CN114046271A - Chord length adjustable axial flow compressor transonic stage stationary blade - Google Patents
Chord length adjustable axial flow compressor transonic stage stationary blade Download PDFInfo
- Publication number
- CN114046271A CN114046271A CN202111371857.0A CN202111371857A CN114046271A CN 114046271 A CN114046271 A CN 114046271A CN 202111371857 A CN202111371857 A CN 202111371857A CN 114046271 A CN114046271 A CN 114046271A
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- Prior art keywords
- blade
- transonic
- section
- movable section
- tail end
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Classifications
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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
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
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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
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
Abstract
The invention provides a chord length adjustable transonic stator blade of an axial flow compressor, which comprises a blade body and a blade movable section, wherein a sliding groove is formed in the blade body, the outer end of the sliding groove extends to the tail end of the blade body, and the blade movable section is movably arranged in the sliding groove of the blade body along the extending direction of the sliding groove; when the blade movable section is located at the initial position, the tail end of the blade movable section is connected with the tail end of the blade body, the tail end of the blade movable section and the tail end of the blade body form the tail edge of the transonic stator blade of the axial flow compressor together, and the transonic stator blade of the axial flow compressor has the minimum chord length. In this application, the movable section of blade is portable in the spout of blade body, adjusts the chord length of the quiet leaf of the transonic stage of axial compressor machine through the extension length of adjusting the movable section of blade in from the spout for quiet leaf chord length can be adjusted along with the working condition is nimble, reduces shock wave loss and the relief angle under the design operating mode from this, and improves the surge margin under the variable operating mode.
Description
Technical Field
The invention relates to the field of gas compressors, in particular to a transonic stator blade of an axial flow gas compressor with adjustable chord length.
Background
With the development of the compressor in the direction of high pressure ratio, large flow and wide working range, it becomes more important to expand the attack angle range of safe operation of the blade, reduce the loss of the blade and improve the uniformity of the airflow at the outlet of the blade. The large change of the attack angle can cause the flow stall inside the blade and the efficiency of the compressor is suddenly reduced; when the extreme working condition is approached, the drop angle change is large, so that the air flow at the outlet of the air compressor deviates from the axial direction, and larger loss is brought downstream.
The axial flow compressor stator blade mainly plays a role in adjusting the airflow direction and boosting pressure. For the regulation of the compressor stator blade, the current idea is mainly to regulate the angle of the compressor stator blade and prevent the compressor from surging by regulating and controlling the angle of the stator blade in the process of starting and stopping the compressor. Due to the requirement of the rotatable blade profile angle, gaps are inevitably formed between blade profile sections, and the curvature of the blade profile is greatly changed at a rotating shaft along with the increase of the rotating angle, so that the development of a blade profile surface boundary layer is not facilitated. Factors influencing the aerodynamic performance of the compressor blade have chord lengths besides the blade inlet angle, and the change of the chord lengths means the change of a blade diffusion factor, and particularly for transonic blades, the appropriate chord length adjustment can effectively reduce the surface shock wave loss of the blades.
However, the chord length of the prior axial compressor vanes is fixed and non-adjustable. Such as: chinese utility model with the license number CN205858782U discloses an axial flow fan blade profile with high efficiency and equal width, but its flap is fixedly connected with the main blade, resulting in the blade chord length not being flexibly adjusted with the variable working condition. For another example: the invention patent with the publication number of CN102996328B discloses an extension piece of a fan rotor blade, but the extension piece is bonded to the rotor blade through an adhesive layer, so that the chord length of the blade cannot be flexibly adjusted along with the working conditions. For another example: chinese utility model with the authorized bulletin number of CN203770214U discloses a large-scale axial flow fan impeller with a flap, but the flap is fixedly connected between the inner end and the hub, resulting in that the chord length of the blade can not be flexibly adjusted with changing the working condition.
Disclosure of Invention
In view of the above-mentioned shortcomings of the prior art, an object of the present invention is to provide a chord length adjustable transonic stator blade of an axial compressor, which can reduce shock wave loss and drop angle and improve surge margin under variable working conditions.
In order to achieve the purpose, the invention provides a transonic stator blade of an axial flow compressor with adjustable chord length, which comprises a blade body and a blade movable section, wherein a sliding groove is formed in the blade body, the outer end of the sliding groove extends to the tail end of the blade body, and the blade movable section is movably arranged in the sliding groove of the blade body along the extending direction of the sliding groove;
when the blade movable section is located at the initial position, the tail end of the blade movable section is connected with the tail end of the blade body, the tail end of the blade movable section and the tail end of the blade body form the tail edge of the transonic stator blade of the axial flow compressor together, and the transonic stator blade of the axial flow compressor has the minimum chord length.
Further, the movable section of the blade is a flat plate.
Further, the thickness of the movable section of the blade is the thickness of the tail edge of the transonic stator blade of the axial-flow compressor.
Furthermore, the end surface of the tail end of the movable section of the blade is an arc end surface; when the movable section of the blade is located at the initial position, one end of the arc end surface of the tail end of the movable section of the blade is tangent to the tail end of the suction surface of the blade body, and the other end of the arc end surface of the tail end of the movable section of the blade is tangent to the tail end of the pressure surface of the blade body.
Preferably, the trailing section of the suction side and the trailing section of the pressure side of the blade body are both approximately straight line segments.
Furthermore, the axial compressor transonic stator blade further comprises a control system and an execution mechanism, wherein the execution mechanism comprises an adjusting driving source and a transmission assembly, the adjusting driving source is connected with the movable section of the blade through the transmission assembly, and the adjusting driving source is in communication connection with the control system.
Furthermore, the transonic stator blade of the axial-flow compressor further comprises two slide rails, the two slide rails are respectively arranged in the upper end wall and the lower end wall of the compressor cylinder, the two slide rails are distributed at the upper end and the lower end of the movable section of the blade along the direction perpendicular to the moving direction of the movable section of the blade, and the upper end and the lower end of the movable section of the blade are clamped in the slide rails and are in sliding fit with the slide rails.
Preferably, the sliding groove extends straight in the axial direction of the blade body.
Further, the maximum length of the movable blade section extending out of the sliding groove is half of the length of the movable blade section.
As described above, the axial flow compressor transonic stator blade with adjustable chord length according to the present invention has the following beneficial effects:
in this application, the movable section of blade is portable in the spout of blade body, adjusts the chord length of the quiet leaf of the transonic stage of axial compressor machine through the extension length of adjusting the movable section of blade in from the spout for quiet leaf chord length can be adjusted along with the working condition is nimble, reduces shock wave loss and the relief angle under the design operating mode from this, and improves the surge margin under the variable operating mode. Through arranging two slide rails that parallel, make the upper and lower both ends sliding fit ground joint of blade movable section in the slide rail, can guarantee that no matter quiet leaf is parallel flow channel or non-parallel flow channel, hardly there is the air current to reveal.
Drawings
Fig. 1 is a schematic structural diagram of a transonic stator blade of an axial flow compressor according to the present application when a movable section of the blade is in an initial position.
Fig. 2 and 3 are schematic structural views of a transonic stator blade of an axial flow compressor according to the present application when a movable section of the blade extends to the maximum length.
Fig. 4 is a schematic flow path diagram of a transonic stator blade of a axial flow compressor according to the present application when a movable section of the blade is in an initial position.
Fig. 5 is a schematic flow path diagram of a transonic stator blade of a axial flow compressor according to the present application when a movable section of the blade extends to a maximum length.
Fig. 6 is a comparison schematic diagram of the isentropic mach number of the blade profile surface of the blade with the blade height section of 10% at the design point before and after the blade movable section of the transonic stator blade of the axial flow compressor extends to 20% of the chord length.
Fig. 7 is a comparison schematic diagram of the distribution of the blade height exit angles of the variable blade sections of the transonic stator blades of the axial flow compressor before and after the blade movable sections extend out to 20% of chord length and at different design points.
Fig. 8 is a comparison schematic diagram of the total pressure loss of different blade heights at design points before and after the movable section of the transonic stator blade of the axial flow compressor extends to 20% of chord length.
Description of the element reference numerals
10 blade body
11 chute
12 suction surface
13 pressure surface
20 blade movable section
21 arc end face
30 trailing edge
40 control system
50 actuator
60 slide rail
70 upper end wall
80 lower end wall
90 leading edge
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure.
It should be understood that the structures, proportions, and dimensions shown in the drawings and described herein are for illustrative purposes only and are not intended to limit the scope of the present invention, which is defined by the claims, but rather by the claims. In addition, the terms such as "upper", "lower", "left", "right", "middle" and "one" used in the present specification are for convenience of description only and are not intended to limit the scope of the present invention, and changes or modifications of the relative relationship thereof may be made without substantial technical changes and modifications.
The application provides a chord length adjustable axial flow compressor transonic stator blade used for a compressor. In the following embodiments, the axial compressor transonic vanes are simply referred to as vanes.
As shown in fig. 1 to 3, the stator blade according to the present application includes a blade body 10 and a blade movable section 20, a sliding groove 11 is formed in the blade body 10, an outer end of the sliding groove 11 extends to a tail end of the blade body 10, the blade movable section 20 is movably installed in the sliding groove 11 of the blade body 10 along an extending direction of the sliding groove 11, and the blade movable section 20 can protrude from the sliding groove 11 and has an adjustable protruding length. In particular, when the blade movable section 20 is in the initial position, as shown in fig. 1, the trailing end of the blade movable section 20 is engaged with the trailing end of the blade body 10, and the two jointly constitute the trailing edge 30 of the transonic vane of the axial compressor, so that the blade body 10 does not have a hollow groove at the trailing end of the chute 11, at which point the transonic vane of the axial compressor has the minimum chord length, and the initial position of the blade movable section 20 is located at the belly of the blade body 10.
In the above-mentioned stator blade, the movable blade section 20 is movable in the sliding slot 11 of the blade body 10, and at a design point, as shown in fig. 1 and 4, the movable blade section 20 is located at an initial position, at which the movable blade section 20 is completely located at the belly of the blade body 10, and the transonic stator blade of the axial flow compressor has a minimum chord length. At a non-design point, the movable blade section 20 is moved in the chute 11 of the blade body 10, and the length of the movable blade section 20 extending from the chute 11 is adjusted according to the system working condition, thereby adjusting the chord length of the stationary blade; such as: the movable blade section 20 is allowed to protrude from the chute 11 to the maximum extent, as shown in fig. 2, 3 and 5, when the axial compressor transonic vane has the maximum chord length. Therefore, the movable blade section 20 which is movable and has adjustable extension length is arranged, so that the chord length of the transonic stator blade of the axial flow compressor can be flexibly adjusted along with the variable working condition, the consistency of the stator blade is changed, the shock wave loss and the drop relief angle under the design working condition are reduced, the surge margin under the variable working condition is improved, and the variable working condition performance is effectively improved.
Further, as shown in fig. 4 and 5, the transonic stator blade of the axial compressor further includes a control system 40 and an actuator 50, the actuator 50 includes an adjusting drive source and a transmission assembly, the adjusting drive source is connected to the blade movable section 20 through the transmission assembly, and the adjusting drive source is connected to the control system 40 in a communication manner; the control system 40 sends an instruction to the adjusting drive source according to the working condition, the adjusting drive source drives the movable blade section 20 to translate through the transmission assembly, the control system 40 controls the actuating mechanism 50 to control the extending distance of the movable blade section 20, and further the chord length of the stationary blade is regulated and controlled, so that the movable blade section 20 can be completely positioned on the belly of the blade body 10 at the design point and can be translated according to the system signal at the non-design point. Preferably, the control system 40 is a gas turbine control system and the regulated drive source is an electric motor.
Further, as shown in fig. 4 and 5, the transonic stator blade of the axial-flow compressor further includes two parallel slide rails 60, the two slide rails 60 are respectively disposed in an upper end wall 70 and a lower end wall 80 of a compressor cylinder, each slide rail 60 extends straight along a translation direction of the movable blade section 20, the two slide rails 60 are distributed at upper and lower ends of the movable blade section 20 along a direction perpendicular to the movement direction of the movable blade section 20, the upper and lower ends of the movable blade section 20 are clamped in the slide rails 60 and are in sliding fit with each other, and a distance between the two slide rails 60 is equal to a height of the movable blade section 20. The movable blade segment 20 is driven by the actuator 50 and translated along the slide rails 60, which ensures that there is little leakage of the flow whether the stationary blade is a parallel flow path or a non-parallel flow path.
Further, as shown in fig. 1 to 3, the blade movable section 20 is a flat plate; the thickness of the blade movable section 20 is the thickness of the trailing edge 30 of the transonic stator blade of the axial compressor. Specifically, the end surface of the tail end of the blade movable section 20 is a circular arc end surface 21; when the blade movable section 20 is located at the initial position, as shown in fig. 1, the upper end of the arc end surface 21 at the tail end of the blade movable section 20 is tangent to the tail end of the suction surface 12 of the blade body 10, and the lower end of the arc end surface 21 at the tail end of the blade movable section 20 is tangent to the tail end of the pressure surface 13 of the blade body 10, so that the engagement between the tail end of the blade movable section 20 and the tail end of the blade body 10 is realized. Moreover, the tail section of the suction surface 12 of the blade body 10 and the tail section of the pressure surface 13 are all approximately straight-line sections, that is, the profile of the suction surface 12 of the blade body 10 near the trailing edge 30 of the stator blade and the profile of the pressure surface 13 of the blade body 10 near the trailing edge 30 of the stator blade are all approximately straight-line, and the part of the movable blade section 20 extending out of the blade body 10 is a plane, so that the curvature change of the turning part of the suction surface 12 after the movable blade section 20 extends out is not too large, as shown in fig. 3.
Preferably, as shown in fig. 1 to 3, the sliding chute 11 extends straight along the axial direction of the blade body 10, the axial direction of the blade body 10 is the axial direction of the stationary blade, that is, the direction in which the stationary blade leading edge 90 faces the trailing edge 30, so the extending path of the blade movable section 20 is the axial direction of the stationary blade; moreover, the maximum length of the blade movable section 20 extending from the sliding chute 11 is half of the length of the blade movable section 20, and the length of the blade movable section 20 is 40% of the minimum chord length of the transonic stator blade of the axial flow compressor, so that the maximum length of the blade movable section 20 extending from the sliding chute 11 is 20% of the minimum chord length of the transonic stator blade of the axial flow compressor, and thus the overall rigidity of the stator blade can be ensured.
Further, the prototype in which the movable blade segment 20 does not protrude from the chute 11 and the vane chord length is the smallest is the fixed-chord length non-adjustable vane, the optimized vane profile in which the vane chord length is the adjustable vane is the largest in which the movable blade segment 20 protrudes from the chute 11, and the numerical simulation of the prototype and the optimized vane profile is performed as shown in fig. 6 to 8. The curve S1 in FIG. 6 is the isentropic Mach number of the blade profile surface with 10% blade height section of the prototype under the design condition, and the curve S2 in FIG. 6 is the isentropic Mach number of the blade profile surface with 10% blade height section of the optimized blade profile under the design condition, so that the attack angle of the root part of the stationary blade is reduced after the movable blade section 20 extends out, the peak value of the isentropic Mach number on the suction surface 12 of the stationary blade is reduced to be less than 1, and the shock wave loss is effectively reduced. The isentropic mach number envelope area near the trailing edge 30 of the stator blade is increased, and work is increased. In fig. 7, a curve X1 is a prototype design point and distribution of outlet angles of different blade heights, and a curve X2 is a curve X2 for optimizing distribution of outlet angles of different blade heights at a design point of a blade profile, so that it can be seen that an outlet angle of the movable blade section 20 after extending out is reduced by more than 1 °, and therefore a stationary blade drop clearance angle can be effectively reduced after the movable blade section 20 extends out, and a function of adjusting the outlet angle of a stationary blade is achieved. The curve P1 in fig. 8 is the prototype design point for the total pressure loss of different blade heights, and the curve P2 in fig. 8 is the optimized design point for the total pressure loss of different blade heights, so that it can be seen that the total pressure loss of different blade heights is reduced after the movable blade section 20 is extended, which corresponds to fig. 6. Further, the variable working condition performance of the gas compressor corresponding to the prototype and the optimized blade profile is calculated, and the surge margin is increased by 6%.
In summary, the chord length adjustable axial flow compressor transonic stator blade according to the present application has almost no air flow leakage when the movable blade section 20 is translated in the axial direction, and the adjustment of the chord length of the stator blade can reduce shock wave loss and drop relief angle under the design working condition, improve the performance of the variable working condition, and improve the surge margin. Therefore, the invention effectively overcomes various defects in the prior art and has high industrial utilization value.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (9)
1. A chord length adjustable axial compressor transonic stator blade comprises a blade body (10) and is characterized in that: the blade moving device is characterized by further comprising a blade moving section (20), a sliding groove (11) is formed in the blade body (10), the outer end of the sliding groove (11) extends to the tail end of the blade body (10), and the blade moving section (20) is movably installed in the sliding groove (11) of the blade body (10) along the extending direction of the sliding groove (11);
when the blade movable section (20) is located at the initial position, the tail end of the blade movable section (20) is connected with the tail end of the blade body (10), and the tail end of the blade movable section and the tail end of the blade body jointly form a tail edge (30) of the transonic stator blade of the axial flow compressor, and the transonic stator blade of the axial flow compressor has the minimum chord length.
2. The axial compressor transonic vane of claim 1, wherein: the movable blade section (20) is a flat plate.
3. The axial compressor transonic vane of claim 1, wherein: the thickness of the blade movable section (20) is the thickness of the trailing edge (30) of the transonic stator blade of the axial-flow compressor.
4. The axial compressor transonic vane of any one of claims 1-3, wherein: the end surface of the tail end of the blade movable section (20) is an arc end surface (21); when the blade movable section (20) is located at the initial position, one end of the arc end surface (21) at the tail end of the blade movable section (20) is tangent to the tail end of the suction surface (12) of the blade body (10), and the other end of the arc end surface (21) at the tail end of the blade movable section (20) is tangent to the tail end of the pressure surface (13) of the blade body (10).
5. The axial compressor transonic vane of claim 4, wherein: the tail section part of the suction surface (12) and the tail section part of the pressure surface (13) of the blade body (10) are both approximate to straight line sections.
6. The axial compressor transonic vane of claim 1, wherein: the blade adjusting mechanism further comprises a control system (40) and an actuating mechanism (50), wherein the actuating mechanism (50) comprises an adjusting driving source and a transmission assembly, the adjusting driving source is connected with the movable blade section (20) through the transmission assembly, and the adjusting driving source is in communication connection with the control system (40).
7. The axial compressor transonic vane of claim 1, wherein: the blade movable section structure is characterized by further comprising two sliding rails (60), wherein the two sliding rails (60) are respectively arranged in an upper end wall (70) and a lower end wall (80) of the compressor cylinder, the two sliding rails (60) are distributed at the upper end and the lower end of the blade movable section (20) along the direction perpendicular to the moving direction of the blade movable section (20), and the upper end and the lower end of the blade movable section (20) are clamped in the sliding rails (60) and are in sliding fit with the sliding rails.
8. The axial compressor transonic vane of claim 1, wherein: the sliding groove (11) extends straightly along the axial direction of the blade body (10).
9. The axial compressor transonic vane of claim 1, wherein: the maximum length of the movable blade section (20) extending out of the sliding chute (11) is half of the length of the movable blade section (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111371857.0A CN114046271A (en) | 2021-11-18 | 2021-11-18 | Chord length adjustable axial flow compressor transonic stage stationary blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111371857.0A CN114046271A (en) | 2021-11-18 | 2021-11-18 | Chord length adjustable axial flow compressor transonic stage stationary blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114046271A true CN114046271A (en) | 2022-02-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111371857.0A Pending CN114046271A (en) | 2021-11-18 | 2021-11-18 | Chord length adjustable axial flow compressor transonic stage stationary blade |
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| Country | Link |
|---|---|
| CN (1) | CN114046271A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115949970A (en) * | 2023-01-05 | 2023-04-11 | 中国航空发动机研究院 | Swirler vane and swirler |
| CN116861703A (en) * | 2023-09-01 | 2023-10-10 | 中国航发上海商用航空发动机制造有限责任公司 | Adjustable stator angle optimization method for air compressor |
-
2021
- 2021-11-18 CN CN202111371857.0A patent/CN114046271A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115949970A (en) * | 2023-01-05 | 2023-04-11 | 中国航空发动机研究院 | Swirler vane and swirler |
| CN115949970B (en) * | 2023-01-05 | 2023-08-22 | 中国航空发动机研究院 | Cyclone blade and cyclone |
| CN116861703A (en) * | 2023-09-01 | 2023-10-10 | 中国航发上海商用航空发动机制造有限责任公司 | Adjustable stator angle optimization method for air compressor |
| CN116861703B (en) * | 2023-09-01 | 2023-11-21 | 中国航发上海商用航空发动机制造有限责任公司 | Adjustable stator angle optimization method for air compressor |
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