General Electric Company

Anthony Paul Greenwood

Christophe Jude Day

Thomas Alan Wall

Kenneth Edward Seitzer

Michael Alan Hile

Carol Anne Venn

Jonathan Russell Ratzlaff

Tod Robert Steen

Amid Ansari

Marwan Al-Roub

Clifford Stephen Creevy

Paul C Daiber

Jeremy Kevin Payne

Ted E Bailey

Anthony G O'Meara

John Wilbur Acree

Hubert Smith Roberts, Jr

Anthony James Bailey

Satyambabu Kalyani

Michael Alan Zupancic

Kevin William Caldwell

An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

Turbine engine inducer assembly

An apparatus and method for a turbine engine having an engine core. A casing can contain a compressor section, a combustor section and a turbine section in axial flow arrangement. An air conduit can extend at least partially between the compressor section and the turbine section. A compliant interface can include a nut and a biasing device mount the air conduit to the casing.

Turbine engine conduit interface

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

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

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 A.sub.1 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 B.sub.1 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 A.sub.2 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 B.sub.2 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 A.sub.2 and B.sub.2 are less than A.sub.1 and B.sub.1, respectively.

Lubricated bearing assembly

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Kings Mills, OH, United States of America

Anthony Paul Greenwood