CN104595245B - The adjustable stator blade of first half section and method of work thereof for axial flow compressor final stage - Google Patents
The adjustable stator blade of first half section and method of work thereof for axial flow compressor final stage Download PDFInfo
- Publication number
- CN104595245B CN104595245B CN201510000610.6A CN201510000610A CN104595245B CN 104595245 B CN104595245 B CN 104595245B CN 201510000610 A CN201510000610 A CN 201510000610A CN 104595245 B CN104595245 B CN 104595245B
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- Prior art keywords
- blade
- adjustable
- final stage
- half section
- axial flow
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Mechanical Engineering (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of adjustable stator blade of first half section for axial flow compressor final stage, and method of work, belong to impeller machinery technical field.This final stage stator blade is divided into adjustable first half section blade (8) and non-adjustable second half section blade (10), the most adjustable first half section blade (8) is arranged on non-adjustable second half section blade (10) by rotary shaft (9), rotary shaft (9) is positioned at final stage stator blade maximum gauge, and non-adjustable back segment blade (10) is fixedly mounted on the outer casing of axial flow compressor.Use this blade can reach: 1), expand the operation pressure ratio of compressor and range of flow；2) compressor, is improved in whole working range internal efficiency.
Description
Technical field
The present invention relates to a kind of adjustable stator blade of first half section for axial flow compressor final stage and method of work thereof, belong to leaf
Wheel mechanical technical field.
Background technology
The general work principle of axial flow compressor is: when gas flows through the movable vane of high speed rotating, movable vane is by mechanical energy
For pressure energy and the kinetic energy of gas, thus improve pressure and the speed of gas.Small part mechanical energy is had during energy conversion
It is changed into heat energy by other loss mode, therefore in compression process, gas temperature can gradually step up.During airflow passes stator blade, a side
Part kinetic energy is further converted to pressure energy by face, plays diffusion action, is on the other hand drawn with certain speed and direction by gas
Enter next stage movable vane.Multiple movable vanes are arranged on wheel disc and constitute rotor；Multiple stator blades are fixed on casing, form stator.One turns
Son and a stator are combined one " level " of composition.The basic functional principle of every stage compressor is roughly the same.
For industry axial flow compressor or be applied to the axial flow compressor of gas turbine and aero-engine, in order to expand work
Make flow and pressure ratio scope generally use the adjustable stator of established angle, as Schobeiri M T be published on ASME magazine entitled
“Active Aerodynamic Control of Multi-stage Axial Compressor Instability and
Surge by Dynamically Adjusting the Stator Blades. " (ASME Paper No. 2001-T-
479. 2001) article.Fig. 2 be turn stator blade passage simplify gained plane cascade, for its Leaf of adjustable stator around
A fixing rotary shaft to rotate, change blade angle (Fig. 3) by blade integral-rotation, to adapt to rotor outlet gas
The change of stream angle, makes stator at the appropriate angle of attacki(Fig. 2) operated within range.Adjustable stator blade is mainly used in axial flow
Before compressor in what, also have and apply in whole levels of whole compressor.Owing to Conventional tunable stator blade bent angle is fixed, gas
Stream range of accommodation is narrower.Entitled " the Single-stage experimental that Jones B.A and Wright D.L delivers
evaluation of variable geometry guide vanes and stators. Part I analysis and
Designs " (article of NASA CR-54554 (1965) propose leading portion fix, back segment moving blade structure, go out realizing blade
During mouth angle adjustment, entrance angle is constant, makes blade be in the favourable angle of attack all the time.In order to compressor outlet air current flow direction is protected
Holding axially, usual afterbody (final stage) stator is non-adjustable.Therefore change along with compressor operating state, at final stage stator possibility
Work under the bigger positive and negative angle of attack, cause loss to increase.If use overall adjustable stator blade to change the angle of attack, cannot
Ensure that final stage stator is axially given vent to anger, produce greater loss.
Summary of the invention
Present invention aim at, for axial flow compressor final stage stator, proposing a kind of first half for axial flow compressor final stage
Section adjustable stator blade and method of work thereof, uses this blade can reach: 1), expand operation pressure ratio and the flow model of compressor
Enclose；2) compressor, is improved in whole working range internal efficiency.And the stator blade gone out by actual design has carried out calculating point
Analysis, verifies its feasibility.
A kind of adjustable stator blade of first half section for axial flow compressor final stage, overall blade profile is set by axial flow compressor is pneumatic
Meter method gained, it is characterised in that: this final stage stator blade is divided into adjustable first half section blade and non-adjustable second half section blade, wherein
Adjustable first half section blade is arranged on non-adjustable second half section blade by rotary shaft, and it is thick that rotary shaft is positioned at final stage stator blade maximum
At degree, non-adjustable second half section blade is fixedly mounted on the outer casing of axial flow compressor.
The method of work of the adjustable stator blade of first half section for axial flow compressor final stage in accordance with the above, its feature
It is to include procedure below:
By its design requirement by direct problem method for designing, rhetorical question when step 1, final stage stator blade profile are designed by axial flow compressor
Topic method for designing or Optimization Design obtain, and the adjustable first half section blade of final stage stator is under design conditions when rotating zero degree
Final stage stator blade profile；
Step 2, change final stage stator blade air inlet angle beta1To calculate the pitot loss of corresponding stator, imitated by computer
Really obtain air inlet angle beta1Relation curve with pitot loss；This stator is can get by the relation curve of flow inlet angle Yu pitot loss
Low loss range；
Step 3, change the deflection angle of adjustable first half section blade, obtain under different deflection angle according to the mode of step 2
The low loss range of stator；
Step 4, adjustable first half section blade the angle of deflection finally by final stage rotor under axial flow compressor difference operating mode
Outlet flow angle determines, utilizes step 3 curve obtained, selects final stage stator blade flow inlet angle, to ensure that flow inlet angle is located all the time
In the range of final stage stator blade low loss flow angle, reduce loss, improve efficiency.
This invention compares with current prior art and has the advantage that, 1) fixing with final stage stator comparing, leading portion is adjustable to be made
This stator inlet air flow is in the favourable angle of attack, can widen the range of operation of compressor, improve compressor efficiency.2) can with entirety
Adjusting stator blade camber to fix to compare, leading portion is adjustable makes this stator direction constant (keeping axially giving vent to anger).
The adjustable stator blade of leading portion that this invention is proposed, can be directly used for axial flow compressor or gas turbine and aviation
In the Axial Flow Compressor Design of electromotor, improve its aeroperformance it can also be used to existing axial flow compressor is improved upgrading.
Accompanying drawing explanation
Fig. 1 is axial flow compressor meridian plane schematic diagram；
Fig. 2 is plane cascade geometric parameter schematic diagram；
Fig. 3 is overall adjustable stator blade schematic diagram；
Fig. 4 is that overall adjustable stator blade regulates schematic diagram；
Fig. 5 is first half section adjustable stator blade schematic diagram；
Fig. 6 is that the adjustable stator blade of first half section regulates angle；
Fig. 7 is profile loss and flow inlet angle graph of a relation；
Label title in figure: 1, axial flow compressor first order rotor blade, 2, axial flow compressor first order stator blade, 3,
Casing, 4, wheel disc, 5, final stage stator, 6, overall adjustable stator blade, 7, rotary shaft, 8, adjustable first half section blade, 9, rotary shaft,
10, non-adjustable second half section blade, 11, blade leading portion deflection-5 degree, 12, leading portion deflect 0 degree, 13, leading portion deflection 5 degree, 14, leading portion
Deflect 10 degree.
Specific implementation method
Below in conjunction with figure to the figure explanation adjustable stator blade of leading portion of the present invention and the stator implementation that is made up of it:
The blade of final stage stator is obtained by axial flow compressor Pneumatic design method, i.e. by initial designs, through-flow design, two dimension
Blade design and three dimendional blade design obtain.
The concrete structure of final stage stator blade: adjustable first half section blade 8 is fixed together with rotary shaft 9；Non-adjustable later half
Section blade 10 is fixedly mounted on the outer casing of axial flow compressor (Fig. 5).When axial flow compressor operating condition adjusts joint, rotary shaft
Rotate and drive leading portion blade deflection, to adapt to the change of its inlet air flow angle.
Embodiment.Such as Fig. 6, rotate stator leading portion, make stator blade leading portion deflect successively-5 degree, 0 degree (rotation), 5
Degree, 10 degree (deflection angle is to calculate checking stator pitot loss scope under different blade profile cambers and choose).Use meter
Calculation machine simulation calculation pitot loss and flow inlet angle relation curve, be shown in Fig. 7.In Fig. 7, with circular, square, triangle, diamond-shaped pattern
Target curve represents blade leading portion deflection-5 degree, 0 degree, 5 degree, 10 degree of flow angles and loss relation respectively.This figure shows: each
The all corresponding low loss inlet air flow angle range of the stator blade of camber, such as: blade leading portion deflection angle is 0 degree (non deflected)
Stator (blade profile of icon 12 correspondence in Fig. 6), low loss inlet air flow scope is about 13 degree to 36 degree.Blade leading portion deflection angle
Difference, low loss range difference also respective change, during specific design, deflection angle step-length can be diminished, be calculated in more detail
Pitot loss and flow inlet angle graph of a relation.
In the present invention is applied to axial flow compressor, blade leading portion deflection angle can be regulated according to the difference of operating condition
Degree, in the range of ensureing that flow inlet angle is in stator blade low loss flow angle all the time, reduces loss, improves efficiency.Such as, certain work
Under condition, rotor outlet flow angle is about 20 degree, and scalable leading portion blade deflection-5 is spent so that it is be placed exactly in leading portion rotation-5 degree quiet
The centre position of blades correspondence least disadvantage.
Claims (2)
1., for the adjustable stator blade of first half section of axial flow compressor final stage, overall blade profile is by axial flow compressor pneumatic design
Method gained, it is characterised in that: this final stage stator blade is divided into adjustable first half section blade (8) and non-adjustable second half section blade
(10), the most adjustable first half section blade (8) is arranged on non-adjustable second half section blade (10) by rotary shaft (9), rotary shaft (9)
Being positioned at final stage stator blade maximum gauge, non-adjustable second half section blade (10) is fixedly mounted on the outer casing of axial flow compressor.
The method of work of the adjustable stator blade of first half section for axial flow compressor final stage the most according to claim 1, its
It is characterised by including procedure below:
Set by direct problem method for designing, indirect problem by its design requirement when step 1, final stage stator blade profile are designed by axial flow compressor
Meter method or Optimization Design obtain, and adjustable first half section blade (8) of final stage stator is under design conditions when rotating zero degree
Final stage stator blade profile；
Step 2, change final stage stator blade air inlet angle beta1To calculate the pitot loss of corresponding stator, obtained by Computer Simulation
To air inlet angle beta1Relation curve with pitot loss；The low of this stator is can get with the relation curve of pitot loss by flow inlet angle
Loss range；
Step 3, change the deflection angle of adjustable first half section blade (8), obtain under different deflection angle quiet according to the mode of step 2
The low loss range of son；
Step 4, adjustable first half section blade (8) the angle of deflection finally by the going out of final stage rotor under axial flow compressor difference operating mode
Mouth flow angle determines, utilizes step 3 curve obtained, selects final stage stator blade flow inlet angle, to ensure that flow inlet angle is in all the time
In the range of final stage stator blade low loss flow angle, reduce loss, improve efficiency.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510000610.6A CN104595245B (en) | 2015-01-04 | 2015-01-04 | The adjustable stator blade of first half section and method of work thereof for axial flow compressor final stage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510000610.6A CN104595245B (en) | 2015-01-04 | 2015-01-04 | The adjustable stator blade of first half section and method of work thereof for axial flow compressor final stage |
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| Publication Number | Publication Date |
|---|---|
| CN104595245A CN104595245A (en) | 2015-05-06 |
| CN104595245B true CN104595245B (en) | 2016-12-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510000610.6A Expired - Fee Related CN104595245B (en) | 2015-01-04 | 2015-01-04 | The adjustable stator blade of first half section and method of work thereof for axial flow compressor final stage |
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| CN105332952B (en) * | 2015-11-02 | 2017-10-31 | 南京航空航天大学 | A kind of adjustable stator design method of small camber |
| CN107725482A (en) * | 2016-08-10 | 2018-02-23 | 上海电气燃气轮机有限公司 | Improve the sectional-regulated exit guide blade and its governor motion of compressor off design performance |
| CN107061314A (en) * | 2017-03-28 | 2017-08-18 | 沈阳冠能燃气轮机科技有限公司 | The low-pressure compressor changed a social system using retired engine |
| CN107301268A (en) * | 2017-05-18 | 2017-10-27 | 哈尔滨工程大学 | A kind of ship gas turbine variable stator vane angle compressor deflection angle optimization method |
| CN107742011B (en) * | 2017-09-26 | 2020-12-11 | 南京航空航天大学 | Design method of impeller blade drag reduction micro-texture |
| CN108729958A (en) * | 2018-04-24 | 2018-11-02 | 哈尔滨工程大学 | A kind of reversion variable geometry turbine of the variable stator vane angle with low consistency zero-lift blade profile |
| CN109578335B (en) * | 2018-11-27 | 2020-05-15 | 中国航发湖南动力机械研究所 | Variable camber blade type tandem stator and compressor |
| CN110530595A (en) * | 2019-07-19 | 2019-12-03 | 南京航空航天大学 | A kind of plane cascade test platform test section inlet system of the adjustable angle of attack |
| CN112253545B (en) * | 2020-12-21 | 2021-03-05 | 中国航发上海商用航空发动机制造有限责任公司 | Method for measuring and calculating influence of angle change of adjustable stationary blade of gas compressor on flow |
| CN112814949B (en) * | 2021-01-13 | 2022-01-21 | 南京航空航天大学 | Oblique-section type double-freedom-degree inlet adjustable guide vane suitable for wide bypass ratio variation range |
| CN112665861B (en) * | 2021-03-18 | 2021-06-15 | 中国航发上海商用航空发动机制造有限责任公司 | Blade-shaped probe and performance testing method for aircraft engine using same |
| CN113864243A (en) * | 2021-09-10 | 2021-12-31 | 中国民航大学 | Axial flow compressor for improving full-circumferential flow field |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9203168D0 (en) * | 1992-02-13 | 1992-04-01 | Rolls Royce Plc | Guide vanes for gas turbine engines |
| CN201180686Y (en) * | 2007-12-27 | 2009-01-14 | 西安陕鼓动力股份有限公司 | Electrically driven static vane controlling mechanism of axial flow compressor |
| JP5644302B2 (en) * | 2010-09-15 | 2014-12-24 | 株式会社Ihi | Axial compressor and gas turbine engine |
| JP2012233424A (en) * | 2011-04-28 | 2012-11-29 | Ihi Corp | Variable stator blade mechanism of axial flow type compressor |
| CN103291377B (en) * | 2013-06-25 | 2015-05-27 | 上海交通大学 | Gas compressor multistage stationary blade rigid adjusting mechanism |
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