31 results about "Turbopump" patented technology

This invention discloses a design method and inducer for a liquid rocket engine turbopump. Based on the overall design requirements of the liquid rocket engine, the operating conditions of the inducer are determined. According to the design requirements and empirical formulas, the basic parameters of the inducer are initially determined. Based on the range of core parameters, different combinations of core parameters are used to establish multiple initial three-dimensional models of the inducer. Simulations are performed on each of the established initial three-dimensional models to obtain the cavitation performance of the inducer. Based on the flow analysis results, the inducer with the optimal blade profile among all parameter combinations is obtained. The selected inducer with the optimal blade profile is then optimized and adjusted until the liquid rocket engine turbopump inducer with the best cavitation performance is obtained. This invention can design a liquid rocket engine turbopump inducer with good cavitation performance.

This invention discloses a method and apparatus for determining the residual axial force of an engine turbopump rotor system, relating to the field of engine turbopump technology, to solve the problem in the prior art that it is impossible to evaluate and predict the residual axial force of an engine turbopump during the design stage. The method includes: obtaining the structural parameters and target operating condition parameters of the target engine turbopump; performing one-dimensional simulation calculations on the target structure in the target engine turbopump based on the target structure and operating condition parameters to obtain the axial force of the target structure; determining the axial force of the balance cavity in the dual-clearance balancing system based on the initial axial clearance and the pressure within the balance cavity; and determining the residual axial force of the target engine turbopump rotor system based on the axial force of the target structure and the axial force of the balance cavity in the dual-clearance balancing system. This achieves efficient and accurate evaluation and prediction of the residual axial force of the engine turbopump rotor system during the design stage.

A vacuum pump is proposed that has favorable back pressure performance even in a case where an intake gas is a hydrogen gas or the like. A vacuum pump 100 includes an exhaust portion 114 constituted of a turbine pump portion 115 that includes a plurality of stages of rotor blades 102 and a plurality of stages of stator blades 123, and a drag pump portion 116 that is located on a further toward exhaust downstream side than the turbine pump portion 115, exhausts from an outlet port 133 through a gas flow passage FP1 an intake gas sucked from an inlet port 101 by the exhaust portion 114, and includes an introduction flow passage FP3 through which an intermediate introduction gas having viscosity higher than that of the intake gas is introduced, and the introduction flow passage FP3 is connected to the gas flow passage FP1 on the further toward exhaust downstream side than the rotor blade 102, from among the plurality of stages of the rotor blades 102, that is closest to the inlet port 101 in the exhaust portion 114.

The utility model relates to oil detection technical field, concretely relates to a kind of oilfield development rapid sampling detection device, including support plate, hydraulic cylinder output end is fixedly connected with connecting plate, motor output end is fixedly connected with gear one through shaft coupling, gear one outside is equipped with chain, drilling rod side wall is fixedly connected with gear two, connecting pipe one intercommunication turbine pump output end with filter inside, connecting pipe two connects sampling tank one with sampling tank two inside.The utility model is when entering sampling tank one after petroleum after filter, start ultrasonic homogenizer, make oil, water, solid particle etc. in sample fully mix by high-frequency vibration, form uniform stable suspension or emulsion, ensure the representativeness and accuracy of subsequent detection, sensor carries out detection to petroleum sample, and the preliminary detection parameter of sample in sampling tank two inside can be quickly viewed parameter display screen.

Turbopump assemblies and pump turbine assemblies utilized in rocket propulsion systems or other systems are disclosed. The turbopump assembly may include a rotor with at least one integral pump impeller and at least one integral turbine impeller, a housing containing the rotor, and first and second bearings supporting the rotor. The first and second bearings are supported by the housing. The rotor is disposed between the first and second bearings such that the at least one integral pump impeller and the at least one integral turbine impeller are supported between the first and second bearings. At least one integral pump impeller and at least one integral turbine impeller are provided between all bearings supporting the pump and turbine in the housing.

This application relates to the field of liquid rocket engine technology and discloses a rocket engine turbopump fixing device, comprising: a connector, at least two connecting plates, a first telescopic rod, and a second telescopic rod. The connector has a notch adapted to avoid the turbopump and is adapted to connect to the rocket engine. The two connecting plates are adapted to be fixed to the turbopump, and the portions of the two connecting plates corresponding to the periphery of the notch are detachably connected. One end of the first telescopic rod is hinged to the connector, and the other end is adapted to connect to the turbopump. One end of the second telescopic rod is hinged to the connector, and the other end is adapted to connect to the turbopump. The first and second telescopic rods are located on opposite sides of the connecting plates along a first direction. This rocket engine turbopump fixing device discloses a solution to or improvement of the problems of complex assembly and disassembly and difficult positioning of turbopumps.

The embodiment of the present application provides an inducer and a turbopump, which are used for further improving the cavitation erosion resistance of the inducer. The inducer is suitable for a liquid rocket engine, and the inducer comprises a rotating shaft and blades fixed to the rotating shaft; a first development surface corresponding to the blades comprises a first region, and a part of the first development surface located in the first region is in a curve shape; the first development surface is a planar pattern obtained by unfolding a first section surface of the blades which is cut by a cylindrical surface of the rotating shaft on a shaft radius. The inducer and the turbopump provided by the embodiment of the present application can further improve the cavitation erosion resistance of the inducer.

This invention relates to the field of aerospace propulsion technology and discloses a gas generator circulating liquid rocket engine system with an electric bypass. This invention constructs an electric bypass supply channel by reusing the discharge pipeline, introducing the originally directly discharged high-pressure propellant into the fuel electric pump and oxidizer electric pump for secondary pressurization, and then injecting it into the main thrust chamber via a separately set bypass injector. This solves the problems of traditional open gas generator circulating liquid engines, such as the main turbopump easily entering the critical speed range and causing mechanical resonance under deep throttling conditions, and the deterioration of atomization mixing effect due to insufficient pressure drop of the main injector. It achieves stable operation of the main turbopump within the rated operating speed range and stable high-pressure atomization and combustion of propellant under extremely low thrust conditions, expands the lower limit of the engine's deep throttling capability, and improves propellant energy utilization efficiency and system operational reliability. Simultaneously, the electric bypass supply system enables rapid response and precise adjustment under low thrust conditions.

The application relates to a manufacturing method of a turbine pump accessory and the turbine pump accessory, the accessory comprising a turbine end bearing seat, a pump end bearing seat, a positioning shaft, a pump inlet shell and a pump outlet shell; the manufacturing method of the turbine pump accessory comprises the following steps: machining the turbine end bearing seat so that the turbine end bearing seat has first preset parameters; the turbine end bearing seat has a first shaft hole; machining the pump end bearing seat so that the pump end bearing seat has second preset parameters; the pump end bearing seat has a second shaft hole; one of the size precision, the shape and position tolerance and the surface roughness is included in the first preset parameters and the second preset parameters; the turbine end bearing seat is assembled to the pump outlet shell, and the coaxiality and the straightness of the first shaft hole of the turbine end bearing seat are aligned; the positioning shaft is assembled to the turbine end bearing seat; the pump inlet shell is sleeved on the positioning shaft and assembled to the pump outlet shell; and the pump end bearing seat is sleeved on the positioning shaft through the second shaft hole and assembled to the pump inlet shell.

An electric motor as well as a manufacturing method for the electric motor and a manufacturing tool are provided, the electric motor being for a deep well vertical turbine pump and having a stator assembly that has a stator bore to hold a rotor and slots that are radially open to the inside, respectively separated from each other by a stator tooth, and in which electrical conductors made of round wire of coils of a coil assembly lie, with the distributed windings on one axial end of the coil assembly forming a winding head in which the coils are encapsulated. The winding head only extends between an inner diameter and an outer diameter which is smaller than the diameter of the stator bore in which the coil assembly is inserted axially into the slots of the stator assembly.

To address the problem of insufficient design margin caused by the inability to obtain design boundaries in existing turbopump seal-rotor design methods, this invention discloses a liquid rocket engine turbopump seal-rotor design method comprising the following steps: Step S1, establishing a deterministic dynamic model of the seal-rotor; Step S2, setting the optimization parameters, optimization constraints, and objective function of the engine turbopump seal-rotor; Step S3, sampling the dimension and range of the uncertainty parameters to generate a sample library; Step S4, constructing a polynomial surrogate model of the seal-rotor dynamic characteristics; Step S5, determining the boundaries of the seal-rotor dynamic characteristics; Step S6, screening and optimizing the deterministic dynamic model of the seal-rotor to determine the final seal-rotor model result. This invention optimizes the seal-rotor design by combining uncertainty with rotor design, improving the reliability and safety of the rotor, and is simple, efficient, and easy to operate.

The application discloses a kind of electric pre-press pump double active inhibition control system and method.This application is by high power density permanent magnet synchronous motor driven electric pre-press pump unit between storage tank and main pump is set, and cooperate state monitoring unit makes controller unit can generate Pogo oscillation inhibition instruction based on arrow body vibration signal, while generating cavitation inhibition instruction based on inlet pressure signal, superimposes after the two to form motor control instruction to adjust motor speed and / or torque, solve the structure of traditional turbo pump pressurization mode Complex, heavy, the high requirement of storage tank pressure leads to tank wall thickening, and traditional Pogo inhibition means slow response, additional weight is big, cannot adapt to the problem of dynamic change of working condition, realizes the integration active control of propellant supply system and vibration inhibition, cavitation protection, improves the stability and reliability of launch vehicle propellant supply system, reduce the structure quality and enhance the adaptability to dynamic change of engine working condition.

This invention discloses a bearing cooling structure and a turbopump for a turbopump, relating to the field of aerospace engine technology, to address the problem of insufficient or excessive propellant affecting bearing performance and service life. The bearing cooling structure for the turbopump includes a shaft, a centrifugal impeller, a bearing, a pump housing, and a flow-limiting nozzle. The bearing and centrifugal impeller are sequentially mounted on the shaft along its axial direction. The pump housing surrounds the centrifugal impeller and bearing, and has a flow channel for propellant flow. The two ends of the flow channel face the centrifugal impeller and the bearing, respectively. The flow-limiting nozzle is detachably connected to the pump housing and communicates with the flow channel. Propellant flows to the bearing through the flow-limiting nozzle and the flow channel. The flow-limiting nozzle contains a flow-limiting orifice, the diameter of which is smaller than the diameter of the flow channel. The turbopump includes the bearing cooling structure described above.

The present application relates to the technical field of fluid sealing, in particular to a turbine pump with a mechanical seal composite open-cell foam medium sealing ring, comprising a dynamic ring and a static ring of mechanical seal, the dynamic ring is uniformly distributed with flush holes from the ring bottom surface to the outer diameter side in the circumferential direction, the outer diameter side of the dynamic ring and the static ring is provided with an annular channel, and the flush holes and the annular channel of the dynamic ring and the static ring are embedded with foam medium. The sealing ring improves the structure of the turbine pump mechanical seal ring by embedding open-cell foam medium, strengthens the heat transfer of the sealing end face, and reduces the end face temperature.

This invention relates to a channel-type rotating ring structure for a turbine pump mechanical seal, comprising a hollow rotating ring with a sealing end face on its top. Multiple heat transfer channels are formed on the inner periphery of the rotating ring for communication with the sealing cavity. The inlets of the heat transfer channels are located at the bottom of the rotating ring, and the outlets are located on the outer periphery of the rotating ring. When the rotating ring of the turbine pump mechanical seal rotates at high speed, the low-temperature fluid in the sealing cavity flows from the bottom of the rotating ring into the heat transfer channels due to centrifugal force, undergoes convective heat exchange with the rotating ring, and then flows back into the sealing cavity from the outer periphery of the rotating ring. This increases the heat exchange between the rotating ring and the medium in the sealing cavity, improves the efficiency of convective heat exchange between the medium in the sealing cavity and the high-temperature area on the inner side, and thus reduces the end face temperature of the turbine pump mechanical seal ring.

The embodiment of the invention provides a shafting locking structure, a turbine pump, an engine and a rocket. The shafting locking structure comprises a main shaft, a plurality of shafting rotating components connected to the main shaft, a locking nut arranged between every two adjacent shafting rotating components and a limiting structure for limiting the circumferential position of the locking nut. According to the technical scheme, the locking mode is compact in structure and high in reliability, the requirement for repeated use is met, and the locking device is suitable for being applied to the rocket turbine pump.

The present disclosure relates to a turbine assembly including a turbo pump configured to pressurize an oxidant and fuel to a high pressure and supply the oxidant and fuel to a combustor, and more particularly, to a technology capable of recycling exhaust gas that has operated a turbine of a turbo pump.

The application discloses a rocket engine turbine pump rotating speed extraction method based on parameter spectrum analysis, and solves the technical problems of high calculation complexity, long operation time and poor real-time performance of a calculation method for obtaining the phase information of the first-order signal of the vibration signal by carrying out Hilbert demodulation on the first-order signal of the vibration signal, deriving the phase information of the first-order signal of the vibration signal with respect to time, and finally calculating the instantaneous rotating speed of the turbine pump according to the derivation result, and comprises the following steps: collecting a fuel pump acceleration response signal, selecting a sliding window for the collected data to obtain a to-be-processed signal, carrying out band-pass filter processing on the to-be-processed signal, carrying out power spectrum calculation on the processed data in an autoregressive process to obtain a single-sideband power spectrum, and calculating the rotating speed of the turbine pump based on the peak frequency of the single-sideband power spectrum.

The application discloses a turbine type photovoltaic pump and belongs to the technical field of pump bodies, which comprises a solar panel, an MPPT controller, a brushless DC motor and a turbine pump body unit, the solar panel is electrically connected with the MPPT controller, the MPPT controller is electrically connected with the brushless DC motor, the brushless DC motor is installed on the turbine pump body unit, and a sealing protection unit is arranged on the turbine pump body unit; the brushless DC motor comprises a machine cylinder, front and rear end covers are fixed on both ends of the machine cylinder through internal hexagon screws, front and rear bearings are respectively installed in the front and rear end covers, a rotor and a coil are installed in the machine cylinder, the turbine pump body unit comprises a pump head and a volute, the pump head and the volute are fixedly connected through external hexagon screws, a water inlet and a water outlet are installed on the pump head, and an impeller is installed in the volute. The application discloses a turbine type photovoltaic pump which is reliable in sealing and has perfect protection function.

The application discloses a series layout method of an oxygen-rich hypergolic cycle engine and belongs to the field of overall layout of the oxygen-rich hypergolic cycle engine. The engine comprises an oxidizer half system and a fuel half system, the oxidizer half system at least comprises an oxygen pre-pressure pump, an oxygen turbine pump and a thrust chamber connected in sequence, and the fuel half system at least comprises a fuel pre-pressure pump and a fuel turbine pump. The axis of the oxidizer half system coincides with the thrust line of the engine, thereby forming a series layout main body. The oxygen pre-pressure pump, an oxygen swing hose, the oxygen turbine pump integrated with an annular oxygen-rich gas generator and the thrust chamber are connected in sequence along the axis direction. The oxygen swing hose is arranged on a low-pressure pipeline between the oxygen pre-pressure pump and the oxygen turbine pump, so that the oxygen pre-pressure pump does not participate in swing when the engine swings. The application is applied to the oxygen-rich hypergolic cycle engine, breaks through the limitation of the traditional parallel layout and realizes an overall layout scheme of high compactness, centroid alignment, low swing torque and avoidance of use of a high-pressure swing hose.

The application provides a monitoring method for a turbine pump in an inadmissible rub fault, which comprises the following steps: firstly, collecting output signals of vibration sensors at each monitoring position of the turbine pump during the working process of the turbine pump; secondly, obtaining multi-dimensional judgment elements according to the vibration sensor signals; and finally, comprehensively scoring according to three-dimensional judgment elements, judging the rub level of the turbine pump, and determining whether the turbine pump appears in the inadmissible rub fault. The application evaluates the rub level of the turbine pump by means of the multi-dimensional evaluation idea, and refines and divides the rub level of the turbine pump. After judging that the rub phenomenon appears, the method is no longer directly adopted to stop the machine, but is adopted to judge whether the rub phenomenon is admissible or not by means of the scoring evaluation mode. For the admissible slight rub, the method is adopted to keep monitoring, and for the inadmissible rub fault, the method is adopted to stop the machine. The method can reduce the waste of manpower and material resources, and improve the repeatability of the rocket turbine pump.

This application relates to a fuel-rich pre-combustion chamber. The fuel-rich pre-combustion chamber includes a combustion chamber and a flow guiding structure. The combustion chamber has a gas inlet and a gas outlet, and the gas in the combustion chamber flows from the gas inlet to the gas outlet. The flow guiding structure is disposed within the combustion chamber and configured to guide the gas in the combustion chamber towards the inner wall of the combustion chamber. In the fuel-rich pre-combustion chamber provided by this application, fuel and oxidant are burned at the gas inlet end of the combustion chamber to form gas, which then flows towards the gas outlet end to enter subsequent mechanisms for driving a turbopump or other purposes. By providing a flow guiding structure within the combustion chamber to guide the gas in the combustion chamber towards the inner wall of the combustion chamber, the flow direction of the gas is changed, breaking the stratification phenomenon, thereby accelerating the mixing of the high-temperature gas in the central region with the low-temperature gas in the peripheral region, achieving the purpose of improving the uniformity of gas temperature at the gas outlet, and thus improving the service life and operating efficiency of the turbopump.

There is disclosed a turbopump for use in an engine, such as a reaction engine, the engine having an engine passage within which combustion of a propellant takes place so as to provide thrust (for example motive thrust), and having a cooling system to extract heat from the engine passage. The described turbopump comprises: a rotatable shaft; an impeller for pumping propellant from a propellant supply to the cooling system, and a turbine for being driven by propellant subsequently flowing from the cooling system to the engine passage for combustion, the impeller and the turbine being coupled to opposing ends of the shaft; an electrical machine disposed between the impeller and the turbine, the electrical machine comprising a rotor and a stator surrounding the rotor, the rotor forming part of the shaft so as to corotate with the impeller and the turbine, the electrical machine being controllable to selectively either deliver electrical power to the stator to drive rotation of the shaft, or to receive electrical power from the stator generated by rotation of the shaft.

The application discloses a kind of extrusion type first-stage liquid rocket, comprising: liquid nitrogen tank, liquid oxygen tank, fuel tank, thrust chamber, liquid nitrogen booster turbine pump, vaporizer around being arranged in the outer wall of thrust chamber, relevant valve and pipeline;The top of the thrust chamber is equipped with double-group element injector.Hollow shaft blade transports liquid nitrogen to actively cool turbine end, adopt turbine end internal cavity to realize efficient heat exchange, cooperate with the micro-hole of turbine end peripheral wall and open turbine blade cooling, effectively alleviate the scouring and damage of high-temperature gas to turbine end, realize liquid nitrogen booster turbine pump super multiple test run is not damaged.Liquid nitrogen booster turbine pump only carries out booster operation to a small amount of liquid nitrogen, without bearing the high-pressure pumping task of liquid propellant, can directly use civil-grade turbocharger pump to replace traditional high-cost aerospace-grade turbine pump as the liquid nitrogen booster turbine pump of the application, so that the manufacturing cost and research and development cost of rocket are significantly controlled, and the threshold of large-scale application is greatly reduced.

The application provides a guide structure of a turbine pump exhaust ring cavity, which comprises a plurality of first vertical support plates, a second vertical support plate and a ring guide structure. The plurality of first vertical support plates are arranged at intervals around a central axis of the exhaust ring cavity, and two ends of each first vertical support plate are connected to a top wall and a bottom wall of an exhaust shell respectively; each first vertical support plate deviates from a thrust chamber of the exhaust ring cavity by a first preset included angle; two ends of the second vertical support plate are connected to the top wall and the bottom wall of the exhaust shell respectively; the ring guide structure extends along the exhaust ring cavity and protrudes towards the bottom wall of the exhaust shell, and a leading edge of the ring guide structure is located at a gas inlet of the exhaust shell. On the basis of weakening the influence of the rotational flow, the application weakens the flow around the vertical section of the exhaust ring cavity, greatly reduces the flow loss of the gas, and further improves the performance of the rocket engine.

This invention discloses a flexible docking device for a liquid rocket engine turbopump housing, comprising: a cylinder assembly and an axial motion device connected via a slide rail structure; an actuating rod of the cylinder assembly fixedly connected to a planar floating device; a locking mechanism for locking or unlocking the axial motion device and the planar floating device; when locked, the cylinder assembly can only drive the planar floating device to move axially, and the planar floating device cannot swing relative to the cylinder assembly; after unlocking, the cylinder assembly can not only drive the planar floating device to move axially, but the planar floating device can also swing relative to the cylinder assembly; the bottom of the planar floating device and a circumferential rotating device are fixedly connected; the circumferential rotating device secures the external docking product. Using the flexible docking device for a liquid rocket engine turbopump housing provided by this invention for component docking and assembly is simple in process and convenient in operation, effectively improving the assembly efficiency and accuracy of the turbopump and reducing the labor intensity of workers.

The application discloses a model for identifying dynamic stiffness of a turbine pump rotor bearing, which is used for improving the accuracy of dynamic parameter design of the turbine pump rotor bearing, supporting high-speed, high-power and long-time stable operation of the turbine pump rotor, and providing important support for design of a liquid rocket engine turbine pump rotor.

The application discloses an electric pump pre-pressurization liquid rocket engine, which comprises a pre-pressurization unit, a turbine pump and a gas generator which are sequentially connected; and a thrust chamber connected with the turbine pump; the pre-pressurization unit comprises a power supply, and an oxidant pre-pressurization assembly and a fuel pre-pressurization assembly are connected to the power supply; the oxidant pre-pressurization assembly and the fuel pre-pressurization assembly are connected with the turbine pump. The electric pump pre-pressurization liquid rocket engine overcomes the deficiency that the pre-pressurization pump cannot provide positive lift and has low efficiency at the initial stage of starting of a traditional engine, is beneficial to improving the adaptability of the engine to low inlet pressure in the whole working process, avoids cavitation of the main pump, has a simple structure and improves working reliability. The application further discloses a working method of the electric pump pre-pressurization liquid rocket engine.

A rocket engine using expander bleed cycle includes an aerospike nozzle to thereby maintain optimal performance even in an environment where the atmospheric pressure varies. A rocket engine includes: a regenerative cooling nozzle; at least one turbine that rotates by fuel vapor vaporized in the regenerative cooling nozzle; a fuel transfer turbopump that is driven by the turbine; an oxidizer transfer turbopump that is driven by the turbine; and a combustion chamber in which an oxidizer and a fuel are mixed and burned. In the rocket engine, the regenerative cooling nozzle is shaped into an aerospike nozzle, and the rocket engine uses an expander bleed cycle that discharges fuel vapor vaporized in the regenerative cooling nozzle, after use, to outside of the combustion chamber.

This invention discloses a high-power CO2 amplifier and its operating method, relating to the field of EUV lithography technology. The amplifier includes a vacuum system, a resonant cavity, and a pump source. The vacuum system consists of a turbopump, a vacuum pump, stainless steel tubing, and a glass tube forming a gas circulation channel. A large-diameter ceramic discharge tube is placed within the channel, with high-transmittance windows mounted at both ends via input and output window assemblies. The pump source uses a DC high-voltage power supply in conjunction with an anode needle and a cathode ring electrode arranged axially along the ceramic discharge tube. The operating method involves evacuating the cavity to a low pressure and backfilling it with a mixture of helium, carbon dioxide, and nitrogen. The turbopump is then activated to create an axial fast flow. A DC high voltage is set, and 10.6μm signal light is injected into the input window to achieve pulse amplification. The combination of the large-diameter discharge channel and the axial fast-flow DC discharge improves the amplifier's saturation intensity and discharge uniformity, reduces thermal damage, and is suitable for post-amplification stages of LPP-EUV light sources.