A wake reducing structure includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the
A wake reducing structure includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is a wake generating component boss operatively coupled to the combustor liner and disposed within a combustor liner aperture. Also included is a cooling channel extending through the wake generating component boss, the cooling channel having an air inlet on an upstream region of the wake generating component boss and an air outlet on a downstream region of the wake generating component boss, the cooling channel configured to supply air to the wake region.
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1. A wake reducing structure for a turbine system comprising: a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber;a sleeve at least partially surrounding the combustion liner;an airflow path located along the outer surface of the combustor l
1. A wake reducing structure for a turbine system comprising: a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber;a sleeve at least partially surrounding the combustion liner;an airflow path located along the outer surface of the combustor liner and between the combustion liner and the sleeve;a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region, in the air flow path, located downstream of the wake generating component;a wake generating component boss operatively coupled to the combustor liner and disposed within a combustor liner aperture; anda cooling channel extending through the wake generating component boss, the cooling channel having an air inlet on an upstream region of the wake generating component boss and an air outlet on a downstream region of the wake generating component boss, the cooling channel air outlet configured to supply air to the wake region of the wake generating component. 2. The wake reducing structure of claim 1, wherein the wake generating component comprises a fuel injector. 3. The wake reducing structure of claim 1, wherein the wake generating component boss is formed by an additive manufacturing process. 4. The wake reducing structure of claim 3, wherein the additive manufacturing process comprises direct metal laser melting (DMLM). 5. The wake reducing structure of claim 3, wherein the additive manufacturing process comprises direct metal laser sintering (DMLS). 6. The wake reducing structure of claim 1, wherein the wake generating component boss is welded to the combustor liner. 7. The wake reducing structure of claim 1, further comprising a plurality of cooling channels extending through the wake generating component boss. 8. A fuel injector assembly for a combustor assembly of a gas turbine engine comprising: a combustor liner having an outer surface;a sleeve surrounding the combustor liner at a radially outwardly spaced location;an airflow path defined by the outer surface of the combustor liner and the sleeve and between the combustion liner and the sleeve;a fuel injector disposed in the airflow path and extending at least partially through a combustor liner aperture and a sleeve aperture;a boss disposed in the airflow path, the boss disposed within a combustor liner aperture and operatively coupled to a combustor liner aperture wall, the boss formed by an additive manufacturing process; anda cooling channel extending through the boss, the cooling channel having an air inlet on an upstream region of the boss and an air outlet on a downstream region of the boss, the cooling channel air outlet configured to supply air to a wake region, in the air flow path, located downstream of the fuel injector. 9. The fuel injector assembly of claim 8, wherein the additive manufacturing process comprises direct metal laser melting (DMLM). 10. The fuel injector assembly of claim 8, wherein the additive manufacturing process comprises direct metal laser sintering (DMLS). 11. The fuel injector assembly of claim 8, wherein the boss is welded to the combustor liner aperture wall. 12. The fuel injector assembly of claim 8, further comprising a plurality of cooling channels extending through the boss. 13. The fuel injector assembly of claim 8, wherein the cooling channel comprises a diameter ranging from about 100 micrometers (μm) to about 3 millimeters (mm). 14. A gas turbine engine comprising: a compressor section;a turbine section; anda combustor assembly comprising:an airflow path defined by an outer surface of a combustor liner and a sleeve surrounding the combustor liner and between the combustion liner and the sleeve;a fuel injector disposed in the airflow path and extending at least partially through a combustor liner aperture and a sleeve aperture;a boss disposed in the airflow path, the boss disposed within a combustor liner aperture, and operatively coupled to a combustor liner aperture wall, the boss formed by an additive manufacturing process; anda plurality of cooling channels extending through the boss, the plurality of cooling channels each having an air inlet on an upstream region of the boss and an air outlet on a downstream region of the boss, the air outlet of each of the plurality of cooling channels configured to supply air to a wake region, in the air flow path, located downstream of the fuel injector. 15. The gas turbine engine of claim 14, wherein the additive manufacturing process comprises direct metal laser melting (DMLM). 16. The gas turbine engine of claim 14, wherein the additive manufacturing process comprises direct metal laser sintering (DMLS). 17. The gas turbine engine of claim 14, wherein the boss is welded to the combustor liner aperture wall. 18. The gas turbine engine of claim 14, wherein each of the plurality of cooling channels comprise a diameter ranging from about 100 micrometers (μm) to about 3 millimeters (mm).
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이 특허에 인용된 특허 (7)
Khan, Abdul Rafey; Crawley, Bradley Donald; Paniharam, Rajendra; Parsania, Nishant Govindbhai, Combustor having wake air injection.
Leglaye, Francois; Bidart, Olivier; Pireyre, Pierre-Francois; Pieussergues, Christophe, Turbomachine combustion chamber provided with air deflection means for reducing the wake created by an ignition plug.
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