We claim:
1. A turbomachine diffuser comprising:
a body having an inner surface defining a diffuser flow path;
a plurality of stationary struts extending from the inner surface; and
a plurality of flow mixing lobes arranged in an annular array on the inner surface, wherein the plurality of flow mixing lobes is configured and disposed to guide a substantially high momentum flow toward the inner surface of the body.
2. The turbomachine diffuser as claimed in claim 1, wherein each of the plurality of flow mixing lobes includes a first lobe member and a second lobe member, each of the first and second lobe members extending radially outwardly of the inner surface into the diffuser flow path.
3. The turbomachine diffuser as claimed in claim 2, wherein at least one of the first and second lobe members extends substantially perpendicularly from the inner surface.
4. The turbomachine diffuser as claimed in claim 2, wherein at least one of the first and second lobe members extends at an angle from the inner surface.
5. The turbomachine diffuser as claimed in claim 2, further comprising: an airfoil portion extending between the first and second lobe members.
6. The turbomachine diffuser as claimed in claim 5, wherein the airfoil portion includes one of a substantially rectangular cross-section and a curvilinear cross-section.
7. The turbomachine diffuser as claimed in claim 5, wherein the airfoil portion includes first and second airfoil members extending from
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corresponding ones of the first and second lobe members at a non-perpendicular angle.
8. The turbomachine diffuser as claimed in claim 1, wherein at least one of the first and second lobe members includes a base section extending circumferentially outwardly of the one of the first and second lobe members, the base section being joined to the inner surface of the body.
9. The turbomachine diffuser as claimed in claim 7, wherein the base section extends substantially perpendicularly outwardly of the one of the first and second lobe members away from the other of the first and second lobe members.
10. A turbomachine comprising:
a compressor portion;
a turbine portion operatively connected to the compressor portion, the turbine portion including an outlet;
a combustor assembly including at least one combustor fluidically connected to the compressor portion and the turbine portion; and
a diffuser fluidically connected to the outlet of the turbine portion, the diffuser comprising:
a body having an inner surface defining a diffuser flow path;
a plurality of stationary struts extending from the inner surface; and
a plurality of flow mixing lobes arranged in an annular array on the inner surface, wherein the plurality of flow mixing lobes is configured and disposed to guide a substantially high momentum flow toward the inner surface of the body.
11. The turbomachine as claimed in claim 10, wherein each of the
plurality of flow mixing lobes includes a first lobe member and a second lobe
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member, each of the first and second lobe members extending radially outwardly of the inner surface into the diffuser flow path.
12. The turbomachine as claimed in claim 11, wherein at least one of the first and second lobe members extends substantially perpendicularly from the inner surface.
13. The turbomachine as claimed in claim 11, wherein at least one of the first and second lobe members extends at an angle from the inner surface.
14. The turbomachine as claimed in claim 11, further comprising: an airfoil portion extending between the first and second lobe members.
15. The turbomachine as claimed in claim 14, wherein the airfoil portion includes one of a substantially rectangular cross-section and a curvilinear cross-section.
16. The turbomachine as claimed in claim 14, wherein the airfoil portion includes first and second airfoil members extending from corresponding ones of the first and second lobe members at a non-perpendicular angle.
17. The turbomachine as claimed in claim 11, wherein at least one of the first and second lobe members includes a base section extending circumferentially outwardly of the one of the first and second lobe members, the base section being joined to the inner surface of the body.
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18. A method of passing exhaust gases from a turbomachine into a
diffuser, the method comprising:
passing hot gases toward an outlet of a turbine portion of the turbomachine;
delivering the hot gases into an inlet of the diffuser;
directing a portion of the hot gases toward a plurality of flow mixing lobes arranged circumferentially about an inner surface of the diffuser;
forming the portion of the hot gases into a substantially high momentum flow;
guiding the substantially high momentum flow toward the inner surface of the diffuser; and
mixing the substantially high momentum flow with a boundary layer flow passing along the inner surface.
19. The method as claimed in claim 18, wherein guiding the substantially high momentum flow toward the inner surface of the diffuser includes directing a flow passing from an outlet of a turbine portion of a turbomachine across an airfoil portion of a plurality of flow mixing lobes.
20. The method as claimed in claim 19, wherein directing the flow across an airfoil portion of a plurality of flow mixing lobes includes passing the flow across an airfoil portion extending between first and second lobe members of the plurality of flow mixing lobes.

Sandeep Rao
Agent for Applicant IN/PA-2098
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Dated this the 22nd day of May, 2015 Total Claims: 20