Abstract: In a featured embodiment, a heat exchanger includes a plate including a plate portion having outer walls. A plurality of internal passages extend between end portions. A ratio between an outer wall cross-sectional thickness at one of the end portions and a cross-sectional wall thickness of the outer wall within the plate portion is greater than 2.5 and no more than 10. An inlet manifold is attached to the inlet end. An outlet manifold is attached to the outlet end.

Abstract: A method of cooling a portion of a gas turbine engine includes positioning a tie rod relative to an inner frame case. The tie rod includes a bushing opening and the inner frame case includes a fastener opening. A fastener is secured through the fastener opening in the inner frame case to a threaded bushing located in the bushing opening. The threaded bushing includes a distal end that forms a clearance gap with the inner frame case. Heat is transferred from the fastener through the threaded bushing to prevent the fastener from creeping.

Abstract: A heat exchanger assembly includes a plate including a plate portion having a leading edge, a trailing edge, an inlet side and an outlet side. The leading edge of the plate portion includes a terminal tip and a varying radius that decreases in a direction toward the terminal tip. An inlet manifold is on the inlet side. An outlet manifold is on the outlet side. A cast plate for a plate fin heat exchanger is also disclosed.

Abstract: In a featured embodiment, a heat exchanger includes a plate including a plate portion having outer walls. A plurality of internal passages extend between end portions. A ratio between an outer wall cross-sectional thickness at one of the end portions and a cross-sectional wall thickness of the outer wall within the plate portion is greater than 2.5 and no more than 10. An inlet manifold is attached to the inlet end. An outlet manifold is attached to the outlet end.

Abstract: A gas turbine engine component has an engine case structure surrounding an engine center axis. A plurality of holes are formed in the engine case structure, wherein the holes are circumferentially spaced apart from each other about the engine center axis. The plurality of holes includes at least one balance hole and at least one service hole that is configured to allow another engine component to pass through the at least one service hole. At least one cover is configured to cover at least one balance hole such that air is prevented from passing through the at least one balance hole.

Abstract: A method of cooling a portion of a gas turbine engine includes positioning a tie rod relative to an inner frame case. The tie rod includes a bushing opening and the inner frame case includes a fastener opening. A fastener is secured through the fastener opening in the inner frame case to a threaded bushing located in the bushing opening. The threaded bushing includes a distal end that forms a clearance gap with the inner frame case. Heat is transferred from the fastener through the threaded bushing to prevent the fastener from creeping.

Abstract: A featured embodiment of a cast plate heat exchanger assembly includes a cast plate including a plate portion defining a plurality of internal passages. A plurality of fin portions extend from the plate portion. First augmentation structures are disposed on surfaces of the fin portions for conditioning cooling airflow to enhance transfer of thermal energy. A method is also disclosed.

Abstract: A heat exchanger includes a primary plate including a first surface, a second surface, a leading edge, a trailing edge and a plurality of internal passages extending between an inlet and an outlet. A secondary plate is attached to at least one of the first surface and second surface of the primary plate. The secondary plate includes heat transfer structures. A method is also disclosed.

Abstract: A heat exchanger assembly includes a plate including a plate portion having a leading edge, a trailing edge, an inlet side and an outlet side. The leading edge of the plate portion includes a terminal tip and a varying radius that decreases in a direction toward the terminal tip. An inlet manifold is on the inlet side. An outlet manifold is on the outlet side. A cast plate for a plate fin heat exchanger is also disclosed.

Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor section. The combustor includes a combustor region defined by at least one bulkhead panel and at least one heat shielding panel inside the combustor region. The at least one heat shielding panel is connected to the bulkhead panel via at least one cooled fastener.

Abstract: A plate fin heat exchanger includes a first cast plate assembly includes at least two plate portions separated by at least one cooling channel. Each of the two plate portions include a plurality of internal passages extending between a corresponding plurality of inlets and outlets. A common inlet perimeter surrounds the plurality of inlets from each of the two plate portions and an outlet perimeter surrounds the plurality of outlets from each of the two plate portions. An inlet manifold is attached at an inlet joint to the inlet perimeter. An outlet manifold is attached at an outlet joint to the outlet perimeter. A method is also disclosed.

Abstract: A heat exchanger includes a plate portion including a top surface, bottom surface, a leading edge, a trailing edge and a plurality of internal passages extending between an inlet and an outlet. A fin portion extends outward from one of the top surface and the bottom surface. The fin portion and the leading edge of the plate portion define a leading edge contour. A cast plate for a heat exchanger and a method are also disclosed.

Abstract: A heat exchanger includes a plate portion including a top surface, bottom surface, a leading edge, a trailing edge and a plurality of internal passages extending between an inlet and an outlet. A plurality of fin portion rows are included. A first row of the plurality of fin portions includes at least two discrete fin portions and a second row of the plurality of in portions includes fewer fin portions than the first row. The first row is closer to the inlet than the second row. A cast plate for a heat exchanger and a method are also disclosed.

Abstract: A fastener assembly includes a first component that includes a bushing opening. A second component includes a fastener opening. A threaded bushing is at least partially located within the bushing opening. A fastener extends through the fastener opening and engages the bushing.

Abstract: A tie rod assembly for a mid-turbine frame includes at least one tie rod for connecting an outer frame case to an inner frame case. At least one tie rod includes an inlet passage that branches into a first branch and a second branch. A plug is located in the first branch to block flow through a portion of the first branch.

Abstract: A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuser case shroud. A multiple of struts extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud.

Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.

Abstract: A fastener assembly includes a first component including a first fastener opening that has a cylindrical portion and a conical portion. A second component includes a second fastener opening. A fastener for extending through the first fastener opening and the second fastener opening and a clinch nut for attaching to the fastener is included.

Abstract: A spoke for a mid-turbine frame on a gas turbine engine includes a cylindrical portion. A flange is attached to the cylindrical portion. At least one gusset extends between the cylindrical portion and the flange. At least one gusset extends to a perimeter of the flange.

Abstract: A mid-turbine frame is provided. The mid-turbine frame may comprise an inner case having an annular surface with an interface section disposed on the annular surface. The interface section may include an interface feature. A balancing section may be disposed on the annular surface defining an opening and disposed circumferentially adjacent the interface section.