CN108798788A - A kind of big meridian expands aerodynamic arrangement's method of the orthogonal turbine of wide string and raising turbine performance - Google Patents
A kind of big meridian expands aerodynamic arrangement's method of the orthogonal turbine of wide string and raising turbine performance Download PDFInfo
- Publication number
- CN108798788A CN108798788A CN201810532450.3A CN201810532450A CN108798788A CN 108798788 A CN108798788 A CN 108798788A CN 201810532450 A CN201810532450 A CN 201810532450A CN 108798788 A CN108798788 A CN 108798788A
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- China
- Prior art keywords
- stator blade
- turbine
- wheel hub
- movable vane
- orthogonal
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
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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
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
-
- 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
Abstract
The present invention provides a kind of orthogonal turbine of the wide string of big meridian expansion and improves aerodynamic arrangement's method of turbine performance, including casing, stator blade wheel hub, movable vane wheel hub, changeover portion and power turbine, movable vane wheel hub is arranged by stator blade wheel hub, between casing and stator blade wheel hub and stator blade is along the circumferential direction uniformly installed, between casing and movable vane wheel hub and movable vane piece is along the circumferential direction uniformly installed, stator blade, movable vane piece, stator blade wheel hub, movable vane wheel hub, machine lock constitutes stator blade turbine, changeover portion and power turbine are successively set on the downstream of stator blade turbine, the stator blade is that stator blade itself and stator blade hub end wall are orthogonal the orthogonal molded breadth string blade of arrangement, the center of gravity product superimposing thread of stator blade and the angle in radial coordinate direction are between 5 °~15 °.The present invention has delayed air-flow in the diffusion degree of big meridian expanding channel petiolarea, and makes blade orthogonal with end wall, so that air-flow is flowed approximately along blade profile direction, improves big meridian expansion turbine petiolarea flowing.
Description
Technical field
The present invention relates to a kind of turbine of gas turbine/aero-engine more particularly to a kind of big wide strings of meridian expansion just
It hands over turbine and improves aerodynamic arrangement's method of turbine performance.
Background technology
In modern high performance gas turbine/aero-engine, to improve turbine efficiency, axial flow turbine mostly uses casing
Outer end wall large expansion angle runner design acutely increases so that the degree of convergence of turbo blade runner is not enough to more along cross section is flowed to
The diffusion for mending meridional channel, causes large expansion angle petiolarea boundary layer to thicken rapidly, or even the complicated whirlpool such as generate larger recirculating zone
System, brings larger petiolarea to lose, hence it is evident that influences turbine efficiency.Also, high performance gas-turbine engine/aeroplane engine of the prior art
All there is long changeover portion in the low-pressure turbine of machine, cause gas turbine/aero-engine structure huger downstream
Greatly, compactedness is poor.Due to the deficiencies in the prior art, it is desirable to have a kind of big son effectively improving pneumatic efficiency and compactedness
Noon expands turbine and its advanced design method.
Invention content
The purpose of the invention is to effectively improve turbine pneumatic performance, and so that turbine part structure is more compact and
A kind of orthogonal turbine of the wide string of big meridian expansion is provided and improves aerodynamic arrangement's method of turbine performance.
The object of the present invention is achieved like this：Including casing, stator blade wheel hub, movable vane wheel hub, changeover portion and power turbine,
Movable vane wheel hub be arranged by stator blade wheel hub, be along the circumferential direction equipped between casing and stator blade wheel hub and uniformly stator blade,
Movable vane piece, stator blade, movable vane piece, stator blade wheel hub, movable vane wheel are along the circumferential direction installed between casing and movable vane wheel hub and uniformly
Hub, machine lock constitute stator blade turbine, and changeover portion and power turbine are successively set on the downstream of stator blade turbine, and the stator blade is stator blade
Piece itself and stator blade hub end wall are orthogonal the orthogonal molded breadth string blade of arrangement, center of gravity product superimposing thread and the radial coordinate side of stator blade
To angle between 5 °~15 °.
The invention also includes some such structure features：
1. the stator blade leading edge molded line respectively with casing, stator blade hub end wall intersection position at tangent line and leading-edge profile
The angle of line is 80 °~100 °, stator blade trailing edge molded line respectively with casing, stator blade hub end wall intersection position at tangent line with
The angle of trailing edge molded line is 80 °~100 °.
2. a kind of aerodynamic arrangement's method improving turbine performance, including the orthogonal turbine of the wide string of big meridian expansion, tool
Body is as follows：
It is constant to retain stator blade upper end wall molded line, is moved towards along changeover portion upper end wall molded line, modification movable vane piece upper end wall-shaped
Line changes simultaneously stator blade lower end wall molded line and movable vane piece molded line, and changeover portion lower end wall initial position is transitioned into adaptability, and
It is smoothly connected with it.
Compared with prior art, the beneficial effects of the invention are as follows：The present invention is fully understanding efficient turbine rate design parameter
On the basis of choosing rule and fully considering that Turbine flow is three-dimensionality, by using wide string blade, to delay air-flow in big meridian
The diffusion degree of expanding channel petiolarea, and make blade orthogonal with end wall, so that air-flow is flowed approximately along blade profile direction, improve
Big meridian expansion turbine petiolarea flowing；And by raising the orthogonal turbine of wide string, especially its movable vane piece, reduce turbine flow system
Number and loading coefficient so that turbine is in higher efficiency scope of design, and substantially shortens changeover portion axial length；In addition, this
Inventive structure is fairly simple, and processing and manufacturing is also more convenient, is easy to Project Realization.
Description of the drawings
Fig. 1 is the through-flow view of meridian of orthogonal turbine, changeover portion and power turbine；
Fig. 2 is the characteristic size schematic diagram of orthogonal turbine stator vane two-end structure.
Specific implementation mode
Present invention is further described in detail with specific implementation mode below in conjunction with the accompanying drawings.
In conjunction with Fig. 1, the present invention includes casing 3, stator blade 1, movable vane piece 2, stator blade wheel hub 4 and movable vane wheel hub 5, in casing 3
The along the circumferential direction uniform installation stator blade 1 and movable vane piece 2 between wheel hub 4 and 5, stator blade 1 is preceding, and movable vane piece 2 is in rear, stator blade
Piece 1 is connected with casing 3, wheel hub 4, and movable vane piece 2 is mounted on wheel hub 5, and for movable vane wheel hub 5 by stator blade wheel hub 4, stator blade 1 is leaf
Piece itself and end wall are orthogonal the orthogonal molded breadth string blade of arrangement, can significantly improve turbine petiolarea flow field and mobile performance.Just
Turbine stator vane 1 and 2 downstream of movable vane piece is handed over to there is the changeover portion 6 with support plate and power turbine stator blade 7 and movable vane piece 8, transition
For section 6 between orthogonal turbine and power turbine, orthogonal turbine drives low-pressure compressor load, power turbine drives propeller etc.
Load.Stator blade is that blade itself and end wall are orthogonal the orthogonal molded breadth string blade of arrangement, and the center of gravity of stator blade accumulates superimposing thread and diameter
To coordinate direction angle between 5 °~15 °.
Preferably, stator blade leading edge molded line respectively with casing, wheel hub end wall intersection position at tangent line and leading edge molded line
Angle be 80 °~100 °, stator blade trailing edge molded line respectively with casing, wheel hub end wall intersection position at tangent line and trailing edge type
The angle of line is 80 °~100 °.
In conjunction with Fig. 2, the orthogonal turbine of the wide string of big meridian expansion of the present invention is manufactured, is designed first using traditional design method
Conventional twisted blade, then for given turbine population parameter and operating condition range situations such as, it is appropriate which is carried out
Quadrature operation, the tangent line at intersection position to ensure blade inlet edge, trailing edge molded line and casing end wall respectively with leading edge, trailing edge type
The angle α of line1、α2Between 80 °~100 °, and blade inlet edge, trailing edge molded line and cutting at the intersection position of wheel hub end wall
Line respectively with leading edge, the angle α of trailing edge molded line4、α5Simultaneously between 80 °~100 °.In addition, in order to ensure the orthogonal leaf of wide string
To the validity of turbine petiolarea flowing control, the center of gravity product superimposing thread and the angle in radial coordinate direction of stator blade should usually be located piece
Between 5 °~15 °.It is worth noting that, the best value of all of above parameter can be by means of existing computational fluid dynamics
Software Numerical Simulation or correlation test obtain.
A kind of aerodynamic arrangement's method improving turbine performance, raises the orthogonal quiet movable vane piece of turbine, especially movable vane piece, reduces
Turbine flow coefficient and loading coefficient so that turbine is in higher efficiency scope of design, and it is axially long substantially to shorten changeover portion
Degree.Its specific practice is that the big meridian expansion stator blade upper end wall molded line of reservation is constant, is moved towards along changeover portion upper end wall molded line, greatly
Width changes movable vane piece upper end wall molded line, meanwhile, slightly change stator blade lower end wall molded line and movable vane piece molded line, with adaptability transition
It is smoothly connected to changeover portion lower end wall initial position, and with it.This treating method has in fact raised orthogonal turbine average half
Diameter improves average peripheral speed, thus reduces stage of turbine loading coefficient (ratio of wheel work and peripheral speed square) leaf
Piece, while flow cross section increases, and reduces axial velocity and discharge coefficient (ratio of axial velocity and peripheral speed), load
Being reduced while coefficient and discharge coefficient causes turbine design point to be within the scope of the high efficiency in Smith chart, and at the same time greatly
Width shortens changeover portion axial length so that turbine part structure is more compact and light, processing and manufacturing is more convenient.
To sum up, it expands the orthogonal turbine of wide string the purpose of the present invention is to provide a kind of big meridian and improves the pneumatic of its performance
Layout method, including casing, stator blade, movable vane piece and wheel hub along the circumferential direction uniformly install stator blade between casing and wheel hub
Piece and movable vane piece, stator blade is preceding, and rear, stator blade is connected movable vane piece with casing, wheel hub, and movable vane piece is mounted on wheel hub, moves
For impeller boss by stator blade wheel hub, stator blade is that blade itself and end wall are orthogonal the orthogonal molded breadth string blade of arrangement, can obviously be carried
There is changeover portion and power turbine with support plate in high turbine petiolarea mobile performance, changeover portion is located at orthogonal in orthogonal turbine downstream
Between turbine and power turbine, orthogonal turbine drives low-pressure compressor load, power turbine drives the loads such as propeller, improves whirlpool
Aerodynamic arrangement's method of performance is taken turns, it is characterized in that raising orthogonal turbine, reduces turbine flow coefficient and loading coefficient so that turbine
It is in higher efficiency scope of design, and substantially shortens changeover portion axial length.The wide string of big meridian expansion that the present invention designs is just
Friendship turbine and the aerodynamic arrangement's method for improving its performance can effectively improve turbine pneumatic performance, and make turbine part structure more
It is compact and light, processing and manufacturing it is more convenient.
Claims (3)
1. a kind of big meridian expands the orthogonal turbine of wide string, including casing, stator blade wheel hub, movable vane wheel hub, changeover portion and power turbine,
Movable vane wheel hub be arranged by stator blade wheel hub, be along the circumferential direction equipped between casing and stator blade wheel hub and uniformly stator blade,
Movable vane piece, stator blade, movable vane piece, stator blade wheel hub, movable vane wheel are along the circumferential direction installed between casing and movable vane wheel hub and uniformly
Hub, machine lock constitute stator blade turbine, and changeover portion and power turbine are successively set on the downstream of stator blade turbine, it is characterised in that：It is described
Stator blade is that stator blade itself and stator blade hub end wall are orthogonal the orthogonal molded breadth string blade of arrangement, the center of gravity product superimposing thread of stator blade
Angle with radial coordinate direction is between 5 °~15 °.
2. a kind of big meridian according to claim 1 expands the orthogonal turbine of wide string, it is characterised in that：The stator blade leading edge
Molded line respectively with casing, stator blade hub end wall intersection position at the angle of tangent line and leading edge molded line be 80 °~100 °, stator blade
Piece trailing edge molded line respectively with casing, stator blade hub end wall intersection position at tangent line and trailing edge molded line angle be 80 °~
100°。
3. a kind of aerodynamic arrangement's method improving turbine performance, it is characterised in that：Including the big meridian expansion described in claim 2
The orthogonal turbine of wide string, it is specific as follows：
It is constant to retain stator blade upper end wall molded line, is moved towards along changeover portion upper end wall molded line, changes movable vane piece upper end wall molded line, together
When change stator blade lower end wall molded line and movable vane piece molded line, changeover portion lower end wall initial position is transitioned into adaptability, and and its
It is smoothly connected.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810369496 | 2018-04-24 | ||
| CN2018103694968 | 2018-04-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108798788A true CN108798788A (en) | 2018-11-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810532450.3A Pending CN108798788A (en) | 2018-04-24 | 2018-05-29 | A kind of big meridian expands aerodynamic arrangement's method of the orthogonal turbine of wide string and raising turbine performance |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
| CN113513368A (en) * | 2021-07-08 | 2021-10-19 | 哈尔滨工程大学 | Turbine capable of directly backing with primary and secondary moving blade structures |
| CN115680780A (en) * | 2022-10-13 | 2023-02-03 | 中国航发四川燃气涡轮研究院 | Turbine blade plane cascade inlet axial speed control method |
| CN115749968A (en) * | 2022-10-31 | 2023-03-07 | 东方电气集团东方汽轮机有限公司 | Hybrid turbine structure and operation method of hybrid turbine |
| CN115680780B (en) * | 2022-10-13 | 2024-05-03 | 中国航发四川燃气涡轮研究院 | Turbine blade plane blade grid inlet axial speed control method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104153820A (en) * | 2014-07-22 | 2014-11-19 | 哈尔滨工程大学 | Large meridional expansion variable-geometry turbine with stepped spherical end wall |
| US20150046126A1 (en) * | 2013-08-08 | 2015-02-12 | Solar Turbines Incorporated | Gas turbine engine rotor assembly optimization |
| CN104100305B (en) * | 2014-07-22 | 2016-01-27 | 哈尔滨工程大学 | A kind of large meridian expansion variable geometry turbine with orthogonal type adjustable stator blade |
| CN105781626A (en) * | 2016-03-03 | 2016-07-20 | 哈尔滨工程大学 | Three-dimensional orthogonal unsteady design method of large meridian expansion turbine |
-
2018
- 2018-05-29 CN CN201810532450.3A patent/CN108798788A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150046126A1 (en) * | 2013-08-08 | 2015-02-12 | Solar Turbines Incorporated | Gas turbine engine rotor assembly optimization |
| CN104153820A (en) * | 2014-07-22 | 2014-11-19 | 哈尔滨工程大学 | Large meridional expansion variable-geometry turbine with stepped spherical end wall |
| CN104100305B (en) * | 2014-07-22 | 2016-01-27 | 哈尔滨工程大学 | A kind of large meridian expansion variable geometry turbine with orthogonal type adjustable stator blade |
| CN105781626A (en) * | 2016-03-03 | 2016-07-20 | 哈尔滨工程大学 | Three-dimensional orthogonal unsteady design method of large meridian expansion turbine |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
| CN113513368A (en) * | 2021-07-08 | 2021-10-19 | 哈尔滨工程大学 | Turbine capable of directly backing with primary and secondary moving blade structures |
| CN115680780A (en) * | 2022-10-13 | 2023-02-03 | 中国航发四川燃气涡轮研究院 | Turbine blade plane cascade inlet axial speed control method |
| CN115680780B (en) * | 2022-10-13 | 2024-05-03 | 中国航发四川燃气涡轮研究院 | Turbine blade plane blade grid inlet axial speed control method |
| CN115749968A (en) * | 2022-10-31 | 2023-03-07 | 东方电气集团东方汽轮机有限公司 | Hybrid turbine structure and operation method of hybrid turbine |
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Application publication date: 20181113 |