CN104595245A - Last-stage front half section adjustable stator blade for axial-flow compressor and working method thereof - Google Patents

Last-stage front half section adjustable stator blade for axial-flow compressor and working method thereof Download PDF

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Publication number
CN104595245A
CN104595245A CN201510000610.6A CN201510000610A CN104595245A CN 104595245 A CN104595245 A CN 104595245A CN 201510000610 A CN201510000610 A CN 201510000610A CN 104595245 A CN104595245 A CN 104595245A
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China
Prior art keywords
blade
half section
adjustable
final stage
stator
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CN201510000610.6A
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CN104595245B (en
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周正贵
李琪
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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    • 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)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Theoretical Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Evolutionary Computation (AREA)
  • Geometry (AREA)
  • General Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a last-stage front half section adjustable stator blade for an axial-flow compressor and a working method thereof and belongs to the technical field of impeller machinery. The last-stage stator blade comprises an adjustable front half section blade (8) and a nonadjustable rear half section blade (10), wherein the adjustable front half section blade (8) is arranged on the nonadjustable rear half section blade (10) through a rotating shaft (9); the rotating shaft (9) is positioned at the position with the largest thickness of the last-stage stator blade; the nonadjustable rear half section blade (10) is fixedly arranged on an outer cartridge receiver of the axial-flow compressor. The blade has the advantages of (1) the operation pressure ratio and the flow rate range of the compressor are expanded; (2) the efficiency of the compressor in the whole working range is improved.

Description

For the adjustable stator blade of first half section and the method for work thereof of axial flow compressor final stage
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 impeller machinery technical field.
Background technique
The general work principle of axial flow compressor is: gas flow is when movable vane (1) of High Rotation Speed, and mechanical energy is pressure energy and the kinetic energy of gas by movable vane, thus improves pressure and the speed of gas.In energy conversion process, have small part mechanical energy to change heat energy into by other loss mode, therefore in compression process, gas temperature can improve gradually.Time airflow passes stator blade (2), on the one hand part kinetic energy is further converted to pressure energy, plays diffusion action, on the other hand gas is introduced next stage movable vane with certain speed and direction.Multiple movable vane is arranged on wheel disc (4) and forms rotor; Multiple stator blade is fixed on casing (3), composition stator.A rotor and a stator are combined formation one " level ".The basic functional principle of every stage compressor is roughly the same.
For industrial axial flow compressor or the axial flow compressor being applied to gas turbine and aeroengine, in order to expand working flow and pressure ratio scope adopts the adjustable stator of established angle usually, be published in the article being entitled as " Active Aerodynamic Control of Multi-stage Axial Compressor Instability and Surge by Dynamically Adjusting the Stator Blades. " (ASME Paper No. 2001-T-479. 2001) on ASME magazine as Schobeiri M T.Fig. 2 turns the plane cascade that stator blade passage simplifies gained, its Leaf of adjustable stator is rotated around a fixing running shaft, rotated by blade integral and change blade angle (Fig. 3), to adapt to the change of rotor outlet air-flow angle, make stator at the more suitable angle of attack i(Fig. 2) operated within range.Adjustable stator blade is mainly used in before axial flow compressor, in what, also to be had and is applied in whole levels of whole compressor.Because Conventional tunable stator blade bent angle is fixed, gas flow modulation scope is narrower.What Jones B.A and Wright D.L delivered is entitled as " Single-stage experimental evaluation of variable geometry guide vanes and stators. Part I analysis and designs ", and (the article proposition leading portion of NASA CR-54554 (1965) is fixed, back segment rotor blade structure, constant to realize entrance angle when blade outlet angle adjusts, make blade be in the favourable angle of attack all the time.In order to compressor outlet air current flow direction retainer shaft to, usual afterbody (final stage) stator (5) is non-adjustable.Therefore along with compressor operating change of state, final stage stator works under may being in the larger positive and negative angle of attack, causes loss to increase.If adopt overall adjustable stator blade to change the angle of attack, just can not ensure that final stage stator is axially given vent to anger, produce greater loss.
Summary of the invention
The object of the invention is for axial flow compressor final stage stator, proposes a kind of adjustable stator blade of first half section for axial flow compressor final stage and method of work thereof, adopts this blade to reach: 1), expand the operation pressure ratio of compressor and range of flow; 2) compressor, is improved in whole operating range internal efficiency.And carried out computational analysis by the stator blade that actual design goes out, verify its feasibility.
A kind of adjustable stator blade of first half section for axial flow compressor final stage, overall blade profile is by axial flow compressor Pneumatic design method gained, it is characterized 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 running shaft, running shaft is positioned at final stage stator blade maximum ga(u)ge place, and non-adjustable back segment blade is fixedly mounted on the outer casing of axial flow compressor.
According to the method for work of the above-described adjustable stator blade of first half section for axial flow compressor final stage, it is characterized in that comprising following process:
Step 1, final stage stator blade profile are obtained by Blade Design Method such as direct problem design method, indirect problem design method or Optimization Design by its designing requirement when being designed by axial flow compressor, are the final stage stator blade profile under design conditions during the adjustable first half section blade rotary zero degree of final stage stator;
Step 2, change final stage stator blade flow inlet angle β 1to calculate the pitot loss of corresponding stator, obtain flow inlet angle β by computer simulation 1with the relation curve of pitot loss; The low loss range of this stator can be obtained by the relation curve of flow inlet angle and pitot loss;
Step 3, change the deflection angle of adjustable first half section blade, obtain the low loss range of stator under different deflection angle according to the mode of step 2;
The angle of the deflection of step 4, adjustable first half section blade is finally decided by the outlet flow angle of final stage rotor under the different operating mode of axial flow compressor, utilize step 3 curve obtained, select final stage stator blade flow inlet angle, to ensure that flow inlet angle is within the scope of the low loss flow angle of final stage stator blade all the time, reduce loss, raise the efficiency.
This invention compares with current prior art has following advantage, 1), fixedly compare with final stage stator, leading portion is adjustable makes this stator inlet air flow be in the favourable angle of attack, can widen the range of operation of compressor, improve compressor efficiency.2) stator blade camber adjustable with entirety fixedly compares, and leading portion is adjustable makes this stator direction constant (retainer shaft is to giving vent to anger).
The leading portion that this invention proposes is adjustable stator blade, can be directly used in the For Axial Flow Compressor Design of axial flow compressor or gas turbine and aeroengine, improve its aeroperformance, also can be used for carrying out improvement upgrading to existing axial flow compressor.
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 the adjustable stator blade schematic diagram of first half section;
Fig. 6 is the adjustable stator blade adjusting angle of first half section;
Fig. 7 is profile loss and flow inlet angle graph of a relation;
Number in the figure title: 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, running shaft, 8, rotatable leading portion blade, 9, rotatingshaft, 10, fixing back segment blade, 11, blade leading portion deflection-5 degree, 12, leading portion deflection 0 degree, 13, leading portion deflection 5 degree, 14, leading portion deflect 10 degree.
Specific implementation method
Stator implementation methods below in conjunction with Fig. 1 to Fig. 7 illustrates the adjustable stator blade of leading portion of the present invention and is made up of it:
The blade of final stage stator is obtained by axial flow compressor Pneumatic design method, is namely obtained by the designs of initial designs, through-flow reconstruct, two-dimentional blade design and three dimendional blade.
The concrete structure of final stage stator blade: rotatable leading portion blade 8 is fixed together with rotatingshaft 9; Non-adjustable back segment blade 10 is fixedly mounted on the outer casing of axial flow compressor (Fig. 5).When axial flow compressor operating conditions adjustment joint, rotatingshaft rotates and drives leading portion blade deflection, to adapt to the change of its inlet air flow angle.
Embodiment.As Fig. 6, rotate stator leading portion, make stator blade leading portion deflect-5 degree, 0 degree (rotation), 5 degree, 10 degree (deflection angle is calculate the pitot loss scope of checking stator under different blade profile camber to choose) successively.Adopt Computer Simulation pitot loss and flow inlet angle relation curve, see Fig. 7.In Fig. 7, represent blade leading portion deflection-5 degree, 0 degree, 5 degree, 10 degree flow angles and loss relation respectively with circular, square, triangle, diamond-shaped pattern target curve.This figure shows: the corresponding low loss inlet air flow angular region of the stator blade of each camber, and if: blade leading portion angle of yaw is the stator blade profile of icon 12 correspondence (in the Fig. 6) of 0 degree (deflection), low loss inlet stream scope is about 13 degree to 36 degree.Blade leading portion deflection angle is different, and low loss range difference also respective change, during specific design, can diminish deflection angle step-length, calculate more detailed pitot loss and flow inlet angle graph of a relation.
When the present invention is applied in axial flow compressor, can according to the difference of operating conditions, adjusting vane leading portion deflection angle, to ensure that flow inlet angle is within the scope of the low loss flow angle of stator blade all the time, reduces loss, raises the efficiency.Such as, under certain operating mode, rotor outlet flow angle is about 20 degree, adjustable leading portion blade deflection-5 degree, makes it just in time be positioned at leading portion and rotates the neutral position that-5 spend the corresponding least disadvantages of stator blade.

Claims (2)

1. the adjustable stator blade of first half section for axial flow compressor final stage, overall blade profile is by axial flow compressor Pneumatic design method gained, it is characterized in that: this final stage stator blade is divided into adjustable first half section blade (8) and non-adjustable second half section blade (10), wherein adjustable first half section blade (8) is arranged on non-adjustable second half section blade (10) by running shaft (9), running shaft (9) is positioned at final stage stator blade maximum ga(u)ge place, and non-adjustable back segment blade (10) is fixedly mounted on the outer casing of axial flow compressor.
2. the method for work of the adjustable stator blade of first half section for axial flow compressor final stage according to claim 1, is characterized in that comprising following process:
Step 1, final stage stator blade profile are obtained by Blade Design Method such as direct problem design method, indirect problem design method or Optimization Design by its designing requirement when being designed by axial flow compressor, are the final stage stator blade profile under design conditions when the adjustable first half section blade (8) of final stage stator rotates zero degree;
Step 2, change final stage stator blade flow inlet angle β 1to calculate the pitot loss of corresponding stator, obtain flow inlet angle β by computer simulation 1with the relation curve of pitot loss; The low loss range of this stator can be obtained by the relation curve of flow inlet angle and pitot loss;
Step 3, change the deflection angle of adjustable first half section blade (8), obtain the low loss range of stator under different deflection angle according to the mode of step 2;
The angle of the deflection of step 4, adjustable first half section blade (8) is finally decided by the outlet flow angle of final stage rotor under the different operating mode of axial flow compressor, utilize step 3 curve obtained, select final stage stator blade flow inlet angle, to ensure that flow inlet angle is within the scope of the low loss flow angle of final stage stator blade all the time, reduce loss, raise the efficiency.
CN201510000610.6A 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 Expired - Fee Related CN104595245B (en)

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105332952A (en) * 2015-11-02 2016-02-17 南京航空航天大学 Small-bend adjustable stator design method
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
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
CN107742011A (en) * 2017-09-26 2018-02-27 南京航空航天大学 The design method of the micro- texture of impeller blade drag reduction
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
CN109578335A (en) * 2018-11-27 2019-04-05 中国航发湖南动力机械研究所 Variable camber vane 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
CN112253545A (en) * 2020-12-21 2021-01-22 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
CN112665861A (en) * 2021-03-18 2021-04-16 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
CN112814949A (en) * 2021-01-13 2021-05-18 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
WO2023050693A1 (en) * 2021-09-10 2023-04-06 中国民航大学 Axial-flow compressor and method for improving full-circumference flow field

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
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
JP2012062801A (en) * 2010-09-15 2012-03-29 Ihi Corp Axial flow compressor and gas turbine engine
JP2012233424A (en) * 2011-04-28 2012-11-29 Ihi Corp Variable stator blade mechanism of axial flow type compressor
CN103291377A (en) * 2013-06-25 2013-09-11 上海交通大学 Gas compressor multistage stationary blade rigid adjusting mechanism

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
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
JP2012062801A (en) * 2010-09-15 2012-03-29 Ihi Corp Axial flow compressor and gas turbine engine
JP2012233424A (en) * 2011-04-28 2012-11-29 Ihi Corp Variable stator blade mechanism of axial flow type compressor
CN103291377A (en) * 2013-06-25 2013-09-11 上海交通大学 Gas compressor multistage stationary blade rigid adjusting mechanism

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105332952A (en) * 2015-11-02 2016-02-17 南京航空航天大学 Small-bend adjustable stator design method
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
CN107742011A (en) * 2017-09-26 2018-02-27 南京航空航天大学 The design method of the micro- texture of impeller blade drag reduction
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
CN109578335A (en) * 2018-11-27 2019-04-05 中国航发湖南动力机械研究所 Variable camber vane 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
CN112253545A (en) * 2020-12-21 2021-01-22 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
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
CN112814949A (en) * 2021-01-13 2021-05-18 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
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
CN112665861A (en) * 2021-03-18 2021-04-16 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
WO2023050693A1 (en) * 2021-09-10 2023-04-06 中国民航大学 Axial-flow compressor and method for improving full-circumference flow field

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