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IPC classes for russian patent Turbo-pump supply system for liquid-propellant rocket engine (RU 2246023):
Another patents in same IPC classes:
 Turbo-pump supply system for liquid-propellant rocket engine / 2246023
Proposed system includes lines of different propellant components, gas lines and gas generator. Mounted in front of main turbo-pump unit with multi-stage propellant component pump and drive gas turbine is booster turbo-pump unit with propellant component pump and drive single-stage hydraulic turbine fed from "n" stage of main pump. Working passage of hydraulic turbine is located in connecting line between outlet of "n" stage and inlet of "(n+1)" stage of main pump.
 Liquid-propellant rocket engine operating on fuel containing helium additive / 2273754
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 Liquid-propellant rocket engine / 2279563
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 Low-thrust cryogenic propulsion module / 2282744
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 Method of and device for creating thrust of liquid-propellant rocket engine / 2290525
According to proposed method of creating thrust of liquid-propellant rocket engine with circulation of heat carrier based on taking of propellant components from tanks, increasing their pressure by pumps driven by turbine and introducing them into gas generator and combustion chamber, combustion of components in gas generator and chamber and creating thrust with ejection of combustion products through nozzle, when introducing component of propellant and products of their gasification into combustion chamber, tangential speed component is imparted to them and part of combustion products is replaced by heat carrier and in process of recirculation it is successively expanded at higher pressure of diverting part of nozzle, cooled, condensed in head exchanger-condenser, pressure is raised by pump and it is then delivered to near-critical part of nozzle to repeat the cycle. Liquid-propellant rocket engine with closed circuit of heat carrier contains chamber with mixing head and regenerative cooling duct, turbopump set with oxidizer and propellant pumps whose output main lines are connected with said mixing head of chamber and gas generator, and said closed circuit of heat carrier is formed with successively interconnected circulating pump, unit to introduce heat carrier to near-critical area of nozzle, heat exchanger-condenser, means to supply condensed component to input of circulating pump. According to invention, closed circuit is provided with section of diverting part of nozzle on which ring ribs made of heat-resistant material are secured over circumference.
 Liquid propellant rocket power plant / 2295052
The liquid propellant rocket power plant having liquid-hydrogen and liquid-oxygen tanks with booster pumps and main turbopump units uses also an electrochemical generator with an oxygen inlet and outlet and a hydrogen inlet and outlet, oxygen ejector, hydrogen ejector and two electric motors, one of which is connected to the shaft of the oxygen booster pump, and the other-to the shaft of the hydrogen booster pump, the oxygen inlet of the electrochemical generator is connected through a pipe to the gas cushion of tank with liquid oxygen, and the outlet-to the inlet of oxygen ejector, whose outlet is connected to the gaseous oxygen supply pipe to the reaction chamber: the hydrogen inlet of the electrochemical generator is connected through a pipe to the gas, cushion of the tank with liquid hydrogen, and the outlet is connected to the inlet of the hydrogen ejector, whose outlet is connected to the gaseous hydrogen supply line to the reaction chamber.
 Booster turbo-pump aggregate with the axial pump / 2299343
The invention is pertaining to the field of rocket engineering, in particular, to production of the booster turbo-pump aggregates with the axial pumps used in the liquid rocket engines (LRE). The booster turbo-pump aggregate consists of the body (1), in which there is the pump (3) axial wheel fixed on the shaft (2) and the wheel of the hydraulic turbine (4). The wheel of the hydraulic turbine (4) is connected to the axial wheel of the pump (3) by soldering along its outer diameter. The shaft (2) rests on the fixed bearing (5) and on the movable bearing (6). The axial stops (7) and (8) of the body (1) eliminate the possibility of the axial motion of the fixed bearing (5) with respect to the body (1), and consequently, the motion of the shaft (2). The movable bearing (6) may have the shift in the axial direction concerning the body (1) because of the difference of the axial power and thermal deformations of the body (1) and the shaft (2). From the side of the axial intake in the body there is the axial stop (9). Between the axial stop of the body (1) and the movable bearing (6) the axial spring (10) is installed. The support ring (11) is mounted between the axial spring (10) and the movable bearing (6). The axial spring (10) is made in the form of the resilient conical ring. The invention ensures the increased service life of the fixed bearing (5) and the service life of the whole aggregate.
 Device for separation of the pump and the turbine of the booster turbo-pump aggregate of the liquid propellant rocket engine / 2299344
The invention is pertaining to the field of rocket engineering and may be used in the liquid propellant rocket engines (LPRE). The device for separation of the pump and the turbine of the booster turbo-pump aggregate of the LPRE consists of the pump (2), the turbine (3), the separating cavity (1) located between the pump (2) and the turbine (3) and the external intake tract (4). The separating cavity (1) is limited from the side of the pump (2) by the shaft gasket (5), which diameter is made smaller than the diameter of the shaft (10) in the area of the seat of the bearing of the turbine (11), and from the side of the turbine (3) - by the unloading disk (6) aligned with the turbine impeller (7). On the turbine impeller (7) there is the gasket of the unloading disk (8). The axial impeller of the pump (9) and the turbine impeller (7) are fixed on the shaft (10). From the direction of the turbine (3) the shaft (10) rests on the turbine bearing (11), which is brought out beyond the bounds of the separating cavity (1) and is installed from the direction of the pump (2). The cavity of the turbine bearing (12) which is adjoining the shaft gasket (5) is connected by the delivery channels (13) with the pump outlet (14). The offered device ensures the minimum losses of the power used for separation of the pump and the turbine, and also the effective refrigeration of the bearings by the liquid monophase hydrogen.
 Liquid-propellant rocket engine and the method of its starting / 2299345
The invention is pertaining to the field of rocket engineering, in particular, to production of the liquid propellant rocket engines powered by the cryogenic oxidant and the hydrocarbon propellant. The liquid propellant rocket engine contains the combustion chamber with the tract of the regenerative cooling, the turbo-pumping aggregate with the turbine having the inlet and outlet trunks, and the pumps of the oxidant and the propellant, for which the outlet of the propellant p[ump is connected through the propellant valve to the combustion chamber, and the outlet of the oxidant pump through the oxidant valve is connected to the gas generator. At that the turbo-pump aggregate contains the additional propellant pump, which inlet is connected to the outlet of the propellant pump, and the outlet is connected to the gas generator through the high pressure pipeline, in which there is the high-pressure valve and the consumption regulator. In the trunk of the turbine there is the thrust regulator, to which the on-board trunk and the starting trunk with the return valve and the connector are connected. The method of the liquid propellant rocket engine starting provides for the spinning-up of the turbo-pump aggregate and opening of valves of the oxidant, the propellant, the propellant in the high-pressure trunk, run-up of the turbine conduct a compressed air from a land bulb, and the turbine spinning-up is exercised by the compressed air from the ground pressure vessel and the turbine drive at operation is exercised from the on-board vessel. The invention ensures simplification of the pneumatic-hydraulic circuit, the increased reliability, the increase of the power and the specific characteristics of the liquid propellant rocket engine, the decreased mass of the engines, the improved engine starting and cutoff and provision of the engine cleansing from the leavings of the propellant after the engine cutoff.
 Turbopump set of rocket engine / 2299346
Invention relates to liquid-propellant rocket engines operating on cryogenic oxidizer and on hydrocarbon fuel. Proposed turbopump set of rocket engine contains the following parts of rotor of turbopump set mounted on shaft: oxidizer pump impeller, fuel pump impeller and turbine wheel arranged in housing of turbopump set and additional fuel pump with shaft and impeller of additional fuel pump. Design peculiarity of turbopump set is that magnetic clutch is installed between rotor of turbopump set and rotor of additional fuel pump. Driving disk of magnetic clutch is installed on shaft of turbopump set, and driven disk is mounted on shaft of additional fuel pump. Partition made on nonmagnetic material is found between driving and driven disks of magnetic clutch. Said partition is aligned with housing of additional fuel pump. Partition, driving and driven disks can be made spherical and/or provided with ribbing.
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FIELD: liquid-propellant rocket engines.
SUBSTANCE: proposed system includes lines of different propellant components, gas lines and gas generator. Mounted in front of main turbo-pump unit with multi-stage propellant component pump and drive gas turbine is booster turbo-pump unit with propellant component pump and drive single-stage hydraulic turbine fed from "n" stage of main pump. Working passage of hydraulic turbine is located in connecting line between outlet of "n" stage and inlet of "(n+1)" stage of main pump.
EFFECT: simplified construction; reduced mass of liquid propellant.
3 cl, 1 dwg
The invention relates to liquid propellant rocket engines (LPRE), specifically to the design of power systems rocket engine turbopump with a supply of two-component fuel, consisting of separately stored oxidizer and fuel.
Known turbopump feed system LRE, including highway opposite the fuel components; the gas pipeline and the gas generator (GG); the main turbopump Assembly (TNA) with multi-stage pump of the fuel component and drive the gas turbine; placed before the main booster TNA with pump fuel component and drive a turbine powered by the n-th stage of the main pump; a connecting line between the output of the nth stage and the input of the (n+1)-th stage of the main pump: see Timnath I., Rocket engines on chemical fuel. TRANS. from English., M., Mir, 1990, s.
A known power supply system, which is the prototype of the invention ensures the production of high energy parameters LPRE at low pressure fuel components (oxidizer and fuel) to the engine inlet, which allows you to create rocket apparatus with light, thin-walled fuel tanks. However, the known power supply system is characterized by structural complexity and has a large mass, which is associated with the presence of booster TNA turbine, the output of which is connected to the inlet of the main pump. the turbine is shown to relieve the great pressure drop (in case π t=10), which requires a correspondingly large number of turbine stages (n=5). For this reason, booster TNA has a complex and heavy construction. Additional increase in mass supply system caused by the large size of the main pump due to passing through the additional mass of the component (in particular, 21% of the flow through the engine).
The invention solves the technical problem of simplifying system power LPRE with simultaneous reduction of its weight.
The technical problem is solved by the fact that in the turbopump feed system LRE, including highway opposite the fuel components; the gas pipeline and the gas generator; the main living area with multi-fuel pump component and drive the gas turbine; placed before the main booster TNA with pump fuel component and drive a turbine powered by the n-th stage of the main pump; a connecting line between the output of the nth stage and the input of the (n+1)-th stage of the main pump, according to the invention the working path of the turbine is placed in the connecting line, and the turbine is made of a single-stage.
In some cases, of the invention:
the turbine is in communication with the main pump through the working path of another turbine to drive the booster pump another fuel component is a;
- one General, the turbine causes the booster pumps unlike fuel components.
When carrying out the invention are expected technical result, which coincides with the essence of the problem being solved.
Proposed turbopump feed system LRE presented schematically in the drawing. The power system contains the main living area with two-stage pump (centrifugal) fuel component 1 (for definiteness - liquid methane fuel) and drive the gas turbine 2 and the booster TNA pump 3 and drive the turbine 4. The output of the booster pump is connected to the inlet of the main pump through the fuel line 5. The entrance of the turbine is connected to the output of the first stage of the main pump through line 6, and the output of the turbine is connected to the input of the second stage of the same pump through line 7. Thus, there Interconnector 6-7 between the output of the nth stage and the input of the (n+1)-th stage of the main pump, and in this line posted by the working path of the turbine, which is made of a single-stage.
The main pump feeds the chamber rocket engine and a gas generator (not shown) on highways 8 and 9, respectively. Producer gas is supplied through pipe 10 to the turbine main TNA and after tripping on it is given by gazivoda 11 into the chamber for afterburning with the rest of the top is willow LRE.
The power supply system also contains the units for the filing of another component of liquid rocket fuel (for definiteness - oxygen oxidizer). These units can include shown on the left side of the drawing of the booster pump 12 driven by the turbine 13. It is powered by the exhaust pipe 14 of the body of the turbine 4 with the subsequent reset it through line 15 to the input of the second stage of the pump 1. In the right part of the drawing shows a variant of the drive of the booster pump 12 (with booster pump 3) from turbine 4.
The described power supply system operates as follows. The fuel component (for definiteness - liquid methane fuel) pressure (p1in a few atmospheres comes from tank missile vehicle in the booster pump 3, the pressure component is increased by several times (up to p2), and in line 5 he enters the first stage of the main pump 1. From it under the pressure of hundreds of atmospheres (R3component is fed through line 6 to the turbine 4 to drive the booster pump 3. When triggered, the turbine pressure liquid working fluid is reduced by several tens of atmospheres (up to R4), and it is discharged through line 7 to the input of the second stage of the pump 1. From under her pressure p5exceeding the value of p3fuel component (i.e. liquid methane fuel which is served in the cities and in the camera. In GG rings (not shown in the drawing, the main pump) another component of liquid rocket fuel (in the specific example liquid oxygen oxidizer), and in the combustion of fuel with oxidant produced gas with a temperature of about 1000 K), leading turbine main TNA. Exhaust gas doregama with the rest of the fuel rocket engine in the camera (at a pressure pto>10 MPa), creating cravings during the subsequent expiration of the jet nozzle.
The invention is not limited to the shown in the drawing scheme:
- main pumps unlike fuel components (oxidizer and fuel) can be driven from a common gas turbine or from their own turbines;
the number of impellers in pumps and turbines can be various;
the main pump 1 may have a different number of stages, i.e. in the General case, the working path of the turbine 4 is placed in the line connecting the n - and (n+1)-th level of the specified pump;
camera can be powered by the first (or intermediate) stage of the main pump, as well as cooling jacketed chamber, and expended for these purposes, the weight of the fuel component may not act in line 6;
- exhaust turbine generator gas may not digitise in the chamber and be discharged into the atmosphere through the exhaust pipe, etc.
As is clear from the description, the picture is eenie allows you to apply for driving the booster pump vysokoriskovannuju nitropropane the turbine with its distinctive high efficiency.
The effectiveness of the invention is visible on the example of a specific rocket engines with rated thrust 2 MN, with turbopump feed two fuel oxygen - methane".
When the chamber pressure pto=24 MPa supply system of this rocket engine on the fuel line has the following parameters: R1=0.5 MPa, p2=2,25 MPa, p3=32 MPa, p4=28 MPa, p5=50 MPa. Thus, the turbine 4 is characterized by a value πt=p3/p4=32/28=1,14. This value is realized in one turbine stage with an efficiency=0.65 is that the turbine is high. Used in booster TNA simple, single-stage design of the turbine, along with the exception of the "loop" fuel component through the main pump, designed to simplify and facilitate the turbopump feed system rocket engine.
Thus, the expected technical result of the invention is confirmed.
1. Turbopump feed system liquid-propellant rocket engine, including highway opposite the fuel components; the gas pipeline and the gas generator: the main turbopump Assembly with multi-stage pump of the fuel component and drive the gas turbine; placed before the main booster turbopump Assembly with pump fuel component and the drive turbine is fed from the nth stage cos the main pump; the connecting line between the output of the n-th and the input of the (n+1)-th stage of the main pump, characterized in that the working path of the turbine is placed in the connecting line, and the turbine is made of a single-stage.
2. Turbopump feed system liquid-propellant rocket engine under item 1, characterized in that the turbine is in communication with the main pump through the working path of another turbine to drive the booster pump another fuel component.
3. Turbopump feed system liquid-propellant rocket engine under item 1, characterized in that one, General, turbine leads booster pumps unlike fuel components.
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