Diffuser with strut-induced vortex mixing
AssigneeSiemens Aktiengesellschaft
InventorJohn A. Orosa
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield. A trailing edge flap is located at the downstream end of each shield, the trailing edge flap including first and second span-wise portions. The first span-wise portion is oriented to direct flow at an angle relative to the chordal axis of the main body and the second span-wise portion is oriented to direct flow in a direction that is at a different angle than the angle of first span-wise portion.
Claims18
A gas turbine engine having a turbine exhaust section comprising:
- a pair of concentrically spaced rings;
- a plurality of strut structures extending radially between the rings, interconnecting and supporting the rings;
- the strut structures supported downstream of a last row of rotating blades and comprising a main body portion having an elongated chordal dimension in the direction of an axial gas flow through the engine and defining a chordal axis extending in a downstream direction from an upstream end of the main body portion toward a downstream end of the strut structure;
- and
- a trailing edge flap located at the downstream end of each main body portion, the trailing edge flap including first and second span-wise portions, the first span-wise portion oriented to direct flow at an angle relative to the chordal axis of the main body portion and the second span-wise portion oriented to direct flow in a direction that is at a different angle than the angle of the first span-wise portion.
In a gas turbine engine, an exhaust diffuser comprising:
- an inner shroud and an outer shroud forming an annular gas path;
- a plurality of struts connecting the inner shroud to the outer shroud and located within the gas path downstream of a last row of rotating blades;
- airfoil shaped shields surrounding the struts, each of the shields comprise a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield;
- and
- a trailing edge flap located at the downstream end of each shield, the trailing edge flap including first and second span-wise portions, the first span-wise portion oriented to direct flow at an angle relative to the chordal axis of the main body and the second span-wise portion oriented to direct flow in a direction that is at a different angle than the angle of first span-wise portion.
Dependencies are inferred from the claim text.