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Louver systems for gas turbine bleed air systems are disclosed. An example louver system may include a bleed system discharge opening arranged to vent bleed air from a bleed flow conduit and a plurality of pivotable louvers disposed proximate the discharge opening, the pivotable louvers being pivota

Louver systems for gas turbine bleed air systems are disclosed. An example louver system may include a bleed system discharge opening arranged to vent bleed air from a bleed flow conduit and a plurality of pivotable louvers disposed proximate the discharge opening, the pivotable louvers being pivotable between a shut position and an open position. In the shut position, individual louvers may at least partially obstruct the discharge opening. In the open position, individual louvers may at least partially control a direction of flow of the bleed air exiting the discharge opening.

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1. A louver system for a gas turbine engine bleed system, the louver system comprising: a bleed system discharge opening arranged to vent bleed air from a bleed flow conduit; anda plurality of pivotable louvers disposed in a core engine casing and proximate the discharge opening, the pivotable louve

1. A louver system for a gas turbine engine bleed system, the louver system comprising: a bleed system discharge opening arranged to vent bleed air from a bleed flow conduit; anda plurality of pivotable louvers disposed in a core engine casing and proximate the discharge opening, the pivotable louvers being pivotable between a shut position and an open position;wherein, in the shut position, individual louvers at least partially obstruct the discharge opening; andwherein, in the open position, individual louvers at least partially control a direction of flow of the bleed air exiting the discharge opening. 2. The louver system of claim 1, further comprising a first connecting rod operatively coupled to a first louver of the plurality of louvers and to a second louver of the plurality of louvers, the first connecting rod providing substantially coordinated pivoting of the first louver and the second louver. 3. The louver system of claim 2, further comprising a second connecting rod operatively coupled to a third louver of the plurality of louvers and to a fourth louver of the plurality of louvers, the second connecting rod providing substantially coordinated pivoting of the third louver and the fourth louver. 4. The louver system of claim 3, wherein the first connecting rod and the second connecting rod are independently operable. 5. The louver system of claim 1, wherein the plurality of pivotable louvers comprises at least two groups of louvers, each group of louvers being associated with a connecting rod providing substantially coordinated pivoting of the respective group of louvers. 6. The louver system of claim 1, further comprising an open position stopper arranged to limit pivoting of at least one louver of the plurality of louvers in an opening direction. 7. The louver system of claim 1, further comprising a shut position stopper arranged to limit pivoting of at least one louver of the plurality of louvers in a shutting direction. 8. The louver system of claim 1, wherein an individual louver comprises a trailing edge; wherein the trailing edge comprises a mixing feature; and wherein the mixing feature comprises at least one of a grooved edge, a scalloped edge, and a chevron-shaped edge. 9. A gas turbine engine, comprising: a compressor;a combustor arranged to combust fuel in compressed air received from the compressor;a turbine configured to receive hot, pressurized gas from the combustor and to drive the compressor;a bleed conduit arranged to receive bleed air from the compressor; anda louver system in a core engine casing, operatively coupled to the bleed conduit, the louver system comprisinga plurality of louvers disposed in a discharge opening, the plurality of louvers being pivotable between a shut position and an open position. 10. The gas turbine engine of claim 9, wherein, in the shut position, the plurality of louvers substantially obstructs the discharge opening. 11. The gas turbine engine of claim 9, wherein, in the open position, the plurality of louvers are arranged to direct a flow of bleed air exiting the discharge opening. 12. The gas turbine engine of claim 9, further comprising a transient bleed valve fluidicly interposing the compressor and the bleed conduit; anda muffling device fluidicly interposing the bleed conduit and the discharge opening. 13. The gas turbine engine of claim 9, wherein the discharge opening is arranged to vent the bleed air into a bypass flow stream. 14. The gas turbine engine of claim 13, wherein, in the open position, the plurality of louvers is arranged to prevent bleed air impingement on a bypass duct wall. 15. A method of operating a bleed system associated with a gas turbine engine, the method comprising: receiving a flow of bleed air from a compressor of a gas turbine engine at a discharge opening in a core engine casing;pivoting a plurality of louvers disposed in the discharge opening from a shut position to an open position;discharging the flow of bleed air through the discharge opening; anddirecting the flow of bleed air through the discharge opening using the plurality of louvers. 16. The method of claim 15, further comprising substantially stopping the flow of bleed air from the compressor; andpivoting the plurality of louvers from the open position to the shut position, the louvers substantially obstructing the discharge opening in the shut position. 17. The method of claim 15, wherein pivoting a plurality of louvers disposed in the discharge opening from the shut position to the open position comprises pivoting a first group of pivotable louvers from the shut position to the open position, andmaintaining a second group of pivotable louvers in the shut position. 18. The method of claim 17, further comprising pivoting the second group of louvers from the shut position to the open position in response to an increase in a flow rate of bleed air from the compressor. 19. The method of claim 15, wherein receiving the flow of bleed air from the compressor of the gas turbine engine at the discharge opening comprises flowing the flow of bleed air through a muffling device fluidicly coupled upstream of the discharge opening.