Abstract: A preswirler of a gas turbine engine includes an outer ring. The outer ring includes an outer flange with a plurality of first holes, and an outer cylindrical portion extending from the outer flange. The preswirler also includes an inner ring. The inner ring includes an inner flange spaced apart from the outer flange. The inner ring also includes an inner cylindrical portion located within the outer cylindrical portion and a back portion extending from the inner flange to the inner cylindrical portion. The inner ring further includes a plurality of second holes.

Abstract: A gas turbine engine preswirler (470) includes an outer ring (471) and an inner ring (472). The inner ring (472) includes a plurality of angled holes (490). Each angled hole (490) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular a radial from an axis of the preswirler (470). The component of the angle is angled relative to an axial direction of the preswirler (470).

Abstract: A turbine housing (430) includes a support housing (440) with an annular shape. The support housing (432) includes an outer surface (433) and an inner surface (434). The inner surface (434) is located radially inward from the outer surface (433). A plurality of cooling holes (431) extols through the support housing(440) from the outer surface (433) to the inner surface (434). The cooling holes (431) include a stadium shape. The stadium shape includes a rectangle with a top and bottom of a first length and ends capped with semicircles with a radius of a second length. The cooling holes (431) are disposed at an angle (98) from thirty to sixty degrees. The angle (98) is between a line (96) projected to the outer surface (433) from an axis of the turbine housing (430) and a line (97) extending through a center of each cooling hole (431) parallel to the first length.

Abstract: A gas turbine engine preswirler (470) includes an outer ring (471) and an inner ring (472). The inner ring (472) includes a plurality of angled holes (490). Each angled hole (490) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular a radial from an axis of the preswirler (470). The component of the angle is angled relative to an axial direction of the preswirler (470).

Abstract: A preswirler of a gas turbine engine includes an outer ring. The outer ring includes an outer flange with a plurality of first holes, and an outer cylindrical portion extending from the outer flange. The preswirler also includes an inner ring. The inner ring includes an inner flange spaced apart from the outer flange. The inner ring also includes an inner cylindrical portion located within the outer cylindrical portion and a back portion extending from the inner flange to the inner cylindrical portion. The inner ring further includes a plurality of second holes.