Abstract: A method for assembling a gas turbine engine includes providing a first fan assembly including a plurality of rotor blades that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly axially aft of the first fan assembly, wherein the second fan assembly includes a plurality of rotor blades that are configured to rotate in a second rotational direction, and coupling a gearbox to the second fan assembly that is configured to rotate the second fan assembly at a second rotational speed that is different than the first rotational speed.

Abstract: An apparatus enables a turbine nozzle, including at least two turbine nozzle singlets to be fabricated. Each singlet includes inner and outer bands and a vane extending therebetween. The vane also includes first and second sidewalls coupled together at a leading edge and a trailing edge. The apparatus comprises a fixture, and at least two support members extending from the fixture. Each support member has first and second abutment surfaces, wherein a first of the at least two support members contacts at least one of the leading and trailing edges of a first of the vanes. At least two locating features extend from the fixture, wherein a first of the locating features contacts one of the first and second sidewalls of the first vane. At least two biasing members are coupled to the fixture, wherein a first of the biasing members biases the first vane against the first locating feature.

Abstract: A method for coupling a conduit to a fitting. The method includes providing a fitting having a body and a passageway extending through the fitting body, inserting at least a portion of the fitting body within at least a portion of a collar, and compressing at least a portion of the collar around at least a portion of the fitting body such that the fitting body is not internally supported from within the passageway.

Abstract: A method facilitates assembling a flap system for a gas turbine engine exhaust nozzle including at least one backbone assembly. The method comprises providing a basesheet including a pair of circumferentially-spaced sides coupled together by an upstream side and a downstream side, forming at least one relief cut in the basesheet that extends at least partially across the basesheet from at least one of the circumferentially-spaced sides, and coupling the basesheet to the backbone assembly.

Abstract: A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within each respective casing rail, and coupling a stator vane assembly including two dovetails, and at least two stator vanes coupled together within the casing rails within the liner such that a first dovetail is received within a first casing rail and a first rail liner, and a second dovetail is received within a second casing rail and a second rail liner.

Abstract: An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip, a first side wall that extends in radial span between an airfoil root and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib extending outwardly from at least one of the first side wall and the second side wall, wherein the rib is configured to reduce airflow spillage past the tip.

Abstract: A method for assembling a gas turbine engine including a compressor and a combustor includes providing a heat exchanger assembly that includes at least one heat exchanger, and coupling the heat exchanger assembly to the gas turbine engine such that the heat exchanger is positioned substantially concentrically with respect to a gas turbine engine axis of rotation, and such that the heat exchanger is configured to channel compressor discharge air from the compressor discharge air to the combustor.

Abstract: A system and a method for managing user and data profiles utilizing a web-enabled interactive database to organize, store and retrieve the information to create a consistent security model through centralized administration, are disclosed. The system captures various rules and pre-determined methodologies to provide on-line, up-to-date decisions to the users when users request access to a set of specific data or an application. The system further provides the capability to the user to request access to information that the user currently does not have access to, tracks the status of the request, obtains approval/disapproval decision from the data owner, implements the decision, and notifies requester within a reasonable time.

Abstract: A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine. The method also comprises coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas turbine engine upstream from the core engine turbine, and channeled to the auxiliary engine for generating power.

Abstract: A method for fabricating a turbine casing including a plurality of turbine shroud assemblies is provided. The method includes providing a base casing having a forward mounting flange and an aft mounting flange and at least one channel defined therebetween, machining a rim on the base casing proximate the at least one channel, and coupling a ring member to the base casing with an interference fit such that the rim is at least partially received within a groove formed within the ring member.

Abstract: A web-based system standardizes data from a plurality of different programs to facilitate design review comparisons in a cost-effective and reliable manner. The system includes a client system including a browser, a data storage device for storing information, and a server system coupled to the client system and the database. The server system is configured to store data in the data storage device in a standardized format, generate characteristics unique to the data input using pre-determined calculations, compare the characteristics to pre-determined target values, quantify shifts of the characteristics from respective target values, and generate standardized graphical representations of the data using based on the generated characteristics.

Abstract: A combustor for a gas turbine engine operates with low nitrous oxide emissions during engine operations. The combustor includes a center mixer assembly and a second mixer assembly radially outward from the center mixer assembly. The center mixer assembly includes a pilot fuel injector, a swirler, and an air splitter, and the second mixer assembly includes a plurality of mixers that include a swirler, an atomizer, and a venturi. A combustor fuel delivery system includes a pilot fuel circuit to supply fuel to the center mixer assembly and a main fuel circuit to supply fuel to the second mixer assembly.