CN112302984A - Implementation method of experimental suction groove of plane cascade of gas compressor - Google Patents

Implementation method of experimental suction groove of plane cascade of gas compressor Download PDF

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Publication number
CN112302984A
CN112302984A CN202011171918.4A CN202011171918A CN112302984A CN 112302984 A CN112302984 A CN 112302984A CN 202011171918 A CN202011171918 A CN 202011171918A CN 112302984 A CN112302984 A CN 112302984A
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China
Prior art keywords
suction
line
blade
suction groove
cascade
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Pending
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CN202011171918.4A
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Chinese (zh)
Inventor
马宇晨
滕金芳
朱铭敏
羌晓青
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Shanghai Jiaotong University
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Shanghai Jiaotong University
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Priority to CN202011171918.4A priority Critical patent/CN112302984A/en
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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
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • 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
    • F04D29/66—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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction

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

Abstract

A method for realizing a planar cascade experiment suction slot of a gas compressor comprises the steps of selecting adjacent cascades in a planar cascade as a first cascade and a second cascade, wherein the second cascade is positioned in the direction of the blade back of the first cascade; the method comprises the steps of designing the central position of a suction groove, the vertical line position of the suction groove and the parallel line position of the suction groove, and then arranging the suction groove.

Description

Implementation method of experimental suction groove of plane cascade of gas compressor
Technical Field
The invention relates to the technology in the field of axial flow compressors, in particular to a method for realizing a planar cascade experiment suction groove of a compressor.
Background
When a plane cascade experiment of the gas compressor is carried out, the condition of boundary layer separation near the end wall of the gas compressor often occurs under the influence of stronger counter pressure gradient and an incoming flow boundary layer in a cascade channel of the gas compressor. Separation of the end wall boundary layers within the cascade channels results in an increase in the dense flow ratio. Under the condition of high load of the blades of the compressor, the separation degree of the boundary layer of the end wall is increased, and great influence is generated on a main flow area of the blades, so that relevant cascade parameters, such as outlet airflow angle, loss coefficient, surface pressure coefficient of the blades and the like, have great deviation with performance parameters of the blades under a two-dimensional flow field condition when plane cascade measurement of the compressor is carried out, and the actual performance of the cascade cannot be accurately reflected.
The traditional suction mode comprises that in a blade cascade channel of a gas compressor, uniform suction grooves are arranged from an inlet to an outlet at the upper end wall and the lower end wall or suction grooves close to a suction surface are arranged after 50% of axial chord length of a blade, the density flow ratio is controlled by a mode of pumping away an inlet boundary layer, and the duality of a cascade flow field is ensured. Although the traditional suction mode has a simple structure and is easy to realize, the requirement on the suction amount is higher due to the larger size of the suction groove, the uniformity of suction at different positions of the suction groove is difficult to ensure, and the periodicity of a cascade flow field is greatly influenced. The mode of slotting the rear half part close to the suction surface has insufficient control capability on the blade cascade separation area of the air compressor with low consistency and high load, and the binary flow at the position near 50 percent of the blade height is difficult to ensure, thereby influencing the measurement of the performance parameters of the blade cascade.
Disclosure of Invention
The invention provides a method for realizing a plane cascade experiment suction groove of a gas compressor, aiming at solving the problems that the prior art can not control low consistency and the density ratio of a cascade of the high-load gas compressor and the binary performance of a cascade flow field can not be ensured, wherein the axial density ratio (namely the ratio of the product of the axial speed and the density of an outlet and an inlet of the cascade) is equal to 1 to ensure the measurement accuracy of the plane cascade of the gas compressor, and the control of the axial density ratio in the plane cascade experiment process of the gas compressor is realized.
The invention is realized by the following technical scheme:
the invention relates to a method for realizing a plane cascade experiment suction groove of a gas compressor, which comprises the following steps:
step 1) designing a blade cascade: selecting adjacent blade grids in the plane blade grid as a first blade grid and a second blade grid, wherein the second blade grid is positioned in the blade back direction of the first blade grid;
step 2) designing the central position of the suction groove: moving the distance H1 between the central line of the suction slot and the camber line of the blade along the connecting line of the front edge point to the suction surface of the blade at the front edge point of the first blade row along the connecting line of the front edge point, and making the central line of the suction slot parallel to the camber line of the blade;
step 3) designing the position of a vertical line of the suction groove: respectively making parallel lines of a front edge point connecting line at the position of 40% axial chord length and the position of 80% axial chord length of the first blade cascade, and respectively making a first vertical line and a second vertical line which are vertical to the central line of the suction groove and have the length of H2 by taking the central line of the suction groove as a symmetry axis at the intersection point of the two parallel lines and the central line of the suction groove;
step 4), designing the parallel line position of the suction groove: the two end points of the first vertical line are respectively made into a first parallel line and a second parallel line which are parallel to the central line of the suction groove, and the closed area formed by the first parallel line, the second parallel line, the first vertical line and the second vertical line is the actual range of the first suction groove.
Of the first and second parallel lines, the first parallel line is close to the first blade cascade, and the second parallel line is far away from the first blade cascade.
Step 5) arranging a suction groove: the first suction groove is moved by a single-adjacent suction groove pitch H3 in a direction away from the suction surface of the first cascade along a leading edge point connecting line with the starting point of the center line of the first suction groove as a reference to obtain a second suction groove, and is moved by a distance twice H3 to obtain a third suction groove.
Preferably, the movement H3 is continued by repeating step 5) to create more suction slots.
The invention relates to a plane cascade structure of a gas compressor obtained by the method, which comprises a plurality of cascades vertically arranged in upper and lower end walls, wherein: a plurality of suction grooves are arranged between the adjacent blade grids on the upper end wall and the lower end wall and close to one side of the blade back of the suction surface.
The suction grooves are preferably three and arranged in parallel, and specifically comprise: three suction grooves with the same shape are arranged along the connecting line of the front edge point and towards the direction far away from the suction surface.
The first suction groove includes: a first side wall surface parallel to the central line of the suction groove and close to the suction surface of the first blade cascade, a second side wall surface parallel to the central line of the suction groove and close to the pressure surface of the second blade cascade, a third side wall surface vertical to the central line of the suction groove and a fourth side wall surface vertical to the central line of the suction groove.
The distance between the first side wall surface and the central line of the suction groove is 0.5 times H2, and the distance between the central line of the suction groove and the mean camber line of the blade along the direction of the connecting line of the front edge point is H1.
The distance between the second side wall surface and the central line of the suction groove is 0.5 times H2;
the axial position of a foot of the third side wall surface is the length of 40% of the axial chord of the blade cascade;
the vertical foot axial position of the fourth side wall surface is the length of 80% of the axial chord of the blade cascade;
the second suction groove and the third suction groove center line are respectively separated from the first suction groove center line H3 and 2 times H3.
Technical effects
The invention integrally solves the problem that the prior art can not control the influence of the flow near the end wall on the main flow area at the pitch diameter of the blade cascade in the experiment of the blade cascade of the gas compressor. Compared with the prior art, the invention can effectively pump low-energy fluid from the cascade end wall under the condition of a certain pumping quantity through the design and reasonable arrangement of the pumping grooves, eliminates the boundary layer separation of the high-load compressor cascade near the end region, effectively controls the dense flow ratio, ensures the duality of a cascade flow field, and can meet the measurement requirement of a plane cascade experiment of the compressor. Meanwhile, by the design of the suction groove, the suction amount is reasonably utilized, the suction distribution is more uniform, the influence on the periodicity of the blade cascade is lower, the control force on an end region of the high-load compressor is stronger, a better density flow ratio control effect is achieved, and the requirements on suction equipment and the cost of a suction experiment of the blade cascade of the compressor are reduced.
Drawings
FIG. 1 is a schematic view of a planar cascade structure of a compressor according to the present invention;
FIG. 2 is a schematic view of a compressor plane cascade suction groove structure according to the present invention;
FIGS. 3(a) and (b) are schematic views of upper and lower cover plates according to the embodiment;
in the figure: 1 end wall, 2 suction side, 3 pressure side, 4 leading edge point, 5 trailing edge point, 6 cascade camber line, 7 leading edge point connecting line, 8 trailing edge point connecting line, 9 suction groove central line, 10 suction groove initial axial position line, 11 suction groove end axial position line, 12 first parallel line, 13 second parallel line, 14 first cascade, 15 second cascade, 16 suction groove, 17 upper cover plate, 18 lower cover plate.
Detailed Description
As shown in fig. 1 and fig. 2, the embodiment relates to a method for implementing a planar cascade suction slot of a low-consistency compressor, which comprises the following steps:
step 1) determining a blade cascade: one blade of the planar blade cascade is selected as a first blade cascade 14, the planar blade cascade adjacent to the first blade cascade is selected as a second blade cascade 15, and the second blade cascade 15 is located on one side of the suction surface of the first blade cascade 14.
Step 2) determining the position of the central line of the suction groove: at the leading edge point 4 of the cascade, a curve parallel to the mean camber line 6 of the blade is made, with the end point of the curve and the trailing edge line 8 of the cascade having the same axial position, along the leading edge point line 7 in the direction of the suction surface of the blade, by a distance H1 as the starting point, which curve is called the suction slot centre line 9.
Step 3) determining the position of a vertical line of the suction groove: and (3) respectively connecting parallel lines with the leading edge point connecting line 7 at the position of 40% of axial chord length and the position of 80% of axial chord length to obtain a suction groove starting axial position line 10 and a suction groove ending axial position line 11, taking the suction groove central line 9 as a symmetry axis at the intersection point position of the two parallel lines of the suction groove starting and ending position lines 10 and 11 and the suction groove central line 9, making a line segment perpendicular to the suction groove central line 9, wherein the line segment is H2 in length, the line segment close to the leading edge is a first vertical line, and the line segment close to the trailing edge is a second vertical line.
Step 4) determining the parallel line position of the suction groove: the two ends of the first vertical line are respectively made into two curves parallel to the central line 9 of the suction groove, the first parallel line 12 is close to the first blade cascade, and the second parallel line 13 is far away from the first blade cascade.
Step 5) determining the range of the suction groove: the first parallel lines 12, the second parallel lines 13, and the closed area formed by the first vertical lines and the second vertical lines are the actual range of the suction grooves, which are referred to as first suction grooves.
Step 6) determining the suction slot arrangement: the first suction groove is moved by a distance H3 in a direction away from the first cascade suction surface along the leading edge point connecting line 7 with the starting point of the first suction groove center line 9 as a reference to obtain a second suction groove, and is moved by a distance 2 times H3 to obtain a third suction groove.
Step 7), opening a suction groove: the closed curve area of the suction groove is opened as the suction groove.
The embodiment relates to a suction slot of a plane cascade of a compressor realized by the method, the suction slot is arranged on the upper end wall 1 and the lower end wall 1 of the plane cascade of the compressor and is positioned between the suction surface of a first cascade 14 and the pressure surface of a second cascade 15, and the first cascade 14 and the second cascade 15 are adjacent cascades in the whole plane cascade experimental part;
three suction slots are arranged in total in a direction away from the suction surface 2 of the first cascade 14 with reference to the starting point of the first suction slot center line 9, wherein the second and third suction slots have the same shape as the first suction slot.
The first suction groove has:
the first side wall surface is parallel to the central line of the suction groove, is close to the suction surface 2 of the first blade row 14, has a distance of 0.5 times H2 with the central line 9 of the suction groove, and has a distance of H1 with the central arc line of the blade row along the direction of the connecting line 7 of the front edge point;
a second side wall surface parallel to the suction slot center line 9 and close to the pressure surface 3 of the second cascade 15, the distance from the suction slot center line 9 is 0.5 times H2;
the third side wall surface is vertical to the central line 9 of the suction groove, and the axial position of the foot is the length of 40% of the axial chord of the blade cascade;
the fourth side wall surface is vertical to the central line 9 of the suction groove, and the axial position of the foot is the length of 80% of the axial chord of the blade cascade;
the distance between the starting points of the second and third suction slot centre lines and the starting point of the first suction slot centre line 9 in the direction of the leading edge point connection 7 is H3 and 2 times H3.
Fig. 3 is a schematic view of the end walls, i.e., the upper and lower cover plates, designed in accordance with the above-described method. In this embodiment, H1 is 1/12 pitch; h2 is 1/30 grid distance; h3 is 1/6 grid pitch, and the distance H1 corresponding to the connecting line direction of the central line of the first suction groove and the camber line of the blade along the front edge point is 5 mm; the suction slot width H2 is 2 mm; the single adjacent suction slot spacing H3 is 10mm, wherein the grid pitch is 60mm, and the cascade chord length is 60 mm. The whole body is provided with three suction grooves, the distance between every two adjacent suction grooves is 10mm, the suction starting position of the blade cascade is 40% of the axial chord length, and the termination position is 80% of the axial chord length.
Through specific practical experiments, the design and arrangement mode of the suction grooves can realize effective control of the density flow ratio under different incoming flow conditions, and in the experiments, when the Reynolds numbers of the incoming flows are respectively 1.5 multiplied by 105The density-flow ratio is reduced from 1.08 to 1.03, and the Reynolds number is 2.5 multiplied by 105The density-flow ratio is reduced from 1.12 to 1.05, and the Reynolds number is 4.0 multiplied by 105The density flow ratio is reduced from 1.13 to 1.06.
In conclusion, the end wall suction grooves are designed and arranged, so that the influence of uneven suction capacity caused by excessively long suction grooves on the periodicity of the blade cascade and the problem of insufficient flow control force of the end region of the high-load blade cascade are effectively avoided, the flow near the end wall of the low-consistency high-load blade cascade is effectively controlled under the condition of a certain suction capacity, the duality and the periodicity of a blade cascade test are ensured, and the experiment difficulty and the experiment cost are reduced.
The foregoing embodiments may be modified in many different ways by those skilled in the art without departing from the spirit and scope of the invention, which is defined by the appended claims and all changes that come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.

Claims (8)

1. A method for realizing a suction groove of a plane cascade experiment of a compressor is characterized by comprising the following steps:
step 1) designing a blade cascade: selecting adjacent blade grids in the plane blade grid as a first blade grid and a second blade grid, wherein the second blade grid is positioned in the blade back direction of the first blade grid;
step 2) designing the central position of the suction groove: moving the distance H1 between the central line of the suction slot and the camber line of the blade along the connecting line of the front edge point to the suction surface of the blade at the front edge point of the first blade row along the connecting line of the front edge point, and making the central line of the suction slot parallel to the camber line of the blade;
step 3) designing the position of a vertical line of the suction groove: respectively making parallel lines of a front edge point connecting line at the position of 40% axial chord length and the position of 80% axial chord length of the first blade cascade, and respectively making a first vertical line and a second vertical line which are vertical to the central line of the suction groove and have the length of H2 by taking the central line of the suction groove as a symmetry axis at the intersection point of the two parallel lines and the central line of the suction groove;
step 4), designing the parallel line position of the suction groove: two end points of the first vertical line are respectively made into a first parallel line and a second parallel line which are parallel to the central line of the suction groove, and a closed area formed by the first parallel line, the second parallel line, the first vertical line and the second vertical line is the actual range of the first suction groove;
step 5) arranging a suction groove: the first suction groove is moved by a single-adjacent suction groove pitch H3 in a direction away from the suction surface of the first cascade along a leading edge point connecting line with the starting point of the center line of the first suction groove as a reference to obtain a second suction groove, and is moved by a distance twice H3 to obtain a third suction groove.
2. The method for realizing experimental suction grooves of planar blade cascades of a compressor, as set forth in claim 1, wherein the first and second parallel lines are closer to the first blade cascade, and the second parallel line is farther from the first blade cascade.
3. The method for realizing experimental suction slots of the plane blade cascade of the compressor as claimed in claim 1, wherein the H3 is continuously moved to establish more suction slots by repeating the step 5).
4. A compressor planar cascade structure obtained by the method of any one of the preceding claims comprising a plurality of cascades disposed vertically in upper and lower end walls, wherein: a plurality of suction grooves are arranged between the adjacent blade grids on the upper end wall and the lower end wall and close to one side of the blade back of the suction surface.
5. The compressor planar cascade structure of claim 4 wherein said suction slots are three and parallel to each other, specifically: three suction grooves with the same shape are arranged along the connecting line of the front edge point and towards the direction far away from the suction surface.
6. The compressor planar cascade structure of claim 4 or 5 wherein said first suction groove comprises: a first side wall surface parallel to the central line of the suction groove and close to the suction surface of the first blade cascade, a second side wall surface parallel to the central line of the suction groove and close to the pressure surface of the second blade cascade, a third side wall surface vertical to the central line of the suction groove and a fourth side wall surface vertical to the central line of the suction groove.
7. The compressor planar cascade structure of claim 6 wherein the first sidewall surface is spaced from the centerline of the suction slot by 0.5 times H2, the centerline of the suction slot is spaced from the mean camber line of the vane by H1 in the direction of the line joining the leading edge points;
the distance between the second side wall surface and the central line of the suction groove is 0.5 times H2;
the second suction groove and the third suction groove center line are respectively separated from the first suction groove center line H3 and 2 times H3.
8. The compressor planar cascade structure of claim 7 wherein the axial location of the foot of the third sidewall surface is at the axial chord length of 40% of the cascade;
the vertical foot axial position of the fourth side wall surface is the length of 80% of the axial chord of the blade cascade.
CN202011171918.4A 2020-10-28 2020-10-28 Implementation method of experimental suction groove of plane cascade of gas compressor Pending CN112302984A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113446261A (en) * 2021-07-24 2021-09-28 西北工业大学 Supersonic adsorption type compressor serial stator blade

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2000297789A (en) * 1999-04-14 2000-10-24 Tokyo Electric Power Co Inc:The Axial flow compressor
CN108108549A (en) * 2017-12-15 2018-06-01 中国航发沈阳发动机研究所 A kind of close stream of plane cascade axial velocity compares control method
CN109386490A (en) * 2018-12-13 2019-02-26 中国航发沈阳发动机研究所 A kind of Compressor Cascades suction socket and its design method
CN109826817A (en) * 2019-02-21 2019-05-31 西北工业大学 A kind of combination drawing-in type plane cascade experimental provision

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2000297789A (en) * 1999-04-14 2000-10-24 Tokyo Electric Power Co Inc:The Axial flow compressor
CN108108549A (en) * 2017-12-15 2018-06-01 中国航发沈阳发动机研究所 A kind of close stream of plane cascade axial velocity compares control method
CN109386490A (en) * 2018-12-13 2019-02-26 中国航发沈阳发动机研究所 A kind of Compressor Cascades suction socket and its design method
CN109826817A (en) * 2019-02-21 2019-05-31 西北工业大学 A kind of combination drawing-in type plane cascade experimental provision

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113446261A (en) * 2021-07-24 2021-09-28 西北工业大学 Supersonic adsorption type compressor serial stator blade

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Application publication date: 20210202