CN111255742A - Trans/supersonic compressor rotor blade with shock wave control bulge - Google Patents

Trans/supersonic compressor rotor blade with shock wave control bulge Download PDF

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Publication number
CN111255742A
CN111255742A CN202010121759.0A CN202010121759A CN111255742A CN 111255742 A CN111255742 A CN 111255742A CN 202010121759 A CN202010121759 A CN 202010121759A CN 111255742 A CN111255742 A CN 111255742A
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shock wave
bulge
blade
wave control
shock
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CN111255742B (en
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韩吉昂
钱薪伟
胡义
丁小娟
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Dalian Maritime University
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Dalian Maritime University
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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
    • 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
    • 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
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • 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
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/306—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the suction side of a rotor blade

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention provides a rotor blade of a cross/supersonic compressor with a shock wave control bulge, which comprises a blade root, a blade top, a pressure surface and a suction surface, wherein the blade root is provided with a blade root; a shock wave control bulge is arranged on the suction surface and comprises a continuous shock wave control bulge and a discontinuous shock wave control bulge; the continuous shock wave controls the continuous distribution of the bulges along the leaf height direction; the discontinuous shock wave controls the discontinuous distribution of the bulges along the leaf height direction; the continuous shock wave control bulge comprises a continuous whole-leaf high shock wave control bulge and a continuous partial-leaf high shock wave control bulge; the discontinuous shock wave control bulge comprises a discontinuous full-leaf high shock wave control bulge and a discontinuous part-leaf high shock wave control bulge. The invention only needs to slightly change the local suction surface of the blade, can improve the shock wave system structure in the cross/supersonic speed compressor on the premise of basically not changing the flow, improves the performance of the cross/supersonic speed compressor, and has the advantages of simple structure, flexible design, lower cost and the like.

Description

Trans/supersonic compressor rotor blade with shock wave control bulge
Technical Field
The invention relates to a rotor blade of a cross/supersonic compressor with a shock wave control bulge.
Background
Since its practical use in 1939, gas turbines have been widely used as power plants in aerospace and marine applications. In order to further increase the thrust-weight ratio/power-weight ratio of a gas turbine and reduce fuel consumption, a compressor, which is one of three major core components of the gas turbine, is required to continuously increase the pressure increase ratio and efficiency. The improvement of the pressure ratio and the efficiency of the compressor mainly depends on the continuous deep understanding of the internal flow characteristics of the compressor and the development and application of various flow control technologies.
Shock losses and shock induced boundary layer separation losses are one of the major sources of flow losses for a cross/supersonic compressor. Therefore, in order to improve the performance of the cross/supersonic compressor, the method for reasonably controlling the shock wave is an effective method, because the control of the shock wave not only can reduce the loss of the shock wave, but also can effectively control the flow direction pressure gradient distribution, thereby inhibiting the boundary layer separation loss induced by the shock wave. The existing shock wave control methods comprise active control methods such as boundary layer suction, plasma excitation and the like, and passive control methods such as blade type optimization design, swept blade design and the like. Although the active control method can well control the shock wave and the induced separation flow loss, it needs to add extra devices and energy sources, which not only needs extra energy consumption, but also causes increased design difficulty. The design variables of the passive control method are generally more, and in most cases, the design variables can cause the blade profile or the channel structure of the cross/supersonic speed compressor to be changed greatly. Therefore, finding a control method for shock waves and induced flow loss thereof, which do not require additional energy consumption and have small blade profile change, is one of the problems to be solved urgently in the research of the existing transonic/supersonic compressor.
The shock wave control bulge is used as a novel shock wave control technology, and disperses a shock wave incident to the vicinity of a wall surface into a lambda shock wave from a stronger shock wave by utilizing the bulge arranged on the wall surface, so that the shock wave intensity and the pressure gradient distribution along the flow direction near the wall surface are reduced, the shock wave loss near the wall surface can be reduced, and the boundary layer separation loss induced by the shock wave can be inhibited. At present, the shock wave control technology is mainly applied to outer flow wings for controlling wave resistance, and has some applications in inner flow supersonic speed air inlet channels, while the application in the field of inner flow impeller machinery is very little, and particularly, the application research in a cross/supersonic speed air compressor is just started.
Disclosure of Invention
According to the phenomena of complex shock wave systems, boundary layer separation caused by shock wave-shock wave and shock wave-boundary layer mutual interference and the like existing in the rotor of the cross/supersonic speed compressor, the efficiency of the cross/supersonic speed compressor is reduced, the flow loss is increased, and the aerodynamic performance is reduced. In order to control the technical problems of shock wave loss inside the cross/supersonic speed compressor and flow separation loss induced by shock waves, the invention provides a cross/supersonic speed compressor rotor blade with a shock wave control bulge. The invention mainly integrates the shock wave control bulge into the suction surface of the rotor blade of the cross/supersonic compressor so as to form a novel cross/supersonic compressor rotor blade; the introduction of the shock wave control bulge only slightly changes the local suction surface of the rotor blade, so that the shock wave system structure near the suction surface of the rotor blade of the cross/supersonic compressor can be improved and the boundary layer separation can be inhibited on the premise of basically not changing the flow of the cross/supersonic compressor, thereby reducing the flow loss in the cross/supersonic compressor and further improving the performance of the cross/supersonic compressor.
The technical means adopted by the invention are as follows:
a striding/supersonic compressor rotor blade with a shock wave control bulge comprises a blade root, a blade top, a pressure surface and a suction surface;
the suction surface is provided with a shock wave control bulge, and the shock wave control bulge comprises a continuous shock wave control bulge and a discontinuous shock wave control bulge; the continuous shock wave control bulges are continuously distributed along the leaf height direction; and the discontinuous shock waves control the non-continuous distribution of the bulges along the blade height direction.
Further, the shock wave control bulge is tangent to the suction surface in a smooth flow direction at the flow direction starting position and the flow direction ending position. The flow direction starting position refers to a position where the shock wave control bulge begins to bulge from the suction surface of the blade in the flow direction; the flow direction ending position refers to a position where the shock wave control bulge disappears from the suction surface of the blade in the flow direction.
Further, the continuous shock wave control bulge comprises a continuous whole-leaf high shock wave control bulge and a continuous partial-leaf high shock wave control bulge; the non-continuous shock wave control bulge comprises a non-continuous full-leaf high shock wave control bulge and a non-continuous partial-leaf high shock wave control bulge.
Further, the spanwise starting position I of the continuous shock wave control bulge is located at the blade root or at the section between the blade root and the blade top; and the spreading direction ending positions I of the continuous shock wave control bulges are all positioned at the leaf tops.
Further, when the spanwise starting position i is located at the blade root, the curvature of the spanwise starting position i is consistent with the curvature of the blade root.
Further, when the spanwise starting position I is located at a section between the blade root and the blade top, the spanwise starting position I and the suction surface below the blade height position of the section are kept smooth and tangent in a spanwise direction; the curvature of the spanwise end position I is consistent with the curvature at the leaf top.
Furthermore, the discontinuous shock wave control bulge is formed by arranging a plurality of shock wave control bulges at intervals in the spanwise direction of the blade, the spanwise starting position II and the spanwise ending position II of each discontinuous shock wave control bulge are both positioned at the section between the blade root and the blade top, and each discontinuous shock wave control bulge is positioned at the spanwise starting position II and the spanwise ending position II and keeps smooth tangency with the suction surface in the spanwise direction.
Furthermore, the bulge molded lines of the shock wave control bulge at different heights of the spanwise lobe are determined by a parsec profiling method, and the following formula is satisfied:
Figure BDA0002393183550000031
wherein x is the relative abscissa of the bulge along the flow direction; y is the relative ordinate of the bulge; h isBIs the height of the flow direction of the bulge; a isnIs a polynomial coefficient; x is the number of0Controlling an absolute abscissa of a flow direction starting position of the bulge for the shock wave; x is the absolute horizontal coordinate of each point on the bulge; lBIs the length of the flow direction of the bulge; n is the order of the polynomial coefficient.
Further, the continuous shock wave controls the height h of the bulge flow direction of the bulgeBThe following formula is satisfied:
0≤hB≤0.01C；
the continuous shock wave controls the flow direction length l of the bulgeBThe following formula is satisfied:
0.15C≤lB≤0.3C；
the absolute abscissa x of the flow direction starting position of the continuous shock wave control bulge0The following formula is satisfied:
0.3C≤x0≤0.55C；
in the formula, C is the blade profile chord length of a basic rotor blade of the cross/supersonic compressor;
the flow direction ending position of the continuous shock wave control bulge is determined by the flow direction starting position and the flow direction length of the bulge;
the spanwise starting position I of the continuous shock wave control bulge is determined by the shock wave intensity in a rotor blade channel of the cross/supersonic compressor.
Further, the flow direction shape and parameters of each discontinuous shock wave control bulge, including flow direction height, flow direction length, flow direction starting position and flow direction ending position, are also determined by a parsec profiling method; the spanwise length of the discontinuous shock wave control bulge and the spanwise distance between two adjacent discontinuous shock wave control bulges are determined by actual conditions.
The spanwise starting position refers to a position where the shock wave control bulge starts to bulge from the suction surface of the blade in the blade height direction, and the spanwise ending position refers to a position where the shock wave control bulge disappears from the suction surface of the blade in the blade height direction.
Compared with the prior art, the invention has the following advantages:
1. the rotor blade of the cross/supersonic compressor with the shock wave control bulge provided by the invention only needs to slightly change the local suction surface of the blade, and can improve the shock wave system structure near the suction surface of the rotor blade in the cross/supersonic compressor on the premise of basically not changing the flow, thereby improving the performance of the cross/supersonic compressor.
2. According to the cross/supersonic compressor rotor blade with the shock wave control bulge, the shock wave incident to the vicinity of the suction surface is dispersed into the lambda shock wave from a stronger shock wave, so that the shock wave strength and the pressure gradient distribution along the flow direction of the shock wave near the suction surface are reduced, the shock wave loss near the suction surface is reduced, the boundary layer separation loss induced by the shock wave is inhibited, and the performance of the cross/supersonic compressor is improved.
3. The cross/supersonic compressor rotor blade with the shock wave control bulge provided by the invention can improve the blocking degree of airflow in the blade channel by inhibiting the coherent effect of a shock wave/boundary layer with a strong suction surface of the blade, thereby improving the stable working range of the cross/supersonic compressor.
4. The cross/supersonic compressor rotor blade with the shock wave control bulge has the advantages of simple structure, low design cost and the like.
In conclusion, the technical scheme of the invention can solve the problems of how to control the shock wave loss inside the cross/supersonic compressor and the flow separation loss induced by the shock wave in the prior art, effectively improve the shock wave system structure and the airflow blockage degree inside the cross/supersonic compressor, weaken the shock wave strength, and delay the boundary layer separation phenomenon caused by the mutual interference of the shock wave and the boundary layer, thereby improving the aerodynamic performance of the cross/supersonic compressor.
Based on the reason, the invention can be widely popularized in the field of impeller machinery such as a cross/supersonic speed air compressor used by a high-performance gas turbine.
Drawings
In order to more clearly illustrate the embodiments of the present invention 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, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic view of a cross/supersonic compressor rotor with a continuous full-blade high-shock control bulge according to the present invention.
FIG. 2 is a schematic view of a cross/supersonic compressor rotor blade with a continuous full-blade high-shock control bulge according to the present invention.
FIG. 3 is a schematic view of the pressure surface of a rotor blade of a cross/supersonic compressor with a continuous full-blade high-shock control bulge according to the present invention.
FIG. 4 is a schematic view of a cross/supersonic compressor rotor with a continuous partial-lobe-height shock-wave control bulge according to the present invention.
FIG. 5 is a schematic view of a cross/supersonic compressor rotor blade with a continuous partial-lobe-height shock-wave control bulge of the present invention.
FIG. 6 is a schematic view of a cross/supersonic compressor rotor with a non-continuous full-blade high-shock control bulge according to the present invention.
FIG. 7 is a schematic view of a cross/supersonic compressor rotor blade with a non-continuous full-blade high-shock control bulge according to the present invention.
FIG. 8 is a schematic view of a cross/supersonic compressor rotor with a discontinuous partial-lobe-height shock-wave control bulge according to the present invention.
FIG. 9 is a schematic view of a cross/supersonic compressor rotor blade with a discontinuous partial-lobe-height shock-wave control bulge according to the present invention.
In the figure: 1. a wheel disc; 2. a hub; 3. a cross/supersonic compressor rotor blade with a continuous full-blade high shock wave control bulge; 4. a blade root; 5. a flow direction starting position; 6. a suction surface; 7. continuous shock wave control bulging; 8. a flow direction end position; 9. a blade leading edge; 10. a trailing edge of the blade; 11. a pressure surface; 12. leaf tops; 13. a cross/supersonic compressor rotor blade with a continuous part blade height shock wave control bulge; 14. a deployment direction ending position I; 15. a spanwise starting position I; 16. a cross/supersonic compressor rotor blade with a non-continuous full-blade high shock wave control bulge; 17. a spanwise starting position II; 18. a deployment direction ending position II; 19. controlling the bulge by using the discontinuous shock wave; 20. a cross/supersonic compressor rotor blade with a discontinuous part blade height shock wave control bulge.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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 of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. 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 invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. Any specific values in all examples shown and discussed herein are to be construed as exemplary only and not as limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are used for convenience of description and simplicity of description only, and in the absence of any contrary indication, these directional terms are not intended to indicate and imply that the device or element so referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore should not be considered as limiting the scope of the present invention: the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
As shown in the figure, the invention provides a rotor blade of a cross/supersonic compressor with a shock wave control bulge, which comprises a blade root 4, a blade top 12, a pressure surface 11 and a suction surface 6;
the suction surface 6 is provided with a shock wave control bulge, and the shock wave control bulge comprises a continuous shock wave control bulge 7 and a discontinuous shock wave control bulge 19; the continuous shock wave control bulges 7 are continuously distributed along the leaf height direction; the discontinuous shock wave controls the discontinuous distribution of the bulges 19 along the blade height direction.
Preferably, the shock wave control bulge is tangent to the suction surface 6 at the flow direction smoothness at the flow direction starting position 5 and the flow direction ending position 8. The flow direction starting position 5 refers to a position where the shock wave control bulge begins to bulge from the suction surface of the blade in the flow direction; the flow direction end position 8 is a position where the shock wave control bulge disappears from the suction surface of the blade in the flow direction.
Preferably, the continuous shock wave control bump 7 comprises a continuous whole-leaf high shock wave control bump and a continuous partial-leaf high shock wave control bump; the discontinuous shock wave control bulge 19 comprises a discontinuous full-leaf high shock wave control bulge and a discontinuous part-leaf high shock wave control bulge.
Preferably, the spanwise starting position i 15 of the continuous shock wave control bulge 7 is located at the blade root 4 or at a certain cross section between the blade root 4 and the blade top 12; the spanwise ending positions I14 of the continuous shock wave control bulges 7 are all positioned at the blade tops 12.
Preferably, when the spanwise starting position i 15 is located at the blade root 4, the curvature of the spanwise starting position i 15 is consistent with the curvature of the blade root 4.
Preferably, when the spanwise starting position i 15 is located at a section between the blade root 4 and the blade top 12, the spanwise starting position i 15 is kept smoothly tangent to the suction surface 6 below the blade height position of the section in the spanwise direction; the curvature of the spanwise end position i 14 is kept the same as the curvature at the tip 12.
Preferably, the discontinuous shock wave control bulge 19 is formed by arranging a plurality of shock wave control bulges at intervals in the spanwise direction of the blade, the spanwise starting position ii 17 and the spanwise ending position ii 18 of each discontinuous shock wave control bulge 19 are both located at the section between the blade root 4 and the blade tip 12, and each discontinuous shock wave control bulge 19 is located at the spanwise starting position ii 17 and the spanwise ending position ii 18 and keeps a smooth tangent with the suction surface 6 in the spanwise direction.
Preferably, the bulge lines of the shock wave control bulge at different heights of the spanwise direction are determined by a parsec profiling method, and the following formula is satisfied:
Figure BDA0002393183550000091
wherein x is the relative abscissa of the bulge along the flow direction; y is the relative ordinate of the bulge; h isBIs the height of the flow direction of the bulge; a isnIs a polynomial coefficient; x is the number of0Controlling an absolute abscissa of a flow direction starting position of the bulge for the shock wave; x is the absolute horizontal coordinate of each point on the bulge; lBIs the length of the flow direction of the bulge; n is the order of the polynomial coefficient.
Preferably, the continuous shock wave controls the height h of the bulge flow direction of the bulge 7BThe following formula is satisfied:
0≤hB≤0.01C；
the continuous shock wave controls the flow direction length l of the bulge 7BThe following formula is satisfied:
0.15C≤lB≤0.3C；
the absolute abscissa x of the flow direction starting position of the continuous shock wave control bulge 70The following formula is satisfied:
0.3C≤x0≤0.55C；
in the formula, C is the blade profile chord length of a basic (prototype) rotor blade of the cross/supersonic compressor;
the flow direction ending position 8 of the continuous shock wave control bulge 7 is determined by the flow direction starting position 5 and the flow direction length of the bulge;
the spanwise starting position I15 of the continuous shock wave control bulge 7 is specifically determined by the shock wave intensity in a rotor blade channel of the cross/supersonic compressor.
Preferably, the flow direction shape and parameters of each of the discontinuous shock wave control bulges 19, including the flow direction height, the flow direction length, the flow direction starting position 5 and the flow direction ending position 8, are also determined by the parsec profiling method; the spanwise length of each non-continuous shock wave control bulge 19 and the spanwise distance between two adjacent non-continuous shock wave control bulges 19 are determined by actual conditions.
The spanwise starting position refers to a position where the shock wave control bulge starts to bulge from the suction surface of the blade in the blade height direction, and the spanwise ending position refers to a position where the shock wave control bulge disappears from the suction surface of the blade in the blade height direction.
Example 1
As shown in fig. 1-5, the cross/supersonic compressor rotor with continuous shock wave control bulge provided by the present invention is a cross/supersonic compressor rotor with a continuous full-blade high shock wave control bulge and a cross/supersonic compressor rotor with a continuous partial-blade high shock wave control bulge.
The cross/supersonic compressor rotor with the continuous full-blade high-shock-wave control bulge comprises a wheel disc 1 and cross/supersonic compressor rotor blades 3 with the continuous full-blade high-shock-wave control bulge, wherein the wheel disc 1 is a base of the cross/supersonic compressor rotor blades 3 with the continuous full-blade high-shock-wave control bulge, a hub 2 is arranged at the outer edge of the wheel disc 1, and a plurality of cross/supersonic compressor rotor blades 3 with the continuous full-blade high-shock-wave control bulge are sequentially arranged at intervals along the circumferential direction of the hub 2.
The rotor of the cross/supersonic compressor with the continuous part blade height shock wave control bulge comprises a wheel disc 1 and a rotor blade 13 of the cross/supersonic compressor with the continuous part blade height shock wave control bulge. The wheel disc 1 is a base of a rotor blade 13 of a cross/supersonic compressor with a continuous part blade height shock wave control bulge. The outer edge of the wheel disc 1 is provided with a hub 2, and a plurality of rotor blades 13 of the cross/supersonic speed compressor with continuous partial blade height shock wave control bulges are sequentially arranged at intervals along the circumferential direction of the hub 2.
The cross/supersonic compressor rotor blade with the continuous shock wave control bulge in the embodiment comprises a blade root 4, a blade top 12, a pressure surface 11, a suction surface 6, a continuous shock wave control bulge 7, a blade leading edge 9 and a blade trailing edge 10.
In a cross/supersonic compressor rotor blade 3 with a continuous full-blade high-shock-wave control bulge, the continuous shock-wave control bulge 7 is a continuous full-blade high-shock-wave control bulge; in a cross/supersonic compressor rotor blade 13 with a continuous part blade height shock wave control bulge, the continuous shock wave control bulge 7 is the continuous part blade height shock wave control bulge.
The continuous shock wave control bump 7 is located on the suction surface 6, the flow direction shape and geometric parameters of the continuous shock wave control bump are determined by the parsec shape method, and the flow direction starting position 5 and the flow direction ending position 8 of the continuous shock wave control bump are smoothly tangent to the suction surface 6 in the flow direction. The spanwise starting position I15 of the continuous shock wave control bulge is located at the blade root 4 or at a certain section between the blade root 4 and the blade top 12, and the spanwise starting position I15 is specifically determined by the shock wave intensity in a rotor blade channel of the cross/supersonic compressor. When the spanwise starting position I15 is positioned at the blade root 4, the curvature of the spanwise starting position I15 is consistent with the curvature of the blade root 4 of the blade suction surface 6; when the spanwise starting position i 15 is located at a section between the blade root 4 and the blade tip 12, the spanwise starting position i 15 is kept in smooth tangency with the suction surface 6 of the blade below the blade height position of the section. The spanwise ending position I14 of the continuous shock wave control bulge is located at the blade tip 12, and the curvature of the spanwise ending position I is consistent with the curvature of the blade tip 12 of the suction surface 6 of the blade.
Example 2
Different from the embodiment 1, the shock wave control bulges in the embodiment are discontinuously distributed in the blade height direction of the suction surface of the blade of the cross/supersonic compressor.
As shown in fig. 6-9, the rotor of the cross/supersonic compressor with the discontinuous shock wave control bulge provided by the invention is a rotor of a cross/supersonic compressor with a discontinuous full-blade high shock wave control bulge and a rotor of a cross/supersonic compressor with a discontinuous partial-blade high shock wave control bulge.
The rotor of the cross/supersonic compressor with the non-continuous full-blade high-shock-wave control bulge comprises a wheel disc 1 and rotor blades 16 of the cross/supersonic compressor with the non-continuous full-blade high-shock-wave control bulge. The wheel disc 1 is a base of a striding/supersonic compressor rotor blade 16 with a non-continuous full-blade high-shock wave control bulge, a hub 2 is arranged at the outer edge of the wheel disc 1, and a plurality of striding/supersonic compressor rotor blades 16 with the non-continuous full-blade high-shock wave control bulge are sequentially arranged at intervals along the circumferential direction of the hub 2.
The rotor of the cross/supersonic speed compressor with the discontinuous part blade height shock wave control bulge comprises a wheel disc 1 and a rotor blade 20 of the cross/supersonic speed compressor with the discontinuous part blade height shock wave control bulge. The wheel disc 1 is a base of a cross/supersonic compressor rotor blade 20 with a discontinuous part blade height shock wave control bulge, a hub 2 is arranged at the outer edge of the wheel disc 1, and a plurality of cross/supersonic compressor rotor blades 20 with a discontinuous part blade height shock wave control bulge are sequentially arranged at intervals along the circumferential direction of the hub 2.
The cross/supersonic compressor rotor blade with the discontinuous shock wave control bulge in the embodiment comprises a blade root 4, a blade top 12, a pressure surface 11, a suction surface 6, a discontinuous shock wave control bulge 19, a blade leading edge 9 and a blade trailing edge 10.
In a rotor blade 16 of a cross/supersonic compressor with a non-continuous whole-blade high-shock-wave control bulge, the non-continuous shock-wave control bulge 19 is a non-continuous whole-blade high-shock-wave control bulge; in the rotor blade 20 of the cross/supersonic compressor with the shock wave control bulge of the blade height of the discontinuous part, the shock wave control bulge 19 of the discontinuous part is the shock wave control bulge of the blade height of the discontinuous part.
The discontinuous shock wave control bulge 19 is positioned on the suction surface 6, and the flow direction starting position 5 and the flow direction ending position 8 of the discontinuous shock wave control bulge are tangent to the suction surface 6 in a smooth flow direction. The flow direction shape and geometry of each of the non-continuous shock control bumps 19 is also determined by the parsec profiling method.
Unlike embodiment 1, the spanwise starting position 17 and the spanwise ending position 18 of the discontinuous shock wave control bulge 19 are both located between the blade root 4 and the blade tip 12, and the spanwise starting position ii 17 and the spanwise ending position ii 18 are both kept smoothly tangent to the blade suction surface 6 in the spanwise direction.
The spanwise length of the discontinuous shock wave control bulge 19 and the spanwise distance between two adjacent shock wave control bulges in the embodiment are determined by actual conditions.
The working process is as follows: when the transonic/supersonic compressor rotor blade with the shock wave control bulge rotates at a high speed, subsonic airflow is sucked into a compressor rotor blade channel; under the condition of high-speed rotation of the rotor, the relative speed of the air flow at the inlet of the air compressor reaches a cross/supersonic speed. When the cross/supersonic speed airflow flows through the rotor blade front edge 9, front edge shock waves are formed, the pressure surface 11 branches of the front edge shock waves can penetrate deep into a rotor blade channel and are incident on a shock wave control bulge arranged on the suction surface of the rotor blade, and the strong shock waves incident on the suction surface of the blade can be dispersed into lambda shock waves under the action of the shock wave control bulge, so that the shock wave strength near the suction surface of the blade is weakened, the loss of the shock waves is reduced, the shock wave induced boundary layer separation loss is inhibited, the pneumatic blockage caused by boundary layer separation is relieved, and the performance of the cross/supersonic speed compressor is improved.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims (9)

1. A striding/supersonic compressor rotor blade with a shock wave control bulge comprises a blade root (4), a blade top (12), a pressure surface (11) and a suction surface (6);
the shock wave suction device is characterized in that a shock wave control bulge is arranged on the suction surface (6), and the shock wave control bulge comprises a continuous shock wave control bulge (7) and a discontinuous shock wave control bulge (19); the continuous shock wave control bulges (7) are continuously distributed along the leaf height direction; the discontinuous shock wave control bulges (19) are discontinuously distributed along the blade height direction.
2. The cross/supersonic compressor rotor blade with shock control bulge according to claim 1, characterized in that the shock control bulge is smoothly tangential to the suction surface (6) in the flow direction at both the flow direction starting position (5) and the flow direction ending position (8).
3. The cross/supersonic compressor rotor blade with shock control bumps according to claim 2, wherein the continuous shock control bumps (7) comprise continuous full-lobe high shock control bumps and continuous partial-lobe high shock control bumps; the discontinuous shock wave control bulge (19) comprises a discontinuous full-leaf high shock wave control bulge and a discontinuous part-leaf high shock wave control bulge.
4. The transonic/supersonic compressor rotor blade with shock control bumps according to claim 3, characterized in that the spanwise starting position I (15) of the continuous shock control bump (7) is located at the blade root (4) or at the section between the blade root (4) to the blade tip (12); the spanwise ending positions I (14) of the continuous shock wave control bulges (7) are all located at the blade tops (12).
5. The transonic/supersonic compressor rotor blade with shock control bulge according to claim 4, characterized in that the curvature of the spanwise starting position I (15) is consistent with the curvature at the blade root (4) when the spanwise starting position I (15) is at the blade root (4).
6. The transonic/supersonic compressor rotor blade with shock control bulge according to claim 4, characterized in that when said spanwise starting position I (15) is located at a section between said blade root (4) and said blade tip (12), said spanwise starting position I (15) is kept smooth tangentially in a spanwise direction to said suction surface (6) below a blade height position at which said section is located; the curvature of the spanwise end position I (14) is consistent with the curvature at the blade tip (12).
7. The transonic/supersonic compressor rotor blade with shock control bumps according to claim 3, wherein the discontinuous shock control bumps (19) are a plurality of shock control bumps arranged at intervals along the spanwise direction of the blade, the spanwise starting position II (17) and the spanwise ending position II (18) of each discontinuous shock control bump (19) are both located at the section between the blade root (4) and the blade tip (12), and each discontinuous shock control bump (19) is kept tangent to the suction surface (6) at the spanwise starting position II (17) and the spanwise ending position II (18) in a smooth manner.
8. The cross/supersonic compressor rotor blade with a shock control bump according to claim 1, 2, 3, 4, 5, 6 or 7, wherein the bump profile of the shock control bump at different blade heights in the spanwise direction is determined by the parsec profiling method, and satisfies the following formula:
Figure FDA0002393183540000021
wherein x is the relative abscissa of the bulge along the flow direction; y is the relative ordinate of the bulge; h isBIs the height of the flow direction of the bulge; a isnIs a polynomial coefficient; x is the number of0Controlling an absolute abscissa of a flow direction starting position of the bulge for the shock wave; x is the absolute horizontal coordinate of each point on the bulge; lBIs the length of the flow direction of the bulge; n is the order of the polynomial coefficient.
9. The transonic/supersonic compressor rotor blade with shock control bumps according to claim 8, characterized in that the bump flow direction height h of the continuous shock control bump (7)BThe following formula is satisfied:
0≤hB≤0.01C；
the continuous shock wave controls the flow direction length l of the bulge (7)BThe following formula is satisfied:
0.15C≤lB≤0.3C；
the absolute abscissa x of the flow direction starting position of the continuous shock wave control bulge (7)0The following formula is satisfied:
0.3C≤x0≤0.55C；
in the formula, C is the blade profile chord length of a basic rotor blade of the cross/supersonic compressor;
the flow direction ending position (8) of the continuous shock wave control bulge (7) is determined by the flow direction starting position (5) and the flow direction length of the bulge;
the spanwise starting position I (15) of the continuous shock wave control bulge (7) is determined by the shock wave intensity in a rotor blade channel of the cross/supersonic compressor.
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114893429A (en) * 2022-04-29 2022-08-12 山东科技大学 Gas compressor clearance leakage flow control method based on shock wave deceleration effect and gas compressor

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Publication number Priority date Publication date Assignee Title
GB920260A (en) * 1958-07-07 1963-03-06 Commissariat Energie Atomique Improvements in supersonic compressors
CN101959755A (en) * 2008-02-29 2011-01-26 空中客车英国有限公司 Aerodynamic structure with non-uniformly spaced shock bumps
CN203978917U (en) * 2014-05-09 2014-12-03 贵州航空发动机研究所 A kind of transonic fan rotor blade
CN110287647A (en) * 2019-07-18 2019-09-27 大连海事大学 A kind of design method of transonic compressor plane cascade shock wave control

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB920260A (en) * 1958-07-07 1963-03-06 Commissariat Energie Atomique Improvements in supersonic compressors
CN101959755A (en) * 2008-02-29 2011-01-26 空中客车英国有限公司 Aerodynamic structure with non-uniformly spaced shock bumps
CN203978917U (en) * 2014-05-09 2014-12-03 贵州航空发动机研究所 A kind of transonic fan rotor blade
CN110287647A (en) * 2019-07-18 2019-09-27 大连海事大学 A kind of design method of transonic compressor plane cascade shock wave control

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114893429A (en) * 2022-04-29 2022-08-12 山东科技大学 Gas compressor clearance leakage flow control method based on shock wave deceleration effect and gas compressor
CN114893429B (en) * 2022-04-29 2024-03-15 山东科技大学 Compressor clearance leakage flow control method based on shock wave deceleration effect and compressor

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