General Electric Company

Mitchell Allan Merrill

Jason Edward Albert

Matthew Peter Scoffone

Xiuzhang James Zhang

Michael Robert Berry

Gary Michael Itzel

David Martin Johnson

Jeffrey Clarence Jones

Jaime Javier Maldonado

Bradley James Miller

Adebukola Oluwaseun Benson

Jason Adam Neville

Richard William Johnson

Nicholas Alvin Hogberg

Stephen Walter Newman

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.

System and method for converting turbine cooling nozzle

Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.

Wheel space purge flow mixing chamber

Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.

A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded continuously by pressure and suction side walls of the airfoil. The tip cap further includes an aperture that extends through the tip cap and provides for fluid communication between an internal cavity defined within the airfoil and the tip cavity. An exhaust port provides for fluid communication out the tip cavity through one of the pressure side wall, the suction side wall or the trailing edge. A portion of at least one of the suction side wall and the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity with respect to a radial direction.

Rotor blade having a flared tip

A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

Turbine airfoil turbulator arrangement

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.

Mixing chambers for turbine wheel space cooling

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.

Growing community of inventors

Taylor, SC, United States of America

Mitchell Allan Merrill