Realization method of rocket power and device for its implementation

FIELD: aviation, astronautic science.

SUBSTANCE: invention can be used for launching the rocket stages separating parts after switching off the sustainer liquid propellant engine (LPE). The method is based on injection into the combustion chamber of the gasified liquid propellant components (PC), by stopping the sustainer LPE, including PC gasification systems, based on the pressurization gas supply to spherical tanks with additional PC, and by oxidizing or reducing gas generator, depending on the particular fuel in the tanks, supply of coolant into the tanks with the PC remains. The fuel and oxidizer feed line into the tanks from the shut-off valves is to be blown-down after stopping the sustainer LPE, the gasification products from each tank are supplied into the combustion chamber of sustainer LPE. The device for implementing the power of the liquid propellant engine includes the system of control and guidance and gasification system, located behind the shut-off valves, in the main fuel lines of the oxidizer and fuel there are spherical tanks for blowing-down the lines and extra feed lines, supplying the gasified fuel mixture, connecting the oxidizer and fuel tanks with the main LPE to bypass the turbopump unit.

EFFECT: LPE energy efficiency increase by means of energy resources implementation.

2 cl, 1 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: invention relates to liquid-propellant engines (LPE) and can be used at their bench fire development for improvement of operating reliability of a combustion chamber. LPE containing a frame, components, consumption manifolds, a chamber that includes fuel manifolds on a nozzle and a cylindrical part, a pipeline for fuel transfer between manifolds with a fuel drain valve installed in it, in which, according to the invention, in the pipeline for fuel transfer between manifolds in front of the fuel drain valve there installed is a T-piece, to the threaded nozzle of which there connected is a fuel drain line consisting of a transition piece, a pipeline and a reusable start and cutoff valve fixed on the frame tie member, between the transition piece and the pipeline of the fuel drain line there installed is an eccentric compensator, in a detachable connection between the pipeline and the reusable start and cutoff valve of the fuel drain line there installed is a turning flange, and attachment clamps of the reusable start and cutoff valve to the frame tie member are adjustable. The pipeline of the fuel drain line has a compensation bend.

EFFECT: improving reliability and duration of operation of the chamber due to excluding the occurrence of a coke-shaped film on the inner cover of the chamber on the side of the cooling circuit during several cutoffs of the engine at shutdown.

4 cl, 12 dwg

FIELD: engines and pumps.

SUBSTANCE: engine comprises combustion chamber with mixing head, turbopump unit, gas generator, power supply and control units. Proposed chamber comprises inner shaped shell with cooling path ribs made at outer surface of the latter, outer shaped shell fitted at inner one and secured therewith by crests of said ribs. Said shells and ribs make the cooling channels. Hollow webs are made between cooling path ribs to connect crests of said ribs, outer profile of said web complying with that of cooling path. Said webs connect the sets of ribs. Channel is made between sets of ribs, on their every side, its width being equal to that of cooling path at the location of webs.Note here that adjacent webs are shifted relative to each other by cooling channel width at their location. Width of said webs equals that of cooling channel at the location of webs. Sets of ribs includes three ribs.

EFFECT: higher reliability owing to higher stiffness of outer shell.

2 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: in a combined engine unit of a rocket pod, which includes tanks for cryogenic fuel components 1, liquid-propellant sustainer with a turbo-pump system for supply of cryogenic fuel components to regeneratively-cooled chamber 2, impulse engines of a system of stabilisation, orientation and start 3, which use gaseous fuel components, tanks 4 for gaseous fuel components of impulse engines 3; tanks are located near the tanks under heat insulation 5 that is common for them; with that, tank walls are connected to walls of tanks with thermostats 6 with the specified length and cross-sectional area; cavities of tanks of each of the fuel components are interconnected through mixers 7 and pipelines 11, 12 with cut-off valves 9, 10, with outlets of the corresponding fuel components from pumps of turbo-pump unit 8 and cooling circuits of chamber 2, and in the tanks there installed are pressure sensors 13 and temperature sensors 14 of gaseous fuel components, which perform a function of sensitive elements of the control system of the rocket pod.

EFFECT: improving reliability of engine units of rocket pods using liquid cryogenic fuel components.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises combustion chamber, gas generator, turbopump unit, booster turbopump with gas turbine and heat exchanger. In compliance with this invention, heat exchanges cold inlet is communicated with oxidizer pump outlet. heat exchanges cold outlet is connected via booster turbopump gas feed line with turbopump turbine inlet. Turbine outlet is connected with oxidizer inlet line.

EFFECT: ruled out high-temperature power gas as booster turbopump turbine drive working fluid.

1 dwg

Turbo-pump unit // 2548331

FIELD: engines and pumps.

SUBSTANCE: turbo-pump unit (TPU), incorporating a rotor and a stator, according to the invention, is fitted with the controlled plunger with a working end face placed in the stator and mobile in the axial direction, and on the rotor the companion end face is provided, and in the working position of the plunger both end faces are in power contact for keeping of the rotor in motionless position. Besides, the stator is interconnected with the plunger by a tight bellow valve interconnected with the control pressure nipple, from the side, opposite to the working end face.

EFFECT: prevention of rotation of TPU shaft in the autorotation mode at purges and technological works on the engine for increase of resource of operation of bearings and other TPU elements.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: rocket engine contains a combustion chamber where borane, or silane, or phosphene, or germane, or other hydrides with a positive enthalpy of formation from simple substances or their mix are fed. The named above substances a fed at the temperature ensuring self-sustaining course of reaction of their thermal decomposition due to heat of exothermic reaction. Another invention of the group relates to the liquid or solid fuel rocket engine into the combustion chamber of which in addition to stoichiometric composition of the main fuel borane, or silane, or phosphene, or germane, or other hydrides, or methane are fed. Another one invention of the group relates to the solid fuel rocket engine in which solid hydrides in addition to stoichiometric composition of the main fuel are a part of solid rocket fuel.

EFFECT: group of inventions allows to increase a specific impulse of a rocket engine.

9 cl

FIELD: engines and pumps.

SUBSTANCE: this process proceeds from addition of polymer anti-turbulence additive (ATA) as agent reducing hydrodynamic loss in kerosene fuel line. It comprises feed of oxidiser and fuel to engine combustion chamber to get combustion products and their expansion in jet nozzle to create engine thrust. Note here that polymer ATA is added from extra tanks and mixed with pure kerosene flow fed to engine inlet fuel line at engine starting and operation in the mixer arranged in said line. Said polymer ATA represents the solution of polyisobutylene in concentration of 0.6-0.8% of pure kerosene bulk or the solution of high alpha-olefins in kerosene with concentration of 0.6-0.8% of pure kerosene bulk. Rocket engine plant comprises liquid-propellant rocket engine with turbopump fuel component feed system, oxidiser ( liquid oxygen) tank and fuel (pure kerosene) tank and fuel lines to connect said tanks with engine. Besides, it comprises extra tank filled with the solution of aforesaid polymers and displacement system for feed of said polymer in fuel inlet line for its mixing with pure kerosene during engine operation. Said extra tank has diaphragm to divide its in two chambers so that fluid chamber is communicated with the engine inlet line. Second, gas chamber is communicated with high-pressure cylinder via the valve and pressure control valve.

EFFECT: higher payload to be placed in orbit.

5 cl, 3 dwg

FIELD: motors and pumps.

SUBSTANCE: power pack comprising the tanks with circuits 1, 2, boosting system 3, gas-producer 4 with ignition device 5 for transforming of liquid cryogenic oxidant into gaseous oxidant with preset temperature and storage receiver 6 for gaseous oxidants as a fuel for motor units 7, contains the heat exchanger 8 for transforming of liquid cryogenic fuel into gaseous fuel with heating up to preset temperature comprised by heat transfer path into the circuit downstream the gas-producer 4, by the heat receiving path - into the circuit for supply of cryogenic liquid fuel, storage receiver 9 for gaseous combustible fuel for power supply of motor units 7, comprised in the circuit downstream the heat receiving path of the heat exchanger 8, gas liquid mixer 10, comprised in the circuit between the output of the heat receiving path of the heat exchanger 8 and input of the storage receiver 6 for gaseous oxidants, meanwhile the fluid input of the mixer 10 is connected with the circuit of liquid oxidant supply to the gas-producer through the pipeline 11 with the adjusting throttle washer 12 installed.

EFFECT: improvement of reliability of power packs of reaction control systems using liquid cryogenic fuels.

1 dwg

Propelling device // 2532326

FIELD: engines and pumps.

SUBSTANCE: propelling device comprises a body, a cone-shaped combustion chamber, an exhaust pipe, two spring valves between the exhaust pipe and the combustion chamber, a control unit with hydraulic outlets.

EFFECT: invention makes it possible to increase reliability of operation of a jet engine without speed reduction.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: liquid propellant rocket engine comprising a combustion chamber, a turbopump set, a drainage cavity connected with a drainage pipeline, at the same time the drainage cavity is located between an oxidant pump and a turbine, and the drainage pipeline is equipped with a gas ejector, at the same time the gas ejector is connected by a pipeline with a cavity downstream the turbine. The pipeline comprises a valve and a throttle.

EFFECT: increased efficiency of a system of LPRE cavities draining and removal of fuel components from them.

2 cl, 2 dwg

FIELD: rocket technology; heating gases using heat produced in nuclear fusion.

SUBSTANCE: proposed method is characterized in that gas is introduced in at least one chamber. The latter has wall coated with disintegrating material. This material is exposed to neutron flux to induce disintegration into fragments within chamber. Mentioned wall is cooled down on rear end relative to chamber and mentioned coating. In addition, device implementing this method is proposed. Gas heating device has at least one gas holding chamber. It has wall coated with disintegrating material and facility for exposing disintegrating material to neutron flux so as to induce and emit disintegration fragments within chamber. Device is designed to cool down mentioned wall on rear end of chamber and mentioned coating of disintegrating material. In addition, space engine using mentioned method for gas heating is proposed. This space engine has gas heating device and facility for exhausting hot gas into space to afford thrusting. Alternative way is proposed for gas heating by using nuclear fusion reaction suited to space engines for thrusting.

EFFECT: facilitated procedure of gas heating.

42 cl, 24 dwg

FIELD: rocketry and space engineering; rocket pod engine plants.

SUBSTANCE: proposed engine plant includes propeller tanks (oxidizer tank and fuel tank), cruise engine, actuating members and high-pressure gas bottles. Oxidizer and fuel tanks are filled with low-boiling and high-boiling components, respectively. High-pressure gas bottles are installed in oxidizer tank. Rocket pod engine plant is provided with pipe lines mounted on fuel tank by means of brackets forming heat exchange unit. Pipe line inlets are communicated with outlets of high-pressure gas bottles and their outlets are communicated with actuating members of engine plant.

EFFECT: reduced mass and volume of high-pressure gas bottles and consequently reduced mass of rocket pod.

1 dwg

FIELD: rocket-space equipment, mainly means and methods for water supply to low-orbital spacecraft.

SUBSTANCE: the offered method provides for use of the energy of formation of the raw material, in particular, of water from the fuel components for increasing the efficiency of the means of its injection into orbit. The offered rocket power plant has a chemical reactor, in which the given product is formed, as well as a heat-exchange unit, in which the heat of the chemical reaction is transferred to the fuel components. The latter results in the growth of the power plant specific impulse. The reaction product is cooled, and a condensate (water) is obtained which is accumulated in the storage tank. The offered rocket may use one of the cleared fuel tanks for accumulation of condensate. The offered transportation system includes the offered rocket, orbital station equipped with a system of water processing to fuel components, and means of delivery of the space vehicle to the station together with the non-filled boosting unit. The offered transportation-fueling station includes also an orbital fueling complex. Space vehicles injected into high-altitude orbits, in particular, into a geostationary orbit, as well as space vehicles returning on the Earth, may be refueled there. At injection of the space vehicle into a geostationary orbit the dependence of the efficiency of injection on the latitude of the cosmodrome is essentially reduced (by 2-3 times).

EFFECT: reduced cost of supply of the orbital stations and cost of injection of the space vehicle into a geostationary orbit, as well as into other trajectories, reduced dependence of the cost of injection of the space vehicle into a geostationary orbit on the latitude of the cosmodrome.

19 cl, 3 dwg

FIELD: aircraft industry; rocketry.

SUBSTANCE: invention relates to design of liquid-propellant rocket engines. Proposed liquid-propellant rocket engine without afterburning of generator gas contains regenerative cooling chamber 1, turbopump set 2 with gas generator 3 to drive turbine 4, two flow rate controls and two nozzles 9, 10 installed in pressure main lines 11, 12 of pumps of turbopump set 2. Sensing elements of spools 5, 6 of controls communicate through pipelines with inputs of nozzles 9, 10 and their minimum sections. According to invention servo-actuate restrictor 14 of control, playing the part of thrust control, installed in feed main line 12 of one of propellant components into gas generator 3. Restricting element of servo-actuated restrictor 14 communicates through pipeline 21 with pressure main line 12 of pump of said component after nozzle 10, and pipeline 22 delivering second component into gas generator 3 is connected with pressure main line 11 of pump of said component after servo-actuated restrictor 13 of control playing the part of propellant components flow rate ratio control.

EFFECT: improved energy-mass ratios of engine, provision of constant propellant components flow rate through engine and thrust irrespective of ratio of components passing through engine.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket-propelled vehicles, particularly, to the gas duct of liquid-propellant rocket engines with after-burning. The aforesaid gas duct comprises the outlet manifold of the main turbo-pump unit, a bent pipeline and a swinging assembly. The aforesaid bent pipeline is coupled with the outlet manifold and the said swinging assembly is linked with the engine chamber. Note here that the aforesaid swinging assembly is furnished with a bi-degree universal joint and the joint of the swinging assembly with the engine chamber and bent pipeline represents a flange coupling incorporating a metal T-shape gasket furnished with a load-bearing ring with two flexible springs provided with mountain-like ledges. Note also that the aforesaid one-piece bent pipeline is made from a heat-resistant nickel-alloy, while the bent pipeline flange represents a load-bearing belt with a developed end face surface for the engine frame support to be attached thereto. The aforesaid T-shape taper gasket springs feature the thickness varying over their length, while their length L-to-mean thickness δ ratio makes L/δ ˜8 to 10 and the angle α of the spring taper surface inclination to the flange coupling axis makes 1.5 to 2.5 degrees. The flexible spring OD including the aforesaid mountain-like ledges exceeds the ID of the flange coupling sealing surfaces by 0.1 to 0.2 mm. All parts of the gas duct are made from the EK-61 heat-resistant nickel alloy. The propose invention allows a higher tightness of the fixed joints and pipelines carrying high-temperature high-pressure oxidising medium.

EFFECT: improved performances due to ease of uncoupling gas duct from engine chamber and bent pipeline.

7 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: in method for compensation of differences in physical properties of fuel components based on matching of operation modes of universal liquid-propellant rocket engine supply units, according to invention for generator-free engine with separate turbine pump (TP) during its transfer from hydrogen to liquefied natural gas (LNG) (methane), at first fuel (LNG, methane) flow is increased to required value for provision of reliable cooling of chamber, after cooling prior to fuel supply to turbine of TP its total flow is divided into two parts, one of which is supplied to TP turbine, and the other one is discharged, at that after TP passing, fuel fission process is repeated, at that its one part is sent for combustion in combustion chamber, and the other is discharged or sent for further use. Discharged parts of fuel flow may be used as working fluid, for instance, for steering nozzles, for turbine of engine swinging system, for supercharging of tanks, repeatedly as working fluid of chamber fuel and/or propellant pump. Invention provides for operation of engine both on fuel components "oxygen+hydrogen" and also on fuel "oxygen+liquefied natural gas" (methane).

EFFECT: reduced cost of engine and expanded field of its application.

7 cl, 4 dwg

Rocket engine unit // 2381378

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry and can be used in designing rocker carrier first stages with multi-tank propellant compartments with wrap-around arrangement. Engine unit comprises multi-tank propellant compartment and fluid propellant rocket engines, every engine being communicated, via feed lines, with adjoining tanks. One of the engines communicates, via feed lines and booster pump units, with all tanks.

EFFECT: synchronised utilisation of propellant components from like tanks without introducing disturbing torques to rocket.

1 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry, particularly to liquid propellant rocket engines operated on three fuel components, i.e. cryogenic oxidiser, hydrocarbon fuel and liquid hydrogen. Proposed engine comprises at least one combustion chamber with jet nozzle, regenerative cooling system, gas generator, and turbopump unit comprising turbine, oxidiser pump and fuel pumps. It differs from known designs in that said turbopump unit comprises two fuels pumps and two extra fuel pumps designed to operate on first fuel and second fuel. Note here that second fuel pump and additional second fuel pump are arranged below oxidiser pump. Downstream of fuel pumps, first and second fuel valves are arranged connected, via electric line, with synchronisation device. Proposed engine incorporates also control unit connected with aforesaid synchronisation device. Method of operation of above described engine comprises feeding fuel and oxidiser into gas generator and combustion chamber, igniting them and exhausting combustion products via jet nozzle. In compliance with this invention, first fuel utilised, second fuel is fed into gas generator and combustion chamber. Prior to feeding second fuel, fuel pipelines and nozzle regenerative cooling systems are blown down to remove first fuel residues.

EFFECT: improved operating performances of liquid propellant engine in wide range of flight conditions at various altitudes.

5 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry, particularly to liquid propellant rocket engines operated on three fuel components, i.e. cryogenic oxidiser, hydrocarbon fuel and liquid hydrogen. Proposed rocket comprises first- and second-stage rocket units connected in parallel, oxidiser and fuel tanks coupled by power assemblies and equipped with at least one first-stage engine and one second-stage engine. In compliance with this invention, second-stage unit comprises second fuel tank, every second-stage engine incorporates combustion chamber and fuel feed turbopump unit. Proposed engine comprises at least one combustion chamber with jet nozzle, regenerative cooling system, gas generator, and two turbopump units comprising turbine, oxidiser pump and fuel pumps. In compliance with this invention, outlets of all pumps communicate, via gas duct, with gas generator outlet communicates with every combustion chamber. Method of operation of above described engine comprises feeding fuel and oxidiser into gas generator and combustion chamber, igniting them and exhausting combustion products via jet nozzle. In compliance with this invention, first fuel utilised, second fuel is fed into gas generator and combustion chamber. Prior to feeding second fuel, fuel pipelines and nozzle regenerative cooling systems are blown down to remove first fuel residues.

EFFECT: higher thrust-to-weight ratio, improved operating performances.

12 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: invention can be used during development of liquid-propellant engines (LPI) for carrier rockets (CR). Method consists in the fact that acceleration pulse is created owing to combustion of fuel components in ignition device (ID) and supply of its combustion products to chamber nozzle. Ignition device is tripped after the required pulse is obtained by the mixture in CR tank. At that, combustion products are supplied to the combustion chamber nozzle together with their ballasting, e.g. with fuel which is first passed through the cooling path of the chamber. The proposed method is implemented in LPI containing combustion chamber with ID, nozzle, turbo-pump unit, automation and control units, which, according to the invention, is equipped with an additional line with the valve for ballasting of ID combustion products, which connects the outlet of the cooling path of combustion chamber to its mixing head.

EFFECT: simplifying the design and reducing power consumption.

3 cl, 1 dwg

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