CN110608068B - Radial flow turbine guide vane structure coupled with non-axisymmetric end wall - Google Patents
Radial flow turbine guide vane structure coupled with non-axisymmetric end wall Download PDFInfo
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- CN110608068B CN110608068B CN201910854065.5A CN201910854065A CN110608068B CN 110608068 B CN110608068 B CN 110608068B CN 201910854065 A CN201910854065 A CN 201910854065A CN 110608068 B CN110608068 B CN 110608068B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/048—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial admission
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Abstract
In order to solve the technical problems of obvious secondary flow of the end wall of the radial flow guide vane with low aspect ratio, relatively large channel vortex size, poor outlet airflow uniformity and the like, the invention relates to a radial flow turbine guide vane structure coupled with a non-axisymmetric end wall. According to the invention, through modifying the blade cascade, specifically, through respectively setting the inner surfaces of the front end wall and the rear end wall into non-axisymmetric concave-convex end wall structures, the flow area of each flow channel is changed, and the airflow pressure difference between the pressure surface at one side and the suction surface at the other side of each flow channel is reduced, so that the velocity distribution of the secondary flow is influenced, the formation and development of the channel vortex are delayed, the vortex strength of the channel is reduced, and the reduction of the loss of the secondary flow is finally realized.
Description
Technical Field
The invention belongs to the field of radial flow turbines in fluid machinery, and relates to a radial flow turbine guide vane structure, in particular to a high-efficiency low-aspect-ratio three-dimensional radial flow turbine guide vane structure coupled with non-axisymmetric end walls.
Background
In recent years, the radial flow turbine utilizing the pressure energy and the heat energy of the gas working medium has wide application and various structural forms, and provides electric power and power for industrial production and people's life. In order to make the equipment of unit volume output mechanical energy as much as possible under the same thermodynamic parameters, the efficiency of the radial-flow turbine needs to be improved. As one kind of rotary machinery, in order to realize energy conversion and work of working medium gas, most of radial flow turbines adopt a guide vane structure form, pressure difference is inevitably formed between a pressure surface and a suction surface of a guide vane, secondary flow in the direction from the pressure surface of the vane to the suction surface of an adjacent vane is generated in a flow channel due to the pressure difference, and a channel vortex is further formed, so that the flow angle of an outlet of the guide vane is changed while the loss of the secondary flow is caused, and the uniformity of the outlet airflow is influenced. Because the flow of the radial-flow turbine is relatively small, the aspect ratio of the radial-flow guide vane is relatively low, and the relative blade height is reduced, the influence ranges of the secondary flow and the channel vortex in the flow channel are relatively increased, and the important part of the flow loss of the guide vane is formed, so that the control of the low-aspect ratio radial-flow top clearance flow loss by adopting a proper technical means is an important way for improving the efficiency of the radial-flow turbine.
There are many methods for controlling the secondary flow loss, and a non-axisymmetric end wall structure is an important means, and the basic principle of the method is as follows: concave/convex curved surfaces are applied to the end walls of the guide vane flow channels, so that the local change of the flow area of the flow channels is realized, the distribution of the flow field pressure gradient near the pressure surface and the suction surface of the guide vane is improved, the transverse pressure of the pressure surface of the guide vane to the suction surface is effectively controlled, and the aim of inhibiting the development of secondary flow is finally fulfilled; the three-dimensional structure of the guide vane mainly comprises bending, twisting, sweeping and the like, and the method realizes effective control of secondary flow structures such as channel vortex and separation in a flow passage by improving pressure distribution of the guide vane from a vane root to a vane top direction. At present, the method is applied to axial flow turbines and gas compressors more and obtains obvious effect, but almost not seen in radial flow turbines.
Compared with an axial flow turbine, the radial flow turbine has high expansion ratio and small relative flow, the aspect ratio of the guide vane is lower than that of the axial flow turbine, the proportion of the secondary flow structure in the channel is higher, and the caused loss is more obvious; the secondary flow structure can also cause the flow field distortion of the outlet of the guide vane, so that the airflow angle of the outlet of the guide vane deviates from the design value, the nonuniformity of the flow field of the outlet is caused, and the influence on the inlet flow field of the downstream impeller is caused. Radial flow turbine vanes are therefore more desirable for secondary flow control methods than axial flow turbine vanes.
Disclosure of Invention
In order to solve the technical problems of obvious secondary flow of the end wall of the low-aspect-ratio radial flow guide vane, relatively large size of a channel vortex, poor uniformity of outlet airflow and the like in the prior art, the invention provides a radial flow turbine guide vane structure coupled with a non-axisymmetric end wall, which can effectively control the secondary flow loss of the end wall of the low-aspect-ratio radial flow turbine guide vane, reduce the size of the channel vortex and improve the uniformity of the outlet airflow, thereby improving the pneumatic efficiency and the work-doing capability of the radial flow turbine, increasing the utilization efficiency of the radial flow turbine on energy, meeting the requirement of the radial flow turbine on high-efficiency operation and promoting the application of the radial flow turbine on a high-efficiency operation system.
In order to achieve the above purpose, the technical solution of the invention is as follows:
a radial flow turbine vane structure coupled with non-axisymmetrical end walls, comprising a front end wall, a rear end wall, and a plurality of radial flow turbine vanes disposed between the front and rear end walls and uniformly arranged in a circumferential direction,
a flow channel is formed between two adjacent radial flow turbine guide vanes, one side of the flow channel is a pressure surface of one radial flow turbine guide vane, the other side of the flow channel is a suction surface of the other radial flow turbine guide vane,
the front end wall and the rear end wall are basically in disc-shaped structures, and the inner surfaces of the front end wall and the rear end wall are respectively formed into non-axisymmetric concave-convex end wall structures, so that the flow area of each flow channel is increased, and the airflow pressure difference between the pressure surface on one side and the suction surface on the other side of each flow channel is reduced.
In the radial flow turbine guide vane structure coupled with the non-axisymmetric end wall, the control principle of the end wall secondary flow loss is as follows: because the existing radial flow turbine guide vane has the operation characteristics of small flow and high expansion ratio, the characteristic enables the flow area of the radial flow turbine guide vane to be small, the relative blade height of the guide vane is low, the load is large, the secondary flow characteristic between the front end wall and the rear end wall of the guide vane is very obvious, the size of a channel vortex is relatively large, and the secondary flow loss becomes a main factor influencing the pneumatic efficiency of the guide vane. According to the invention, through modifying the blade cascade, specifically, through respectively setting the inner surfaces of the front end wall and the rear end wall into non-axisymmetric concave-convex end wall structures, the flow area of each flow channel is changed, and the airflow pressure difference between the pressure surface at one side and the suction surface at the other side of each flow channel is reduced, so that the velocity distribution of the secondary flow is influenced, the formation and development of the channel vortex are delayed, the vortex strength of the channel is reduced, and the reduction of the loss of the secondary flow is finally realized.
Preferably, the non-axisymmetric concave-convex end wall structure has a geometrical configuration curve of a rational B-spline surface, a trigonometric function, a polynomial function, a fourier series, an attenuation function, and the like.
Preferably, the non-axisymmetric concave-convex end wall structure is in the shape of a front end wall convex rear end wall concave, a front end wall concave rear end wall convex, a convex near one suction surface and a concave near the other pressure surface, a concave near one suction surface and a convex near the other pressure surface, and the like.
Preferably, the number, the spacing distance, the shape and the length of the non-axisymmetric concave-convex end wall structures are determined according to actual geometric dimensions and operation conditions.
Further, each radial flow turbine guide vane adopts a three-dimensional configuration structure.
Preferably, the three-dimensional structure is that the blade is bent from the pressure surface to the suction surface, the blade is bent from the suction surface to the pressure surface, the blade is twisted from the blade root to the blade tip by a certain angle, the blade is twisted from the blade tip to the blade root by a certain angle, the middle part of the blade is twisted by a certain angle, and the blade root and the blade tip are twisted by a certain angle.
Preferably, the bending amplitude and the torsion angle of each radial flow turbine guide vane are determined according to the geometric parameters and the operating conditions of the actual radial flow turbine.
According to another aspect of the invention, a radial flow turbine is also provided, which is characterized in that the radial flow turbine comprises the radial flow turbine guide vane structure coupled with the non-axisymmetric end wall.
Preferably, the type of the radial flow turbine is a centripetal, mixed flow, single-stage or multi-stage structure, and the number, the geometric shape, the structural size and the rotating speed of the turbine are determined according to overall thermodynamic design parameters.
Preferably, the working medium of the radial-flow turbine is air, nitrogen, oxygen, carbon dioxide, natural gas, ammonia, freon or steam.
Compared with the prior art, the radial flow turbine guide vane structure coupled with the non-axisymmetric end wall has the advantages and beneficial effects that: (1) through the improvement of the blade cascade, particularly, the inner surfaces of the front end wall and the rear end wall are respectively provided with a non-axisymmetric concave-convex end wall structure, so that the flow area of each flow channel is changed, the airflow pressure difference between the pressure surface at one side of each flow channel and the suction surface at the other side of each flow channel is reduced, the secondary flow velocity distribution is influenced, the formation and the development of channel vortexes are delayed, the channel vortex strength is reduced, and the reduction of the secondary flow loss is finally realized. (2) The geometrical configuration of the non-axisymmetrical end wall and the three-dimensional geometrical configuration size of the radial-flow turbine guide vane can be optimally designed according to the actual operating condition and condition of the radial-flow turbine, so that the radial-flow turbine guide vane can be suitable for radial-flow turbines operating under different operating conditions. (3) The non-axisymmetrical end wall structure and the three-dimensional configuration of the radial flow guide vane are integrally and optimally designed, so that the secondary flow channel vortex structure in the radial flow guide vane can be controlled to the maximum extent, the secondary flow loss is reduced to the maximum extent, the uniformity of airflow at the outlet of the guide vane can be improved, the utilization efficiency of the radial flow turbine on energy is higher, the power-applying capacity is improved, and the radial flow turbine is suitable for various radial flow turbines.
Drawings
FIG. 1 is a view of the operation of the airflow in a radial flow turbine;
FIG. 2 is a schematic view of a high efficiency, low aspect ratio, three dimensional radial flow turbine vane coupled to a non-axisymmetrical endwall;
FIG. 3 is a schematic view of a radial flow turbine vane non-axisymmetrical endwall configuration;
FIG. 4 is a schematic diagram of a three-dimensional modeling structure of a radial flow turbine guide vane;
wherein:
(a) -spline curve
(b) Curve of cosine function
(c) -upward convex curve
(d) Concave curve
(e) -linear stacking manner
(f) -L-shaped stacking manner
(g) -C-shaped stacking manner
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1, the radial flow turbine includes an impeller 10 and a radial flow turbine guide vane structure 20 disposed on the circumferential periphery of the impeller 10, the radial flow turbine guide vane structure 20 includes a front end wall 21, a rear end wall 22 and a plurality of radial flow turbine guide vanes 23 disposed between the front end wall 21 and the rear end wall 22 and uniformly arranged in the circumferential direction, the front end wall 21 and the rear end wall 22 are substantially disc-shaped structures, a flow channel is formed between two adjacent radial flow turbine guide vanes 23, one side of the flow channel is a pressure surface of one radial flow turbine guide vane, and the other side of the flow channel is a suction surface of the other radial flow turbine guide vane.
The application fields of the radial flow turbine include but are not limited to compressed air energy storage systems, vehicle engine turbochargers, medium and low temperature waste heat power generation devices, renewable energy power generation devices, chemical process expanders, rocket engine turbopumps and the like. The type of the radial flow turbine is a centripetal, mixed flow, single-stage or multi-stage structure, and the number, the geometric shape, the structural size and the rotating speed of the turbine are determined according to overall thermodynamic design parameters. The working medium gas source of the radial-flow turbine comprises atmospheric environment, engine tail gas, boiler steam, fuel gas, industrial exhaust flue gas, compressed air, solar heat collector steam, heat accumulator steam, chemical process gas and the like. The working medium gas is air, nitrogen, oxygen, carbon dioxide, natural gas, ammonia, freon, etc.
The working process of the radial flow turbine is as follows: the working medium firstly enters the radial-flow turbine guide vane structure 20, is accelerated in the flow channel between the radial-flow turbine guide vanes 23, and then enters the impeller 10 to push the impeller to rotate to do work. The flow direction changes while the air flow pushes the impeller to do work in the impeller 10.
As shown in fig. 2, the inner surfaces of the front end wall 21 and the rear end wall 22 are formed into a non-axisymmetric concave-convex end wall structure 24. So that the flow area of each flow channel is increased and the pressure difference of the air flow between the pressure surface on one side and the suction surface on the other side of each flow channel is reduced. In the radial flow turbine guide vane structure coupled with the non-axisymmetric end wall, the control principle of the end wall secondary flow loss is as follows: because the existing radial flow turbine guide vane has the operation characteristics of small flow and high expansion ratio, the characteristic enables the flow area of the radial flow turbine guide vane to be small, the relative blade height of the guide vane is low, the load is large, the secondary flow characteristic between the front end wall and the rear end wall of the guide vane is very obvious, the size of a channel vortex is relatively large, and the secondary flow loss becomes a main factor influencing the pneumatic efficiency of the guide vane. According to the invention, through modifying the blade cascade, specifically, through respectively arranging the inner surfaces of the front end wall and the rear end wall into the non-axisymmetric concave-convex end wall structures 24, the flow area of each flow channel is increased, and the airflow pressure difference between the pressure surface at one side and the suction surface at the other side of each flow channel is reduced, so that the velocity distribution of the secondary flow is influenced, the formation and development of the channel vortex are delayed, the vortex strength of the channel is reduced, and the reduction of the loss of the secondary flow is finally realized.
As shown in fig. 3, the non-axisymmetric concave-convex end wall surface may be a single convex hull, a single concave pit, a concave pit near the pressure surface of the guide vane and a convex pit near the suction surface, a convex pit near the pressure surface of the guide vane and a concave pit near the suction surface, and so on. The number, influence range, depth/height and change function curve of the non-axisymmetric end wall pits/bulges are determined according to the geometric dimension and the operating parameters of a specific radial-flow turbine. The non-axisymmetric end wall geometric structure is directly processed by a numerical control machine tool and a 3D printing technology, and has realizability. Non-axisymmetric end wall geometry curves include, but are not limited to: rational B-spline surfaces, trigonometric functions, polynomial functions, fourier series, attenuation functions, and the like. Structural shapes include, but are not limited to: front end wall projections/recesses, rear end wall projections/recesses, vane suction surface vicinity projections/recesses, vane pressure surface vicinity projections/recesses, and the like. The number, spacing distance, shape and length of the non-axisymmetric end wall structures are determined according to actual geometric dimensions and operating conditions. As shown in fig. 3, the non-axisymmetric end wall profile is described by a sine curve (b) from the pressure surface to the suction surface, and the parameters of the sine curve such as wave crest, wave trough, length and the like are determined according to the parameters of the radial-flow turbine inlet airflow speed, viscosity and the like.
As shown in fig. 4, the radial flow turbine guide vane 23 is three-dimensionally configured in a bent, twisted, swept or other form, and can be matched with a non-axisymmetric end wall, so that the size of a channel vortex can be further controlled, and the uniformity of a guide vane outlet flow field and a downstream impeller intake flow field can be improved. The bending amplitude and the torsion angle of each radial flow turbine guide vane 23 are determined according to the geometric parameters and the operation working conditions of the actual radial flow turbine. As shown in fig. 4, the three-dimensional configuration of the radial flow turbine vane 23 is described by a blade root to blade height stacking manner using a C-shaped curve (g). And the included angle between the C-shaped curve and the end wall and the highest point offset distance parameter are determined according to the working condition of the radial flow turbine.
The non-axisymmetric end wall structure and the radial-flow turbine guide vane are stacked in a three-dimensional mode, and the purpose of improving the pneumatic efficiency loss is achieved through comprehensive control of the secondary flow structure and the loss.
The object of the present invention is fully effectively achieved by the above embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, what is described in the accompanying drawings and the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications within the spirit and scope of the appended claims.
Claims (6)
1. A radial flow turbine vane structure coupled with non-axisymmetrical end walls, comprising a front end wall, a rear end wall, and a plurality of radial flow turbine vanes disposed between the front and rear end walls and uniformly arranged in a circumferential direction,
a flow channel is formed between two adjacent radial flow turbine guide vanes, one side of the flow channel is a pressure surface of one radial flow turbine guide vane, the other side of the flow channel is a suction surface of the other radial flow turbine guide vane,
the front end wall and the rear end wall are of disc-shaped structures, the inner surfaces of the front end wall and the rear end wall are respectively formed into non-axisymmetric concave-convex end wall structures, and the geometric configuration curve of each non-axisymmetric concave-convex end wall structure is a rational B-spline surface, a trigonometric function, a polynomial function, a Fourier series or an attenuation function; the non-axisymmetric concave-convex end wall structure is structurally shaped like a convex front end wall and a concave rear end wall, a concave front end wall and a convex rear end wall, a convex part near a suction surface at one side and a concave part near a pressure surface at the other side, or a concave part near a suction surface at one side and a convex part near a pressure surface at the other side; the non-axisymmetric concave-convex end wall structure enables the flow area of each flow channel to be changed and the airflow pressure difference between the pressure surface at one side and the suction surface at the other side of each flow channel to be reduced;
each radial flow turbine guide vane adopts a three-dimensional structure, and the three-dimensional structure is that the blade is bent from the pressure surface to the suction surface, the blade is bent from the suction surface to the pressure surface, the blade is twisted from the blade root to the blade top by a certain angle, the blade is twisted from the blade top to the blade root by a certain angle, the middle part of the blade is twisted by a certain angle, or the blade root and the blade top are twisted by a certain angle.
2. A radial flow turbine vane structure coupling non-axisymmetric endwalls of claim 1, wherein said non-axisymmetric concave-convex endwall structure, number, spacing distance, shape, length thereof are determined in accordance with actual geometry and operating conditions.
3. A radial flow turbine vane structure coupled with non-axisymmetrical end walls according to claim 1, wherein the bending amplitude and torsion angle of each radial flow turbine vane are determined according to actual radial flow turbine geometric parameters and operation conditions.
4. A radial flow turbine comprising a radial flow turbine vane structure coupled to non-axisymmetric endwalls of any of the above claims 1-3.
5. A radial flow turbine according to claim 4, wherein the radial flow turbine is of the radial, mixed flow, single or multi-stage configuration, the number and geometry of the turbines and the size and speed of the structure being determined by the overall thermodynamic design parameters.
6. A radial flow turbine according to claim 5, wherein the working medium of the radial flow turbine is air, nitrogen, oxygen, carbon dioxide, natural gas, ammonia, freon or steam.
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| CN112177679B (en) * | 2020-09-30 | 2022-12-27 | 中国科学院工程热物理研究所 | Coupling control structure and method for secondary flow in low-pressure turbine end area |
| CN112560195A (en) * | 2020-12-07 | 2021-03-26 | 中国科学院工程热物理研究所 | Modeling method for non-axisymmetric end wall of axial-flow impeller |
| CN112377269B (en) * | 2021-01-11 | 2021-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Anti-distortion stator design method suitable for contra-rotating lift propulsion device |
| CN116379000B (en) * | 2023-03-17 | 2024-04-09 | 中交疏浚技术装备国家工程研究中心有限公司 | Non-axisymmetric end wall modeling of dredge mud pump impeller |
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| US8105037B2 (en) * | 2009-04-06 | 2012-01-31 | United Technologies Corporation | Endwall with leading-edge hump |
| CN108915789B (en) * | 2018-09-13 | 2023-08-04 | 中国科学院工程热物理研究所 | Passive-active coupling control structure for clearance flow loss of top of radial turbine blade |
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