CN111219362A - Axial compressor blade, axial compressor and gas turbine - Google Patents
Axial compressor blade, axial compressor and gas turbine Download PDFInfo
- Publication number
- CN111219362A CN111219362A CN201811420727.XA CN201811420727A CN111219362A CN 111219362 A CN111219362 A CN 111219362A CN 201811420727 A CN201811420727 A CN 201811420727A CN 111219362 A CN111219362 A CN 111219362A
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- Prior art keywords
- blade
- flow
- axial
- axial compressor
- blade tip
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
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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
- F04D29/66—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 relates to an axial flow compressor blade, an axial flow compressor and a gas turbine. Wherein, axial compressor, it includes: a pressure sidewall; a blade tip; the flow guide structure is arranged in the area where the blade tip of the pressure side wall is located and extends along the chord direction of the axial flow compressor blade; the flow guide structure is used for increasing separation bubbles formed by airflow passing through the flow guide structure on the outer side of the top end face of the blade tip so as to reduce leakage flow at the blade tip. According to the invention, the flow guide structure is arranged on the pressure side wall of the area where the blade tip is located, the shape of the pressure side wall is changed, the pressure side wall of the blade of the axial-flow compressor and the top end face of the blade tip form a preset angle, and gas flows to the radial gap after being guided by the flow guide structure, so that the separation bubble generated by the leakage flow of the gas outside the top end face of the blade tip is increased, the effective radial gap is reduced, the leakage flow is reduced, the leakage vortex strength is weakened, the loss caused by the gap leakage flow is reduced, and the performance of the axial-flow compressor is improved.
Description
Technical Field
The invention relates to the field of aviation equipment, in particular to an axial flow compressor blade, an axial flow compressor and a gas turbine.
Background
Axial compressors are used as the main components of aircraft engines and gas turbines, and the efficiency of the axial compressors plays a decisive role in the performance of the aircraft engines. In an axial-flow compressor, a radial gap exists between a rotor blade and a casing or between a stator blade and a hub, and gas can generate gap leakage flow when passing through the radial gap under the action of pressure gradients on two sides of the radial gap of the blade. The interaction of the clearance leakage flow and the main flow in the cascade channel leads to increased flow loss and reduced efficiency of the compressor, so that the clearance leakage flow needs to be controlled by some technical means to reduce the loss caused by the leakage flow and improve the performance of the compressor.
Disclosure of Invention
One of the objectives of the present invention is to provide an axial compressor and a gas turbine, which solve the problem of the gap leakage flow to some extent.
Some embodiments of the present invention provide an axial flow compressor, comprising: a pressure sidewall; a blade tip; the flow guide structure is arranged in the area where the blade tip of the pressure side wall is located and extends along the chord direction of the axial flow compressor blade; the flow guide structure is used for increasing separation bubbles formed by airflow passing through the flow guide structure on the outer side of the top end face of the blade tip so as to reduce leakage flow at the blade tip.
Optionally, the flow guide structure extends from the top end surface of the blade tip to the root direction of the axial flow compressor blade.
Optionally, the flow guiding structure extends in a leading edge to trailing edge direction of the axial compressor blade.
Optionally, the flow directing structure is configured as an arc.
Optionally, the flow directing structure comprises a groove.
Optionally, the groove is configured to extend from a pressure side of the axial compressor blade in a direction toward a suction side of the axial compressor blade.
Optionally, the flow directing structure comprises a protrusion.
Optionally, the projection is configured to extend from a pressure side of the blade in a direction away from a suction side of the blade.
Optionally, the protrusion gradually protrudes from a position away from the top end surface of the blade tip to the top end surface of the blade tip.
Some embodiments of the invention provide an axial flow compressor comprising the axial flow compressor blade described above.
Optionally, the axial-flow compressor blade further comprises a casing and a hub, the axial-flow compressor blade comprises a rotor blade and a stator blade, the blade root of the rotor blade is arranged on the hub, a first radial gap is formed between the blade tip of the rotor blade and the casing, the blade root of the stator blade is arranged on the casing, and a second radial gap is formed between the blade tip of the stator blade and the hub.
Some embodiments of the invention provide a gas turbine comprising the axial compressor described above.
Based on the technical scheme, the invention at least has the following beneficial effects:
in some embodiments, the flow guide structure is arranged on the pressure side wall of the region where the blade tip is located, the shape of the pressure side wall is changed, the pressure side wall of the blade of the axial-flow compressor and the top end face of the blade tip form a preset angle, and after being guided by the flow guide structure, gas flows to the radial gap, so that separation bubbles generated by the gas flowing due to leakage outside the top end face of the blade tip are increased, the effective radial gap is reduced, the leakage flow is reduced, the leakage vortex strength is weakened, the loss caused by the gap leakage flowing is reduced, and the performance of the axial-flow compressor is improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a partial schematic view of an axial compressor inner blade arrangement;
FIG. 2 is a schematic radial clearance leakage flow diagram illustrating a tip clearance of a rotor blade;
FIG. 3 is a schematic view of a first embodiment of an axial compressor blade provided by the present invention;
3 FIG. 3 4 3 is 3 a 3 cross 3- 3 sectional 3 view 3 of 3 the 3 radial 3 clearance 3 leakage 3 flow 3 of 3 the 3 axial 3 compressor 3 blade 3 A 3- 3 A 3 shown 3 in 3 FIG. 3 3 3; 3
FIG. 5 is a schematic view of a second embodiment of an axial compressor blade provided by the present invention;
FIG. 6 is a schematic radial clearance leakage flow diagram of the axial compressor blade shown in FIG. 5.
The reference numbers in the drawings:
1-axial compressor blades; 11-pressure side wall; 12-blade tip; 13-pressure side; 14-suction side; 15-rotor blades; 16-stator blades;
2-a flow guide structure; 21-a groove; 22-a bump;
3-a casing;
4-a hub;
5-a first radial gap;
6-a second radial gap;
7-separation of the bubbles.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without any inventive step, are within the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
As shown in fig. 1, the axial compressor includes a casing 3, a hub 4, rotor blades 15, and stator blades 16. The root of the rotor blade 15 is arranged at the hub 4, and a first radial gap 5 exists between the tip of the rotor blade 15 and the casing 3. The root of the stator blade 16 is arranged in the casing 3, and a second radial gap 6 is formed between the tip of the stator blade 16 and the hub 4. The first radial gap 5 and the second radial gap 6 are collectively referred to as a radial gap. When gas flows through the radial gap, secondary flow, i.e., gap leakage flow, is caused by the pressure gradient on both sides of the radial gap of the vane.
The inventor finds out through research that: the clearance leakage flow is significantly affected by the height of the radial clearance, the shape of the blade tip, the static pressure difference on both sides of the radial clearance, and the like. And when leakage gas flows through the radial clearance, separation bubbles can be formed on the outer side of the top end face of the blade tip, and a contraction effect is generated, so that the effective clearance is smaller than the geometric clearance.
As shown in fig. 2, the first radial gap 5 formed between the rotor blade 15 and the casing 3 is taken as an example for analysis. The same applies to the second radial gap 6 formed between the stator blade 16 and the hub 4.
The height of the first radial gap 5 (geometric tip clearance) formed between the tip end surface of the rotor blade 15 and the casing 3 is τ, but when gas flows through the first radial gap 5, tip leakage flow is generated, and a tip separation bubble 7 is generated at the first radial gap 5 (a flow separation phenomenon in a dashed line frame corresponding to reference numeral 7 in fig. 2), so that the flow area at the first radial gap 5 is changed, which reduces the actual flow clearance height at the first radial gap 5 from τ to σ. The effective tip clearance height is σ when there is gas flow through the first radial clearance 5.
The axial flow compressor blade provided by the disclosure reduces the limited clearance height sigma by increasing the separation bubble outside the top end surface of the blade tip, thereby achieving the purpose of reducing the leakage flow and further reducing the loss caused by clearance leakage.
Referring to fig. 3 and 5, an axial compressor blade according to some embodiments of the present invention is provided.
In some embodiments, the axial compressor blade includes a pressure sidewall 11. The axial compressor blade also includes a suction sidewall. The position of the pressure side wall 11 of the axial flow compressor blade is a pressure side 13, and the position of the suction side wall of the axial flow compressor blade is a suction side 14. The direction between the pressure side 13 and the suction side 14 of the axial compressor blade is chordal.
The axial compressor blade includes a blade tip 12. The axial compressor blades comprise blade roots which are intended to be connected to the casing 3 or to the hub 4.
The axial-flow compressor blade comprises a flow guide structure 2, and the flow guide structure 2 is arranged in the area where the blade tip 12 of the pressure side wall 11 is located.
The flow guide structure 2 extends along the chord direction of the axial flow compressor blade.
The flow guiding structure 2 serves to enlarge the separation bubble 7 formed by the air flow passing through it outside the top end face of the blade tip 12, so as to reduce the leakage flow at the blade tip 12.
In some embodiments, the guide structure 2 is arranged on the pressure side wall 11 of the region where the blade tip 12 is located, and the shape of the pressure side wall 11 is changed, so that the pressure side wall 11 of the axial flow compressor blade and the top end surface of the blade tip 12 form a preset angle, thereby achieving the purpose of increasing the separation bubbles. After the gas is guided by the flow guide structure 2, the gas flows to the radial gap, so that the separation bubble generated by the leakage flow of the gas on the outer side of the top end surface of the blade tip 12 is increased, the effective radial gap is reduced, the leakage flow is reduced, the leakage vortex strength is weakened, the loss caused by the gap leakage flow is reduced, and the purpose of improving the performance of the gas compressor is achieved.
In some embodiments, the flow guiding structure 2 extends from the tip end surface of the blade tip 12 in the direction of the root of the axial compressor blade 1.
One end of the flow guiding structure 2 starts from the top end surface of the blade tip 12.
In some embodiments, the flow guiding structure 2 extends in a leading edge to trailing edge direction of the axial compressor blade 1.
In some embodiments, the flow directing structure 2 is configured as an arc. The guide structure 2 is arranged on the pressure side wall 11 of the axial flow compressor blade, the shape of the pressure side wall 11 is changed, the pressure side wall 11 of the axial flow compressor blade and the top end face of the blade tip 12 form a preset angle, and therefore the purpose of increasing the separation bubbles is achieved.
The flow guide structure 2 is not limited to an arc shape, and the gap leakage flow can be controlled by setting the flow guide structure 2 in different shapes, so that the pneumatic loss caused by the leakage flow is reduced.
In some embodiments, as shown in fig. 4, the flow directing structure 2 comprises a groove 21. The groove 21 is arranged in the area of the blade tip 12 of the pressure side wall 11 to be used as the flow guide structure 2, and is relatively suitable for thicker axial flow compressor blades.
In some embodiments, the groove 21 is configured to extend from the pressure side 13 of the axial compressor blade in a direction toward the suction side 14 of the axial compressor blade.
As shown in fig. 4, after the air flow is guided by the grooves 21, the separation bubbles formed outside the top end surface of the blade tip 12 are increased (relative to the case where no grooves 21 are provided), so that the effective radial clearance height of the end structure of the axial flow compressor blade is σ 1, and σ 1 is smaller than the effective radial clearance height σ when the design of the end structure of the blade is not adopted in the prior art.
In some embodiments, as shown in fig. 6, the flow directing structure 2 comprises protrusions 22. The bulge 22 is arranged in the area of the blade tip 12 of the pressure side wall 11 to serve as the flow guide structure 2, and is relatively suitable for thin axial flow compressor blades.
In some embodiments, the protrusion 22 is configured to extend from the pressure side 13 of the blade in a direction away from the suction side 14 of the blade.
In some embodiments, the bulge 22 gradually bulges from a location away from the top end surface of the blade tip 12 to the top end surface of the blade tip 12.
As shown in fig. 6, after the airflow is guided by the protrusions 22, the separation bubbles formed outside the top end surface of the blade tip 12 are increased (relative to the case where no protrusions 22 are provided), so that the effective radial clearance height of the axial compressor blade tip structure is σ 2, and σ 2 is smaller than the effective radial clearance height σ when the blade tip structure design is not adopted in the prior art.
Some embodiments provide an axial compressor comprising an axial compressor blade 1 as described above.
The axial flow compressor is an impeller mechanical device which has the airflow flowing direction basically parallel to the axis of a rotating impeller and utilizes the rotating mechanical energy to improve the air pressure.
In some embodiments, the axial flow compressor further includes a casing 3 and a hub 4, the axial flow compressor blade 1 includes a rotor blade and a stator blade, the blade root of the rotor blade is disposed on the hub 4, a first radial gap 5 is formed between the blade tip 12 of the rotor blade and the casing 3, the blade root of the stator blade is disposed on the casing 3, and a second radial gap 6 is formed between the blade tip 12 of the stator blade and the hub 4.
Rotor blade and stator blade adopt this disclosure to provide the blade, can reduce effective radial clearance height to reduce the leakage flow, realize the control to clearance leakage flow, reach the purpose that reduces the loss.
Some embodiments provide a gas turbine comprising the axial compressor described above.
In the description of the present invention, it should be understood that the terms "first", "second", "third", etc. are used to define the components, and are used only for the convenience of distinguishing the components, and if not otherwise stated, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present invention.
Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present invention and not to limit the same; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the invention as defined by the appended claims.
Claims (12)
1. An axial flow compressor blade, comprising:
a pressure side wall (11);
a blade tip (12); and
the flow guide structure (2) is arranged in the area where the blade tip (12) of the pressure side wall (11) is located and extends along the chord direction of the axial flow compressor blade; the flow guide structure (2) is used for increasing a separation bubble (7) formed by airflow passing through the flow guide structure outside the top end face of the blade tip (12) so as to reduce leakage flow at the blade tip (12).
2. The axial compressor blade according to claim 1, characterized in that the flow guiding structure (2) extends from the tip end face of the blade tip (12) in the direction of the root of the axial compressor blade (1).
3. The axial compressor blade according to claim 1, characterized in that the flow guiding structure (2) extends in a leading edge to trailing edge direction of the axial compressor blade (1).
4. The axial compressor blade according to claim 1, characterized in that the flow guiding structure (2) is configured as an arc.
5. The axial compressor blade according to any one of claims 1 to 4, characterized in that the flow guiding structure (2) comprises grooves (21).
6. The axial compressor blade according to claim 5, characterized in that the groove (21) is configured to extend from the pressure side (13) of the axial compressor blade in the direction of the suction side (14) of the axial compressor blade.
7. The axial compressor blade according to any one of claims 1 to 4, wherein the flow guiding structure (2) comprises a protrusion (22).
8. The axial compressor blade according to claim 7, wherein the projection (22) is configured to extend from the pressure side (13) of the blade in a direction away from the suction side (14) of the blade.
9. The axial compressor blade of claim 8, wherein the projection (22) is gradually convex from a position away from the top end surface of the blade tip (12) to the top end surface of the blade tip (12).
10. An axial compressor, characterized by comprising an axial compressor blade (1) according to any one of claims 1 to 9.
11. The axial compressor according to claim 10, further comprising a casing (3) and a hub (4), wherein the axial compressor blade (1) comprises a rotor blade and a stator blade, the blade root of the rotor blade is arranged on the hub (4), a first radial gap (5) is formed between the blade tip (12) of the rotor blade and the casing (3), the blade root of the stator blade is arranged on the casing (3), and a second radial gap (6) is formed between the blade tip (12) of the stator blade and the hub (4).
12. A gas turbine comprising an axial compressor according to claim 10 or 11.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811420727.XA CN111219362A (en) | 2018-11-27 | 2018-11-27 | Axial compressor blade, axial compressor and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811420727.XA CN111219362A (en) | 2018-11-27 | 2018-11-27 | Axial compressor blade, axial compressor and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111219362A true CN111219362A (en) | 2020-06-02 |
Family
ID=70810789
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811420727.XA Pending CN111219362A (en) | 2018-11-27 | 2018-11-27 | Axial compressor blade, axial compressor and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111219362A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112283160A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
| CN114046269A (en) * | 2022-01-11 | 2022-02-15 | 中国航发上海商用航空发动机制造有限责任公司 | Rotor blade of axial flow compressor and design method thereof |
| CN114576202A (en) * | 2022-02-28 | 2022-06-03 | 北京航空航天大学 | Blade structure, compressor and compressor control method |
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| CN114046269A (en) * | 2022-01-11 | 2022-02-15 | 中国航发上海商用航空发动机制造有限责任公司 | Rotor blade of axial flow compressor and design method thereof |
| CN114576202A (en) * | 2022-02-28 | 2022-06-03 | 北京航空航天大学 | Blade structure, compressor and compressor control method |
| CN114576202B (en) * | 2022-02-28 | 2022-12-06 | 北京航空航天大学 | Blade structure, compressor and compressor control method |
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