CN111997694B - Turbine wheel with improved shroud structure - Google Patents
Turbine wheel with improved shroud structure Download PDFInfo
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- CN111997694B CN111997694B CN202010697509.1A CN202010697509A CN111997694B CN 111997694 B CN111997694 B CN 111997694B CN 202010697509 A CN202010697509 A CN 202010697509A CN 111997694 B CN111997694 B CN 111997694B
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- shroud
- blades
- impeller
- turbine
- turbine wheel
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- 230000004323 axial length Effects 0.000 claims description 10
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 5
- 238000012545 processing Methods 0.000 abstract description 4
- 238000013461 design Methods 0.000 description 6
- 238000012423 maintenance Methods 0.000 description 6
- 230000000052 comparative effect Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of turbines, and particularly relates to a turbine impeller with an improved shroud structure. The invention comprises a wheel disc, a plurality of blades and an annular shroud, wherein the blades are milled and distributed along the circumferential direction of the wheel disc, and air flow channels are formed between adjacent blades; the shroud is disposed over the inlet ends of the plurality of blades. The shroud ring is integrally annular and partially covered on the blades, so that the energy loss is less when airflow flows out, the efficiency of the turbine impeller is higher, the integrally milled and formed impeller is an integral seamless part, no external connection fastener is used, compared with the traditional turbine connected by more accessories, the airflow flowing-out loss is greatly reduced, the processing and assembling risks are reduced, and the efficiency of the turbine impeller and the reliability of equipment are further improved.
Description
Technical Field
The invention belongs to the field of turbines, and particularly relates to a turbine impeller with an improved shroud structure.
Background
Turbines are machines, also known as turbines, that convert energy contained in a fluid medium into mechanical work. The different turbines can be classified into water turbines, steam turbines, gas turbine and air turbine according to the fluid medium used. The working principle is that the fluid converts the energy into kinetic energy when flowing through the spray pipe, and the kinetic energy impacts the blades when flowing through the rotor to drive the rotor to rotate, so that the turbine shaft is driven to rotate. The turbine shaft drives other machines directly or through a transmission mechanism to output mechanical work. Turbines are the main equipment of modern hydropower stations and thermal power plants, and are also used in power plants of metallurgical industry, chemical industry, ships and jet planes.
The impeller is a core component of the turbine, plays an important role in external work, and has good and bad performance, and the service cycle is directly related to the use and maintenance of the turbine. In the existing structure, the shroud bands at the top of the steam turbine are of a sectional structure, the impeller blades are all covered, and then the shroud bands are connected and fixed with each blade by rivet pins; each blade is manufactured independently and is embedded into the wheel disc through a mortise, and then fixed by a pin; the number of the turbine blades is large, and tens or hundreds of turbine blades exist in the traditional structure:
1) The width of the shroud of the existing impeller is the same as the axial length of the blades along the impeller, and the blades of the impeller are fully covered, so that the track of the airflow flowing out of the impeller can only be a straight line, and the paths of the airflow in the turbine device flowing out of the impeller are all nonlinear, thereby easily causing energy loss of the airflow;
2) The shroud ring is riveted with the blades by adopting a sectional structure, so that a certain gap is necessarily formed between the blades and the shroud ring, secondary flow loss can be increased by the gap, and the acting performance of the impeller is reduced, thereby reducing the efficiency of the impeller;
2) The structure is complex, the processing amount is large, the manufacturing cost is high, the number of assembled parts is large, the matching requirement is high, the operation risk is relatively high, the failure points are numerous and dispersed, and the reliability and maintainability are relatively poor.
Disclosure of Invention
To overcome the above-described deficiencies in the prior art, the present invention provides a turbine wheel with an improved shroud configuration. The invention has the advantage of improving the efficiency of the turbine wheel.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
a turbine impeller with improved shroud structure comprises a wheel disc, a plurality of blades and an annular shroud, wherein the blades are milled and distributed along the circumferential direction of the wheel disc, and air flow channels are formed between adjacent blades; the shroud is disposed over the inlet ends of the plurality of blades.
Preferably, the top end of the shroud and the top end of the blade are located on the same circular arc surface.
Preferably, the wheel disc, the plurality of blades and the shroud are integrally milled by adopting titanium alloy.
Preferably, the width L of the shroud in the direction of gas flow is 50% -80% of the axial length of the blades along the impeller.
Preferably, the width L of the shroud in the direction of gas flow is 60% of the axial length of the blades along the impeller.
Preferably, the inner and outer edges of the shroud outlet are provided with a chamfer a and a chamfer b, respectively.
Preferably, the radii of chamfer a and chamfer b are both 2mm.
Preferably, the cross sections of the blades are crescent.
The invention has the advantages that:
(1) The shroud ring is integrally annular and partially covered on the blades, so that the energy loss is less when airflow flows out, the efficiency of the turbine impeller is higher, the integrally milled and formed impeller is an integral seamless part, no external connection fastener is used, compared with the traditional turbine connected by more accessories, the airflow flowing-out loss is greatly reduced, the processing and assembling risks are reduced, and the efficiency of the turbine impeller and the reliability of equipment are further improved.
(2) The wheel disc, the blades and the shroud ring which are made of titanium alloy materials are integrally formed through milling, so that the structure is simple, and the processing is simple and convenient; the titanium alloy has high strength and good corrosion resistance, can effectively reduce the influence of water erosion, improve the integral rigidity of the impeller, bear impact load and deformation resistance, and reduce the vibration amplitude of the blades and the shroud; the assembly is not needed for multiple times, so that the assembly difficulty and the workload are reduced; meanwhile, the turbine impeller integrally milled changes the design and assembly of the traditional turbine impeller, and compared with the traditional steam turbine impeller, the turbine impeller has high reliability, can effectively prolong the maintenance period, improve the utilization rate of equipment and reduce the manual maintenance cost of users; in the use process, if the blade or the shroud is corroded and can not meet the use requirement, the turbine impeller integrally milled integrally can be detached from the equipment, the corroded part is directly and locally repaired by using a 3D repair technology after being treated, so that the impeller is restored to the impeller state before corrosion and is continuously used, and the remanufacturing cycle of use, maintenance and recycle is realized.
(3) The shroud is positioned at the inlet end of the blade tip of the blade, the width of the shroud does not cover the axial length of the whole blade along the impeller, the inner edge and the outer edge of the outlet of the shroud are designed to be round angles, the top end of the shroud and the top end of the blade are positioned at the same round arc surface, through CFD numerical simulation analysis, when the width of the shroud is 60% of the axial length of the blade along the impeller, the efficiency of the impeller is highest, and compared with the traditional design that the existing shroud covers the whole blade tip of the impeller, the efficiency of the turbine impeller is improved by about 2.7%, and the performance is obvious.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is an enlarged partial schematic view of fig. 1.
Fig. 3 is a schematic diagram of the front structure of the present invention.
Fig. 4 is an enlarged schematic side view of the present invention.
FIG. 5 is a schematic view of a partial structure of the invention A-A.
Fig. 6 is a schematic view of the partial enlarged structure of fig. 5.
FIG. 7 is a schematic diagram of the structure of the B-B according to the present invention.
FIG. 8 is a schematic representation of simulated flow lines for a turbine wheel CFD at 60% shroud width in accordance with the present invention.
FIG. 9 is a schematic representation of simulated flow lines for a turbine wheel CFD of conventional design with shroud covering the entire tip of the blade.
Fig. 10 is a schematic view of the assembled structure of the present invention.
FIG. 11 is an enlarged view of the vane and nozzle assembly of FIG. 10.
The meaning of the reference symbols in the figures is as follows:
1-wheel disc, 2-blade, 3-shroud, 4-turbine expander, 41-main shaft and 42-nozzle.
Detailed Description
1-7, a turbine wheel with an improved shroud structure comprises a wheel disc 1, a plurality of blades 2 and an annular shroud 3, wherein the blades 2 are milled and distributed along the circumferential direction of the wheel disc 1, and air flow channels are formed between the adjacent blades 2; the shroud 3 is disposed over the inlet ends of the plurality of vanes 2. The top end of the shroud ring 3 and the top end of the blade 2 are positioned on the same arc surface. The blades 2 are crescent. The wheel disc 1, the blades 2 and the shroud 3 are integrally milled by adopting titanium alloy, so that the design and assembly of the traditional turbine impeller are changed, and compared with the traditional steam turbine impeller, the reliability is high, the maintenance period can be effectively prolonged, the utilization rate of equipment is improved, and the manual maintenance cost of a user is reduced. The outer diameter of the shroud 3 is equal to the diameter of the blade tip of the impeller outlet, and the side of the shroud 3 away from the airflow channel outlet is positioned on the same plane with the inlet end face of the blade 2.
Example 1
The turbine wheel models under different shroud conditions were produced, and the performance calculation results are shown in Table 1 below (the width L1 of the shroud 3 in the gas flow direction is the width L of the shroud 3 in the gas flow direction) 1 The method comprises the steps of carrying out a first treatment on the surface of the The chord length of the blade 2 is the axial length of the blade 2 along the impeller):
TABLE 1
As can be seen from table 1:
1) Comparison of models 1, 2, 6 and comparative example 1 shows that the shroud width has a significant effect on the efficiency of the turbine wheel, and that the efficiency of the turbine wheel is highest when the shroud width is 60% of the axial length of the blades along the wheel; and compared to comparative example 1 (conventional design where the shroud covers the entire impeller tip), the turbine wheel efficiency of the present invention is improved by 2.7% over that of comparative example 1 when the shroud width is 60% of the axial length of the blades along the wheel;
2) Comparing models 2, 3, 4 and 5, it was found that the turbine wheel efficiency was highest and polytropic efficiency was 97.93% when the inner and outer edges of the shroud outlet were all rounded.
FIG. 8 is a schematic view of a CFD simulated streamline of the turbine wheel with the straight flow of the air flow under the condition of 60% shroud width, and FIG. 9 is a schematic view of a CFD simulated streamline of the turbine wheel with the straight flow of the air flow of the turbine wheel with the conventional design of the conventional shroud covering the whole blade tip, as can be seen from FIG. 8, the air flow at the outlet of the turbine wheel with the straight flow of the air flow under the condition of 60% shroud 3 width forms two eddies, namely the eddies at the top of the shroud 3 and the eddies at the outlet of the blade tip, and the area is relatively small, which indicates that the internal low energy group is less, that is, the energy loss is less when the air flow flows out, and the efficiency of the turbine wheel is higher, more particularly, the internal and external edges of the outlet of the shroud 3 are respectively provided with chamfer angle a and chamfer angle b (the best when the radius is 2 mm), that is to enlarge the outflow range of the air flow, so that the air flow flows more easily, and the efficiency of the turbine wheel is higher; in the conventional turbine impeller in the state of straight flow of the air flow under the condition of 100% of the shroud width in fig. 9, the whole outer ring of the outlet forms a large vortex, which indicates that the internal low-energy groups are more, and the energy loss is larger when the air flow flows out, i.e. the conventional turbine impeller is unfavorable for the air flow, and the flow loss is obviously increased, so that the efficiency of the turbine impeller is lower.
As shown in fig. 10-11, the integrated turbine impeller manufactured by the invention is applied to the turbine expander 4, namely, the wheel disc 1 of the turbine impeller is installed on the main shaft 41 of the turbine expander 4, when the integrated turbine impeller works, air flow axially enters the nozzle 42, turns and accelerates in the nozzle 42, after exiting the nozzle 42, the high-speed air flow impacts on the blades 2 of the turbine impeller to push the impeller to rotate at a high speed and output mechanical work outwards, and the air flow flows out of an air flow channel between adjacent blades 2 and enters the casing of the turbine expander 4, and finally is discharged through the outlet of the casing of the expander. The outlet angle alpha of the nozzle is designed to be 15 degrees, so that the air flow just enters the blade channel along the tangential direction of the inlet of the impeller blade, and the flow loss is reduced.
The above embodiments are merely preferred embodiments of the present invention and are not intended to limit the present invention, and any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of the present invention.
Claims (7)
1. A turbine wheel with improved shroud structure, characterized by: the novel air flow type air flow control device comprises a wheel disc (1), a plurality of blades (2) and an annular shroud ring (3), wherein the blades (2) are milled and distributed along the circumferential direction of the wheel disc (1), and air flow channels are formed between the adjacent blades (2); the shroud ring (3) is arranged on the inlet ends of the blades (2); the top end of the shroud ring (3) and the top end of the blade (2) are positioned on the same arc surface, and one side of the shroud ring (3) away from the outlet of the airflow channel and the inlet end face of the blade (2) are positioned on the same plane.
2. A turbine wheel with improved shroud structure as in claim 1, wherein: the wheel disc (1), the blades (2) and the shroud (3) are integrally milled by adopting titanium alloy.
3. A turbine wheel with improved shroud structure as in claim 1, wherein: the width L of the shroud (3) in the direction of gas flow 1 50% -80% of the axial length of the blade (2) along the impeller.
4. A turbine wheel with improved shroud structure according to claim 3, wherein: the width L of the shroud (3) in the direction of gas flow 1 Is 60% of the axial length of the blade (2) along the impeller.
5. A turbine wheel with improved shroud structure as in claim 1, wherein: the inner edge and the outer edge of the outlet of the shroud ring (3) are respectively provided with a chamfer angle a and a chamfer angle b.
6. A turbine wheel with improved shroud structure as in claim 5, wherein: the radii of the chamfer angle a and the chamfer angle b are 2mm.
7. A turbine wheel with improved shroud structure as in claim 1, wherein: the cross sections of the blades (2) are crescent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010697509.1A CN111997694B (en) | 2020-07-20 | 2020-07-20 | Turbine wheel with improved shroud structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010697509.1A CN111997694B (en) | 2020-07-20 | 2020-07-20 | Turbine wheel with improved shroud structure |
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| Publication Number | Publication Date |
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| CN111997694A CN111997694A (en) | 2020-11-27 |
| CN111997694B true CN111997694B (en) | 2023-12-08 |
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| Application Number | Title | Priority Date | Filing Date |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3556675A (en) * | 1969-01-29 | 1971-01-19 | Gen Electric | Turbomachinery rotor with integral shroud |
| DE10336863A1 (en) * | 2002-09-17 | 2004-03-25 | Alstom (Switzerland) Ltd. | Thermal turbo-machine e.g. gas turbine, has at least two adjacent turbine vanes, and continuous cover band that extends in rear part of vane to smallest cross-section region of maximum plus/minus 3 per cent of chord length |
| WO2010137576A1 (en) * | 2009-05-25 | 2010-12-02 | 株式会社Ihi | Impeller wheel and turbocharger |
| CN104763477A (en) * | 2015-04-13 | 2015-07-08 | 大连理工大学 | Partial shroud structure of tip of moving blade of turbo machine |
| CN204851335U (en) * | 2015-07-03 | 2015-12-09 | 上海尚实能源科技有限公司 | Integration impeller |
| CN106256993A (en) * | 2016-08-09 | 2016-12-28 | 杭州汽轮机股份有限公司 | A kind of final stage moving blade of feed pump industrial steam turbine |
| CN109890558A (en) * | 2016-10-27 | 2019-06-14 | 曼恩能源方案有限公司 | Method for producing turbine wheel |
-
2020
- 2020-07-20 CN CN202010697509.1A patent/CN111997694B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3556675A (en) * | 1969-01-29 | 1971-01-19 | Gen Electric | Turbomachinery rotor with integral shroud |
| DE10336863A1 (en) * | 2002-09-17 | 2004-03-25 | Alstom (Switzerland) Ltd. | Thermal turbo-machine e.g. gas turbine, has at least two adjacent turbine vanes, and continuous cover band that extends in rear part of vane to smallest cross-section region of maximum plus/minus 3 per cent of chord length |
| WO2010137576A1 (en) * | 2009-05-25 | 2010-12-02 | 株式会社Ihi | Impeller wheel and turbocharger |
| CN104763477A (en) * | 2015-04-13 | 2015-07-08 | 大连理工大学 | Partial shroud structure of tip of moving blade of turbo machine |
| CN204851335U (en) * | 2015-07-03 | 2015-12-09 | 上海尚实能源科技有限公司 | Integration impeller |
| CN106256993A (en) * | 2016-08-09 | 2016-12-28 | 杭州汽轮机股份有限公司 | A kind of final stage moving blade of feed pump industrial steam turbine |
| CN109890558A (en) * | 2016-10-27 | 2019-06-14 | 曼恩能源方案有限公司 | Method for producing turbine wheel |
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| Publication number | Publication date |
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| CN111997694A (en) | 2020-11-27 |
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Inventor after: Chen Qiming Inventor after: Chang Chao Inventor after: Wang Xiao Inventor after: Wang Bi Inventor after: Hu Sibing Inventor after: Yu Yueping Inventor after: Zhu Xiaonong Inventor before: Rao Jie Inventor before: Chen Qiming Inventor before: Wang Xiao Inventor before: Hu Sibing Inventor before: Wang Bi Inventor before: Chang Chao Inventor before: Yu Yueping Inventor before: Zhu Xiaonong |
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