CN104895839A - Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof - Google Patents
Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof Download PDFInfo
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- CN104895839A CN104895839A CN201510191499.3A CN201510191499A CN104895839A CN 104895839 A CN104895839 A CN 104895839A CN 201510191499 A CN201510191499 A CN 201510191499A CN 104895839 A CN104895839 A CN 104895839A
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Abstract
The invention relates to an axial-flow compressor stator blade system with adjustable first and second half segments and a working method thereof and belongs to the field of mechanical technology of impellers. A single-stage stator blade is divided into a first half segment adjustable blade (1) and a second half segment adjustable blade (4). Sleeve ring structures (3) of the first and second half segment adjustable blades are connected via a connection cylinder (2). The connection cylinder (2) is arranged at the biggest thickness part of the last-stage stator blade and installed between an external casing and a stator inner ring. A stepping motor rotates so as to drive a worm, a worm wheel, a rotation ring, a cylindrical pulling block, and the first half or second half segment blade to rotate and move successively, thereby achieving adjustment of angles. Compared with the prior art, the stator blade system is advantageous in that 1) for a middle-stage stator blade, by rotating the first half segment blade, the blade is arranged at a favorable attack angle, and by rotating the second half segment blade, a rotator at the backward position of the stator is arranged at a favorable attack angle; and 2) an adjusting mechanism is simple and easy to realize in engineering.
Description
Technical field
The present invention relates to adjustable axial flow compressor stator blade system of front second half section and method of work thereof, belong to impeller machinery technical field.
Background technique
For industrial axial flow compressor or gas turbine engine axial flow compressor, in order to expand its efficiency operation scope, can adopt stator blade established angle can conditioning technology.As: the article that what Linder, c.G.and Jones.B.A delivered is entitled as " Single-stage experimental evaluation of variable geometry guide vanes and stators. Part II annular cascade investigations of candidate variable geometry designs " (NASA CR-54555,1967).
For first order entry guide vane, adopt established angle adjustable, the larger positive incidence of vane inlet or negative angle of attack can be caused, cause loss to increase.Grahl, and Tabakoff k., W. " Off-design behavior for axial flow compressor stages with invariable and variable geometry the blades " (AD 767265 delivered in 1967, Sep.1973) propose leading portion fix, back segment rotor blade structure, constant to realize entrance angle when blade outlet angle adjusts, make blade be in the favourable angle of attack (not causing the low loss flow inlet angle of blade surface flow separation) all the time.
For afterbody stator, exit flow flow direction need retainer shaft to, usual afterbody (final stage) stator is non-adjustable.Therefore along with the change of gas compressor working state, final stage stator works under may being in the larger positive and negative angle of attack, causes loss to increase.The patent of invention of straight expensive, Li Qi application " first half section is adjustable stator blade " (number of patent application: propose 201510000610.6) that a kind of first half section is adjustable, the second half section fixes stator, be applicable to non-level stator, improve its off-design performance.
But for the intergrade stator of multi stage axial flow compressor, along with the change of gas compressor working state, the inlet air flow angle change of its upstream rotor exit flow that is this intergrade stator upstream; And this stator downstream rotor inlet air flow direction also can respective change.Therefore for gas compressor intergrade stator blade, need blade first half section adjustable to make intergrade stator blade itself be in the favourable angle of attack; Second half section is adjustable to make this stator downstream rotor be in the favourable angle of attack.
Summary of the invention
The object of the invention is to propose adjustable axial flow compressor stator blade system of a kind of front second half section and method of work thereof, be adapted to axial flow compressor intergrade stator, reach the adjustment to the adjustment of self angle of attack of intergrade stator blade and its downstream rotor angle of attack, improve gas compressor efficient operating regime.
The axial flow compressor stator blade system that the front second half section is adjustable, is characterized in that: be made up of single-stage stator and stator controlling mechanism; Above-mentioned single-stage stator comprises some stator blades and stator inner ring; Each stator blade forms by first half section blade, second half section blade and connecting cylinder; The first half section blade first half has thimble structure, and second half section blade Lower Half has thimble structure; Described first half section blade, second half section blade and connecting cylinder are connected by thimble structure and form stator intact leaf, first half section blade, leave radial clearance between second half section blade and connecting cylinder; Described connecting cylinder is positioned at formed stator intact leaf maximum ga(u)ge place; Outer casing is a point half formula casing, and stator inner ring is also divided into two semi-rings; Described connecting cylinder is installed between outer casing and stator inner ring; Above-mentioned stator controlling mechanism comprises first half section propeller regulating mechanism and second half section propeller regulating mechanism; Wherein first half section propeller regulating mechanism is made up of the first turning collar and the first turning collar driving mechanism; Above-mentioned outer casing has the first annular groove, and the first half section blade of above-mentioned each stator blade all has the first cylindricality and affects block, and the first turning collar is positioned at the first annular groove, and affects block to be connected with all first cylindricalitys; First turning collar driving mechanism drives the first turning collar to rotate, and affects block to drive first half section blade to carry out first half section adjustment of blade angle by the first cylindricality; Above-mentioned second half section propeller regulating mechanism is made up of the second turning collar and the second turning collar driving mechanism; Above-mentioned outer casing has the second annular groove, and the second half section blade of above-mentioned each stator blade all has the second cylindricality and affects block, and the second turning collar is positioned at the second annular groove, and affects block to be connected with all second cylindricalitys; Second turning collar driving mechanism drives the second turning collar to rotate, and affects block to drive second half section blade to carry out second half section adjustment of blade angle by the second cylindricality.
The described method of work for the adjustable stator blade system of second half section before axial flow compressor intergrade, is characterized in that comprising following process: step 1, described single-stage stator are as the intergrade stator of axial flow compressor; Intergrade stator blade profile is obtained by Blade Design Method, and the adjustable first half section blade of intergrade stator and second half section blade do not rotate the intergrade stator blade profile be under design conditions; Step 2, calculate various operating mode upstream rotor blade exit flow angle, rotate intergrade stator first half section blade accordingly, make its import be in the favourable angle of attack; Step 3, calculate various operating mode downstream rotor vane inlet flow angle, rotate intergrade stator second half section blade accordingly, make its downstream rotor import be in the favourable angle of attack; Step 4, according to geometrical relationship, by the angle of the deflection of adjustable first half section blade and adjustable second half section blade, calculate the rotation angle of the turning collar needs be connected with front second half section blade respectively; Stepper motor stroke is determined further by calculating.
Above-mentioned first turning collar driving mechanism is identical, specific as follows with the second turning collar driving machine structure: comprise stepper motor, the screw mandrel be arranged on turning collar, also comprises and is installed on stepper motor output shaft and the worm screw coordinated with screw mandrel.
This invention has following advantage compared with the prior art: 1) this blade can be made for intergrade stator self to be in the favourable angle of attack by rotating first half section blade; Rotating second half section blade can make this stator downstream rotor be in the favourable angle of attack; 2) controlling mechanism simple, be easy to Project Realization.
The adjustable front second half section stator blade structure that this invention proposes, industrial axial flow compressor or gas turbine engine axial flow compressor intergrade stator can be directly used in or need to carry out the entry guide vane of section angle adjustment before and after blade and non-level stator, improve gas compressor efficiency operation scope and expand stable operation range.
Accompanying drawing explanation
Second half section adjustable stator blade structure leaf height direction projection before Fig. 1;
Second half section adjustable stator blade structure leaf height side projection before Fig. 2;
Second half section adjustable stator blade structure sectional view before Fig. 3;
Fig. 4 blade installs meridian plane direction projection on gas compressor;
Fig. 5 first turning collar and worm-and-wheel gear;
Number in the figure title: 1. first half section blade, 2. connecting cylinder, the 3. collar, 4. second half section blade, 5-1. first cylindricality affects block, 5-2. second cylindricality affects block, 6. outer casing, 7-1. first annular groove, 7-2. second annular groove, 8-1. first turning collar, 8-2. second turning collar, 9-1. upstream rotor blade, 9-2. downstream rotor blade, 10. stator inner ring, 11. wheel hubs, 12. rotation angles, 13. Worm gear feed screws, 14. worm screws, 15. stepper motors.
specific implementation method
Below in conjunction with Fig. 1 to Fig. 5, second half section adjustable stator blade implementation methods before the present invention is described.Before stator blade, second half section combination forms stator blade entirety, blade integral design method design routinely, namely flow angle is imported and exported along the distribution of leaf height according to design point stator blade, carry out along several two-dimentional blade designs of leaf height direction, higher by long-pending for these two-dimentional blade profiles folded formation three dimendional blade along leaf.Three dimendional blade profile according to above design selectes connecting cylinder 2 external diameter and residing leaf position (near maximum blade thickness); And then blade is divided into first half section blade 1 and second half section blade 4.First half section blade 1 adds man-hour, and the first half processes the collar 3, second half section blade 4 adds man-hour, and Lower Half processes the collar 3; Front second half section blade is connected and leaves gap by the collar can relatively rotate with connecting cylinder.Before connecting cylinder and blade, the second half section forms overall stator blade; Connecting cylinder two ends to be inserted in outer casing 6 and stator inner ring 10 in hole, realize stator blade outside on casing with the installation of stator inner ring.The position of block is affected to determine the mounting point of associated turning collar outside on casing according to cylindricality on front second half section blade; According to turning collar with install and the size of the Worm gear feed screw 13 on it and the worm screw 14 coordinated, stepper motor 15 and position, determine outer casing is slotted shape, size; Slot and be divided into two-part, be roughly a circular groove (installation turning collar) and a rectangle groove (install stepper motor, worm screw and leave space for worm movement).It is rotatable that turning collar is arranged on outer casing groove planted agent, and stepper motor casing is adopted be screwed outside.First half section blade and second half section blade respectively fill a set of angle adjusting mechanism be made up of turning collar, worm and gear, stepper motor.
Specific implementation process.According to second half section rotation angle requirement before blade, calculate the rotation angle 12 of the turning collar needs be connected with front second half section blade respectively; Stepper motor stroke is determined further by calculating.Stepper motor rotates and successively drives worm screw rotation, worm gear wheel, turning collar rotation, cylindricality to affect block motion, first half section or second half section blade rotation.
Claims (3)
1. the axial flow compressor stator blade system that before, the second half section is adjustable, is characterized in that:
Be made up of single-stage stator and stator controlling mechanism;
Above-mentioned single-stage stator comprises some stator blades and stator inner ring (10); Each stator blade forms by first half section blade (1), second half section blade (4) and connecting cylinder (2); First half section blade (1) first half has thimble structure, and second half section blade (4) Lower Half has thimble structure; Described first half section blade (1), second half section blade (4) and connecting cylinder (2) are connected by thimble structure and form stator intact leaf, first half section blade, leave radial clearance between second half section blade and connecting cylinder (2); Described connecting cylinder (2) is positioned at formed stator intact leaf maximum ga(u)ge place; Outer casing (6) is a point half formula casing, and stator inner ring (10) is also divided into two semi-rings; Described connecting cylinder (2) is installed between outer casing (6) and stator inner ring (10);
Above-mentioned stator controlling mechanism comprises first half section propeller regulating mechanism and second half section propeller regulating mechanism;
Wherein first half section propeller regulating mechanism is made up of the first turning collar (8-1) and the first turning collar driving mechanism; Above-mentioned outer casing (6) has the first annular groove (7-1), the first half section blade (1) of above-mentioned each stator blade all has the first cylindricality and affects block (5-1), first turning collar (8-1) is positioned at the first annular groove (7-1), and affects block (5-1) to be connected with all first cylindricalitys; First turning collar driving mechanism drives the first turning collar (8-1) to rotate, and affects block (5-1) to drive first half section blade (1) to carry out first half section adjustment of blade angle by the first cylindricality;
Above-mentioned second half section propeller regulating mechanism is made up of the second turning collar (8-2) and the second turning collar driving mechanism; Above-mentioned outer casing (6) has the second annular groove (7-2), the second half section blade (4) of above-mentioned each stator blade all has the second cylindricality and affects block (5-2), second turning collar (8-2) is positioned at the second annular groove (7-2), and affects block (5-2) to be connected with all second cylindricalitys; Second turning collar driving mechanism drives the second turning collar (8-2) to rotate, and affects block (5-2) to drive second half section blade (4) to carry out second half section adjustment of blade angle by the second cylindricality.
2. the axial flow compressor stator blade system that the front second half section according to claim 1 is adjustable, is characterized in that: above-mentioned first turning collar driving mechanism is identical, specific as follows with the second turning collar driving machine structure:
Comprise stepper motor (15), the screw mandrel (13) be arranged on turning collar, also comprise and be installed on stepper motor (15) output shaft and the worm screw (14) coordinated with screw mandrel (13).
3. the method for work for the adjustable stator blade system of second half section before axial flow compressor intergrade according to claim 1, is characterized in that comprising following process:
Step 1, described single-stage stator are as the intergrade stator of axial flow compressor; Intergrade stator blade profile is obtained by Blade Design Method, and the adjustable first half section blade (1) of intergrade stator and second half section blade (4) do not rotate the intergrade stator blade profile be under design conditions;
Step 2, calculate various operating mode upstream rotor blade (9-1) outlet flow angle, rotate intergrade stator first half section blade (1) accordingly, make its import be in the favourable angle of attack;
Step 3, calculate various operating mode downstream rotor blade (9-2) inlet air flow angle, rotate intergrade stator second half section blade (4) accordingly, make its downstream rotor (9-2) import be in the favourable angle of attack;
Step 4, according to geometrical relationship, by the angle of the deflection of adjustable first half section blade (1) and adjustable second half section blade (4), calculate the rotation angle (12) of the turning collar needs be connected with front second half section blade respectively; Stepper motor stroke is determined further by calculating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510191499.3A CN104895839A (en) | 2015-04-22 | 2015-04-22 | Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510191499.3A CN104895839A (en) | 2015-04-22 | 2015-04-22 | Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof |
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| CN104895839A true CN104895839A (en) | 2015-09-09 |
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| CN201510191499.3A Pending CN104895839A (en) | 2015-04-22 | 2015-04-22 | Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof |
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Cited By (7)
| 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 |
| CN107725476A (en) * | 2017-09-27 | 2018-02-23 | 江苏科技大学海洋装备研究院 | A kind of adjustable hydraulic propeller of blade-section |
| CN110030111A (en) * | 2019-04-04 | 2019-07-19 | 中国航发沈阳发动机研究所 | A kind of variable cycle engine core engine driving fan level structure |
| CN111112950A (en) * | 2019-12-24 | 2020-05-08 | 浙江水利水电学院 | High-speed inducer applicable to low-temperature environment and manufacturing method thereof |
| CN111140341A (en) * | 2019-12-20 | 2020-05-12 | 中国北方发动机研究所(天津) | Segmented adjustable blade vaned diffuser structure |
| CN111664122A (en) * | 2020-06-05 | 2020-09-15 | 中国航发沈阳发动机研究所 | Stator guide blade at outlet of outer duct |
| CN114321019A (en) * | 2021-12-27 | 2022-04-12 | 中国航发沈阳发动机研究所 | Adjustable stator structure of gas compressor |
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Cited By (10)
| 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 |
| CN107725476A (en) * | 2017-09-27 | 2018-02-23 | 江苏科技大学海洋装备研究院 | A kind of adjustable hydraulic propeller of blade-section |
| CN107725476B (en) * | 2017-09-27 | 2019-03-05 | 江苏科技大学海洋装备研究院 | A kind of adjustable hydraulic propeller of blade-section |
| CN110030111A (en) * | 2019-04-04 | 2019-07-19 | 中国航发沈阳发动机研究所 | A kind of variable cycle engine core engine driving fan level structure |
| CN110030111B (en) * | 2019-04-04 | 2022-02-18 | 中国航发沈阳发动机研究所 | Variable cycle engine core machine driving fan level structure |
| CN111140341A (en) * | 2019-12-20 | 2020-05-12 | 中国北方发动机研究所(天津) | Segmented adjustable blade vaned diffuser structure |
| CN111112950A (en) * | 2019-12-24 | 2020-05-08 | 浙江水利水电学院 | High-speed inducer applicable to low-temperature environment and manufacturing method thereof |
| CN111112950B (en) * | 2019-12-24 | 2021-01-12 | 浙江水利水电学院 | High-speed inducer applicable to low-temperature environment and manufacturing method thereof |
| CN111664122A (en) * | 2020-06-05 | 2020-09-15 | 中国航发沈阳发动机研究所 | Stator guide blade at outlet of outer duct |
| CN114321019A (en) * | 2021-12-27 | 2022-04-12 | 中国航发沈阳发动机研究所 | Adjustable stator structure of gas compressor |
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Application publication date: 20150909 |