CN115788953A - Kanda jet blade, impeller and axial-flow compressor - Google Patents
Kanda jet blade, impeller and axial-flow compressor Download PDFInfo
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- CN115788953A CN115788953A CN202211633333.9A CN202211633333A CN115788953A CN 115788953 A CN115788953 A CN 115788953A CN 202211633333 A CN202211633333 A CN 202211633333A CN 115788953 A CN115788953 A CN 115788953A
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Abstract
The application discloses a Kanda jet blade, an impeller and an axial-flow compressor, wherein the Kanda jet blade comprises a gas-guiding cavity and a flow deflector, the gas-guiding cavity is provided with a gas-guiding inlet in a first direction, and the gas-guiding cavity is provided with a gas-guiding outlet in a second direction; the flow deflector is arranged in the air leading cavity, and the flow deflector utilizes the coanda wall attachment effect to enhance the turning capacity of the air flow entering the air jet inlet of the air leading cavity from the air leading inlet and ensure that the flow direction of the air flow leaving the air jet outlet of the air leading cavity from the air leading outlet is consistent with the flow direction of the main flow air flow. According to the Konda jet blade, the jet airflow is bent through the flow deflectors in the air guide cavity, so that the fluid directions of the jet airflow and the main flow airflow are consistent, the mixing loss of jet flow and the main flow can be reduced, and kinetic energy is provided for a high-loss area of the suction surface of the blade.
Description
Technical Field
The application relates to the technical field of aero-engines, in particular to a Kanda jet blade. Still relate to an impeller and axial compressor that adopt above-mentioned coanda jet-propelled blade.
Background
The high-performance engine is developed by taking higher thrust-weight ratio and lower oil consumption rate as main directions, the improvement of the efficiency of the engine is widely realized by increasing bypass ratio, reducing exhaust temperature, increasing pressure ratio and the like at present, and the improvement of the pressure ratio of the gas compressor is one of main indexes for improving the performance of the gas compressor.
The development of future aircraft engines can further improve the total pressure ratio of a single stage of the compressor, and the internal flow is more complicated along with the increase of the single-stage load. In compressor design, the pressure ratio is usually increased by increasing the linear speed of the rotor and increasing the deflection angle of the stator airflow. In the actual design of the compressor, the linear speed of the rotor is limited by the rotating speed of the fan, and the radius of the rotor is not too large due to the development of high bypass ratio. Therefore, the stator is usually responsible for the deflection of the air flow and further increases the load, which leads to the increasing of the blade profile bend angle when the compressor stator is designed. Under the strong adverse pressure gradient of the gas compressor, flow loss caused by secondary flows such as boundary layer separation, corner stall, wake mixing and the like is easily generated, and the working stability of the gas compressor is seriously influenced. In order to improve the single-stage load of the compressor, the problem of aggravated flow separation while improving the stator load is urgently needed to be solved. Therefore, how to develop a control method for inhibiting the flow separation of the stator boundary layer and further improving the single-stage load is a problem to be solved at present.
Disclosure of Invention
The utility model aims at providing a kongda air injection blade, the air injection air current is bent via the inside water conservancy diversion piece of air induction cavity for the fluid direction of air injection air current is unanimous with the mainstream air current, can reduce the mixing loss of efflux and mainstream, provides kinetic energy for the high loss district of blade suction surface. Another object of the present application is to provide an impeller and an axial compressor using the coanda jet blade.
To achieve the above object, the present application provides a coanda jet blade comprising:
the device comprises a gas-leading cavity, a gas-leading cavity and a gas-leading cavity, wherein the gas-leading cavity is provided with a gas-leading inlet in a first direction and a gas-leading outlet in a second direction;
the flow deflector is arranged in the air guide cavity, the flow deflector utilizes the coanda wall effect to enhance the turning capacity of the air flow entering the air guide cavity from the air guide inlet, and the air flow leaving the air guide cavity from the air guide outlet is consistent with the fluid direction of the main flow air flow.
In some embodiments, the first direction is perpendicular to the second direction, and a jet inlet airflow enters the bleed cavity at the bleed inlet in the first direction, a jet outlet airflow exits the bleed cavity at the bleed outlet in the second direction, and a main flow of air flows in the second direction.
In some embodiments, the number of the guide vanes is plural, and the plurality of guide vanes are arranged in the blade height direction of the coanda jet blade inside the induction cavity.
In some embodiments, a plurality of the guide vanes are arranged inside the induction cavity at equal intervals in a blade height direction of the coanda jet blade.
In some embodiments, the flow deflector comprises an inlet section and an outlet section, the inlet section being connected to the outlet section, the junction between the inlet section and the outlet section being a smooth transition.
In some embodiments, the first direction is perpendicular to the second direction, and the entrance segment has a first angle a with the first direction, the exit segment has a second angle b with the first direction, the entrance segment has a third angle c with the exit segment, the first angle a is an acute angle, the second angle b is a right angle, and the third angle c is an obtuse angle.
The application also provides an impeller, including above-mentioned kanda jet blade, it is a plurality of kanda jet blade follows the circumference interval of impeller sets up.
The application also provides an axial flow compressor comprising the above coanda jet vane or the above impeller.
Compared with the background art, the coanda jet vane provided by the application comprises a bleed air cavity and a flow deflector, wherein the bleed air cavity is provided with a bleed air inlet in a first direction, and is provided with a bleed air outlet in a second direction; the flow deflector is arranged in the air guide cavity, the flow deflector utilizes the coanda wall attachment effect to enhance the turning capacity of the air flow entering the air guide cavity from the air guide inlet, and the air flow leaving the air guide cavity from the air guide outlet is consistent with the fluid direction of the main flow air flow.
In the working process of the coanda jet blade, the jet air flow is bent by the flow deflector in the air guide cavity, and when the flow deflector is wound, a coanda wall effect is generated, so that the direction of the jet inlet air flow is changed into a jet outlet air flow, and the fluid direction of the jet outlet air flow is consistent with that of the main flow air flow, thereby reducing the mixing loss of jet flow and the main flow and providing kinetic energy for a high loss area of a suction surface of the blade.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, it is obvious that the drawings in the following description are only embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic structural view of a coanda jet blade provided by embodiments of the present application;
fig. 2 is an angle schematic view of a guide vane provided in an embodiment of the present application;
FIG. 3 is a profile of the outlet airflow angle along the blade height provided by an embodiment of the present application.
Wherein:
10-air-entraining cavity and 20-flow deflector;
101-a bleed air inlet, 102-a bleed air outlet;
011-jet inlet airflow, 012-jet outlet airflow and 020-main flow airflow.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In order to enable those skilled in the art to better understand the scheme of the present application, the present application will be described in further detail with reference to the accompanying drawings and the detailed description.
Referring to fig. 1 to fig. 3, fig. 1 is a schematic structural view of a coanda jet blade provided in an embodiment of the present application, fig. 2 is a schematic angle view of a guide vane provided in an embodiment of the present application, and fig. 3 is a distribution diagram of an outlet airflow angle along a blade height provided in an embodiment of the present application.
In a first specific embodiment, the application provides a coanda jet blade, which mainly comprises a bleed air cavity 10 and a flow deflector 20, wherein the bleed air cavity 10 is arranged in a blade body, and the flow deflector 20 is arranged inside the bleed air cavity 10; namely, the Kanda air injection blade adopts the mode that the flow deflector 20 is arranged in the air guide cavity 10 of the Kanda air injection blade, so that the problem that the speed directions of air injection and main flow are inconsistent is solved.
Specifically, the bleed air cavity 10 is provided with a bleed air inlet 101 in a first direction, and is provided with a bleed air outlet 102 in a second direction, the bleed air outlet 102 is located on a suction surface of the coanda jet vane, the bleed air inlet 101 is specifically in the form of an air inlet, and the bleed air outlet 102 is specifically in the form of a jet slot; during the operation of the coanda jet vane, the jet inlet airflow 011 enters the bleed cavity 10 from the bleed inlet 101, the jet airflow is bent by the guide vane 20 inside the bleed cavity 10, the guide vane 20 enhances the turning capability of the jet airflow by utilizing the coanda effect, the jet outlet airflow 012 leaves the bleed cavity 10 from the bleed outlet 102, and the jet outlet airflow 012 and the main airflow 020 are in the same direction at this time.
The coanda jet blade causes the jet airflow to generate coanda effect when the jet airflow flows around the flow guide sheet 20, so that the jet inlet airflow 011 changes direction to be jet outlet airflow 012, and the jet outlet airflow 012 is consistent with the fluid direction of the main flow airflow 020, thereby reducing the mixing loss of jet flow and main flow and providing kinetic energy for a high loss area of the suction surface of the blade.
For the stator, the current method for constantly controlling the flow separation of the boundary layer mainly comprises boundary layer air injection and boundary layer suction, and the coanda air injection technology referred to herein is different from the traditional boundary layer air injection technology. The coanda jet is that the coanda effect of fluid flow is fully utilized, the coanda surface is applied to the suction surface of the blade to carry out slotted jet, and the coanda effect of wall surface jet flow and the carrying effect of the wall surface jet flow on the main flow are utilized to inhibit the flow separation of the boundary layer.
The rationale for the coanda jet technology is to utilize the coanda effect. The coanda effect is also known as the coanda effect or coanda effect. The coanda effect indicates that when a smooth flow of fluid passes over a convex surface, the fluid adheres to the surface. This force is named by romania aerodynamicists henry kanda. When water flows through the convex surface of the soup ladle, fluid can be attached to the soup ladle to generate a wall attachment effect, and the generation of the wall attachment effect is also the main principle of most airplane wings. During design of part of airplanes, the coanda effect is fully utilized, and the lift force of the airplane is improved by blowing airflow out of the engine.
The jet flow fluid of the traditional boundary layer and the main flow fluid form a certain included angle to further increase the flowing mixing loss, and the jet flow fluid generated by the coanda jet is consistent with the main flow fluid in direction, so that the mixing loss of the jet flow and the main flow can be reduced. The existing research shows that the smaller the included angle between the jet flow direction and the main flow direction is, the more obvious the control effect is. The purpose of the present application is to make the flow direction of the jet outlet air flow 012 and the main flow 020 consistent, reduce the mixing loss of the jet flow and the main flow, and provide kinetic energy to the high loss region of the suction surface of the blade.
In some embodiments, the first direction is perpendicular to the second direction, and jet-inlet airflow 011 enters bleed cavity 10 at bleed inlet 101 in the first direction, jet-outlet airflow 012 exits bleed cavity 10 at bleed outlet 102 in the second direction, and main airflow 020 flows in the second direction.
In the present embodiment, as shown by arrows in fig. 1, the fluid direction of jet inlet airflow 011 coincides with the first direction, the fluid directions of mainstream airflow 020 and jet outlet airflow 012 coincide with the second direction, and the first direction is perpendicular to the second direction; at the moment, the coanda jet vane realizes 90-degree bending through the internal air entraining cavity 10 and the flow deflector 20, so that the jet flow direction is consistent with the main flow direction, the mixing loss of the jet flow and the main flow can be reduced, and kinetic energy is provided for a high loss area of the suction surface of the vane.
In some embodiments, the number of guide vanes 20 is plural, and the plural guide vanes 20 are arranged in the blade height direction of the coanda jet blades inside the bleed air cavity 10.
In the present embodiment, a certain number of flow deflectors 20 are arranged inside the bleed air cavity 10 along the blade height direction, so that the jet air flows around the flow deflectors 20 to generate the coanda wall effect; compared with the jet inlet airflow 011 of the bleed air inlet 101, the jet outlet airflow 012 of the bleed air outlet 102 is vertical jet, so that the turning capacity of the airflow is increased, kinetic energy is provided for a high-loss area of the flow of the suction surface of the blade, and the mixing loss caused by the inconsistency of the jet speed and the main flow speed is avoided.
In some embodiments, a plurality of baffles 20 are arranged equidistantly inside the bleed air cavity 10 in the direction of the blade height of the coanda jet blades.
In this embodiment, the plurality of flow deflectors 20 are further arranged in the bleed air cavity 10 in an even manner at equal intervals along the blade height direction, so that the deflecting capability of the air flow is increased by the flow deflectors 20, and the uniformity of the air flow direction at the bleed air outlet 102 is ensured by the even arrangement manner.
In some embodiments, the baffle 20 includes an inducer portion and an exducer portion, the inducer portion being joined to the exducer portion with a smooth transition at the junction between the inducer portion and the exducer portion.
In this embodiment, as shown in fig. 2, the baffle 20 is divided into two straight segments, with a smooth transition between the two segments, an inlet segment corresponding to the bleed air inlet 101 of the bleed air cavity 10 and an outlet segment corresponding to the bleed air outlet 102 of the bleed air cavity 10. When the jet inlet airflow 011 enters the air-entraining cavity 10 from the air-entraining inlet 101, the jet airflow flows around through the inlet section to generate coanda wall attachment effect; the jet air flow flows around through the outlet section to generate a coanda wall effect; combining the inlet section and the outlet section, the jet air flow is bent by the deflector 20 inside the bleed chamber 10.
Besides, the guide vane 20 may also be in other forms, such as multiple segments with more than two segments, non-linear curved segments, etc., and the description of the present embodiment is also included in the present invention.
In some embodiments, the first direction is perpendicular to the second direction, and the entrance segment has a first angle a with the first direction, the exit segment has a second angle b with the first direction, and the entrance segment has a third angle c with the exit segment, wherein the first angle a is an acute angle, the second angle b is a right angle, and the third angle c is an obtuse angle.
In this embodiment, the outlet section of the flow deflector 20 is flush with the bleed air outlet 102, the flow deflector 20 is composed of an inlet angle and an outlet angle, and is configured as a coanda surface, so that the coanda effect is utilized to increase the flow angle of the outlet and recover the turning angle of the flow, thereby reducing the blending loss with the main flow speed.
Specifically, the inlet angle of the baffle 20 is an included angle between the tangential direction of the front edge (inlet section) of the baffle 20 and the mean camber line, i.e., a first included angle a; the outlet angle of the flow deflector 20 is an included angle between the tangential direction of the trailing edge (outlet section) of the flow deflector 20 and the outlet plane, i.e. a second included angle b, and in order to ensure the uniformity of outlet airflow angle outlet, the outlet section is vertical, and the outlet angle is 90 degrees.
The coanda jet vane can reduce the radial component of the speed at the outlet and increase the air flow turning capacity at the position far away from the vane top by adopting the guide vane 20. The deflection angle of the airflow from the end wall to the leaf position is increased by 20 degrees, and because the suction surface of the guide vane 20 is separated, the pressure difference generates transverse flow towards the suction surface by the pressure surface, the airflow is extruded towards the suction surface, and the condition of positive airflow angle of the outlet is generated. The airflow angle distribution of the whole blade high outlet is not uniform, but the airflow angle of the outlet can be increased by arranging the guide vanes 20, and the airflow deflection angle can be recovered.
Besides, there are two ways to solve the problem of air flow deflection in the cavity:
one is to increase the deflected path of the airflow by decreasing the aspect ratio and increasing the width, giving the airflow a space to develop sufficiently. However, the cavity is constructed in the blade, the aspect ratio is fixed, and the aspect ratio is limited by the chord length and the thickness of the blade, so that the cross section area of the cavity is fixed and is difficult to change, and the geometric construction of the cavity cannot be used for increasing the deflection angle of the airflow outlet by a method of reducing the aspect ratio.
The second method is to construct a certain number of flow deflectors in the cavity, wherein the flow deflectors mainly play a role in flow guiding, and airflow passes through the flow deflectors to increase the airflow angle at the outlet, so that the included angle between the jet airflow and the main flow is reduced.
This application still provides an impeller, including above-mentioned kangda jet-propelled blade, a plurality of kangda jet-propelled blades set up along the circumference interval of impeller, and this impeller should have above-mentioned kangda jet-propelled blade's whole beneficial effect, and here no longer gives unnecessary detail.
The application still provides an axial compressor, including above-mentioned coanda jet blade or above-mentioned impeller, this axial compressor should have above-mentioned coanda jet blade's whole beneficial effect, and here no longer gives unnecessary details.
It should be noted that many of the components mentioned in this application are common standard components or components known to those skilled in the art, and the structure and principle thereof can be known to those skilled in the art through technical manuals or through routine experimentation.
It should be noted that in this specification, relational terms such as first and second, and the like are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities.
The coanda jet vanes, impellers and axial flow compressors provided by the present application are described in detail above. The principles and embodiments of the present application are explained herein using specific examples, which are provided only to help understand the method and the core idea of the present application. It should be noted that, for those skilled in the art, it is possible to make several improvements and modifications to the present application without departing from the principle of the present application, and such improvements and modifications also fall within the scope of the claims of the present application.
Claims (8)
1. A coanda jet vane, comprising:
the device comprises a bleed air cavity (10), wherein the bleed air cavity (10) is provided with a bleed air inlet (101) in a first direction and a bleed air outlet (102) in a second direction;
flow deflector (20), flow deflector (20) install in inside bleed cavity (10), flow deflector (20) utilize the coanda effect of conda to strengthen by bleed inlet (101) get into the turning ability of jet-propelled import air current (011) of bleed cavity (10), and make by bleed outlet (102) leave jet-propelled export air current (012) of bleed cavity (10) are unanimous with the fluid direction of mainstream air current (020).
2. The coanda jet vane according to claim 1, characterized in that the first direction is perpendicular to the second direction and that a jet inlet airflow (011) enters the bleed cavity (10) at the bleed inlet (101) in the first direction, a jet outlet airflow (012) exits the bleed cavity (10) at the bleed outlet (102) in the second direction, and a main flow of air (020) flows in the second direction.
3. The coanda jet blade according to claim 1, characterized in that the number of said guide vanes (20) is a plurality and a plurality of said guide vanes (20) are arranged inside the bleed air cavity (10) in the direction of the blade height of the coanda jet blade.
4. The coanda jet blade according to claim 3, characterized in that a plurality of said deflectors (20) are arranged inside the bleed air cavity (10) at equal distances in the blade height direction of the coanda jet blade.
5. The coanda jet blade of claim 1, wherein the flow deflector (20) comprises an inducer and an exducer, the inducer being connected to the exducer, the junction between the inducer and the exducer being a smooth transition.
6. The coanda jet vane of claim 5, wherein the first direction is perpendicular to the second direction, and wherein the inducer is at a first angle a to the first direction, the exducer is at a second angle b to the first direction, the inducer is at a third angle c to the exducer, the first angle a is an acute angle, the second angle b is a right angle, and the third angle c is an obtuse angle.
7. An impeller comprising the coanda jet blade as recited in any one of claims 1 to 6, wherein a plurality of the coanda jet blades are arranged at intervals in the circumferential direction of the impeller.
8. An axial flow compressor comprising a coanda jet vane as defined in any one of claims 1 to 6 or an impeller as defined in claim 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211633333.9A CN115788953A (en) | 2022-12-19 | 2022-12-19 | Kanda jet blade, impeller and axial-flow compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211633333.9A CN115788953A (en) | 2022-12-19 | 2022-12-19 | Kanda jet blade, impeller and axial-flow compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115788953A true CN115788953A (en) | 2023-03-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211633333.9A Pending CN115788953A (en) | 2022-12-19 | 2022-12-19 | Kanda jet blade, impeller and axial-flow compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115788953A (en) |
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2022
- 2022-12-19 CN CN202211633333.9A patent/CN115788953A/en active Pending
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