CN112228403A - Compressor stator blade cascade with equal-depth grooves formed in end wall - Google Patents
Compressor stator blade cascade with equal-depth grooves formed in end wall Download PDFInfo
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- CN112228403A CN112228403A CN202011084778.7A CN202011084778A CN112228403A CN 112228403 A CN112228403 A CN 112228403A CN 202011084778 A CN202011084778 A CN 202011084778A CN 112228403 A CN112228403 A CN 112228403A
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- end wall
- blade
- cascade
- blades
- groove
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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
Abstract
A compressor stator cascade with equal-depth grooves on the end wall. The blade comprises a lower end wall, an upper end wall and a plurality of blades arranged between the lower end wall and the upper end wall side by side; the space between two adjacent blades is a cascade channel, the blades are arc plates, the inner arc surface is a pressure surface, the outer arc surface is a suction surface, the inner arc surface and the outer arc surface are provided with two intersecting lines in the axial direction, wherein the intersecting line close to the air inlet direction is a leading edge line, the intersecting line close to the outlet direction is a trailing edge line, the distance between the leading edge line and the trailing edge line is the chord length of the blades, the height direction of the blades is the unfolding direction, the connecting line direction between the same parts of the two blades is the circumferential direction, the connecting line length is the pitch of the cascade, and the direction perpendicular to the circumferential direction in the plane of the end wall is the axial direction; the surface of the lower end wall, which is positioned in the cascade channel, is sunken downwards to form at least one groove. The method can obviously influence the flow field of the angular region, and under proper design parameters, the circumferential groove-type end wall treatment can effectively reduce the total pressure loss coefficient of the static blade cascade of the compressor and improve the diffusion capacity of the blade cascade.
Description
Technical Field
The invention belongs to the technical field of impeller machinery, and particularly relates to a compressor stator cascade with an end wall provided with an equal-depth groove.
Background
The requirements of aero-engines for high thrust-weight ratio, high efficiency and high stability margin are driving the development of gas compressors toward high load and low aspect ratio. The influence of the stage load improvement on the airflow flow is reflected in the enhancement of the axial counter pressure gradient and the transverse pressure gradient, so that the boundary layer low-energy fluid in the blade channel is easier to accumulate to the suction surface of the blade and the corner area of the end wall, the separation of the three-dimensional corner area is induced, and the flow channel is blocked. And the application of low aspect ratio further increases the radial proportion of the flow channel occupied by the three-dimensional corner region separation. The result of flow separation is the generation of various concentrated vortices in the flow field, whose morphology, structure and evolution determine the aerodynamic performance of the blade. Angular separation (stall) is one of the most important factors affecting secondary flow in the compressor stator cascade, and flow loss near the end wall greatly limits the improvement of the pneumatic performance of the compressor. The effect of corner separation/stall on the compressor is mainly manifested by the formation of low-velocity fluid regions blocking the flow path and introducing strong mixing losses, the former reducing the pressure-rise capacity and stable working range of the compressor, and the latter reducing the efficiency of the compressor. Therefore, it is important to reasonably organize the flow field structure of the compressor corner regions, and to suppress the generation of corner region separation or control the severity of corner region separation.
In a conventional compressor cascade, a diffusion factor is limited to avoid corner stall, and with the progress of research, researchers have proposed various effective flow control methods to control corner flow. The flow control method may be classified into an active control method and a passive control method according to an energy source. The active control method needs external injection of certain energy to control the flow field, such as: jet vortex generator, plasma excitation, boundary layer suction, boundary layer jet flow, oscillation suction, synthetic jet flow and other methods; accordingly, the passive control method does not need to obtain energy from the outside, and the conditions required by flow control are constructed according to a novel structural design, such as: full three-dimensional modeling of the blade, non-axisymmetric endwalls, a fence, a blade slot, and the like. From the viewpoint of practicability and control effect, the above various control methods have respective advantages and limitations. Therefore, the research on the flow control of the diagonal zone is not finished, and a new control method needs to be further explored and tried.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a compressor stator cascade with an end wall provided with an equal-depth groove.
In order to achieve the aim, the compressor stator blade cascade with the end wall provided with the equal-depth grooves comprises a lower end wall, an upper end wall and a plurality of blades arranged between the lower end wall and the upper end wall in parallel; the space between two adjacent blades is a cascade channel, the blades are arc plates, the inner arc surface is a pressure surface, the outer arc surface is a suction surface, the inner arc surface and the outer arc surface are provided with two intersecting lines in the axial direction, wherein the intersecting line close to the air inlet direction is a leading edge line, the intersecting line close to the outlet direction is a trailing edge line, the distance between the leading edge line and the trailing edge line is the chord length of the blades, the height direction of the blades is the unfolding direction, the connecting line direction between the same parts of the two blades is the circumferential direction, the connecting line length is the cascade pitch, and the direction perpendicular to the circumferential direction in the plane of the end wall is the axial direction; when a stator blade cascade of the gas compressor works, the position where the gas flow close to the suction surface on the blade begins to rise along the blade height direction is the starting point of angular region separation of the gas compressor; the surface of the lower end wall is recessed downwards at the position in the cascade channel to form at least one groove.
The bottom surface of the groove is a plane; the axial center line OO 'of the groove is positioned between the separation starting point of the angular region of the suction surface on the blade and the outlet of the blade, the front end surface and the rear end surface are both planes, and the distances from the axial center line OO' of the groove are equal; the shapes of the profiles of the left side surface, the right side surface and the suction surface of the blade at the positions corresponding to the grooves are the same.
The distance between the front end surface or the rear end surface and the axial center line OO' of the groove is 2-10% of the chord length of the blade.
One side surface of the groove is tightly attached to the suction surface of the blade.
The spanwise depth of the groove is 1-5% of the height of the blade; the axial width is 5-15% of the chord length of the blade; the circumferential length is 5-45% of the blade row pitch.
When the grooves are arranged in a plurality, the grooves are arranged in a row or arranged side by side, but the nearest distance between the adjacent grooves is not less than 1 mm.
The compressor stator cascade with the end wall provided with the equal-depth grooves has the following beneficial effects:
the circumferential groove type end wall processing can effectively reduce the total pressure loss coefficient of the static blade cascade of the gas compressor and improve the diffusion capacity of the blade cascade under the condition of proper design parameters (axial position, axial width, length in the pitch direction and radial depth). The method has the advantages of easy processing, no damage to the physical structure of the blade and less influence on the mechanical property of the solid of the blade, and meanwhile, the processing on the end wall has larger operable space than the processing on the blade, and simultaneously has better design and optimized space.
Drawings
Fig. 1 is a perspective view of a partial structure of a compressor stator cascade with equal-depth grooves formed in the end wall.
FIG. 2 is a side view of a compressor stator cascade structure provided with equal-depth grooves in the end wall.
Fig. 3 is a perspective view of a groove structure in a compressor stator cascade with equal-depth grooves formed in the end wall.
FIG. 4 is a limiting flow diagram of a suction surface of a compressor stator cascade with non-grooved end walls.
FIG. 5 is a limiting flow diagram of a suction surface of a stator cascade of an air compressor provided with an end wall provided with an equal-depth groove.
Fig. 6 is a static pressure rise comparison graph of a compressor stator cascade with an end wall provided with an equal-depth groove and a compressor stator cascade with an end wall not provided with a groove.
Fig. 7 is a graph comparing the total pressure loss coefficient of the compressor stator cascade with the end wall provided with the equal-depth groove and the compressor stator cascade with the end wall not provided with the groove.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
As shown in fig. 1-3, the compressor stator cascade with the end wall provided with the equal-depth groove provided by the invention comprises a lower end wall 1, an upper end wall and a plurality of blades 2 arranged between the lower end wall 1 and the upper end wall in parallel; the space between two adjacent blades 2 is a cascade channel, the blades 2 are arc plates, the inner arc surface is a pressure surface 3, the outer arc surface is a suction surface 4, the inner arc surface and the outer arc surface are provided with two intersecting lines in the axial direction, wherein the intersecting line close to the air inlet direction is a leading edge line, the intersecting line close to the outlet direction is a trailing edge line, the distance between the leading edge line and the trailing edge line is the chord length of the blades, the height direction of the blades 2 is the span direction, the connecting line direction between the same parts of the two blades 2 is the circumferential direction, the connecting line length is the cascade pitch, and the direction perpendicular to the circumferential direction in the plane of the end wall is the axial direction; when a stator blade cascade of the compressor works, the position where the airflow close to the suction surface 4 on the blade 2 begins to rise along the blade height direction is the starting point of angular region separation of the compressor; the surface of the lower end wall 1 in the cascade channel is recessed downwards to form at least one groove 5.
The bottom surface of the groove 5 is a plane; the axial center line OO 'of the groove 5 is positioned between the angular separation starting point of the suction surface 4 on the blade 2 and the outlet of the blade 2, the front end surface 9 and the rear end surface 10 are both planes, and the distances from the axial center line OO' of the groove 5 are equal; the profile shapes of the left side surface 8 and the right side surface 7 and the suction surface 4 of the blade 2 at the positions corresponding to the grooves 5 are the same.
The distance between the front end surface 9 or the rear end surface 10 and the axial center line OO' of the groove 5 is 2-10% of the chord length of the blade 2.
One side surface of the groove 5 is tightly attached to the suction surface 4 of the blade 2.
The spanwise depth of the groove 5 is 1-5% of the height of the blade 2; the axial width is 5-15% of the chord length of the blade 2; the circumferential length is 5-45% of the blade row pitch.
When the grooves 5 are arranged in a plurality, the grooves 5 are arranged in a row or arranged side by side, but the nearest distance between the adjacent grooves 5 is not less than 1 mm.
The working principle of the compressor stator cascade with the end wall provided with the equal-depth groove is explained as follows:
when the airflow flows through the cascade channels, a new vortex structure is induced in the groove 5, radial momentum is injected into the near-wall fluid of the blade 2 near the groove 2, the radial migration of low-energy fluid in an angle region is promoted, the accumulation of the low-energy fluid in the angle region is reduced, the capability of resisting a back pressure gradient of the fluid in the angle region is enhanced, and the formation of the separation of the angle region is delayed.
In order to verify the effect of the invention, the inventor carries out numerical simulation on the compressor stator blade cascade with the end wall not provided with the groove and the compressor stator blade cascade with the blade root provided with the equal-depth groove. The specific simulation parameters are as follows:
as shown in fig. 4 and 5, by comparing the polar current limiting line graphs of the suction surfaces 4 on the blades 2 before and after slotting, it can be found that after the end walls are provided with the equal-depth slots, the topological structure of the limiting flow line of the suction surface 4 of the blade 2 on the stator cascade of the compressor is significantly changed, the radial migration of the fluid in the near end wall area of the suction surface 4 is significantly enhanced, the original separation spiral point in the middle of the span of the blade disappears, and the flow field structure is improved.
As shown in fig. 6, by comparing the total pressure loss coefficient and the static pressure rise of the compressor stator blade cascade, it can be seen that the total loss coefficient of the compressor stator blade cascade after grooving is reduced by 8.08%, and the static pressure rise is increased by 0.67%.
Therefore, after the design scheme that the end wall is provided with the equal-depth grooves is adopted, the radial velocity component is introduced into the near-end wall fluid near the groove 5, the flow field structure of the corner area is improved, the pneumatic loss of the cascade is reduced, the static pressure rise is increased, and the performance and the stability of the air compressor are favorably improved.
Claims (6)
1. A compressor stator cascade with equal-depth grooves formed in the end wall comprises a lower end wall (1), an upper end wall and a plurality of blades (2) arranged between the lower end wall (1) and the upper end wall side by side; the space between two adjacent blades (2) is a cascade channel, the blades (2) are arc plates, the inner arc surface is a pressure surface (3), the outer arc surface is a suction surface (4), the inner arc surface and the outer arc surface are provided with two intersecting lines in the axial direction, wherein the intersecting line close to the air inlet direction is a leading edge line, the intersecting line close to the outlet direction is a trailing edge line, the distance between the leading edge line and the trailing edge line is the chord length of the blades, the height direction of the blades (2) is the unfolding direction, the connecting line direction between the same parts of the two blades (2) is the circumferential direction, the connecting line length is the cascade pitch, and the direction perpendicular to the circumferential direction in the plane of the end wall is the axial direction; when a stator blade cascade of the compressor works, the position where the airflow close to the suction surface (4) on the blade (2) begins to rise along the blade height direction is the angular region separation starting point of the compressor; the method is characterized in that: the surface of the lower end wall (1) is recessed downwards at the position in the cascade channel to form at least one groove (5).
2. The compressor stator cascade with the end wall provided with the equal-depth grooves according to claim 1, characterized in that: the bottom surface of the groove (5) is a plane; the axial center line OO 'of the groove (5) is positioned between the separation starting point of the angular region of the suction surface (4) on the blade (2) and the outlet of the blade (2), the front end surface (9) and the rear end surface (10) are both planes, and the distances from the axial center line OO' of the groove (5) are equal; the shapes of the profiles of the left side surface (8), the right side surface (7) and the suction surface (4) of the blade (2) at the positions corresponding to the grooves (5) are the same.
3. The compressor stator cascade with the end wall provided with the equal-depth grooves according to claim 1, characterized in that: the distance between the front end surface (9) or the rear end surface (10) and the axial center line OO' of the groove (5) is 2-10% of the chord length of the blade (2).
4. The compressor stator cascade with the end wall provided with the equal-depth grooves according to claim 1, characterized in that: one side surface of the groove (5) is tightly attached to the suction surface (4) of the blade (2).
5. The compressor stator cascade with the end wall provided with the equal-depth grooves according to claim 1, characterized in that: the spanwise depth of the groove (5) is 1-5% of the height of the blade (2); the axial width is 5-15% of the chord length of the blade (2); the circumferential length is 5-45% of the blade row pitch.
6. The compressor stator cascade with the end wall provided with the equal-depth grooves according to claim 1, characterized in that: when the grooves (5) are arranged in a plurality, the grooves (5) are arranged in a row or arranged side by side, but the nearest distance between the adjacent grooves (5) is not less than 1 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011084778.7A CN112228403B (en) | 2020-10-12 | 2020-10-12 | Compressor stator blade cascade with equal-depth grooves formed in end wall |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011084778.7A CN112228403B (en) | 2020-10-12 | 2020-10-12 | Compressor stator blade cascade with equal-depth grooves formed in end wall |
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| Publication Number | Publication Date |
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| CN112228403A true CN112228403A (en) | 2021-01-15 |
| CN112228403B CN112228403B (en) | 2022-07-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011084778.7A Active CN112228403B (en) | 2020-10-12 | 2020-10-12 | Compressor stator blade cascade with equal-depth grooves formed in end wall |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000297789A (en) * | 1999-04-14 | 2000-10-24 | Tokyo Electric Power Co Inc:The | Axial flow compressor |
| CN202140297U (en) * | 2011-07-07 | 2012-02-08 | 西北工业大学 | Combined suction type experimental device for blade grids of air compressor |
| CN103807201A (en) * | 2013-09-30 | 2014-05-21 | 北京航空航天大学 | Combined suction layout method for controlling compressor stator corner separation |
| CN105864105A (en) * | 2016-04-25 | 2016-08-17 | 西北工业大学 | Axial flow compressor stator with in-vitro small blades in hub corner area |
| CN108108549A (en) * | 2017-12-15 | 2018-06-01 | 中国航发沈阳发动机研究所 | A kind of close stream of plane cascade axial velocity compares control method |
| CN111692116A (en) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | Suction method and device based on porous medium material |
-
2020
- 2020-10-12 CN CN202011084778.7A patent/CN112228403B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000297789A (en) * | 1999-04-14 | 2000-10-24 | Tokyo Electric Power Co Inc:The | Axial flow compressor |
| CN202140297U (en) * | 2011-07-07 | 2012-02-08 | 西北工业大学 | Combined suction type experimental device for blade grids of air compressor |
| CN103807201A (en) * | 2013-09-30 | 2014-05-21 | 北京航空航天大学 | Combined suction layout method for controlling compressor stator corner separation |
| CN105864105A (en) * | 2016-04-25 | 2016-08-17 | 西北工业大学 | Axial flow compressor stator with in-vitro small blades in hub corner area |
| CN108108549A (en) * | 2017-12-15 | 2018-06-01 | 中国航发沈阳发动机研究所 | A kind of close stream of plane cascade axial velocity compares control method |
| CN111692116A (en) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | Suction method and device based on porous medium material |
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| CN112228403B (en) | 2022-07-01 |
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