67results about How to "Increase boost ratio" patented technology

The invention provides a turbocharger structure which is applied in the technical field of a turbocharger and can change an air flow direction entering into a press shell. The variable air inlet structure turbocharger comprises a turbine shell (1), a middle shell (2) and the press shell (3); a press shell inlet (41) of the turbocharger structure is provided with an air inlet adjusting device (5) which is capable of changing the air flow direction entering into the press shell (3); the air inlet adjusting device (5) comprises a cavity (34) with a hollow structure; more than one sheet-shaped guide blade (44) is installed in the cavity (34); the air inlet adjusting device (5) further comprises a driving mechanism (49) for driving the guide blade (44) to torque. The technical scheme of the invention can change the air flow direction in the inlet of the gas compressor, efficiently reduce the flow rate while surging, improve the flow rate while blocking, widen the flow rate range of the turbocharger and improve the efficiency and pressure ratio of the turbocharger.

Systems and methods for operating a twin flow supercharged engine are provided. The exhaust lines of engine cylinders are grouped into separate manifolds connected to respective inlet ducts of the twin-flow turbine. The inlet ducts of the twin-flow turbine are of different sizes, with different-sized cross sections and/or different-sized exhaust-gas volumes. The exhaust line of a manifold with a smaller exhaust-gas volume is connected to the larger inlet duct, and the exhaust line of a manifold with the larger exhaust-gas volume is connected to the smaller inlet duct.

A turbojet engine comprises all structures of a turbojet engine such as an axial-flow air compressor, an evaporative combustion chamber, a turbine and a tail jet pipe. The turbojet engine is characterized in that a bypass pipe and an inner exhaust valve are further included, an outer exhaust valve is arranged or not arranged in a pipe outside the engine between an air inlet and an air outlet of the bypass pipe, after the engine is started and operates, the inner exhaust valve is opened, by opening and closing of the bypass pipe, the inner exhaust valve and the existing or nonexistent outer exhaust valve, the supercharge ratio of the axial-flow air compressor is increased and kept unchanged, the increased supercharge ratio is not higher than the limitation borne by the axial-flow air compressor and a turbine according to the mechanical strength, turbine inlet temperature is kept unchanged, namely the supercharge ratio and thrust-weight ratio are increased, oil consumption rate is lowered, the levels of the axial-flow air compressor and the turbine are not increased, and the turbine inlet temperature is not raised.

A turbofan engine comprises all structures of a turbofan engine such as a fan, an outer duct, an axial-flow air compressor, an evaporative combustion chamber, a turbine and a tail jet pipe. The turbojet engine is characterized in that a bypass pipe and an inner exhaust valve are further included, an outer exhaust valve is arranged or not arranged on the bypass pipe between an air inlet and an air outlet of the bypass pipe, after the engine is started and operates, the inner exhaust valve is opened, by opening and closing of the bypass pipe, the inner exhaust valve and the existing or nonexistent outer exhaust valve, the supercharge ratio of the axial-flow air compressor or the fan is increased and kept unchanged, the increased supercharge ratio is not higher than the limitation borne by the fan, the axial-flow air compressor and a turbine according to the mechanical strength, turbine inlet temperature is kept unchanged, namely the supercharge ratio and thrust-weight ratio are increased, oil consumption rate is lowered, the levels of the fan, the axial-flow air compressor and the turbine are not increased, and the turbine inlet temperature is not raised.

An engine with a level-variable turbocharging system comprises an engine body (1) and the level-variable turbocharging system, wherein the engine body (1) comprises an engine mechanical assembly and an engine electric control unit; the level-variable turbocharging system comprises a large turbocharger (21), a middle turbocharger (22) and a small turbocharger (23) which are different in flow, each of the turbochargers comprises a turbine and an air compressor which form a network with an air pipe through a tee joint (312), a tee joint (322), a tee joint (331), a tee joint (342), a tee joint (381), a tee joint (412), a tee joint (422), a tee joint (441), a tee joint (451), a three-way valve (311), a three-way valve (321), a three-way valve (341), a three-way valve (351), a three-way valve (411), a three-way valve (421) and a three-way valve (461), and connected with the engine body (1).

The invention discloses a variable geometry volute device which comprises a turbine volute. A volute air inlet runner is arranged in the turbine volute, a turbine pneumatic separation plate divides the volute air inlet runner into an inner volute air inlet runner and an outer volute air inlet runner, a second pneumatic separation plate is arranged in the outer volute air inlet runner and divides the outer volute air inlet runner into a first branch runner and a second branch runner, and the second branch runner is located on a circumferential outside of the first branch runner. The inner volute air inlet runner is a normally-opened air inlet runner, an air inlet adjusting valve for controlling the first branch runner and the second branch runner to open and close is arranged in the volute air inlet runner close to the position of a volute inlet. The variable geometry volute device achieves variable critical area valve at the position of a throat of the turbine volute through the air inlet adjusting valve so as to effectively meet performance requirements of an engine under each working conditions.

A turboprop engine comprises all structures of a propeller, axial-flow compressors, evaporative combustors, turbines, an exhaust nozzle and the like, and is characterized by further comprising by-pass pipes and internal exhaust valves, and external exhaust valves are mounted or are not mounted in pipes outside the engine and between air inlets and air outlets of the by-pass pipes; and when the engine is started for operation, the internal exhaust valves are opened, the supercharge ratios of the axial-flow compressors are increased and kept unchanged by means of the by-pass pipes and through opening and closing of the internal exhaust valves or the internal exhaust valves and the external exhaust valves, the increased supercharge ratios are not larger than the mechanical strength limit which can be borne by the axial-flow compressors and the turbines, the turbine inlet temperature is kept unchanged, that is, the supercharge ratios and a power weight ratio are increased, the oil consumption rate is reduced, however, the number of stages of the axial-flow compressors and the turbines is not increased, and the turbine inlet temperature is not increased.

The invention provides a double-stage centrifugal air compressing device. The double-stage centrifugal air compressing device comprises a first-stage centrifugal air compressing device, a second-grade centrifugal air compressing device, a connecting shaft and a reflowing device, wherein the first-stage centrifugal air compressing device comprises a first centrifugal impeller and a first shell; the second-grade centrifugal air compressing device comprises a second centrifugal impeller and a second shell; the connecting shaft is fixedly connected with the first-stage centrifugal air compressing device; the second-grade centrifugal air compressing device is movably connected with the connecting shaft; and the first-stage centrifugal air compressing device is connected with the second-grade centrifugal air compressing device through the flowing device. According to the double-stage centrifugal air compressing device, the first-stage centrifugal air compressing device is connected with the second-grade centrifugal air compressing device through the flowing device, so that the pressurizing ratio of the air compressing device is improved and the oil consumption amount is reduced; and meanwhile, the quantity of parts of the air compressing device is reduced and the manufacturing cost of the air compressing device is reduced.

The invention relates to a turbine cooler provided with three coaxial impellers and capable of expanding in two ways. The design that the three impellers, namely, the refrigeration turbine impeller (T), the power turbine impeller (T) and the gas compressor impeller (C), are coaxial is adopted for a shaft system of the turbine cooler, and the refrigeration turbine impeller, the power turbine impeller and the gas compressor impeller are sequentially arranged in the sequence of T, T and C. Compared with a conventional double-impeller (T and C) turbine cooler, the turbine cooler has the advantages that a power turbine unit is added between a refrigerator turbine and a gas compressor, auxiliary power is provided for pressurizing the gas compressor, the pressure ratio of the gas compressor and the expansion ratio of the refrigeration turbine are increased, the refrigerating capacity of the refrigeration turbine is improved, and therefore the technical purpose of refrigeration under the low flight Mach number and large cold plate flow resistance of an onboard avionic pod environment control system can be effectively achieved.

The invention relates to a hollow shaft rotation stamping compression rotor based on the shock compression technology, belonging to the gas turbine field, which comprises a hollow shaft, a sealing device, a wheel disc and a gas inlet flow channel on the outer edge of the wheel disc; wherein the wheel disc and the hollow shaft are made into a whole or the wheel disc is connected with the hollow shaft through a connecting key or a bearing; the outer edge of the wheel disc is provided with a certain amount of gas inlet flow channels, the gas inlet flow channel is composed of the outer edge of the wheel disc, a partition board arranged on the outer edge of the wheel disc, a gas flow contraction surface, a subsonic diffuser and an outer casing; the wheel disc and the hollow shaft of the gas inlet end and the gas outlet end of the compression rotor are provided with the sealing device. When the compression rotor rotates with the enough high speed, the gas flow is sucked into the gas inlet flow channel and discharged through the multi-shock produced by the gas flow contraction surface and the pressurization of the subsonic diffuser. The invention has the advantages of the high pressurization ratio, the high compression efficiency, the simple and compact structure, the small volume, the light weight, the low manufacturing cost, the convenient disassembly and assembly, the easy maintenance and the high reliability.

The invention discloses a double-channel turbocharger. The double-channel turbocharger comprises a turbine motor, wherein a worm impeller, a volute high-pressure gas inlet channel and a volute low-pressure gas inlet channel are arranged in the turbine motor; a high-pressure gas exhaust manifold and a low-pressure exhaust manifold are arranged on an engine; the volute high-pressure gas inlet channel is connected with the high-pressure gas exhaust manifold; the volute low-pressure gas inlet channel is connected with the low-pressure gas exhaust manifold; a connecting channel and a regulating valve are arranged between the high-pressure gas exhaust manifold and the low-pressure gas exhaust manifold; and number of connecting air cylinders of the high-pressure gas exhaust manifold is greater than that of the low-pressure gas exhaust manifold. In a low-speed area, the regulating valve is closed or has certain aperture, so that gas exhaust back pressure of the volute high-pressure gas inlet channel is higher than gas inlet pressure after turbo-charge; meanwhile, more exhausted gas flows into a turbine from the volute high-pressure gas inlet channel, so that medium-low-rotation-speed turbo-charge needs of the engine are met. In a large-load medium-high-speed area, the regulating valve is opened for discharging exhausted gas of the high-pressure gas exhaust manifold into the low-pressure gas exhaust manifold under a condition that enough gas exhaust back pressure is guaranteed, so that gas exhaust back pressure of the high-pressure channel is reduced, pumping gas loss is reduced and engine efficiency s improved.

The invention belongs to the gasoline engine field, in particular to an air management system of a supercharger gasoline engine, which comprises an air compressor, an intercooler, a main turbine and a double-effect turbine; in the medium or high speed operating condition, the double-effect turbine is serially connected behind the intercooler; the a cylinder and a main turbine are serially and sequentially connected behind the double-effect turbine; the double-effect turbine acts the turbine cooling effect; in the low speed operating condition, the intercooler, the cylinder and the main turbine are serially connected, and then the double-effect turbine is serially connected; the double-effect turbine acts the effect of improving the output torque. The air management system of a supercharger gasoline engine has the advantages of realizing the functions of turbine cooling and the double turbo supercharging, well controlling the inlet gas temperature, allowing higher supercharging ratio and improving the low-speed torque, adopting different operation modes under the high, medium and low rotation speeds, enabling the operation state of the system to be optimized under different operating conditions.

The invention discloses a hollow-shaft ram-rotor based on the shock wave compression technology. The hollow-shaft ram-rotor comprises a hollow shaft, a wheel disc assembly assembled with the hollow shaft in a synchronously rotating mode and an outer case arranged outside the wheel disc assembly in a covering mode, wherein a plurality of spiral separating plates are evenly distributed on the surface of the outer wall of the outer edge of a wheel disc of the wheel disc assembly, and the installation angles of all the spiral separating plates are identical; an air inlet flow channel is formed by a gap between every two adjacent spiral separating plates, and each air inlet flow channel is provided with an air flow compression section, a throat separating section and a triangular outlet extension section which are sequentially arranged from the inlet end to the outlet end. Each air flow compression section is a compression air channel with the radial gap being gradually reduced; each throat separating section is an equal-area passage with the radial gap kept unchanged; each triangular outlet extension section is an air channel with the radial gap kept unchanged, and the interior of the peripheral cylindrical surface of each triangular outlet extension section is triangular. According to the hollow-shaft ram-rotor adopting the technical scheme, fluid is compressed by a curved shock wave system, the supercharge ratio is high, and the hollow-shaft ram-rotor is simple and compact in overall structure and high in reliability.

The invention discloses a spray pipe for an ejector, an ejection unit and an air ejector. The spray pipe is horn-shaped and comprises a large-diameter end and a small-diameter end; an annular airflowstanding chamber is arranged in the pipe wall of the spray pipe in the circumferential direction of the spray pipe, an opening is formed in the side, facing the small-diameter end, of the annular airflow standing chamber, and the opening extends to the end face of the small-diameter end. A plurality of air inlets are formed in the large-diameter end of the spray pipe in the circumferential direction of the spray pipe, and each air inlet is connected to the annular airflow plenum chamber through an air inlet channel formed in the pipe wall of the spray pipe. According to the invention, the contact area of the injected airflow and the injected airflow can be increased, the pressure loss is reduced, and the mixing efficiency and the pressurization ratio are improved.

The invention provides a boosting turbo expander comprising an intermediate shell. A turbine spiral case is arranged at the left end of the intermediate shell, a booster spiral case is arranged at the right end of the intermediate shell, the intermediate shell is internally and rotatably provided with a rotor, and two ends of the rotor are respectively provided with an expansion wheel and a boosting wheel in the turbine spiral case and the booster spiral case; and a left gas bearing and a right gas bearing are sleeved on the rotor, the left gas bearing is used for supporting the expansion wheel, and the right gas bearing is used for supporting the boosting wheel, wherein the left gas bearing and the right gas bearing are graphite gas bearings. The invention has the beneficial effects of stability, low noise, large supercharging ratio, improved rotation speed of the expander, and more environment protection; the refrigerating effect of the boosting turbo expander is improved about 2-3% compared with the refrigerating effect of an original machine; and the boosting turbo expander is not easy to break.

A turbine shaft engine comprises axial-flow compressors, evaporative combustors, a turbine, a free turbine, a drive shaft, an exhaust nozzle and the like, and is characterized by further comprising by-pass pipes and internal exhaust valves, and external exhaust valves are mounted or are not mounted in pipes outside the engine and between air inlets and air outlets of the by-pass pipes; and when the engine is started for operation, the internal exhaust valves are opened, the supercharge ratios of the axial-flow compressors are increased and kept unchanged by means of the by-pass pipes and through opening and closing of the internal exhaust valves or the internal exhaust valves and the external exhaust valves, the increased supercharge ratios are not larger than the mechanical strength limit which can be borne by the axial-flow compressors, the turbine and the free turbine, the turbine inlet temperature is kept unchanged, that is, the supercharge ratios and a power weight ratio are increased, the oil consumption rate is reduced, however, the number of stages of the axial-flow compressors and the turbines is not increased, and the turbine inlet temperature is not improved.

An inertia force balance type two-dimensional piston air compressor is composed of a connecting plate, a transmission shaft, a guide rail, a balance guide rail, a piston shaft sleeve, a cross-shaped supporting rod, roller assemblies, a piston, a cylinder body and the like. The connecting plate is fixedly connected with the cylinder body through threads; the guide rail is fixedly arranged on a piston left side shaft, the balance guide rail is fixedly arranged on the piston shaft sleeve, the piston shaft sleeve can be sleeved on the piston left side shaft in an axial sliding mode, the cross-shaped supporting rod is fixedly arranged on the cylinder body, and the two groups of roller assemblies are fixed on the cross-shaped supporting rod through constraint of the guide rail and arranged in a90-degree staggered mode in the circumferential direction; one end of the guide rail and one end of the balance guide rail are equal-acceleration and equal-deceleration curved surfaces in the same shape and staggered by 90 degrees in the circumferential direction. The mass sum of a balance rotor composed of the balance guide rail and the piston shaft sleeve is equal to the mass sum of a rotor composed of the guide rail and the piston, and when the guide rail drives the rotor to perform equal acceleration and equal deceleration motion, the balance guide rail performs homodromous equal acceleration and equal deceleration staggered motion in the circumferential direction and reversed equal acceleration and equal deceleration staggered motion in the axial direction to counteract inertia forcegenerated by axial motion of the rotor.

Embodiments for an engine coupled to a first turbocharger and a second turbocharger are provided. One example includes responsive to a first condition, deactivating a first turbine of the first turbocharger and meeting a boost demand via operation of the second turbocharger, and responsive to deactivating the first turbine, increasing a pressure at a compressor-side end of a bearing arrangement of a shaft of the first turbocharger. In this way, oil leakage from the bearing arrangement may be reduced.

The invention provides a moving blade row layout capable of improving axial compressor aerodynamic performance. Axial compressor blades are periodically arranged along the peripheral direction X; each period is composed of 2N numbered blade paths, and the ligature of the axial positions of the front edges of the blades arranged in each period forms a triangular wave; the front edge of the first blade (1) and the front edge of a (2N+1)th blade in each period are positioned on the wave crest of the triangular wave; and the front edge of the (N+1)th blade is positioned on the wave trough of the triangular wave. Under the condition that the bending of the blades is constant and aerodynamic stability is not lowered and can be properly improved, the moving blade row has improved boost ratio, increased blockage flow and unreduced efficiency under the state of small angle of attack of a design point. The compressor of the invention can choose a zero-incidence even negative incidence state to serve as the aerodynamic design point, can obtain the higher boost ratio and efficiency near the design point and has bigger stability margin of the compressor.