| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060390450 | With gear, pressure exchanger, or screw-type compressor | 7 |
| 20080196384 | RECIPICATING COMPRESSOR WITH INLET BOOSTER FOR CNG STATION AND REFUELING MOTOR VEHICLES - The present invention provides a natural gas compression system, comprising a gas inlet component for the entrance of natural gas into the system, a booster component for increasing the pressure of the natural gas, a drying component for drying the natural gas, a compressor component including a reciprocating compressor for further increasing the pressure of the natural gas, a valve control panel and storage component, and a dispensing component. | 08-21-2008 |
| 20130081374 | COUNTER-ROTATABLE FAN GAS TURBINE ENGINE WITH AXIAL FLOW POSITIVE DISPLACEMENT WORM GAS GENERATOR - A counter-rotatable fan turbine engine includes a counter-rotatable fan section, a worm gas generator, and a low pressure turbine to power the counter-rotatable fan section. The low pressure turbine maybe counter-rotatable or have a single direction of rotation in which case it powers the counter-rotatable fan section through a gearbox. The gas generator has inner and outer bodies having offset inner and outer axes extending through first, second, and third sections of a core assembly. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes and extending radially outwardly and inwardly respectively. The helical blades have first, second, and third twist slopes in the first, second, and third sections respectively. A combustor section extends through at least a portion of the second section. | 04-04-2013 |
| 20130276424 | Low Noise Compressor Rotor for Geared Turbofan Engine - A gas turbine engine has a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion. The low pressure turbine portion drives the low pressure compressor portion and the fan. A gear reduction effects a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor portion. At least one of the low pressure turbine portion and low pressure compressor portion has a number of blades in each of a plurality of rows. The blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the at least one of the low pressure turbine portion and/or the low pressure compressor sections: (number of blades×rotational speed)/60≧5500. The rotational speed is an approach speed in revolutions per minute. | 10-24-2013 |
| 20140150401 | GEARED COMPRESSOR FOR GAS TURBINE ENGINE - A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft. The booster assembly comprises a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow and a gearing having first and second input rotors and an output rotor. The first input rotor is arranged to be driven by the first rotor assembly and the second input rotor is arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies. | 06-05-2014 |
| 20140157751 | Screw Shaft Turbine Compressor and System - Disclosed herein are screw shaft turbine compressors having (i) a compressor section, (ii) a turbine section, (iii) a combustion section coupling to the compressor section and the turbine section, and (iv) a grooved shaft. The grooved shaft can include one or more grooves for providing fuel from the compressor section to the combustion section and for allowing exhaust to leave the combustion section and exit the turbine section. A method for generating different speed to torque ratios on the shaft and a system for generating torque on the shaft are further disclosed. | 06-12-2014 |
| 20160160755 | FLUID DISTRIBUTING APPARATUS - The invention is directed to a fluid distributing apparatus comprising a fixed part and a rotating part. The fixed part is provided with at least one inlet channel and at least one outlet channel and wherein each inlet and outlet channel has a facing opening facing the rotating part. The rotating part is rotatably positioned relative to the fixed part such that the rotating part can have multiple rotational positions relative to the fixed part, wherein the rotating part is provided with at least a connecting channel having an inlet and outlet opening in the rotating part. The inlet and outlet opening of at least one connecting channel in the rotating part aligns with the facing openings of at least one inlet and outlet channel in the fixed part in at least one rotational position and not align in another position. | 06-09-2016 |
| 20190145237 | PRESSURE EXCHANGER MANIFOLDING | 05-16-2019 |
