| Entries |
| Document | Title | Date |
|---|
| 20110277447 | Engine, Particularly CROR Engine, for an Aircraft - An engine for an aircraft flying in a cruise flight direction comprises at least one rotor having a plurality of rotor blades. The at least one rotor is driven about a rotor axis at a rotational frequency. The rotor axis is oriented in the cruise flight direction of the aircraft, and at least one geometric parameter of the rotor blades that influences the propulsion characteristics of the rotor is variable. The engine further comprises a controller which periodically varies the geometric parameter of the rotor blades at at least one frequency that is at least as high as the rotational frequency of the rotor. | 11-17-2011 |
| 20120023899 | TURBOFAN ENGINE - Provided is a turbofan engine capable of effectively using the air flowing through the inner diameter side area of a fan that is disposed at the front end side. The turbofan engine in which the fan is disposed at the front end side is equipped with a first low-pressure compressor at the upstream side and on the inner diameter side of the fan. Accordingly, the first low-pressure compressor can be operated by effectively using the air flowing through the rotation center portion of the fan, so that the air can be efficiently used and the output of the engine can be increased. | 02-02-2012 |
| 20090000271 | Gas Turbines with Multiple Gas Flow Paths - Gas turbines with multiple gas flow paths are provided. In this regard, a representative gas turbine includes: a spool; a compressor; a turbine mechanically coupled to the spool; the compressor having a first set of blades and a second set of blades, the second set of blades being located downstream of the first set of blades, the first set of blades and the second set of blades being driven by the spool; and means for enabling the first set of blades to rotate at a lower rotational speed than the second set of blades. | 01-01-2009 |
| 20090313968 | Hypersonic Inlet Systems and Methods - Hypersonic inlet systems and methods are disclosed. In one embodiment, an inlet for an airbreathing propulsion system includes an inboard surface at least partially shaped to conform to a plurality of streamline-traces of a design flowfield approaching an aperture, an outboard surface spaced apart from the inboard surface, an upper surface extending between the inboard and outboard surfaces, and a lower surface extending between the inboard and outboard surfaces, wherein leading edges of the inboard, outboard, upper, and lower surfaces cooperatively define the aperture. | 12-24-2009 |
| 20100223904 | GAS TURBINE ENGINE - A gas turbine engine comprising an intermediate compressor and two shafts connecting respective high and low pressure turbines and compressors respectively is characterised by the intermediate pressure compressor connecting to either the high pressure shaft or the low pressure shaft via a gearbox. | 09-09-2010 |
| 20090000270 | Gas Turbines with Multiple Gas Flow Paths - A representative gas turbine includes: a high pressure spool; a high pressure compressor; a high pressure turbine mechanically coupled to the high pressure spool; a lower pressure spool; a lower pressure turbine mechanically coupled to the lower pressure spool; a fan having a first set of fan blades and a second set of fan blades, the second set of fan blades being located downstream of the first set of fan blades and being operative to rotate at a rotational speed corresponding to a rotational speed of the lower pressure spool; and a gear assembly mechanically coupled to the lower pressure spool and engaging the first set of fan blades such that rotation of the lower pressure spool rotates the first set of fan blades at a lower rotational speed than the rotational speed of the second set of fan blades. | 01-01-2009 |
| 20110107738 | Combined Cycle Integrated Combustor and Nozzle System - An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke. | 05-12-2011 |
| 20110179767 | COOLING DEVICE FOR AIRCRAFT PROPELLER - The invention relates to an aircraft propeller ( | 07-28-2011 |
| 20110146228 | POWER EXTRACTION SYSTEM - A power extraction system is disclosed having a forward fan stage configured to pressurize an airflow, an aft fan stage having a tip-fan configured to pressurize a first portion of a pressurized air flow from the forward fan stage wherein the aft fan stage is driven by a second portion of the pressurized airflow, and a power drive system adapted to supply power from the aft fan stage. | 06-23-2011 |
