49results about How to "Reduced mixing loss" patented technology

An axial flow turbine that can enhance an effect of reducing a mixing loss is disclosed. The axial flow turbine includes a plurality of stator blades provided on the inner circumferential side of a diaphragm outer ring; a plurality of rotor blades provided on the outer circumferential side of a rotor; a shroud provided on the outer circumferential side of the plurality of rotor blades; an annular groove portion formed in the diaphragm outer ring and housing the shroud therein; a clearance passage defined between the groove portion and the shroud, into which a portion of working fluid flows from the downstream side of the stator blades in a main passage; seal fins provided in the clearance passage; a circulation flow generating chamber defined on the downstream side of the clearance passage; and a plurality of shielding plates secured to the diaphragm outer ring.

The invention relates to a hybrid exhaust aircraft engine with a rear-mounted fan. The hybrid exhaust aircraft engine comprises an engine rotor, an inner housing, an outer housing, a main combustion chamber and an interstage combustion chamber which are formed in an inner culvert, and the rear-mounted fan, wherein an outer culvert is formed between the inner housing and the outer housing, and the inner culvert is formed in the inner housing; the engine rotor comprises a front-mounted fan rotor and a high-pressure compressor rotor which are positioned in front of the main combustion chamber, a high-pressure turbine rotor positioned between the main combustion chamber and the interstage combustion chamber, and a low-pressure turbine rotor positioned in the rear of the interstage combustion chamber; the rear-mounted fan is arranged in the rear of the low-pressure turbine rotor in the flowing direction of fluid, and comprises a plurality of fan blades and turbine blades which are arranged circumferentially and an annular margin plate connected with the turbine blades and the fan blades; and the fan blades are positioned in the outer culvert, and the turbine blades are positioned in the inner culvert.

A pressure exchanger transferring pressure energy from a liquid in a first liquid system to a liquid in a second liquid system, having a housing with inlet and outlet connection openings for each liquid and a rotor arranged in the housing for rotation about a longitudinal axis. Through rotor channels are arranged around the rotor longitudinal axis with openings on each axial end face of the rotor. The rotor channels are arranged for connection through opposing flow openings facing the housing to the connection openings of the housing. During rotor rotation high pressure liquid and low pressure liquid are alternately introduced into the respective systems. Liquid flowing to the rotor through the openings generates a circumferential force (cu) for driving the rotor, and starting at or following the openings a flow guiding configuration formed as a rotor channel flow diverting contour is arranged in the rotor channels.

The invention provides a refrigerating system. The refrigerating system comprises a compressor (1), an evaporation device and a condensation device; the compressor comprises more than two compressioncavities and further comprises more than one switching compression cavity, more than one air supplement port and more than one air supplement branch (10), wherein the compression cavities are independent from each other, and the air supplement branches are located outside the compressor; the air supplement ports can be connected to the air supplement branches (10); the air suction ends of the switching compression cavities are connected to the air supplement ports; and the exhaust ends of the switching compression cavities are connected to an exhaust port of the compressor. Compared with an original two-stage or quasi-two-stage air supplement enthalpy increasing system loop, the refrigerating system has the beneficial effects that a technology combining air supplement enthalpy increasing and parallel compression is adopted, air supplement enthalpy increasing can be realized by utilizing the air supplement branches, the mixing loss of air supplement can be effectively reduced, the backflow loss and the flowing resistance loss of air supplement can be reduced, and therefore the air supplement enthalpy increasing effect can be improved, the heating capacity of the refrigerating systemat a low temperature can be improved, and the energy efficiency level of the system can be improved.

In a gas turbine engine, each vane has pressure and suction surfaces extending radially from an inner to outer endwall of an annular working gas engine passage, and extending axially from a leading to a trailing edge of the vane. Each vane has transverse sections providing respective aerofoil sections. Neighbouring vanes are arranged in unequally-shaped pairs in which either: (i) the first vane of each pair exhibits compound lean, and the second vane of the pair exhibits reverse compound lean or has substantially no tangential lean, (ii) the first vane of each pair has substantially no tangential lean, and the second vane of the pair exhibits reverse compound lean, or (iii) the first vane of each pair exhibits reverse compound lean, and the second vane of the pair exhibits greater reverse compound lean. Within each unequally-shaped pair the first vane is on the pressure surface side of the second vane.

A pressure exchanger for transferring pressure energy from a first liquid in a first liquid system to a second liquid in a second liquid system, having a housing with inlet and outlet connection openings for each liquid and a rotor (1) arranged in the housing for rotation about a longitudinal axis. A number of through rotor channels (2) are arranged around the rotor longitudinal axis with openings (4) on each axial end face of the rotor. The rotor channels (2) are arranged for connection through opposing flow openings formed in the housing to the connection openings of the housing such that during rotation of the rotor, high pressure liquid and low pressure liquid are alternately introduced into the respective systems. Liquid flowing to the rotor through the flow openings formed in the housing generates a circumferential force component (cu) in the relative rotating system of the rotor for driving the rotor, and starting at or following the openings (5) a flow guiding configuration (8) formed as a rotor channel flow diverting contour is arranged in the rotor channels (2).

An axial turbine includes a plurality of ribs provided in such a way as to be sandwiched between the diaphragm outer ring and the axial seal fin in the gap between the shroud and the diaphragm outer ring, the ribs being extended from the diaphragm outer ring toward the shroud in the radial direction of the rotor and in the direction of the rotation axis thereof, and a guide plate provided in such a way as to be present along the axial seal fin and a face of the diaphragm outer ring, opposed to the rotor, so as to be extended in the rotation radial direction of the rotor.

A turbine airfoil has a suction side wall and a pressure side wall of an airfoil cavity, through which a cooling fluid flows for cooling of the side walls. The suction side wall has one or more protrusions extending therefrom into the airfoil cavity. The protrusions are arranged such that: a number of the one or more protrusions on the suction side wall is higher than a number of protrusions on the pressure side wall; and / or a protrusion density on the suction side wall is higher than a protrusion density on the pressure side wall, and / or a total protrusion surface area on the suction side wall is larger than a total protrusion surface area on the pressure side wall, so that the heat transfer from the suction side wall to the cooling fluid is higher compared to that of the pressure side wall during operation of the turbomachine.

The turbine (1) according to the present invention includes: a blade body (50) having a blade (59) provided at one of a rotor rotatably supported and a stator provided around the rotor and extending in a radial direction toward the other side from one side and a shroud (51) extending in a circumferential direction at a tip portion in the radial direction of the blade (59); and an accommodating concave body (11) provided at the other of the rotor and the stator, extending in the circumferential direction, accommodating the shroud (51) with a gap (G) interposed therebetween, and relatively rotating with respect to the blade body (50), wherein leakage flow (L) leaked from main flow (M) flowing along the blade (59) flows into the gap (G); and wherein the shroud is provided with a guide curved surface formed between a peripheral surface (53C) facing the accommodating concave body (11) and a trailing edge end portion (56) formed closer to the main flow (M) side in a downstream of the leakage flow (L) than the peripheral surface (53C) in a downstream of the leakage flow (L), wherein a guide curved surface (57) is configured to guide the leakage flow (L) along the peripheral surface (53C) from the peripheral surface (53C) to the trailing edge end portion (56).

The invention provides a refrigerating system. The refrigerating system comprises a compressor (1), an evaporation device and a condensation device; the compressor comprises more than two compressioncavities and further comprises more than one switching compression cavity, more than one air supplement port and more than one air supplement branch (10), wherein the compression cavities are independent from each other, and the air supplement branches (10) are located outside the compressor; the air supplement ports can be connected to at least one of the air supplement branches (10); the air suction ends of the switching compression cavities are connected to the air supplement ports; and the exhaust ends of the switching compression cavities are connected to an exhaust port of the compressor. Compared with an original two-stage or quasi-two-stage air supplement enthalpy increasing system loop, the refrigerating system has the beneficial effects that a technology combining air supplemententhalpy increasing and parallel compression is adopted, air supplement enthalpy increasing can be realized by utilizing the air supplement branches, the mixing loss of air supplement can be effectively reduced, the backflow loss and the flowing resistance loss of air supplement can be reduced, and therefore the air supplement enthalpy increasing effect can be improved, the heating capacity of therefrigerating system at a low temperature can be improved, and the energy efficiency level of the system can be improved.

A turbine airfoil for a turbomachine is provided. The airfoil includes a suction side wall and a pressure side wall bordering an airfoil cavity, which receives a cooling fluid for cooling the airfoil. The suction side wall includes one or more protrusions extending inside the cavity. The number of protrusions on the suction side may be higher than the number of protrusions on the pressure side. The density of protrusions on the suction side may be higher than the density of protrusions on the pressure side and / or the surface of protrusions on the suction side may be larger than the surface of protrusions on the pressure side, so that heat transfer from the suction side to the cooling fluid is higher compared to heat transfer from the pressure side to the cooling fluid during operation of the turbomachine.

A small portable power pack includes a fuel / air supply for mixing fuel, which is supplied from outside, with outside air, thereby providing mixed gas; a uniflow scavenging micro-engine for receiving mixed gas from the fuel / air supply and igniting mixed gas to explode; a control panel for operating and controlling the uniflow scavenging micro-engine; a capacitor battery for powering the control panel and the uniflow scavenging micro-engine. The portable power pack is easily carried and used without the restriction of spaces and sites.

An axial turbine includes a plurality of ribs 9 provided in such a way as to be sandwiched between the diaphragm outer ring 1 and the axial seal fin 7 in the gap between the shroud 6 and the diaphragm outer ring 1, the ribs 9 being extended from the diaphragm outer ring 1 toward the shroud 6 in the radial direction of the rotor 3 and in the direction of the rotation axis thereof, and a guide plate 10 provided in such a way as to be present along the axial seal fin 7 and a face of the diaphragm outer ring 1, opposed to the rotor 3, so as to be extended in the rotation radial direction of the rotor 3.

The shaft-less open impeller suitable for micro pump is one pollution-free and leak-less centrifugal mixed flow pump device suitable for continuous flow artificial heart. The impeller includes one vane combination and one vane holder, and the vane has pressure surface in the horizontal angle of 5-20 deg, conic upper end part of conic angle 40-60 deg, the ration between planar projection area of vane and outer circle area of the impeller of 0.4-0.8, and inlet angle and outlet angle of 45-50 deg. The impeller has effective inhibition of the secondary flow in the pressure surface of the vane, improved inside flow structure, reduced flow loss, small diameter and thus reduced damage to blood cell. The present invention may be also used in various kinds of centrifugal pump or mixed flow pump to improve the performance of the pumps.

The invention discloses a lobe mixer capable of generating swirling jet. Ridge lines of lobes of the mixer forms certain angles with the engine axis. The airflow angle before mixing of external bypassairflow is changed by the deflection angles of the lobes in the lobe mixer, so that swirling jet is generated after the external bypass airflow flows through the lobes, mixing of internal and external bypass airflow is enhanced, an additional connecting structure is not generated, and the structure is simple. The mixer can be applied to an afterburner with medium bypass ratio or a mixed exhaust device with medium and small bypass ratio, and the purposes of low mixing loss and high mixing thermal efficiency can be achieved.

A seal system between a row of buckets supported on a machine rotor and a surrounding stationary casing or stator includes a tip shroud secured at radially outer tips of each of the buckets, the tip shroud formed with a radially-projecting rail. A cellular seal structure is supported in the stationary stator in radial opposition to the tip shroud and the rail. The seal structure has an annular array of individual cells formed to provide continuous, substantially horizontal flow passages devoid of any radial obstruction along substantially an entire axial length dimension of the cellular seal structure to prevent flow about the tip shroud from turning radially inwardly.

In a gas turbine engine, each vane has pressure and suction surfaces extending radially from an inner to outer endwall of an annular working gas engine passage, and extending axially from a leading to a trailing edge of the vane. Each vane has transverse sections providing respective aerofoil sections. Neighboring vanes are arranged in unequally-shaped pairs in which either: (i) the first vane of each pair exhibits compound lean, and the second vane of the pair exhibits reverse compound lean or has substantially no tangential lean, (ii) the first vane of each pair has substantially no tangential lean, and the second vane of the pair exhibits reverse compound lean, or (iii) the first vane of each pair exhibits reverse compound lean, and the second vane of the pair exhibits greater reverse compound lean. Within each unequally-shaped pair the first vane is on the pressure surface side of the second vane.

The invention relates to a thermoacoustic refrigerator, comprising a compressor and a cold head. The cold head is composed of a radiator, a regenerator, a cooling capacity heat exchanger, an inertia tube and a gas reservoir. The compressor adopts a stepped piston structure. A compression chamber and an expansion chamber are formed. The compression chamber is connected to the radiator. The expansion chamber is connected to the gas reservoir. Temperature difference is formed between the compression chamber and the expansion chamber. The thermoacoustic refrigerator adopts the stepped piston structure, so that the compressor forms the compression chamber and the expansion chamber. Compared with a pulse tube refrigerator, temperature difference between room temperature and low temperature is borne by a second stage piston and a second stage air cylinder. In an aspect of a large low-temperature cryocooler, mixing loss due to gas in a vessel can be reduced, thereby achieving higher refrigeration effect.

A turbine includes: a blade body having a blade provided at one of a rotor rotatably supported and a stator provided around the rotor and extending in a radial direction and a shroud extending in a circumferential direction at a tip portion in the radial direction of the blade; and an accommodating concave body provided at another one of the rotor and the stator, extending in the circumferential direction, accommodating the shroud with a gap interposed therebetween, and relatively rotating with respect to the blade body, wherein a leakage flow leaked from a main flow flowing along the blade flows into the gap; and wherein the shroud is provided with a guide curved surface formed between a peripheral surface facing the accommodating concave body and a trailing edge end portion formed closer to a main flow side in a downstream side of the leakage flow than the peripheral surface.

The invention relates to an air source heat pump double-water-tank hot water system and a control method. The air source heat pump double-water-tank hot water system comprises a variable-frequency water supply pump, a hot water tank, a warm water tank and a parallel host which are connected in sequence, and further comprises a water return valve and a water replenishing valve which are connected with the warm water tank; the hot water tank, the warm water tank and the parallel host are sequentially connected to form host-water tank circulation; the warm water tank, the hot water tank, the variable-frequency water supply pump and the water return valve are sequentially connected to form water tank-tail end circulation; and the parallel host comprises a plurality of parallel branches which are independently controlled or not independently controlled, and different heat supply modes are achieved by opening a specific number of parallel branches, so that different tail end load requirements are met. Compared with the prior art, the double-water-tank scheme is adopted, so that the mixing loss among return water, replenished water and hot water is reduced; and meanwhile, the water inlet temperature and the water outlet temperature of the heat pump are reduced, the condensation temperature of the heat pump can be well reduced, and the energy efficiency of the heat pump unit is improved while water consumption of a user is guaranteed.

The invention discloses a multistage gas liquefaction plant driven by a loop multistage thermoacoustic engine. The multistage gas liquefaction plant comprises M thermoacoustic engine units and pulse tube refrigerating machine units, wherein the pulse tube refrigerating machine units are connected with the outlets of the thermoacoustic engine units in a by-pass manner; M is a positive integer ranging from 3 to 6; a refrigerating unit comprises a refrigerating machine regenerator and a low-temperature end heat exchanger; each pulse tube refrigerating machine unit comprises two or more refrigerating units; multiple by-pass pipelines are arranged between each refrigerating machine regenerator and a corresponding pulse tube, so that the refrigerating machine regenerator and the corresponding pulse tube are connected to form at least one by-pass airflow passage; acoustic power generated through self-excitation of the thermoacoustic engine has thermoacoustic conversion in the refrigerating machine regenerators; the multiple low-temperature end heat exchangers are maintained under different refrigerating temperatures; and the to-be-liquefied gas sequentially passes through all low-temperature end heat exchangers to be liquefied in a temperature stepped decrease manner. The multistage gas liquefaction plant has no moving part, and is compact in structure and high in power density; the loop structure enables the engine units to be in the traveling wave phase; the multipath bypass structure realizes gas expansion refrigeration to improve the efficiency of a pulse tube refrigerating machine; and in addition, the multistage refrigerating units reduce the gas temperature in a stepped manner to effectively reduce the irreversible heat transfer loss.

An axial turbine (1) has a plurality of expansion stages (2) each defined by stator blades (13) and rotor blades. The expansion stages (2) are followed by an exhaust diffuser (4) for collecting the flow passing through the expansion stages (2) and discharging it to the outside. The expansion stages (2) and / or the diffuser (4) have at least a non-axial symmetric portion. The stator blades (13) define different openings (17) along the circumference of the turbine.

Embodiments of the present disclosure describe a reflux device blade, a compressor structure and a compressor. The reflux device blade includes a blade main body, a hollow cavity is formed in the blade main body, and an air supplement hole is formed in the blade main body. When the hollow reflux device blade is adopted, the supplemental air entering the hollow cavity of the reflux device blade through an air supplement channel forms jet flow on a suction surface of the reflux device blade to blow off a low-speed low-energy area formed on the suction surface, so as to reduce the airflow mixing loss, prevent the intake distortion of a second-stage impeller, and improve the operation range of the compressor.

The invention provides a heat pump system. The heat pump system comprises a first compressor, a second compressor, a four-way reversing valve, a first heat exchanger and a second heat exchanger, wherein an air inlet of the first compressor communicates with a first port of the four-way reversing valve, and an exhaust port of the first compressor and the exhaust port of the second compressor communicate with the second port of the four-way reversing valve; the first end of the first heat exchanger communicates with a third port of the four-way reversing valve, and the second end of the first heat exchanger communicates with the air inlet of the second compressor; the first end of the second heat exchanger communicates with the fourth port of the four-way reversing valve, and the second endof the second heat exchanger communicates with an air inlet of the second compressor. According to the heat pump system, the gas supplementing and enthalpy increasing of the heat pump system are realized through the second compressor, and compared with a traditional heat pump system, mixing loss during gas supplementation can be reduced, the backflow loss and the flowing resistance loss of the airsupplement can be reduced, the effect of supplementing the gas and increasing the enthalpy is improved, and the problem that the energy efficiency is low when the heat pump system is heated is solved.

The invention relates to methods and apparatus for a vibration-free placement of the concrete and for placement and enforced speed inertial compaction of the concrete under a high pressure. The method permits to optimize the values of the compaction factor of the concrete mix being placed without vibration. Whereupon, in the case of variation assigning and implementing (adjusting and optimizing) the integral indices of the mix, and / or the plume modes, and / or the space medium characteristics, increasing the concrete strength in early time of the concrete curing, increasing the width of the placed and compacted mix in one step of concreting, reducing the mix losses in the case of placing with compacting the concrete mix. The method implements a stage of concreting under super-high pressure using a speed force inertial characteristic of components, wherein the steps are joined into the continuous serial process of the steps of: preparing the mix, unloading and transporting thereof, reconstructing the stream, discharging the mix stream for placing with compacting thereof, particularly by means of stabilizing the uniformity of the concrete mix. The apparatus is designed for implementing the method.

Embodiments of the present disclosure describe a reflux device blade and a compressor. The reflux device blade includes a blade main body, a hollow cavity is formed in the blade main body, and an air supplement hole is formed in the blade main body. When the hollow reflux device blade is adopted, the supplemental air entering the hollow cavity of the reflux device blade through an air supplement channel forms jet flow on a suction surface of the reflux device blade to blow off a low-speed low-energy area formed on the suction surface, so as to reduce the airflow mixing loss, prevent the intake distortion of a second-stage impeller, and improve the operation range of the compressor.