CN105422186B - Axial-flow turbine with leaflet chip architecture - Google Patents
Axial-flow turbine with leaflet chip architecture Download PDFInfo
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- CN105422186B CN105422186B CN201510956218.9A CN201510956218A CN105422186B CN 105422186 B CN105422186 B CN 105422186B CN 201510956218 A CN201510956218 A CN 201510956218A CN 105422186 B CN105422186 B CN 105422186B
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- primary blades
- vanelets
- joint face
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- leading edge
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- 230000004323 axial length Effects 0.000 abstract description 3
- 239000012530 fluid Substances 0.000 description 6
- 238000000926 separation method Methods 0.000 description 6
- 230000008676 import Effects 0.000 description 5
- 239000000126 substance Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
Classifications
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
-
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a kind of axial-flow turbine with leaflet chip architecture, including wheel hub, multiple primary blades and multiple vanelets.Wheel hub is provided with front end face and circumferential surface;Multiple primary blades are uniformly arranged on the circumferential surface of wheel hub, and with pressure face, suction surface and primary blades joint face, primary blades joint face is provided with the first leading edge;Vanelets arrangement alternate with primary blades, with vanelets joint face, vanelets joint face is provided with the second leading edge.The height of vanelets radial direction is h, and the height of primary blades radial direction is H, and h/H is 0.05~0.3;The chord length of vanelets joint face axial direction is L1, the chord length of primary blades joint face axial direction is L2, L1/L2For 0.2~0.6;The axial length of first leading edge of second leading edge of vanelets joint face away from primary blades joint face is m, and m/L is 0~0.4;Circumferential angle between first leading edge of two neighboring primary blades joint face is θ1, the first leading edge and its suction surface of primary blades joint face to vanelets joint face the second leading edge between circumferential angle be θ2, θ2/θ1For 0.3~0.8.
Description
Technical field
The present invention relates to turbomachinery field, more particularly to a kind of axial-flow turbine with leaflet chip architecture.
Background technology
Turbine is a kind of blade mechanism that fluid working substance energy is converted into mechanical energy output, and fluid working substance is in turbine
Expand and promote turbine to rotate, externally export mechanical work.In axial-flow turbine, fluid working substance is flowed into the angle of intimate axial direction
Turbine, axially outflow.Axial-flow turbine is applied to gas turbine, Turbine piston combined engine and turbine composite internal combustion engine
Deng field.
Because the linear velocity of axial-flow turbine rotor blade changes with radius change, cause the relative inlet air flow of rotor
Angle needs to change with the high change of leaf along the high direction change of leaf, therefore the blade design of rotor.At rotator tip, import phase
Smaller to flow angle, blade import and export deflection angle is smaller;And in rotor blade root, because import relative wind angle is larger, because
The deflection angle of this blade import and export is larger.Because fluid is in root of blade experience wide-angle turnover motion, it is easily caused fluid and exists
Flow separation occurs at blade suction surface, larger flow losses are result in.And this flow losses are flowed import is uneven
Under the conditions of can further expand, (or hiigh pressure stage is radial-flow type/combined flow turbine, and low-pressure stage is in multiatage axial flow turbine
Axial-flow turbine), the axial flow turbine inlet air flow of low-pressure stage being unevenly distributed in radial directions, due to low-pressure stage axle
The radius for flowing the radius ratio hiigh pressure stage turbine of turbine is big, and the intermediate conductor for connecting turbine of just arbitrarily downgrading is " S " type, and which results in low
Arbitrarily downgrade turbine inlet air-flow distribution characteristics for blade root nearby liquid mass flow it is larger, and blade tip nearby liquid mass flow compared with
It is small.The uneven distribution of fluid in radial directions causes the load at rotor blade root to become big, therefore the flowing point near blade root
It is easier to occur from phenomenon, separation yardstick is bigger, causes the decline of turbine performance.
The content of the invention
In view of problem present in background technology, it is an object of the invention to provide a kind of axle stream with leaflet chip architecture
Formula turbine, it can reduce the flow losses of turbine, improve the isentropic efficiency of turbine.
To achieve these goals, the invention provides a kind of axial-flow turbine with leaflet chip architecture, it includes wheel
Hub, multiple primary blades and multiple vanelets.
Wheel hub is provided with front end face and circumferential surface.
The multiple primary blades are evenly provided on the circumferential surface of wheel hub, and each primary blades have:Pressure face, with entrance
Airflow direction is relative;Suction surface, it is opposite with pressure face;And primary blades joint face, it is the circumferential surface connection of primary blades and wheel hub
Section, provided with close to wheel hub front end face the first leading edge.
The multiple vanelets are evenly provided on the circumferential surface of wheel hub and arrangement alternate with the multiple primary blades, respectively
Vanelets have:Vanelets joint face, is the section of the circumferential surface connection of vanelets and wheel hub, provided with the front end face close to wheel hub
The second leading edge.
The height of vanelets radially is h, and the height of primary blades radially is H, and h/H scope is 0.05~0.3.
The chord length of vanelets joint face vertically is L1, the chord length of primary blades joint face vertically is L2, L1/L2Scope
For 0.2~0.6.
Second leading edge of vanelets joint face is m, m/L model apart from the axial length of the first leading edge of primary blades joint face
Enclose for 0~0.4.
Circumferential angle between first leading edge of two neighboring primary blades joint face is θ1, primary blades joint face first before
Edge and its suction surface to vanelets joint face the second leading edge between circumferential angle be θ2, θ2/θ1Scope for 0.3~
0.8。
Beneficial effects of the present invention are as follows:
In the axial-flow turbine with leaflet chip architecture according to the present invention, correspondence is added between adjacent primary blades
Vanelets, and depending on each parameter of vanelets is according to primary blades;Due to the inhomogeneities of the inlet air flow of axial-flow turbine, hold
It is easily caused near primary blades joint face and separation flowing occurs and increase the flow losses of turbine, and can be subtracted by increasing vanelets
The load of small primary blades joint face, transverse-pressure gradient reduces, so as to suppress the transverse direction of Secondary Flow in the passage of primary blades formation
Motion, reduces the coverage of separation stream, so as to reduce the flow losses of primary blades joint face, improves the isentropic efficiency of turbine.
Brief description of the drawings
Fig. 1 is the stereogram of the axial-flow turbine with leaflet chip architecture according to the present invention;
Fig. 2 is the front view of the axial-flow turbine with leaflet chip architecture according to the present invention;
Fig. 3 is the single primary blades and the circumference of vanelets of the axial-flow turbine with leaflet chip architecture according to the present invention
Schematic diagram;And
Fig. 4 be according to the present invention the axial-flow turbine with leaflet chip architecture primary blades primary blades joint face with it is small
The schematic diagram of the vanelets joint face of blade.
Wherein, description of reference numerals is as follows:
The primary blades joint face of 1 wheel hub 23
The leading edge of 11 front end face 231 first
The vanelets of 12 circumferential surface 3
The vanelets joint face of 2 primary blades 31
The leading edge of 21 pressure face 311 second
22 suction surfaces
Embodiment
With reference to the accompanying drawings come describe in detail the present invention the axial-flow turbine with leaflet chip architecture.
Referring to figs. 1 to Fig. 4, wheel hub 1, multiple main lobves are included according to the axial-flow turbine with leaflet chip architecture of the present invention
Piece 2 and multiple vanelets 3.
Wheel hub 1 is provided with front end face 11 and circumferential surface 12.
The multiple primary blades 2 are evenly provided on the circumferential surface 12 of wheel hub 1, and each primary blades 2 have:Pressure face 21,
It is relative with the airflow direction of entrance;Suction surface 22, it is opposite with pressure face 21;And primary blades joint face 23, it is primary blades 2 and wheel
The section that the circumferential surface 12 of hub 1 is connected, the first leading edge 231 provided with the front end face 11 close to wheel hub 1.
The multiple vanelets 3 be evenly provided on the circumferential surface 12 of wheel hub 1 and with the alternate cloth of the multiple primary blades 2
Put, each vanelets 3 have:Vanelets joint face 31, is the section that vanelets 3 are connected with the circumferential surface 12 of wheel hub 1, provided with close
Second leading edge 311 of the front end face 11 of wheel hub 1.
The height of vanelets 3 radially is h, and the height of primary blades 2 radially is H, and h/H scope is 0.05~0.3.
The chord length of vanelets joint face 31 vertically is L1, the chord length of primary blades joint face 23 vertically is L2, L1/L2's
Scope is 0.2~0.6.
Axial length of second leading edge 311 of vanelets joint face 31 apart from the first leading edge 231 of primary blades joint face 23
For m, m/L scope is 0~0.4.
Circumferential angle between first leading edge 231 of two neighboring primary blades joint face 23 is θ1, primary blades joint face 23
The first leading edge 231 and its suction surface 22 to vanelets joint face 31 the second leading edge 311 between circumferential angle be θ2,
θ2/θ1Scope be 0.3~0.8.
In the axial-flow turbine with leaflet chip architecture according to the present invention, the addition pair between adjacent primary blades 2
The vanelets answered, and depending on each parameter of vanelets 3 is according to primary blades 2;Due to the inlet air flow (not shown) of axial-flow turbine
Inhomogeneities, be easily caused primary blades joint face 23 and separation flowing nearby occur and increase the flow losses of turbine, and pass through
Increase vanelets 3 can reduce the load of primary blades joint face 23, and transverse-pressure gradient reduces, formed so as to suppress primary blades 2
Passage in Secondary Flow transverse movement, reduce separation stream coverage so that reduce primary blades joint face 23 flowing damage
Lose, improve the isentropic efficiency of turbine.
In the axial-flow turbine with leaflet chip architecture according to the present invention, in one embodiment, h/H scope can be
0.15~0.25.
In the axial-flow turbine with leaflet chip architecture according to the present invention, in one embodiment, L1/L2Scope can
For 0.45~0.55.
In the axial-flow turbine with leaflet chip architecture according to the present invention, in one embodiment, m/L2Scope can
For 0.1~0.2.
In the axial-flow turbine with leaflet chip architecture according to the present invention, in one embodiment, θ2/θ1Scope can
For 0.5~0.6.
In the axial-flow turbine with leaflet chip architecture according to the present invention, in one embodiment, h/H can be 0.2.
In the axial-flow turbine with leaflet chip architecture according to the present invention, in one embodiment, L1/L2Can be 0.5.
In the axial-flow turbine with leaflet chip architecture according to the present invention, in one embodiment, m/L2Can be 0.1.
In the axial-flow turbine with leaflet chip architecture according to the present invention, in one embodiment, θ2/θ1Can be 0.55.
Claims (8)
1. a kind of axial-flow turbine with leaflet chip architecture, including:
Wheel hub (1), provided with front end face (11) and circumferential surface (12);
Multiple primary blades (2), are evenly provided on the circumferential surface of wheel hub (1) (12), and each primary blades (2) have:
Pressure face (21) is relative with the airflow direction of entrance;
Suction surface (22), it is opposite with pressure face (21);And
Primary blades joint face (23), is the section that primary blades (2) are connected with the circumferential surface (12) of wheel hub (1), provided with close to wheel hub
(1) the first leading edge (231) of front end face (11);
Multiple vanelets (3), are evenly provided on the circumferential surface of wheel hub (1) (12) and alternate with the multiple primary blades (2)
Arrangement, each vanelets (3) have:
Vanelets joint face (31), is the section that vanelets (3) are connected with the circumferential surface (12) of wheel hub (1), provided with close to wheel hub
(1) the second leading edge (311) of front end face (11);
Characterized in that,
The height of vanelets (3) radially is h, and the height of primary blades (2) radially is H, and h/H scope is 0.05~0.3;
The chord length of vanelets joint face (31) vertically is L1, the chord length of primary blades joint face (23) vertically is L2, L1/L2Model
Enclose for 0.2~0.6;
The second leading edge (311) of vanelets joint face (31) is apart from the axial direction of the first leading edge (231) of primary blades joint face (23)
Length is m, m/L2Scope be 0.1~0.2;
Circumferential angle between the first leading edge (231) of two neighboring primary blades joint face (23) is θ1, primary blades joint face (23)
The first leading edge (231) and its suction surface (22) to vanelets joint face (31) the second leading edge (311) between circumference
Angle is θ2, θ2/θ1Scope be 0.3~0.8;
Vanelets (3) are completely overlapped in primary blades (2) in the axial direction.
2. the axial-flow turbine according to claim 1 with leaflet chip architecture, it is characterised in that h/H scope is
0.15~0.25.
3. the axial-flow turbine according to claim 1 with leaflet chip architecture, it is characterised in that L1/L2Scope be
0.45~0.55.
4. the axial-flow turbine according to claim 1 with leaflet chip architecture, it is characterised in that θ2/θ1Scope be
0.5~0.6.
5. the axial-flow turbine according to claim 1 with leaflet chip architecture, it is characterised in that h/H is 0.2.
6. the axial-flow turbine according to claim 1 with leaflet chip architecture, it is characterised in that L1/L2For 0.5.
7. the axial-flow turbine according to claim 1 with leaflet chip architecture, it is characterised in that m/L2For 0.1.
8. the axial-flow turbine according to claim 1 with leaflet chip architecture, it is characterised in that θ2/θ1For 0.55.
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CN201510956218.9A CN105422186B (en) | 2015-12-18 | 2015-12-18 | Axial-flow turbine with leaflet chip architecture |
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CN201510956218.9A CN105422186B (en) | 2015-12-18 | 2015-12-18 | Axial-flow turbine with leaflet chip architecture |
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CN105422186A CN105422186A (en) | 2016-03-23 |
CN105422186B true CN105422186B (en) | 2017-10-24 |
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Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
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CN105864105A (en) * | 2016-04-25 | 2016-08-17 | 西北工业大学 | Axial flow compressor stator with in-vitro small blades in hub corner area |
EP3608505B1 (en) * | 2018-08-08 | 2021-06-23 | General Electric Company | Turbine incorporating endwall fences |
CN113653672B (en) * | 2021-08-31 | 2023-11-10 | 佛山市南海九洲普惠风机有限公司 | Axial flow impeller with splitter blades |
CN115977996A (en) * | 2023-03-17 | 2023-04-18 | 潍柴动力股份有限公司 | Impeller of air compressor, air compressor and turbocharger |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4512718A (en) * | 1982-10-14 | 1985-04-23 | United Technologies Corporation | Tandem fan stage for gas turbine engines |
CN2671126Y (en) * | 2003-10-31 | 2005-01-12 | 杨圣安 | Radiative blades |
EP2746534A1 (en) * | 2012-12-19 | 2014-06-25 | MTU Aero Engines GmbH | Stator and/or rotor stage of a turbomachine and corresponding gas turbine |
DE102014203607A1 (en) * | 2014-02-27 | 2015-08-27 | Rolls-Royce Deutschland Ltd & Co Kg | Blade row group |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20070154314A1 (en) * | 2005-12-29 | 2007-07-05 | Minebea Co., Ltd. | Reduction of tonal noise in cooling fans using splitter blades |
EP2799721B8 (en) * | 2013-05-03 | 2016-12-07 | Safran Aero Booster S.A. | Axial turbomachine stator guide with auxiliary vanes on the vane feet |
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- 2015-12-18 CN CN201510956218.9A patent/CN105422186B/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4512718A (en) * | 1982-10-14 | 1985-04-23 | United Technologies Corporation | Tandem fan stage for gas turbine engines |
CN2671126Y (en) * | 2003-10-31 | 2005-01-12 | 杨圣安 | Radiative blades |
EP2746534A1 (en) * | 2012-12-19 | 2014-06-25 | MTU Aero Engines GmbH | Stator and/or rotor stage of a turbomachine and corresponding gas turbine |
DE102014203607A1 (en) * | 2014-02-27 | 2015-08-27 | Rolls-Royce Deutschland Ltd & Co Kg | Blade row group |
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