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US 8,984,890 B2Granted
Turbofan engine mixer assembly
AssigneeGeneral Electric Company
InventorsMustafa Dindar, Vaughn Kunze
Life of this patent
Estimating the term…
Abstract
A mixer for mixing flows in a turbofan engine is provided. The mixer includes a plurality of chevron lobes, each of the plurality of lobes comprising a crown, a keel, a first trailing edge, a second trailing edge, and a first transverse edge extending between first trailing edge and second trailing edge, said mixer configured to receive two separate incoming exhaust flows and mix the two flows into at least one rotational exhaust flow that is ejected out at least one of said first trailing edge and said second trailing edge.
Claims9
A mixer for mixing flows in a turbofan engine, said mixer comprising:
- a plurality of chevron lobes, each of the plurality of lobes comprising a crown, a keel, a first trailing edge, a second trailing edge, and a first transverse edge extending between said first trailing edge and said second trailing edge, said mixer configured to receive two separate incoming exhaust flows and mix the two flows;
- wherein said plurality of chevron lobes further comprises a first chevron defined by said first trailing edge and said first transverse edge;
- wherein each of said plurality of chevron lobes comprise first and second chevron tips, said second chevron tip defined between said first transverse edge and said second trailing edge;
- wherein said first chevron tip is defined from said crown to the most radially inward point of said first trailing edge;
- wherein one or both of said first and second chevron tips are folded outward from an interior portion of a respective lobe or folded inwards from said interior portion of said respective lobe.
2 more elements
A turbofan engine comprising:
- a mixer for mixing flows in a turbofan engine, said mixer comprising a plurality of chevron lobes, each of the plurality of lobes comprising a crown, a keel, a first trailing edge, a second trailing edge, and a first transverse edge extending between said first trailing edge and said second trailing edge, said mixer configured to receive two separate incoming exhaust flows and mix the two flows;
- wherein said plurality of chevron lobes further comprises a first chevron defined by said first trailing edge and said first transverse edge;
- wherein each of said plurality of chevron lobes comprise first and second chevron tips, said second chevron tip defined between said first transverse edge and said second trailing edge;
- wherein said first chevron tip is defined from said crown to the most radially inward point of said first trailing edge;
- wherein one or both of said first and second chevron tips are folded outward from an interior portion of a respective lobe or folded inwards from said interior portion of said respective lobe.
2 more elements
An aircraft comprising:
- a turbofan engine comprising a mixer for mixing flows in a turbofan engine, said mixer comprising a plurality of chevron lobes, each of the plurality of lobes comprising a crown, a keel, a first trailing edge, a second trailing edge, and a first transverse edge extending between said first trailing edge and said second trailing edge, said mixer configured to receive two separate incoming exhaust flows and mix the two flows;
- wherein said plurality of chevron lobes further comprises a first chevron defined by said first trailing edge and said first transverse edge;
- wherein each of said plurality of chevron lobes comprise first and second chevron tips, said second chevron tip defined between said first transverse edge and said second trailing edge;
- wherein said first chevron tip is defined from said crown to the most radially inward point of said first trailing edge;
- wherein one or both of said first and second chevron tips are folded outward from an interior portion of a respective lobe or folded inwards from said interior portion of said respective lobe.
2 more elements
Dependencies are inferred from the claim text.