| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416171000 | Impeller driven by fluid motor | 7 |
| 20090148292 | AXIAL COMPRESSOR FOR TIP TURBINE ENGINE - A tip turbine engine ( | 06-11-2009 |
| 20110229325 | ROTOR FOR A CHARGING DEVICE - A rotor for a charging device may include a shaft, a turbine wheel and a compressor wheel. The turbine wheel may be connected to the shaft. The rotor may also include at least one of a metal or ceramic adapter connected to the turbine wheel or the shaft via an infiltration process. | 09-22-2011 |
| 20160032772 | Self Cleaning Debris Filter for Fan Drive Gear System - A pump system for a gas turbine engine has at least one pump. At least one valve has an outlet and at least one inlet is fluidly connected to the at least one pump. A geared architecture is positioned within a bearing compartment. The geared architecture is configured to receive lubricating fluid from the outlet of the at least one valve, a self-cleaning filter is positioned downstream of the at least one valve and upstream of the geared architecture. A gas turbine engine and a method are also disclosed. | 02-04-2016 |
| 20160061048 | ROTOR BLADE WITH L-SHAPED FEATHER SEAL - A turbine engine assembly arranged relative to an axis includes a rotor blade and a feather seal with an L-shaped geometry. The rotor blade includes an airfoil and a base. The airfoil extends axially between an upstream leading edge and a downstream trailing edge, and radially out from the base. The base includes a neck and a pocket. The neck extends axially to a downstream surface. The pocket extends laterally into the neck. The feather seal extends laterally into the pocket, and includes a down stream leg that extends substantially along the downstream surface. | 03-03-2016 |
| 20160090988 | AIRCRAFT ENGINE WITH A COMPRESSOR DEVICE - What is described is an aircraft engine with a compressor device and with a fan device. In the area of a compressor shaft, the compressor device is connected via an epicyclic gear to a fan shaft. A planetary web is operatively connected via bearing devices to the planetary gears. A ring gear is coupled with the fan shaft and a sun gear of the epicyclic gear is coupled with the compressor shaft, while the planetary carrier is held at the housing side in a torque-proof manner. The ring gear is connected via a flexible connection device to the fan shaft and/or the planetary carrier is connected via a flexible connection device to the housing. In the area of the connection device, movements between the ring gear and the planetary gears and/or between the planetary carrier and the housing can be at least approximately compensated in the radial and the axial direction. | 03-31-2016 |
| 20160123344 | COMPRESSOR HAVING HOLLOW SHAFT - A shaft of a compressor may include a first shaft section defining a first cavity axially extending therein and a second shaft section defining a second cavity axially extending therein. A plurality of inlet holes may be defined on an outer surface of the first shaft section, and a plurality of outlet holes may be defined on an outer surface of the second shaft section. The plurality of inlet holes may be in fluid communication with the first cavity and the plurality of outlet holes may be in fluid communication with the second cavity. The first cavity and the second cavity may form a passageway fluidly coupling the plurality of inlet holes and the plurality of outlet holes. | 05-05-2016 |
| 20160153279 | LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE | 06-02-2016 |
