Patent ID: 11905847
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 5:
6. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section having airfoils disposed about a central axis of the gas turbine engine, each of the airfoils includes:
an airfoil wall having a span between first and second radial ends and defining leading and trailing edges, pressure and suction sides each joining the leading and trailing edges, and an internal cavity,
a rib joining the pressure and suction sides and dividing the internal cavity into at least first and second sub-cavities extending over the span, the rib being arced from the first radial end to the second radial end so as to define a curvature,
the first sub-cavity defining a venturi tube, the venturi tube having a convergent-divergent geometry such that a cross-sectional area of the venturi tube decreases from the first radial end to a location along the span at which the cross-sectional area is at a minimum and the cross-sectional area increases from the location of the minimum to the second radial end, and
due to the curvature of the rib s the venturi tube tapering in a chordal direction along the span from the first radial end to the location of the minimum and expanding in the chordal direction along the span from the location of the minimum to the second radial end.