 times greater than a swept area of the inner fan, and the duct length is defined by a range between 6 times a tip radius of the inner fan and 8 times the tip radius of the inner fan.
Dependencies are inferred from the claim text.