Abstract: A stationary component of a turbine section of a turbine engine system includes a hollow vane assembly with an interior rib separating a first interior compartment from a second interior compartment. The first and second interior compartments are configured to receive the cooling fluid. The cooling fluid is allowed to communicate between the first and second interior compartments. The stationary component also includes a diaphragm attached to the hollow vane assembly. The diaphragm is configured to receive the cooling fluid from the hollow vane assembly. The diaphragm includes a chamber and a tube extending through the chamber. The tube is configured to isolate the chamber from the cooling fluid while delivering the cooling fluid from the hollow vane assembly to the wheelspace area.

Abstract: A stationary component of a turbine section of a turbine engine system includes a hollow vane assembly with an interior rib separating a first interior compartment from a second interior compartment. The first and second interior compartments are configured to receive the cooling fluid. The cooling fluid is allowed to communicate between the first and second interior compartments. The stationary component also includes a diaphragm attached to the hollow vane assembly. The diaphragm is configured to receive the cooling fluid from the hollow vane assembly. The diaphragm includes a chamber and a tube extending through the chamber. The tube is configured to isolate the chamber from the cooling fluid while delivering the cooling fluid from the hollow vane assembly to the wheelspace area.

Abstract: The present application provides a purge flow delivery system that may be used with a gas turbine engine. The purge flow delivery system may include a mixing chamber with a first sidewall, a second sidewall, and a cover plate, a first inlet tube positioned about the first sidewall, the first inlet tube configured to deliver a first fluid to the mixing chamber, a second inlet tube positioned about the second sidewall, the second inlet tube configured to deliver a second fluid to the mixing chamber, and a baffle plate attached to the cover plate and positioned to direct the first fluid at a first angle and the second fluid at a second angle.

Abstract: The present application thus provides a method for reducing stress on at least one of a turbine disk and a turbine blade. The method may include the steps of (a) determining a starting line for a dovetail backcut relative to a datum line, (b) determining a cut angle for the dovetail backcut, and (c) removing material from at least one of the blade dovetail or the disk dovetail slot according to the starting line and the cut angle to form the dovetail backcut. The datum line may be positioned about 2.866 inches (about 72.796 millimeters) from a forward face of the blade dovetail and wherein step (a) is practiced such that for the pressure side of the dovetail, the starting line of the dovetail backcut is at least about 2.566 inches (about 65.176 millimeters) in a forward direction from the datum line.

Abstract: The present application provides a purge flow delivery system that may be used with a gas turbine engine. The purge flow delivery system may include a mixing chamber with a first sidewall, a second sidewall, and a cover plate, a first inlet tube positioned about the first sidewall, the first inlet tube configured to deliver a first fluid to the mixing chamber, a second inlet tube positioned about the second sidewall, the second inlet tube configured to deliver a second fluid to the mixing chamber, and a baffle plate attached to the cover plate and positioned to direct the first fluid at a first angle and the second fluid at a second angle.

Abstract: According to one embodiment, there is disclosed an inducer assembly for use with a gas turbine engine. The inducer assembly may include a cavity. The inducer assembly may also include an inducer in fluid communication with the cavity. Moreover, the inducer assembly may include at least one guide vane disposed within the cavity.