A masking system for a turbine including a first quantity of blades attached to a rotor and arranged adjacent one another to define a blade row with each blade including a blade root, includes a second quantity of center plates. Each center plate is disposed between two adjacent blades and includes a resilient member in contact with each of the two adjacent blades, and a first attachment member operable to attach the center plate to the rotor. The system includes a third quantity of side covers, each side cover positioned adjacent the blade root of one of the blades and connected to one of the center plates, each side cover including a resilient member positioned to surround a portion of the adjacent blade root, and a second attachment member operable to attach the side cover to the rotor.

This invention discloses an improved wind turbine suitable for mounting without a wind turbine tower. The wind turbine is based on a rotor with appropriately selected blades. A nozzle and diffuser in the wind flow increase the amount of wind energy available to the rotor. The rotor is interruptibly connected with one or more of a plurality of generators which allows generation at a wide range of wind speeds. The rotor is also interruptibly connected with a co-axial flywheel which allows for storage or use of rotational energy as needed by the availability of wind energy. One or more wind turbines can be grouped together in a common housing. Electricity can also be generated by means of stored energy. The lack of a wind turbine tower and the general compact design allows the wind turbine to be used in close proximity to or on buildings.

A hybrid multi-spool gas turbine engine, has: a LP spool and a HP spool rotatable about a central axis, the LP spool having an LP compressor and an LP turbine engaged to the LP compressor via an LP shaft, the LP shaft engaged to a rotatable load at a first end thereof, the HP spool having an HP turbine and an HP compressor engaged to the HP turbine via a HP shaft; an accessory gearbox (AGB) engaged to both of the LP shaft and the HP shaft and located proximate a second end thereof, the AGB having at least one accessory output drivingly engageable to at least one accessory and at least one input; and at least one electric motor drivingly engaged to the at least one input of the AGB, the at least one electric motor drivingly engaged to the rotatable load via the AGB and the LP shaft.

An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

In one exemplary embodiment, a gas turbine engine includes an engine centerline longitudinal axis. A fan section includes a fan with a plurality of fan blades. The fan has a low corrected fan tip speed less than 1400 ft/sec. A bypass ratio is greater than 13 and less than 20. A fan pressure ratio less than 1.38 at cruise conditions of 0.8 Mach and about 35,000 feet. A speed reduction device comprises a gear system with a gear ratio of at least 2.6 and less than or equal to 4.1. A low pressure turbine is in communication with a first shaft. A high pressure turbine is in communication a second shaft. The first shaft is in communication with the fan through the speed reduction device. The low pressure turbine includes at least three stages and no more than four stages. The high pressure turbine includes two stages.

A method (110) of controlling an imbalance response in a power plant comprising first and second gas turbine engines and a steam turbine driven by steam generated by exhaust from the first and second gas turbine engines can comprise operating the first gas turbine engine at a first power output (116A), operating the second gas turbine engine at a second power output (116B), monitoring load demand from a power grid operating at a steady state condition (114), detecting a load imbalance on the power grid (120) that causes a deviation from the steady state condition, and adjusting the first power output and the second power output incongruently (128) during the imbalance response to change the first power output and the second power output to match the deviation from the steady state condition depending on contemporaneous efficiency states of the first and second gas turbine engines.

A cascade array vane is provided that includes a vane, a first longitudinal portion, a second longitudinal portion, and at least one coupling feature. The vane includes an airfoil portion extending between a first end and a second end. The first longitudinal portion is disposed at the first end of the vane extending outwardly from the vane. The second longitudinal portion is disposed at the second end of the vane extending outwardly from the vane. The at least one coupling feature is incorporated with at least one of the first longitudinal portion or the second longitudinal portion.

A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.

Isolation seals for gas turbine engines are described. The isolation seals include a first interface member configured to be fixedly attached to a first case structure, the first interface member being a full-hoop structure, a housing configured to be mounted to a second case structure, a connector pin arranged within the housing and moveable relative to the housing, and a second interface member located on an end of the connector pin, the second interface member being a full-hoop structure. The first interface member and the second interface member are engageable to form a seal therebetween.

An engine including a motor and a nacelle and a duct between the nacelle and the motor. The nacelle includes a fixed structure, a mobile assembly that is mobile between an advanced position and a retracted position to define a window between the duct and the outside, and a plurality of blades that are mobile in rotation between a stowed position and a deployed position, each one extending on either side of its axis of rotation with a first arm and a second arm. In the stowed position, the first arm is outside the duct and the second arm is inside the nacelle, and where, in the deployed position, the first arm is across the duct and the second arm projects out of the nacelle. With such blades, the flow of air is optimally directed towards the front without it being necessary to provide cascades.