Multi-slot inter-turbine duct assembly for use in a turbine...

Details Multi-slot inter-turbine duct assembly for use in a turbine... Multi-slot inter-turbine duct assembly for use in a turbine...

2005-10-25

2009-06-23

Casaregola, Louis J (Department: 3741)

Power plants

Combustion products used as motive fluid

Multiple fluid-operated motors

C415S117000, C415S914000

Reexamination Certificate

active

07549282

ABSTRACT:
A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the at least two injection openings is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation. Methods for optimizing the flow through the turbine engine are also disclosed.

REFERENCES:
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patent: 5357744 (1994-10-01), Czachor et al.
patent: 6851264 (2005-02-01), Kirtley et al.
patent: 7137245 (2006-11-01), Graziosi et al.
patent: 2006/0069533 (2006-03-01), Florea et al.
R. Florea et al., “Flow-Control-Enabled Aggressive Turbine Transition Ducts and Engine System Analysis,” Journal of Propulsion and Power, vol. 23, No. 4, Jul.-Aug. 2007.
R. Florea et al., “Optimization of Bleed-Flow-Control for an Aggressive Serpentine Duct,” 43rd AIAA Aerospace Sciences Meeting and Exhibit, Jan. 10-13, 2005, Reno, Nevada.

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