Abstract: The example embodiments are directed to a system and method for predicting a flow about an object through the use of a predictive model instead of a machine simulation. Traditional CFD simulations can take hours, even days. The example embodiments provide a predictive model that can predict a CFD flow in seconds which greatly improves design time. In one example, the method may include receiving input data comprising shape parameters of a geometric object and flow parameters associated with the geometric object, predicting, via execution of a predictive model, a computational fluid dynamic (CFD) flow about the geometric object based on the shape parameters and the flow parameters included in the input data, and outputting one or more attributes of the predicted CFD flow about the geometric object via a display device.

Abstract: The example embodiments are directed to a system and method for predicting a flow about an object through the use of a predictive model instead of a machine simulation. Traditional CFD simulations can take hours, even days. The example embodiments provide a predictive model that can predict a CFD flow in seconds which greatly improves design time. In one example, the method may include receiving input data comprising shape parameters of a geometric object and flow parameters associated with the geometric object, predicting, via execution of a predictive model, a computational fluid dynamic (CFD) flow about the geometric object based on the shape parameters and the flow parameters included in the input data, and outputting one or more attributes of the predicted CFD flow about the geometric object via a display device.

Abstract: A hot gas path component including a substrate having an outer surface exposed to a stream of hot gases and an inner surface exposed to a cooling flow. One or more pair of cooling supply inlets is formed at the inner surface of the substrate for receiving the cooling air flow. One or more pair of cooling supply outlets is formed at the outer surface of the substrate for discharging the cooling air flow. A cooling flow channel extends through the substrate and between each of cooling supply inlets and the cooling supply outlets for permitting passage of the cooling air flow.

Abstract: A hot gas path component including a substrate having an outer surface exposed to a stream of hot gases and an inner surface exposed to a cooling flow. One or more pair of cooling supply inlets is formed at the inner surface of the substrate for receiving the cooling air flow. One or more pair of cooling supply outlets is formed at the outer surface of the substrate for discharging the cooling air flow. A cooling flow channel extends through the substrate and between each of cooling supply inlets and the cooling supply outlets for permitting passage of the cooling air flow.

Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.

Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.

Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.

Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.

Abstract: An engine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Extending from a surface of the platforms is a trailing edge ridge structure which adjoins the pressure sides, suction sides, and trailing edges of the airfoils with their respective platforms.

Abstract: An engine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Extending from a surface of the platforms is a trailing edge ridge structure which adjoins the pressure sides, suction sides, and trailing edges of the airfoils with their respective platforms.