A method for operating a gas turbine engine includes channeling fluid from a cooling fluid source to a combustor that includes at least one deflector and flare cone. The deflector and flare cone are coupled together and are configured to define a cooling fluid channel therebetween. The flare cone has a plurality of cooling injectors extending therethrough. The plurality of injectors are spaced circumferentially about a centerline axis of the flare cone and are coupled in flow communication with the fluid source. The plurality of injectors has a plurality of first injectors and a plurality of second injectors. The method also includes directing a portion of the fluid through the plurality of first injectors. The method further includes directing a portion of the fluid through the plurality of second injectors, wherein the first plurality of injectors facilitates cooling a portion of the deflector more than the second plurality of injectors.

Methods and apparatus for cooling gas turbine engine combustors

A gas turbine engine (10) includes a bearing (58) and a bearing support (66) having a first wall (76) extending between first and second ends and operatively supported by the bearing (58) at a first end An engine case (48) is secured to the second end radially outward of the first end A second wall (78) integral with and extending transversely from the first wall (76) provides a flexible support (74) The second wall (78) has a flange (82), and a gear train component (46) is secured to the flange (82) The gas turbine engine (10) includes a support structure which supports the main rotatable structure via bearings and gear train components The support provides both the necessary structural support for the rotor structure as well as desired flexibility for a fan drive gear system

Geared turbofan engine with integral gear and bearing supports

A bearing assembly having dynamic drainage for lubrication oil which incls rings which are provided with races with a conical-shaped cross-section which the balls contact at pairs of side contact points. The central circumference of each ring is free; cooling oil drillings are drilled in it. This arrangement gives better oil circulation characteristics, thus improving the bearing efficiency and less heat is dissipated. Thus higher speed can be expected. The drillings responsible for drainage are inclined in the direction of rotation in order to facilitate drainage outside the roller bearing.

Bearing assembly with dynamic drainage supplied with lubricant

A method of fabricating a fuel nozzle is provided. The method includes providing a unitary portion of material including a first end face, a second end face, and a body extending therebetween. A passageway is fabricated to extend from the first end face to the second end face along a centerline of the portion of material. The method further includes fabricating a plurality of concentrically-aligned channels within the first end face, and fabricating a plurality of inlets that extend through at least one of the second end face and an outer surface of the body to at least one of the passageway and one of the plurality of channels.

Fuel nozzle for a gas turbine engine and method of fabricating the same

A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold in communication with said mid-span pre-diffuser inlet and said combustor section.

Method and apparatus for handling pre-diffuser airflow for use in adjusting a temperature profile

A bearing assembly includes a split inner race disposed on a distal end of an output shaft disposed coaxially about an input shaft. A plurality of bearing elements are disposed around the inner race, with a stationary outer race surrounding the elements. The inner race includes a plural number A1 of radially extending splitline channels in flow communication with a circumferential splitline manifold between the inner race and the output shaft distal end. A first half of the inner race includes a plural number B1 of radially extending first channels disposed in flow communication with a circumferential first manifold defined between the inner race first half and the output shaft distal end for channeling oil to the cage. The output shaft distal end includes a number A2 of axial splitline feed groves joined in flow communication with a respective number of radial splitline feed holes therein for channeling oil to the splitline maniflod, and a number B2 of axial first-manifold feed grooves joined in flow communication with a respective number of radial first-manifold feed holes therein for channeling oil to the first manifold. The numbers A2 and B2 are less than A1 and B1, respectively.

Lubricated bearing assembly

A combustor for a gas turbine engine that facilitates reducing combustor chamber dump pressure losses to improve combustor and engine performance is described. The combustor includes a diffuser that diffuses airflow directed into the combustor. The diffuser includes an outer wall, an inner wall, and a plurality of splitter vanes between the outer wall and the inner wall. The splitter vanes are spaced radially apart, and each is spaced radially from a respective diffuser wall such that an outer passage, an inner passage, and a central passage are defined by the splitter vanes.

Methods and apparatus for supplying air to turbine engine combustors

A gas turbine engine rotor assembly is provided for rotatably mounting a rotor mounted power takeoff gear of an inlet gear box and a forward end of a high pressure rotor within an engine frame. The gear and rotor are mounted to forward and aft portions respectively of a gear shaft which is at least partially supported by a radial roller bearing having an outer race supportably mounted to the fan frame of the engine frame and an inner race directly mounted to the gear shaft between the gear and rotor.

Rotor and bearing assembly

An apparatus and method of cooling a rotatable member enclosed within a casing are provided. The gas compressor includes a rotor, a plurality of stages of compression extending along said rotor from an inlet stage configured to receive a flow of relatively low pressure gas to an outlet stage configured to discharge a flow of relatively high pressure gas, a casing at least partially surrounding said plurality of stages, and a conduit extending radially inwardly from said casing to an area proximate said rotor.

Method and system for bowed rotor start mitigation using rotor cooling

The present invention discloses a combustion system deflection mitigation structure. The turbine engine includes a first outer casing and a second outer casing coupled together at a flange. The firstouter casing and the second outer casing are together disposed around a core engine. An inner casing assembly is extended from the flange between the first outer casing and the second outer casing. Aflow circuit is defined between the first outer casing, the inner casing assembly, and the second outer casing.

Anthony Paul Greenwood

Papers

Lubricated bearing assembly

Methods and apparatus for supplying air to turbine engine combustors

Rotor and bearing assembly

Method and system for bowed rotor start mitigation using rotor cooling

Combustion System Deflection Mitigation Structure