| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060246000 | Turborocket | 7 |
| 20090113873 | Continously air breathing assisted jet engine linear aerospkie rocket - A linear aerospike rocket engine receives continuous air breathing assistance from an oxygen turbopump powered axial flow air compressor and side mounted integrated adjustable ramp shape ramjets. The preferred embodiment receives all its thrust from air breathing during the start to about 1.95 kilometers per second (4300 mph) up to 20 miles altitude. It uses about 50% of the thrust from air breathing from 1.95-3 klm/second (4300-6700 mph). It uses about 10% of the thrust from air breathing engines at 30 miles altitude. It uses rocket turbines for powering the air compressor or the liquid oxygen pump, but not simultaneously. | 05-07-2009 |
| 20090235639 | ROCKET NOZZLE AND CONTROL METHOD FOR COMBUSTION GAS FLOW IN ROCKET ENGINE - A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet. | 09-24-2009 |
| 20120204535 | AUGMENTED EXPANDER CYCLE - A rocket engine includes a thrust chamber having a cooling channel, which is adapted to provide sustained cracking conditions for a fluid (e.g., kerosene) within the cooling channel under steady-state engine operating conditions. An augmenter having a fluid input communicates with an output of the cooling channel, and an output of the augmenter is in fluid communication with a turbine. A pump is mechanically coupled to the turbine, and provides fluid flow to the inlet of the cooling channel. | 08-16-2012 |
| 20130227931 | TURBOPUMP, IN PARTICULAR FOR FEEDING ROCKET ENGINES - A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings. | 09-05-2013 |
| 20130269313 | PROPULSION SYSTEM FOR FLYING MACHINE, PARTICULARLY FOR A MISSILE - A propulsion system including: a booster; a turbojet engine; the booster including a chamber which is fixed to a rear casing of the turbojet engine by being arranged along the longitudinal axis thereof, which chamber includes at a rear a jet pipe and includes at least one charge and a mechanism initiating the charge; and gas bleed tubes connected to the booster and which are configured either for igniting the combustion chamber of the turbojet engine on for starting the turbine of the turbojet. | 10-17-2013 |
| 20140325958 | PROPULSION ASSEMBLY AND METHOD - The invention relates to the field of aerospace propulsion, and more particularly to a propulsion assembly having at least one channel defined by an inner wall and an outer wall, the channel presenting an inlet opening and an outlet opening, the assembly including a plurality of rocket engines oriented axially in the channel and forming ejectors for accelerating a flow of air in the channel to supersonic speed. Downstream from the outlet opening from the channel, the inner wall forms a single expansion ramp nozzle. The invention also provides an aerospace craft and a method of propulsion using such a propulsion assembly. | 11-06-2014 |
| 20140373507 | ROCKET ENGINE WITH OPTIMIZED FUEL SUPPLY - A rocket engine comprises a prechamber and a combustion chamber, two respective feed pipes of the engine, and two turbopumps. The engine is a staged combustion engine. A jet pump is arranged in at least a first feed pipe. After being pressurized, a portion of the fluid flowing in the first feed pipe is directed to the jet pump in order to enable the jet pump to entrain the fluid flowing in said feed pipe to the admission orifice of said first pump, thereby raising the pressure at the feed orifice of the pump. | 12-25-2014 |
