CN108953232B - Axial-flow compressor with static blades distributed in non-axial symmetry manner - Google Patents

Axial-flow compressor with static blades distributed in non-axial symmetry manner Download PDF

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CN108953232B
CN108953232B CN201810803953.XA CN201810803953A CN108953232B CN 108953232 B CN108953232 B CN 108953232B CN 201810803953 A CN201810803953 A CN 201810803953A CN 108953232 B CN108953232 B CN 108953232B
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compressor
distortion
stator blade
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blade
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CN108953232A (en
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孙鹏
傅文广
徐文峰
杨木肖
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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
    • F04D29/40—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
    • 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
    • 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

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

Abstract

The invention relates to an axial-flow compressor, in particular to a non-axisymmetrically distributed stationary blade axial-flow compressor. The invention designs a non-axisymmetrically distributed stator blade axial-flow compressor, which replaces stator blades in the distortion affected area of the compressor with modified stator blades for inhibiting air flow separation, so that the performance of the compressor is approximately the same as that of the axisymmetric compressor under the condition of ensuring uniform inflow of the compressor, and simultaneously, the pressure ratio and the efficiency of the compressor under the condition of distortion inlet can be improved, thereby expanding the stability margin of the axial-flow compressor affected by distortion at the inlet and providing a new design idea and method for designing a high-load fan/compressor.

Description

Axial-flow compressor with static blades distributed in non-axial symmetry manner
Technical Field
The invention belongs to the technical field of impeller machinery, relates to an axial-flow compressor, and particularly relates to a non-axisymmetrically distributed stationary blade axial-flow compressor.
Background
High performance aircraft engines and gas turbines place an urgent demand for high load, high efficiency, and high stability margins on compression systems. Axial-flow compressors are the key components of modern aircraft engines, ship gas turbines and industrial gas turbines, and are the key points of development in all countries in the world. The design mainstream of the current axial-flow compressor is that the inlet of the compressor is assumed to be uniform air inlet, but in practical application, the compressor almost has no exception and works under the condition of distorted inlet. The intake distortion changes the original design condition of the compressor, the axial symmetric flow of the airflow is damaged, the stability margin of the compressor is reduced and the performance is deteriorated if the intake distortion is small, and the stall and surge of the compressor are caused if the intake distortion is large, so that the normal work of the whole compressor is seriously influenced. Therefore, the improvement of the stability and the distortion resistance of the compressor has great practical significance for ensuring the stable operation of a power system.
Research shows that the inlet total pressure distortion enables a flow field of the air compressor to enter a stall state in advance, after the distorted fluid flows through the movable blades, serious angular region separation is generated in the stationary blade flow channel in a circumferential partial range, the angular region separation in the circumferential partial range is only concentrated in the flow channel affected by the distorted fluid, and the flow in the whole air compressor shows a strong non-axisymmetric characteristic.
Disclosure of Invention
The invention provides a concept of non-axisymmetrically distributed stationary blades aiming at the obvious non-axisymmetric characteristic in a compressor under the distortion condition, and designs a non-axisymmetrically distributed stationary blade axial-flow compressor, namely, blades capable of improving angular region separation flow are adopted in a stationary blade region influenced by a distorted fluid, and prototype blades are still adopted in a range influenced by the distorted fluid to achieve the purpose of improving a non-axisymmetric flow field by utilizing a non-axisymmetric geometric structure.
In order to achieve the purpose, the invention adopts the following technical scheme:
a method for prejudging distortion fluid influence areas of an axial-flow compressor is characterized in that a circumferential area affected by distortion fluid in a stator blade is a stator blade distortion influence area, the total pressure distortion position of an inlet of the compressor is fixed, but the circumferential position and the range of the stator blade distortion influence area are changed relative to the inlet along with the rotation of the blades of the compressor, and the prejudging method of the stator blade distortion influence areas comprises the following specific steps:
(1) determining distortion transfer variations
Predicting according to a multi-stage flat compressor theory proposed by Mazzawy to obtain pressure transfer change and particle transfer change, wherein the pressure transfer formula is an expression (1), and the particle transfer formula is an expression (2):
Figure BDA0001737744280000021
Figure BDA0001737744280000022
in the formula: delta thetapressureRepresenting the angle of change of pressure transmission, Delta thetaparticieRepresenting the angle of variation of particle transport, b representing the axial chord length, caxRepresenting axial velocity, ω being angular velocity of blade rotation, csRepresents the speed of sound;
(2) determining stator blade distortion impact zone
The transfer speed of the pressure is faster than the transfer change of the particles, so that the circumferential influence range of the total pressure distortion of the inlet of the compressor on the flow channel of the stator blade can be determined by the formula (3):
Δθst＝Δθparticle-Δθpressure+γ (3)
in the formula: delta thetastThe vane distortion angle is indicated, and γ indicates the distortion angle.
A non-axisymmetrically distributed stator blade axial-flow compressor is characterized in that a prejudging method of a distortion fluid influence area of the axial-flow compressor is applied, in a stator blade distortion influence area obtained through calculation, an original stator blade is replaced by a modified stator blade capable of inhibiting air flow separation, and the original stator blade on an impeller and the modified stator blade in the stator blade distortion influence area are in non-centrosymmetric distribution relative to the central axis of the impeller and are called as non-axisymmetrically distributed; the original stationary blades are distributed on the impeller in central symmetry relative to the central axis of the impeller, which is called axial symmetry distribution; the modified stator blade is replaced in the stator blade distortion affected zone of the compressor, so that the purpose of non-axisymmetric distribution of the stator blades on the impeller is to reduce or even eliminate the separation of the stator blade suction surface of the affected zone of the distorted fluid, namely, the loss of the corner zone of the stator blade suction surface is reduced, and the flow separation is weakened, thereby improving the through-flow capacity of the compressor under the distortion condition; the improved stator blade is designed according to the specific condition that the compressor stator blade is influenced by the deformed fluid.
Further, the modified stator blade is a transonic axial flow type single-stage compressor which adopts a forward-swept stator blade, namely a stator blade tip forward-swept mode.
Furthermore, according to the forward swept stationary blade of the transonic axial flow type single-stage compressor, the included angle between the laminated line at the upper end region of the forward swept stationary blade and the end wall is 5-10 degrees, namely the sweep angle alpha is 5-10 degrees, and the sweep height L is 10-40 percent of the original stationary blade height Lo.
Compared with the prior art, the invention has the beneficial effects that:
the non-axial symmetry of the axial flow compressor is realized by replacing the fixed blade in the distortion affected area of the axial flow compressor with the modified fixed blade for inhibiting the air flow separation, so that the non-axial symmetry of a flow field caused by inlet distortion incoming flow can be improved, the performance of the compressor under the condition of uniform incoming flow is approximately the same as that of the axially symmetric compressor, and the air flow conditions including the pressure ratio and the efficiency of the compressor in the distortion affected area under the condition of distortion inlet can be improved, so that the stability margin of the distortion affected area of the inlet of the axial flow compressor is enlarged, and a new design thought and a new method are provided for the design of a high-load fan/compressor.
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 described below, it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural diagram of a single-stage axisymmetric compressor in the prior art in embodiment 1 of the present invention;
FIG. 2 is a schematic diagram of the total pressure distortion influence area of the inlet of the movable blade in the embodiment 1 of the invention;
FIG. 3 is a schematic diagram showing the principle of transmission of distortion influence in embodiment 1 of the present invention;
FIG. 4 is a schematic view showing an influence region of total pressure distortion of a stationary blade inlet in embodiment 1 of the present invention;
FIG. 5 is a parameter diagram of a forward swept stator vane in embodiment 1 of the present invention, (a) is a view angle diagram of a forward swept stator vane design, and (b) is a scheme diagram of a forward swept stator vane;
FIG. 6 is a schematic view of a non-axisymmetrical stator blade structure in embodiment 1 of the invention;
FIG. 7 is a schematic view of a forward swept stator vane structure in embodiment 1 of the invention;
FIG. 8 is a characteristic line of an axisymmetric and non-axisymmetric stator blade compressor under a distortion condition in embodiment 1 of the present invention;
in the figure: 1. the method comprises the steps of a movable blade, 2, an original static blade, 3, a movable blade distortion influence area, 4, a static blade distortion influence area, 5, a forward swept static blade, 6 and an impeller central shaft.
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.
Example 1
As shown in fig. 1, the prototype axial-flow compressor is a compressor stage experimental part in a key laboratory of the small gas turbine technology for the ship in liaoning province of university of maritime, and consists of a stage-one movable blade and a stage-one stationary blade, and original stationary blades 2 of the prototype compressor are in central symmetrical distribution on an impeller relative to an impeller central shaft 6, and are called as axial symmetrical distribution;
in order to verify the effect of the invention, the inventor carries out numerical simulation on the whole-stage compressor before and after modification, and specific parameters of the single-stage axial-flow compressor for numerical simulation research are shown in the following table:
Figure BDA0001737744280000061
the modified design of the axial-flow compressor in the embodiment is only described by taking a certain transonic axial-flow type single-stage compressor as an example, and the distortion at the inlet of the compressor is mainly defined by a distortion degree DA and a distortion angle gamma;
Figure BDA0001737744280000071
in the formula (I), the compound is shown in the specification,
Figure BDA0001737744280000072
is the average total pressure of the low-pressure area,
Figure BDA0001737744280000073
is the average total pressure of the high-pressure area,
Figure BDA0001737744280000074
is the average total pressure of the inlet cross-section, i.e.
Figure BDA0001737744280000075
Average total pressure sum of low pressure area
Figure BDA0001737744280000076
Average total pressure of the high pressure area.
The inlet distortion parameters of the compressor in the embodiment are as follows:
the distortion angle gamma of the inlet of the air compressor is 60 degrees,
Figure BDA0001737744280000077
DA＝0.05。
as shown in fig. 2, the position of total pressure distortion at the inlet of the compressor is fixed, but with the rotation of the compressor movable blades 1, distortion is transmitted to the stationary blade through the movable blades 1, as shown in fig. 3, the circumferential region affected by the distortion fluid in the stationary blade is a stationary blade distortion affected zone 4, the circumferential position and range of the stationary blade distortion affected zone 4 are changed from the inlet, and the specific steps of predicting the stationary blade distortion affected zone 4 are as follows:
(1) determining distortion transfer variations
Aiming at the steady-state circumferential total pressure distortion, the distortion position at the inlet of the air compressor is not changed, so that the influence of the steady-state circumferential total pressure distortion on the performance and the stability of the engine can be estimated, the pressure transfer change and the particle transfer change can be obtained by predicting according to the multi-level flat air compressor theory proposed by Mazzawy, wherein the pressure transfer formula is formula (1), and the particle transfer formula is formula (2):
Figure BDA0001737744280000079
in the formula: delta thetapressureRepresenting the angle of change of pressure transmission, Delta thetaparticieRepresenting the angle of variation of particle transport, b representing the axial chord length, caxRepresenting axial velocity, ω being angular velocity of blade rotation, csRepresenting the speed of sound.
(2) Determining stator blade distortion impact zone
The transfer speed of the pressure is faster than the transfer change of the particles, so that the circumferential influence range of the total pressure distortion of the inlet of the compressor on the flow channel of the stator blade can be determined by the formula (3):
Δθst＝Δθparticle-Δθpressure+γ (3)
in the formula: delta thetastThe vane distortion angle is indicated, and γ indicates the distortion angle.
The parameters of the compressor in this embodiment are as follows:
n＝24566.8r/min→ω＝147400.8°/s；γ＝60°；
cax＝170m/s；b＝0.03m；cs＝330m/s
the circumferential distortion influence angle Delta theta of the stationary blade cascade obtained according to the parameters of the compressor and the above equations (1) - (3)stThe range is 78 deg., thereby approximately determining the modified vane placement range, as shown in fig. 4.
A non-axisymmetrically distributed stator blade axial-flow compressor, apply the above-mentioned axial-flow compressor distortion fluid influence area's prejudge method, in calculating and obtaining the stator blade distortion influence area 4, change original stator blade 2 into having and inhibit the modified stator blade that the air current separates, make original stator blade and modified stator blade in the stator blade distortion influence area 4 on the impeller present the non-centrosymmetric distribution relatively to impeller central axis 6, call non-axisymmetrically distributed; in contrast, in the prior art shown in fig. 1, the original stationary vanes are distributed on the impeller in a central symmetrical manner with respect to the central axis of the impeller, which is called axial symmetrical distribution. The modified stator blade is replaced in the stator blade distortion affected zone 4 of the compressor, so that the purpose of non-axisymmetric distribution of the stator blades on the impeller is to reduce or even eliminate the separation of the suction surface of the stator blade in the affected zone of the distorted fluid, namely, the loss of the corner area of the suction surface of the stator blade is reduced, and the flow separation is weakened, thereby improving the through-flow capacity of the compressor under the distortion condition; the improved stator blade is designed according to the specific condition that the compressor stator blade is influenced by the deformed fluid.
In the embodiment, the design of the modified stator blade 5 is only described by taking a certain transonic axial flow type single-stage compressor as an example, and other compressors are also applicable to non-axisymmetric stator blades, but different modified stator blade designs can be performed according to specific conditions; the modified stator blade adopts a forward swept stator blade 5 in the embodiment, as shown in fig. 5, the forward swept stator blade 5 selects an optimal swept blade modified scheme by performing numerical simulation calculation on a large number of modified schemes, the forward swept stator blade 5 adopts a blade tip forward swept mode, the included angle between an upper end region stacking line and an end wall, namely the sweep angle alpha of the sweep angle is 10%, and the sweep height L is 30% of the blade height Lo of the original stator blade 2. As shown in FIG. 6, a forward swept vane 5 is disposed within the compressor vane distortion affected zone 4. The forward swept vanes 5 and the original vanes 2 are structurally modified as shown in fig. 7.
Compared with a prototype compressor which is shown in figure 1 and consists of a first-stage movable blade and a first-stage fixed blade and is provided with the fixed blades which are distributed symmetrically and uniformly, the axial flow compressor with the non-axisymmetrically distributed fixed blades has the following optimization effects:
stability margin SM, total pressure ratio pi and isentropic efficiency eta of the compressor, whereinAnd msIs the total pressure ratio and mass flow near the stall point,
Figure BDA0001737744280000092
and moIs the total pressure ratio and mass flow at the point of highest efficiency,
Figure BDA0001737744280000093
andis the mass average total pressure of the inlet and the outlet of the compressor,andis the total temperature of the inlet and outlet of the compressor:
Figure BDA0001737744280000098
Figure BDA0001737744280000099
the improved stationary blades are distributed in the non-axisymmetric mode, the stability margin SM of the compressor under the distortion condition is enlarged, and the total pressure ratio and the efficiency of the compressor are improved.
As shown in fig. 8, the total pressure ratio and the isentropic efficiency of the non-axisymmetric stator blade compressor under the distortion condition are both obviously improved, and the stability margin of the compressor is found to be enlarged by 1% through calculation. Therefore, the axial-flow compressor with the fixed blades distributed in the non-axisymmetric way can effectively improve the performance of the compressor under the condition of inlet incoming flow distortion of the compressor and enlarge the stability margin of the compressor.
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 (4)

1. A method for prejudging a distortion fluid influence area of an axial-flow compressor is characterized in that a circumferential area influenced by a distortion fluid in a stationary blade is a stationary blade distortion influence area, the position of total pressure distortion at an inlet of the compressor is fixed, but the circumferential position and the range of the stationary blade distortion influence area are changed relative to the inlet along with the rotation of a movable blade of the compressor, and the method for prejudging the stationary blade distortion influence area comprises the following specific steps:
(1) determining distortion transfer variations
Predicting the pressure transmission change and the particle transmission change according to the following formulas, wherein the pressure transmission formula is an expression (1), and the particle transmission formula is an expression (2):
Figure FDA0002227196060000011
Figure FDA0002227196060000012
in the formula: delta thetapressureIndicating pressure transmission changeAngle of change, Delta thetaparticleRepresenting the angle of variation of particle transport, b representing the axial chord length, caxRepresenting axial velocity, ω being angular velocity of blade rotation, csRepresents the speed of sound;
(2) determining stator blade distortion impact zone
The transfer speed of the pressure is faster than the transfer change of the particles, so that the circumferential influence range of the total pressure distortion of the inlet of the compressor on the flow channel of the stator blade can be determined by the formula (3):
Figure FDA0002227196060000013
in the formula: delta thetastThe vane distortion angle is indicated, and γ indicates the distortion angle.
2. A non-axisymmetrically distributed stator blade axial-flow compressor is characterized in that a prejudging method of a distortion fluid influence area of the axial-flow compressor is applied, in a stator blade distortion influence area obtained through calculation, an original stator blade is replaced by a modified stator blade capable of inhibiting air flow separation, and the original stator blade on an impeller and the modified stator blade in the stator blade distortion influence area are in non-centrosymmetric distribution relative to the central axis of the impeller and are called as non-axisymmetrically distributed; the original stationary blades are distributed on the impeller in central symmetry relative to the central axis of the impeller, which is called axial symmetry distribution; the modified stator blade is replaced in the stator blade distortion affected zone of the compressor, so that the purpose of non-axisymmetric distribution of the stator blades on the impeller is to reduce or even eliminate the separation of the stator blade suction surface of the affected zone of the distorted fluid, namely, the loss of the corner zone of the stator blade suction surface is reduced, and the flow separation is weakened, thereby improving the through-flow capacity of the compressor under the distortion condition; the improved stator blade is designed according to the specific condition that the compressor stator blade is influenced by the deformed fluid.
3. The non-axisymmetric stator blade axial flow compressor of claim 2, wherein said modified stator blade, transonic axial flow single-stage compressor employs forward swept stator blades, i.e., stator blade tip forward swept.
4. The non-axisymmetrically-distributed stationary blade axial flow compressor of claim 3, wherein in the forward-swept stationary blades of the transonic axial flow single-stage compressor, an included angle between an upper end area stacking line of the forward-swept stationary blades and an end wall, namely a sweep angle α is 5-10 degrees, and a sweep height L is 10-40% of an original stationary blade height Lo.
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