General Electric Company

Wenfeng Lu

Ching-Pang Lee

Joseph M Guentert

Changjie Sun

Gregory Owen Miller

Nicholas Charles Palmer

Christopher Raymond Geisen

Yu Mukherjee

Bangalore Aswatha Nagaraj

Bhaskar Nanda Mondal

Steven Robert Brassfield

Ananda Barua

Atanu Saha

Douglas Marti Fortuna

Luis E Prada

Marcia Boyle Johnson

Baolan Shi

James Robert Bailey

Jakub Roniewicz

Robert Andrzej Gniazdowski

Andrew David Farmer

Russel Michael Castle

Mitchell E Iles

The present disclosure is directed to a shroud assembly for a gas turbine. The shroud assembly includes a casing and a shroud. The shroud includes a radially outer wall engaged with the casing. A radially inner wall integrally couples to the radially outer wall. The radially inner wall and the radially outer wall collectively define a pair of axially opposed cavities. The radially inner wall moves radially outward toward the casing when one or more gas turbine blades contact the radially inner wall.

Compliant shroud for gas turbine engine clearance control

The turbomachine includes a rotatable member defining an axis of rotation and an inner annular casing extending circumferentially over at least a portion of the rotatable member. The inner annular casing includes a radially outer surface. The turbomachine further includes an outer annular casing extending over at least a portion of the inner annular casing. The inner annular casing and the outer annular casing define a plurality of cavities therebetween. The clearance control system includes a manifold system including a plurality of conduits extending circumferentially about the inner annular casing and disposed within the cavities. The clearance control system also includes an impingement system extending circumferentially about the inner annular casing and disposed within the cavities. The conduits are configured to channel a flow of cooling fluid to the impingement system which is configured to channel the cooling fluid to the radially outer surface of the inner annular casing.

Method and apparatus for active clearance control for high pressure compressors using fan/booster exhaust air

A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.

Methods and apparatus for assembling turbine engines

A method facilitates the assembly of a gas turbine engine. The method comprises providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands, wherein the vane includes a first sidewall and a second sidewall connected together at a leading edge and a trailing edge and coupling the turbine nozzle to a combustor that includes a plurality of circumferentially-spaced cooling openings that are oriented with respect to the turbine nozzle such that cooling air discharged therefrom during engine operation is biased towards the vane leading edge.

A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.

Gas turbine nozzle segment and process therefor

A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and suction sides. The flowpath surface joins the first endface at the forward edge in a forward bullnose and joins the second endface at the aft edge in an aft bullnose, with the bullnoses varying in radius from the opposite edges.

Bullnose step turbine nozzle

A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.

Corner cooled turbine nozzle

A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges and root and tip. The tip includes squealer ribs extending from a tip floor forming an open tip cavity. The rib along the pressure sidewall has a squared external corner, and a flute extends along the base of the rib at the tip floor.

Fluted tip turbine blade

A turbine blade includes an airfoil having pressure and suction sidewalls spaced apart between opposite leading and trailing edges and interconnected by a plurality of partitions to define first and second independent cooling circuits therein. The cooling circuits have corresponding inlets in a dovetail of the blade and extend through a platform of the blade and through the airfoil to its tip. A common discharge chamber is disposed below the airfoil tip and includes a plurality of outlet holes for discharging cooling air from the circuits.

Common tip chamber blade

A turbine rotor blade includes an airfoil having pressure and suction sidewalls extending longitudinally in span from root to tip. The sidewalls are spaced apart between leading and trailing edges and joined together by longitudinal partitions defining flow channels therein. Rows of first and second slant turbulators extend from one of the sidewalls in one of the channels and are offset longitudinally. The first and second turbulators overlap chordally to eliminate an axial gap therebetween while maintaining a radial gap for tripping cooling air channeled along the span of the channel.

Offset Coriolis turbulator blade

A turbine nozzle includes hollow vanes extending between outer and inner bands. The vanes include a pattern of outlet holes distributed over the pressure and suction sides thereof for discharging cooling air collectively at a reference flowrate. The pattern of holes includes multiple rows of showerhead holes bridging the leading edge, and two rows of gill holes spaced aft therefrom along the suction side. A row of auxiliary holes is spaced aft from the showerhead holes through the pressure side, and the gill holes are sized to counterbalance the added discharge air through the auxiliary holes for maintaining the reference flowrate.

Counterbalanced flow turbine nozzle

A latch assembly for a door including a door retainer projection is provided. The latch assembly includes a handle pivotally mounted to the door for rotation about a first end, and a latch actuator contacting the handle and mounted to the door for rotation about a first end. The handle rotates in one direction when actuated and the latch actuator rotates in a second direction opposite the first direction. A keeper is engaged to the door retainer projection in a closed position, and the latch actuator is configured to disengage the keeper from the door retainer projection when the handle is actuated.

Methods and apparatus for securing a dishwasher door

A latch assembly includes a handle, a handle retainer, and a keeper. The keeper includes a biasing mechanism and a head comprising a catch, a lock release projection, and a switch actuator. The keeper biasing member configured to facilitate engaging the catch with the door. The handle biasing member configured to facilitate maintaining the handle in a first position. The handle includes a contact surface slidingly coupled to the lock release projection to facilitate coupling the door to the tub assembly.

A turbine nozzle assembly for a gas turbine engine, including: a plurality of segments joined together to form an outer band; a plurality of segments joined together to form an inner band; at least one airfoil positioned between the outer and inner bands; a leaf seal attached to each inner band segment by at least one pin member; and, a leaf seal attached to each outer band segment by at least one pin member. Each of the inner band segments includes a protrusion extending from a surface thereof so as to provide balanced support to the corresponding leaf seal in conjunction with the pin members. Each of the inner band segments further includes a first portion having a flange extending therefrom, a second portion opposite the first portion, a first end, and a second end opposite the first end, wherein the surface extends between the first and second ends and the first and second portions.

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Mason, OH, United States of America

Wenfeng Lu