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Interrelated reaction motors

Subclass of:

060 - Power plants

060200100 - REACTION MOTOR (E.G., MOTIVE FLUID GENERATOR AND REACTION NOZZLE, ETC.)

Patent class list (only not empty are listed)

Deeper subclasses:

Class / Patent application numberDescriptionNumber of patent applications / Date published
060226100 Air and diverse fluid discharge from separate discharge outlets (e.g., fan jet, etc.) 231
060225000 Sequentially operated 2
20090120057DEPLOYABLE AIRCRAFT/SPACECRAFT PROPULSION SYSTEM AND METHODS - A propulsion system for a combined aircraft/spacecraft including: a jet engine having a longitudinal axis defined in a direction from a front end at an air intake to a rear end at a jet exhaust: a front end at an air intake to a rear end at the jet exhaust; a rocket engine having a longitudinal axis defined normal to a rear end at a rocket exhaust; a common engine housing having an elongated shape and wherein the jet engine and the rocket engine are configured substantially coaxially and with respective rear ends facing the same direction when the rocket engine is operated.05-14-2009
20100326045MULTIPLE-USE ROCKET ENGINES AND ASSOCIATED SYSTEMS AND METHODS - Multiple-use rocket engines and associated systems and methods are disclosed. A method in accordance with a particular embodiment includes launching a two-stage vehicle have a first stage and a second stage carried by the first stage. The first stage can be powered with a first rocket engine having first rocket engine components, including a first combustion chamber, arranged in a first component configuration. The method can further include separating the second stage from the first stage, and powering the second stage with a second rocket engine having second engine components arranged in a second component configuration. The second rocket engine components can include a second combustion chamber that is interchangeable with the first combustion chamber. In further particular embodiments, recovered engine components from the first stage may be used to power the second stage of the same or a different two-stage vehicle.12-30-2010
Entries
DocumentTitleDate
20110277447Engine, 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
20120023899TURBOFAN 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
20090000271Gas 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
20090313968Hypersonic 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
20100223904GAS 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
20090000270Gas 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
20110107738Combined 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
20110179767COOLING DEVICE FOR AIRCRAFT PROPELLER - The invention relates to an aircraft propeller (07-28-2011
20110146228POWER 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
20130186060Piecemeal Turbojet - A two-spool turbojet built up of major bladed components first developped for unrelated turbofan engine types. The high pressure (“HP”) spool comes from a turbofan which powered a large airliner carrying 300 or more passengers across a continent or an ocean. The low pressure (“LP”) compressor is the fan from a military aircraft's engine or a smaller airliner turbofan, or both. The object is that all the LP compressor output goes into the HP compressor, making a turbojet from existing turbofan components. This saves development costs, and creates an engine for propelling a large aircraft at supersonic speeds more efficiently than by an afterburning turbofan. In the preferred embodiment, the number of stages in the HP spool is halved, saving weight for the addition of a remote fan (known elsewhere) which doubles the air mass flow. That increases propulsive efficiency during subsonic cruise.07-25-2013
20130199156ADAPTIVE FAN SYSTEM FOR A VARIABLE CYCLE TURBOFAN ENGINE - One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique variable cycle gas turbine engine. Another embodiment is a unique adaptive fan system for a variable cycle turbofan engine having at least one turbine. Another embodiment is a unique method for operating a variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and related systems.08-08-2013

Patent applications in class Interrelated reaction motors

Patent applications in all subclasses Interrelated reaction motors