CN108119406B - Axial compressor circumferential large-interval small-through-hole casing - Google Patents

Axial compressor circumferential large-interval small-through-hole casing Download PDF

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CN108119406B
CN108119406B CN201810027169.4A CN201810027169A CN108119406B CN 108119406 B CN108119406 B CN 108119406B CN 201810027169 A CN201810027169 A CN 201810027169A CN 108119406 B CN108119406 B CN 108119406B
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casing
compressor
hole
holes
rotor
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CN108119406A (en
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黄国平
刘泽鹏
张志远
洪树立
杨雨轩
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence

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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 relates to a casing with large circumferential intervals and small through holes for an axial flow compressor, which structurally comprises the casing, through holes and a rotor; the through hole is arranged on the outer surface of the casing and is directly connected with the external environment atmosphere of the casing, and the rotor is arranged in the casing; the relative movement of the casing and the rotor and the pressure difference between the inside and the outside of the casing at the through hole are utilized to drive the gas at the through hole to flow, and the gas in the through hole realizes the periodic excitation effect on the flow in the compressor by periodically sweeping the rotor flow passage of the compressor. The advantages are that: 1) the influence range and the strength of adverse low-energy flow near the blade tip of the axial flow compressor can be inhibited, so that the stable working margin of the axial flow compressor is remarkably enlarged; 2) the unsteady excitation effect is utilized, so that the influence on the efficiency of the axial flow compressor is small; 3) simple structure and convenient application and implementation.

Description

Axial compressor circumferential large-interval small-through-hole casing
Technical Field
The invention relates to a casing with large circumferential intervals and small through holes for an axial flow compressor, and belongs to the technical field of compressor design.
Background
With the requirements of modern aeroengines on high thrust-weight ratio, low fuel consumption rate and small windward area, the gas compressor needs to have higher stage pressure ratio to meet the performance requirements. However, as the stage pressure ratio of the compressor is higher, the load becomes larger, and unstable conditions such as rotating stall and surge are likely to occur. Unstable conditions such as rotating stall and surge can bring about rapid reduction of engine performance and serious vibration problems, and have adverse effects on the service life of the engine. Therefore, there is a need to develop effective flow control means to extend the compressor stability margin.
The blade tip flow field has higher Mach number, and a complex unsteady flow field structure is formed by the interaction of an end wall boundary layer, blade tip leakage flow and main flow and is most easily taken as a stall initial position, so the stable working range can be more effectively increased by controlling and improving the blade tip flow field. Depending on the characteristics of the excitation applied to the flow field, a control method based on stationary excitation and a control method based on non-stationary excitation can be classified. The former has been researched by a plurality of scholars, and a plurality of control methods are designed to effectively increase the stability margin, such as blade tip steady air injection and the like; however, the excitation strength to be applied is large, the influence on the main flow is obvious, the efficiency of the compressor is reduced while the stability margin is enlarged, a complex pipeline structure and a control valve are required, and the weight and the cost of the engine are increased. The control means based on unsteady excitation can apply excitation with a certain frequency to the flow field, when the excitation frequency is near the main frequency of the flow field, a certain coherence effect can be generated, and a sequence planning mechanism of the flow field is changed to be more orderly, so that the phenomena of rotating stall, surging and the like are delayed, and the stability margin is enlarged. The excitation intensity required by the unsteady excitation is much smaller than that of the steady excitation, the influence on the main flow is small, and the influence on the efficiency can be reduced while the stability is expanded. Therefore, the control mode based on unsteady excitation has great superiority, and a simple and reliable concrete implementation mode which accords with engineering practice is needed.
Disclosure of Invention
The invention provides a casing with large circumferential intervals and small through holes for an axial flow compressor, and aims to furthest enlarge the stability margin of the compressor on the premise of reducing the influence on the efficiency of the compressor and simplifying the complexity of a control method.
The technical solution of the invention is as follows: the axial flow compressor casing with large circumferential intervals and small through holes structurally comprises a casing 1, through holes 2 and a rotor 3; the through hole 2 is arranged on the outer surface of the casing 1 and is directly connected with the external environment atmosphere of the casing 1, and the rotor3 is arranged inside the casing 1.
The invention has the advantages that:
1) the influence range and the strength of adverse low-energy flows (leakage vortex, blade back separation vortex and the like) near the blade tip of the axial flow compressor can be inhibited, so that the stable working margin of the axial flow compressor is remarkably enlarged;
2) by utilizing the unsteady excitation effect, the total through hole area on the casing is smaller than that of a common processing casing by more than one order of magnitude, and the influence on the efficiency of the axial flow compressor is small;
3) simple structure and convenient application and implementation.
Drawings
FIG. 1 is a schematic view of a partial structure of a casing with large circumferential intervals and small through holes of an axial flow compressor.
2-1 and 2-2 are schematic diagrams of excitation modes of a circumferential large-interval small-through-hole casing of the axial flow compressor, wherein the diagram 2-1 is a schematic diagram of injection action, and the diagram 2-2 is a schematic diagram of suction action.
FIG. 3 is a schematic diagram of distribution of through holes of a casing with large circumferential intervals and small through holes of an axial flow compressor.
The attached figures 4-1, 4-2 and 4-3 are schematic diagrams of shapes of circumferential large-interval small-through-hole casing through holes of the axial-flow compressor, wherein the figure 4-1 is a schematic diagram of a rectangular through hole, the figure 4-2 is a schematic diagram of an oval through hole, and the figure 4-3 is a schematic diagram of a super-oval through hole.
FIGS. 5-1 and 5-2 are schematic diagrams showing the positions of the through holes under different excitation modes, wherein FIG. 5-1 is a schematic diagram showing the spraying action and FIG. 5-2 is a schematic diagram showing the pumping action.
Wherein 1 is a casing, 2 is a through hole, 3 is a rotor, L1 and L2 are distances from the through hole to a front edge, B is axial chord length of the axial-flow compressor, R1 is casing radius (thickness of the casing is not counted), R2 is hub radius, A is ellipse (hyperellipse) major axis length, B is ellipse (hyperellipse) minor axis length, C is rectangle length, D is rectangle width, and R is fillet radius.
Detailed Description
As shown in fig. 1, the axial flow compressor casing with large circumferential intervals and small through holes structurally comprises a casing 1, through holes 2 and a rotor 3; the through hole 2 is arranged on the surface of the casing 1 and is directly connected with the external ambient atmosphere of the casing 1, and the rotor3 is arranged inside the casing 1; the relative movement of the casing and the rotor and the pressure difference between the inside and the outside of the casing at the through hole are utilized to drive the gas at the through hole to flow, and the gas in the through hole realizes the periodic excitation effect on the flow in the compressor by periodically sweeping the rotor flow passage of the compressor.
As shown in fig. 2-1 and 2-2, according to different gauge pressures Pb (difference between internal flow field pressure and external environment atmospheric pressure) at the through hole, excitation of the blade tip flow field by external atmosphere is divided into periodic injection excitation and periodic suction excitation, and if the internal flow field gauge pressure of the compressor at the through hole is negative, the excitation mode is periodic injection; if the gauge pressure of the internal flow field of the compressor at the position of the through hole is positive, the excitation mode is a periodic suction effect.
As shown in fig. 3, N1 through holes 2 are arranged around the surface of the casing 1 at the short distance L1 between the rotor wheel inlet and the blade front edge, or around the surface of the casing 1 at the long distance L2 between the rotor wheel inlet and the blade front edge; the number of the through holes 2 is selected according to the number of the blades of the axial flow compressor, the number of the blades of the compressor is set to be Z, the Z is determined by the number of the blades of the existing axial flow compressor model, the range of N1/Z is 0.4-0.7, and the control effect is optimal when the ratio is 0.5.
As shown in fig. 4-1, 4-2, and 4-3, the shape of the through hole 2 can be selected from one of the following shapes:
the ratio of the major axis A to the minor axis B of the ellipse is 1.0-5.0, and the area A1 of a single through hole is 1/4πAB；
② rectangles with the ratio of the long side C to the short side D ranging from 1.0 to 5.0, such rectangles can have a small radius fillet with the fillet radius r being 1/5 of the short side, the area A3 of the fillet rectangle is (CD-pi r)2)；
A hyperellipse generated according to the following formula: (x/A)n+（y/B）n= 1; the ratio of the major axis A to the minor axis B is in the range of 1.0-5.0, the value of the index n is in the range of 2.0-10.0, and the area is 4ab ((1+1/n)) 2/(1+2/n), (z) is tz-1/et integrated t from 0 to positive infinity.
If the excitation is a periodic injection into the compressor, as shown in fig. 5-1, the through-hole position can be designed according to the following criteria: on the meridian plane, the distance between the center of the through hole on the casing and the front edge of the blade is L1, the axial chord length of the axial flow compressor is b, and the range of L1/b is-0.1-0.1. Wherein L1/b is negative, indicating that the through hole opens before the leading edge of the blade; l1/b is positive, indicating that the through hole opens in the cascade channel behind the leading edge of the blade; if the excitation is a periodic pumping of the compressor interior, as shown in fig. 5-2, the through hole position can be designed according to the following criteria: on the meridian plane, the distance between the center of the through hole on the casing and the front edge of the blade is L2, the axial chord length of the axial flow compressor is b, and the range of L2/b is 0.0-0.4.
If the excitation mode is periodic injection into the compressor, the area of the through hole can be designed according to the following criteria: the injection quantity of the through holes of the casing depends on the area of the through holes on the casing, the area of a single through hole is A1, the area of an inlet of the compressor is A2, and the area of A2 isπR12-πR22The range of A1/A2 is 0.01% -0.1%. During actual design, if the stability margin of the compressor needs to be improved and the influence on the efficiency needs to be reduced as much as possible, the A1/A2 is a middle value; if the influence on the efficiency can be larger due to the bias of considering the improvement of the stability margin of the compressor, A1/A2 can be larger; if the improvement of the stability margin can be small only by considering the influence degree on the efficiency of the compressor, the A1/A2 can be small.
If the excitation mode is periodic pumping inside the compressor, the area of the through hole can be designed according to the following criteria: the air extraction amount of the through hole of the casing depends on the area of the through hole on the casing, the area of a single through hole is A3, the area of an inlet of the compressor is A2, and the range of A3/A2 is 0.01-0.05%. During actual design, if the stability margin of the compressor needs to be improved and the influence on the efficiency needs to be reduced as much as possible, the A3/A2 is a middle value; if the influence on the efficiency can be larger due to the bias of considering the improvement of the stability margin of the compressor, A3/A2 can be larger; if the improvement of the stability margin may be small in consideration of the influence degree on the efficiency of the compressor, A3/a2 may be small.
Example 1 (Rotor parameter Rotor37 is taken as an example)
The axial flow compressor casing with large circumferential intervals and small through holes structurally comprises a casing 1, through holes 2 and a rotor 3; the casing 1 is cylindrical, the through hole 2 is formed in the outer surface of the casing 1 and is directly connected with the external environment atmosphere of the casing 1, and the rotors 3 are arranged in the hollow interior of the casing 1.
The number of the through holes 2 is N1, the through holes 2 are arranged around the surface of the casing 1 at the position of a short distance L1 between the inlet of the rotor impeller and the front edge of the blade, the number of the through holes 2 is selected according to the number of the axial flow compressor blades, the number of the compressor blades is Z, and when the number of the compressor blades is known to be Z =36, and N1/Z is 0.5, N1= 18.
The gauge pressure of the internal flow field of the compressor at the position of the through hole is negative, the excitation mode is a periodic injection effect, the distance between the position of the center of the through hole on the casing and the front edge of the blade is L1, the axial chord length of the axial flow compressor is b, the L1/b is-0.1, and the axial chord length b =84mm (rounded) of the known blade tip is arranged in front of the front edge of the blade, so that the L1=8.4 mm.
The area of a single through hole is A1, the area of a compressor inlet is A2, A1/A2=0.01%, A2=πR12-πR22And knowing that the radius of the inlet tip R1=152.86mm and the radius of the hub R2=107.02mm, A2=37420mm2(rounded), A1=3.742mm2。
The shape of the through hole 2 is an ellipse, the ratio of the major axis A to the minor axis B is 3.0, and the area A1 of a single through hole is 1/4πAB, known as A1=3.742mm2Then a =3.642mm, B =1.214 mm.
Example 2 (Rotor parameter Rotor37 is taken as an example)
The axial flow compressor casing with large circumferential intervals and small through holes structurally comprises a casing 1, through holes 2 and a rotor 3; the casing 1 is cylindrical, the through hole 2 is formed in the outer surface of the casing 1 and is directly connected with the external environment atmosphere of the casing 1, and the rotors 3 are arranged in the hollow interior of the casing 1.
The number of the through holes 2 is N1, the through holes 2 are arranged around the surface of the casing 1 at the position of the long distance L2 between the inlet of the rotor impeller and the front edge of the blade, the number of the through holes 2 is selected according to the number of the axial flow compressor blades, the number of the compressor blades is Z, and when the number of the compressor blades is known to be Z =36, and N1/Z is 0.5, N1= 18.
And if the gauge pressure of the internal flow field of the compressor at the position of the through hole is positive, the excitation mode is a periodic suction effect, the distance between the position of the center of the through hole on the casing and the front edge of the blade is L2, the axial chord length of the axial flow compressor is b, and L2/b is 0.2, and the axial chord length b =84mm (rounded), and L2=16.8mm is known to be opened in a cascade channel behind the front edge of the blade.
The area of a single through hole is A3, the area of the inlet of the compressor is A2, the A3/A2 is 0.01 percent, and the A2=πR12-πR22Known inletsThe radius of the blade tip R1=152.86mm, the radius of the hub R2=107.02mm, A2=37420mm2(rounded), A3=3.742mm2。
The shape of the through hole 2 is an ellipse, the ratio of the major axis A to the minor axis B is 3.0, and the area A3 of a single through hole is 1/4πAB, known as A3=3.742mm2Then a =3.642mm, B =1.214 mm.

Claims (1)

1. The axial flow compressor is characterized by comprising a casing, through holes and a rotor; the through hole is arranged on the outer surface of the casing and is directly connected with the external environment atmosphere of the casing, and the rotor is arranged in the casing;
the number of the through holes is N1, and the through holes are arranged around the surface of the casing at the short distance L1 between the rotor impeller inlet and the front edge of the blade;
the number N1 of the through holes is selected by referring to the number Z of the axial compressor blades, the number Z =36 of the compressor blades is obtained, and N1/Z is 0.5, so that N1= 18;
the shape of the through hole is one of an ellipse, a rectangle and a super ellipse; the ratio of the major axis A to the minor axis B of the ellipse is 1.0-5.0; the ratio of the long side C to the short side D of the rectangle is 1.0-5.0, and the rectangle is provided with a small-radius fillet; the hyperellipse is generated according to the following formula: (x/A)n+(y/B)n=1, the ratio of the major axis a to the minor axis B is 1.0-5.0, and the value of the index n is 2.0-10.0;
the gauge pressure of the internal flow field of the compressor at the position of the through hole is negative, the excitation mode is a periodic injection effect, the distance between the position of the center of the through hole on the casing and the front edge of the blade is L1, the axial chord length of the axial flow compressor is b, the L1/b is-0.1, and the axial chord length of the blade tip before the front edge of the blade is b =84 mm;
the area of a single through hole is A1, the area of a compressor inlet is A2, A1/A2=0.01%, A2=πR12-πR22，
The inlet tip radius R1=152.86mm, the hub radius R2=107.02 mm.
CN201810027169.4A 2018-01-11 2018-01-11 Axial compressor circumferential large-interval small-through-hole casing Active CN108119406B (en)

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Publication number Priority date Publication date Assignee Title
CN111520355B (en) * 2020-05-18 2021-06-22 南京航空航天大学 Adjustable phase and frequency unsteady flow control device based on bevel gear transmission
CN111734679A (en) * 2020-07-02 2020-10-02 中国航发常州兰翔机械有限责任公司 Aeroengine compressor inner casing with air vent and machining method thereof

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3993414A (en) * 1973-10-23 1976-11-23 Office National D'etudes Et De Recherches Aerospatiales (O.N.E.R.A.) Supersonic compressors
CN1840864A (en) * 2005-02-16 2006-10-04 斯奈克玛 Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine
CN102817865A (en) * 2011-06-08 2012-12-12 西门子公司 Axial turbo compressor
CN103299084A (en) * 2011-01-11 2013-09-11 斯奈克玛 Turbofan engine
US9726084B2 (en) * 2013-03-14 2017-08-08 Pratt & Whitney Canada Corp. Compressor bleed self-recirculating system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3993414A (en) * 1973-10-23 1976-11-23 Office National D'etudes Et De Recherches Aerospatiales (O.N.E.R.A.) Supersonic compressors
CN1840864A (en) * 2005-02-16 2006-10-04 斯奈克玛 Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine
CN103299084A (en) * 2011-01-11 2013-09-11 斯奈克玛 Turbofan engine
CN102817865A (en) * 2011-06-08 2012-12-12 西门子公司 Axial turbo compressor
US9726084B2 (en) * 2013-03-14 2017-08-08 Pratt & Whitney Canada Corp. Compressor bleed self-recirculating system

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