CN114087229A - Compression impeller and air cycle machine - Google Patents
Compression impeller and air cycle machine Download PDFInfo
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- CN114087229A CN114087229A CN202111347525.9A CN202111347525A CN114087229A CN 114087229 A CN114087229 A CN 114087229A CN 202111347525 A CN202111347525 A CN 202111347525A CN 114087229 A CN114087229 A CN 114087229A
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- 238000007906 compression Methods 0.000 title claims abstract description 28
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- 238000005057 refrigeration Methods 0.000 description 3
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised
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Abstract
The application provides a compression impeller and an air cycle machine. The compression impeller comprises a meridian flow passage, the meridian flow passage comprises a wheel disc molded line and a blade top molded line, and the wheel disc molded line is R/R0 ═ a1(Z/R0)6–b1(Z/R0)5+c1(Z/R0)4–d1(Z/R0)3+e1(Z/R0)2-f 1(Z/R0) + g1, tip line R/R0 ═ a2(Z/R0)6–b2(Z/R0)5+c2(Z/R0)4–d2(Z/R0)3+e2(Z/R0)2-f 2(Z/R0) + g2, wherein R0 is the impeller inlet radius. According to the compression impeller, airflow can flow in the blades orderly, and aerodynamic loss is reduced.
Description
Technical Field
The application relates to the technical field of aircraft air conditioners, in particular to a compression impeller and an air cycle machine.
Background
Modern aircraft mostly employ air cycle refrigeration systems. In order to take ground refrigerating capacity and efficiency of an air circulation refrigerating system into consideration, an air circulating machine in the air circulation refrigerating system adopts three wheels, and is characterized in that: the cooling air fan and booster compressor are mounted on a shaft and are driven by an expansion turbine. The turbine drives the compressor, so that the pressure at the inlet of the turbine is improved, the expansion ratio is also improved, larger turbine temperature drop can be obtained, the air supply pressure or air entraining quantity of a refrigerating system is smaller under the same refrigerating requirement, the compensation loss of the performance of the air entraining airplane is small, the oil consumption of an engine is less, and the economical efficiency is good. High performance air cycle machines also place high demands on the performance of the compressor, and the core component in the compressor is an impeller. The air flow flows in the impeller, not only a turning process from the axial direction to the radial direction, but also the turning flow in the angle direction exists between the blades. The radial runner profile parameters and the blade profile parameters of the impeller are critical to the performance of the compressor.
The prior art lacks a compression impeller capable of solving the problem of orderly flow of air flow between blades.
Disclosure of Invention
Therefore, the technical problem to be solved by the application is to provide a compression impeller and an air cycle machine, which can enable airflow to flow in order in blades and reduce aerodynamic loss.
In order to solve the above problems, the present application provides a compression impeller, including a radial flow channel, the radial flow channel includes a disk profile and a tip profile, the disk profile is formed by mapping a disk curved surface to a radial surface, the tip profile is formed by mapping a tip curved surface to a radial surface, a Z axis is provided along a rotation axis of the compression impeller, a cross-section where an inlet and a hub meet is taken as an origin O, an outlet directed from the inlet is taken as a positive, an R axis is determined perpendicular to the Z axis through the origin O, and the disk profile is R/R0 ═ a1(Z/R0)6–b1(Z/R0)5+c1(Z/R0)4–d1(Z/R0)3+e1(Z/R0)2-f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 is 3-7; f1 is 0-1; g1 is 0-2, and the tip profile is R/R0 is a2(Z/R0)6–b2(Z/R0)5+c2(Z/R0)4–d2(Z/R0)3+e2(Z/R0)2-f 2(Z/R0) + g2, wherein a2 is 7-11; b228-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0-3, wherein R0 is the impeller inlet radius.
Preferably, the meridian plane of the meridian plane flow line from the inlet to the outlet of the impeller is mapped as the meridian coordinate direction m of the impeller, the tangential direction around the rotating shaft is taken as the circumferential coordinate theta, the opposite direction of the rotation of the impeller is taken as the positive direction, the meridian flow line intersects with the blade to form a blade intersecting surface, the blade intersecting surface is unfolded along the meridian coordinate direction m and the circumferential coordinate theta to form a blade section, the blade section molded line comprises a center line, the included angle between the tangent line of the center line and the meridian plane is the blade angle beta, and the included angle between the tangent line of the center line at the end point of the outlet end and the meridian plane is the outlet blade angle beta2，β2＝30°～60°。
Preferably, beta2＝45°。
Preferably, the blades comprise long blades and short blades which are alternately arranged along the circumferential direction, and the length of the long blades in the axial direction of the impeller is greater than that of the short blades in the axial direction of the impeller.
Preferably, the blade angle β corresponding to the center line of the disk of the long blade satisfies: (beta/. beta.)2)＝-a3(m％)6+b3(m％)5+c3(m％)4–d3(m％)3+e3(m％)2+ f3 (m%) + g3, in which2＝30°～60°；0≤m≤100；a3＝1～4；b3＝1～4；c3＝2～5；d3＝8～12；e3＝4～8；f3＝0～1；g3＝0～2。
Preferably, the blade angle β corresponding to the tip center line of the long blade satisfies: (beta/. beta.)2)＝-a4(m％)6+b4(m％)5–c4(m％)4+d4(m％)3–e4(m％)2+ f4 (m%) + g4, in which2＝30°～60°；0≤m≤100；a4＝11～15；b4＝32～36；c4＝35～39；d4＝19～23；e4＝5～9；f4＝0～3；g4＝0～2。
Preferably, the blade angle β corresponding to the center line of the disk of the short blade satisfies: (beta/. beta.)2)＝-a5(m％)6+b5(m％)5–c5(m％)4+d5(m％)3–e5(m％)2+ f5 (m%) + g5, in which2＝30°～60°；22≤m≤100；a5＝10～14；b5＝37～41；c5＝47～51；d5＝26～30；e5＝6～10；f5＝1～5；g5＝0～2。
Preferably, the blade angle β corresponding to the tip center line of the short blade satisfies: (beta/. beta.)2)＝-a6(m％)6+b6(m％)5–c6(m％)4+d6(m％)3–e6(m％)2+ f6 (m%) + g6, in which2＝30°～60°；22≤m≤100；a6＝35～39；b6＝121～126；c6＝164～169；d6＝114～119；e6＝42～47；f6＝6～11；g6＝0～1。
Preferably, the long-blade root thickness t is generated by symmetrically superposing the center line of the long-blade wheel disc in the normal direction, and t satisfies t/R0-a 7 (m%)6+b7(m％)5–c7(m％)4+d7(m％)3–e7(m％)2+ f7 (m%) + g7, wherein m is more than or equal to 0 and less than or equal to 100; a7 is 0-4; b7 is 2-7; c7 is 3-8; d7 is 1-6; e7 is 0-4; f7 is 0-1; g7 is 0-1.
Preferably, the long blade top thickness t is generated by symmetrically superposing the long blade top center lines in the normal direction, and t satisfies t/R0-a 8 (m%)6+b8(m％)5–c8(m％)4+d8(m％)3–e8(m％)2+ f8 (m%) + g8, wherein m is more than or equal to 0 and less than or equal to 100; a8 is 0-3; b8 is 1-4; c8 is 2-6; d8 is 1-5; e8 is 0-3; f8 is 0-1; g8 is 0-0.5.
Preferably, the short blade root thickness t is generated by symmetrically superposing the center line of the short blade wheel disc in the normal direction, and t satisfies the condition that t/R0 is a9 (m%)6–b9(m％)5+c9(m％)4–d9(m％)3–e9(m％)2+ f9 (m%) -g 9, wherein 22. ltoreq. m.ltoreq.100; a9 is 0-3; b9 is 3-8; c9 is 5-9; d9 is 0-4; e9 is 0-4; f9 is 0-4; g9 is 0-0.5.
Preferably, the short blade top thickness t is generated by symmetrically superposing the short blade top center lines in the normal direction, and t satisfies t/R0 ═ a10 (m%)6–b10(m％)5+c10(m％)4–d10(m％)3–e10(m％)2+ f10 (m%) -g 10, wherein 22. ltoreq. m.ltoreq.100; a10 is 0-3; b10 is 2-7; c10 is 4-8; d10 is 0-4; e10 is 0-2; f10 is 0-2; g10 ═ 0 &0.5。
Preferably, the long blade wheel disc center line, the long blade tip center line, the long blade front edge arc surface center line and the long blade rear edge surface center line form a long blade middle surface, the long blade middle surface inclination angle is alpha, the rotation direction side is positive, and alpha/beta is2＝a11(m％)6–b11(m％)5+c11(m％)4–d11(m％)3–e11(m％)2+ f11 (m%) -g 11 wherein β2＝30°～60°；a11＝11～16；b11＝28～33；c11＝27～31；d11＝11～16；e11＝0～4；f11＝1～6；g11＝0～0.5，0≤m≤100。
Preferably, the short blade wheel disc central line, the short blade tip central line, the short blade front edge arc surface central line and the short blade rear edge surface central line form a short blade middle surface, the short blade middle surface inclination angle is alpha, the rotation direction side is positive, and alpha/beta2＝a11(m％)6–b11(m％)5+c11(m％)4–d11(m％)3–e11(m％)2+ f11 (m%) -g 11 wherein β2＝30°～60°；a11＝11～16；b11＝28～33；c11＝27～31；d11＝11～16；e11＝0～4；f11＝1～6；g11＝0～0.5，22≤m≤100。
According to another aspect of the present application, there is provided an air cycle machine including a compressor impeller, the compressor impeller being the compressor impeller described above.
The application provides a compression impeller, including the meridian runner, the meridian runner includes rim plate molded lines and pinnacle molded lines, and the rim plate molded lines is formed by the mapping of rim plate curved surface to meridian plane, and the pinnacle molded lines is formed by the mapping of pinnacle curved surface to meridian plane, sets up the Z axle along compression impeller's rotation axis to import and wheel hub handing-over cross-section are original point O, are just by the directional export of import, through original point O, the R axle is confirmed to perpendicular Z axle, the rim plate molded lines are R/R0 ═ a1(Z/R0)6–b1(Z/R0)5+c1(Z/R0)4–d1(Z/R0)3+e1(Z/R0)2-f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 is 3-7; f1 is 0-1; g1 is 0-2, and the tip profile is R/R0 is a2(Z/R0)6–b2(Z/R0)5+c2(Z/R0)4–d2(Z/R0)3+e2(Z/R0)2-f 2(Z/R0) + g2, wherein a2 is 7-11; b2 is 28-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0-3, wherein R0 is the impeller inlet radius. The radial flow channel of the compression impeller can be limited by limiting the wheel disc molded line and the blade top molded line of the impeller, so that the structure of the compression impeller is optimized by limiting the radial flow channel, airflow can orderly flow in the blades of the compression impeller, and the blades of the impeller can well adapt to the airflow flow, thereby effectively reducing aerodynamic loss.
Drawings
FIG. 1 is a schematic structural diagram of an air cycle machine according to an embodiment of the present application;
FIG. 2 is a cross-sectional structural schematic view of an air cycle machine of an embodiment of the present application;
FIG. 3 is a schematic view of a meridian flow passage structure of a compressor impeller according to an embodiment of the present application;
FIG. 4 is a schematic sectional view of a blade of a compressor impeller according to an embodiment of the present disclosure;
fig. 5 is a schematic perspective view of a compression impeller according to an embodiment of the present application;
FIG. 6 is a schematic structural diagram of a compressor impeller according to an embodiment of the present application;
fig. 7 is a flow chart of relative airflow in a compressor impeller according to an embodiment of the present application.
Detailed Description
With combined reference to fig. 1 to 7, according to an embodiment of the present application, the compression impeller 01 includes a radial flow channel 0101, and the radial flow channel 0101 is composed of a wheel disc profile 010101 and a blade tip profile 010102. The wheel disc profile 010101 is formed by mapping a wheel disc curved surface 0102 to a meridian plane, the tip profile 010102 is formed by mapping a tip curved surface 0103 to a meridian plane, a Z axis is provided along a rotation axis 0106 of the compression impeller 01, an R axis is defined by the origin O and a vertical Z axis with a cross section where the inlet 0104 and the hub meet being the origin O and the inlet 0104 pointing to the outlet 0105, and the wheel disc profile is R/R0 ═ a1(Z/R0)6–b1(Z/R0)5+c1(Z/R0)4–d1(Z/R0)3+e1(Z/R0)2-f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 ═ 3-7; f1 is 0-1; g1 is 0-2, and the tip profile is R/R0 is a2(Z/R0)6–b2(Z/R0)5+c2(Z/R0)4–d2(Z/R0)3+e2(Z/R0)2-f 2(Z/R0) + g2, wherein a2 is 7-11; b2 is 28-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0-3, wherein R0 is the impeller inlet radius.
Preferably, a1 ═ 2.135; b1 ═ 9.9607; c1 ═ 17.511; d1 ═ 14.103; e1 ═ 5.4936; f1 ═ 0.6551; g1 ═ 1.0068.
Preferably, a2 ═ 9.1301; b2 ═ 30.664; c2 ═ 38.809; d2 ═ 22.518; e2 ═ 6.3658; f2 ═ 0.5434; g2 ═ 1.7692.
The radial flow channel 0101 of the compression impeller 01 can be defined by defining the wheel disc molded line 010101 and the blade tip molded line 010102 of the impeller, so that the structure of the compression impeller 01 is optimized by defining the radial flow channel 0101, the air flow can orderly flow in the blades of the compression impeller 01, the blades of the impeller can well adapt to the air flow, and the aerodynamic loss is effectively reduced.
Referring to fig. 7, the relative flow chart of the air flow in the impeller is shown, the color depth represents the mach number of the air flow phase flow velocity, and the air flow mach number in the blade flow passage is below 0.5. The green streamlines are the main flow of the air flow in the blade flow channel, the blue streamlines are the result of the existence of a gap between the rotating blades and the stationary shroud, and a small part of the air flow leaks from the gap against the rotation direction of the impeller, so that spiral turbulence is formed. Generally, the airflow flows in order within the blades. The twisted blades of the impeller can be well adapted to the airflow, so that aerodynamic losses can be reduced.
In one embodiment, a meridian plane streamline from an impeller inlet 0104 to an impeller outlet 0105 is mapped as an impeller meridian coordinate direction m, a tangential direction around a rotating shaft 0106 is taken as a circumferential coordinate θ, a direction opposite to the rotation of the impeller is taken as a positive direction, a blade intersecting plane is formed by intersecting the meridian streamline with the blade, and the blade intersecting plane is expanded along the meridian coordinate direction m and the circumferential coordinate θ to form a blade section 0107. The molded line of the blade section 0107 consists of a central line 010701, a thickness 010702, a front edge arc 010703 and a rear edge010704 are determined synthetically. The modeling mode of the blade is that a midline 010701 is determined firstly, and then the thickness 010702 is generated by symmetrically superposing the midline 010701 in the normal direction of the cambered surface. The included angle between the tangential line of the midline 010701 and the meridian plane is the blade angle beta, and the included angle between the tangential line of the midline 010701 at the end point of the outlet end and the meridian plane is the outlet blade angle beta2，β2＝30°～60°。
Preferably, beta2＝45°。
In one embodiment, the blades include long blades 0108 and short blades 0109 alternately arranged in the circumferential direction, and the length of the long blades in the axial direction of the impeller is greater than the length of the short blades in the axial direction of the impeller. The long blades 0108 and the short blades 0109 are alternately and uniformly arranged in the circumferential direction, so that the blade blockage at the impeller inlet can be reduced.
Wherein the long blade 0108 comprises a long blade disk centerline 010201, a long blade tip centerline 010301, a short blade disk centerline 010202, and a short blade tip centerline 010302.
In one embodiment, the blade angle β corresponding to the long blade disk centerline 010201 satisfies: (beta/. beta.)2)＝-a3(m％)6+b3(m％)5+c3(m％)4–d3(m％)3+e3(m％)2+ f3 (m%) + g3, in which230-60 degrees; m is more than or equal to 0 and less than or equal to 100; a3 is 1-4; b3 is 1-4; c3 is 2-5; d3 is 8-12; e3 is 4-8; f3 is 0-1; g3 is 0-2. Preferably, beta2＝45°；a3＝2.5409；b3＝2.6547；c3＝3.9071；d3＝10.322；e3＝6.1875；f3＝0.1477；g3＝0.9329。
In one embodiment, the long-blade tip centerline 010301 corresponds to a blade angle β satisfying: (beta/. beta.)2)＝-a4(m％)6+b4(m％)5–c4(m％)4+d4(m％)3–e4(m％)2+ f4 (m%) + g4, in which230-60 degrees; m is more than or equal to 0 and less than or equal to 100; a4 is 11-15; b4 is 32-36; c4 is 35-39; d4 is 19-23; e4 is 5-9; f4 is 0-3; g4 is 0-2. Preferably, beta2＝45°；a4＝12.776；b4＝34.618；c4＝37.453；d4＝21.524；e4＝7.1407；f4＝1.5852；g4＝0.6511。
In one embodiment, the short leafThe blade angle beta corresponding to the sheet wheel disc midline 010202 satisfies: (beta/. beta.)2)＝-a5(m％)6+b5(m％)5–c5(m％)4+d5(m％)3–e5(m％)2+ f5 (m%) + g5, in which230-60 degrees; m is more than or equal to 22 and less than or equal to 100; a5 is 10-14; b5 is 37-41; c5 is 47-51; d5 is 26-30; e5 is 6-10; f5 is 1-5; g5 is 0-2. Preferably, beta2＝45°；a5＝12.856；b5＝39.813；c5＝49.188；d5＝28.044；e5＝8.4765；f5＝2.9355；g5＝0.7281。
In one embodiment, the blade angle β corresponding to the short blade tip centerline 010302 satisfies: (beta/. beta.)2)＝-a6(m％)6+b6(m％)5–c6(m％)4+d6(m％)3–e6(m％)2+ f6 (m%) + g6, in which230-60 degrees; m is more than or equal to 22 and less than or equal to 100; a6 is 35-39; b6 is 121-126; c6 is 164-169; d6 is 114-119; e6 is 42-47; f6 is 6-11; g6 is 0-1. Preferably, beta2＝45°；a6＝37.338；b6＝123.81；c6＝166.74；d6＝116.67；e6＝44.36；f6＝8.8703；g6＝0.0964。
In one embodiment, the long-blade root thickness t is generated by symmetrically superposing the long-blade wheel disc midline 010201 in the normal direction, and t satisfies t/R0 ═ a7 (m%)6+b7(m％)5–c7(m％)4+d7(m％)3–e7(m％)2+ f7 (m%) + g7, wherein m is more than or equal to 0 and less than or equal to 100; a7 is 0-4; b7 is 2-7; c7 is 3-8; d7 is 1-6; e7 is 0-4; f7 is 0-1; g7 is 0-1. Preferably, a7 is 1.792; b7 ═ 4.7269; c7 ═ 5.6062; d7 ═ 3.8293; e7 ═ 1.6052; f7 ═ 0.3925; g7 ═ 0.0857.
In one embodiment, the long blade top thickness t is generated by symmetrically superposing the long blade top midline 010301 in the normal direction, and t satisfies t/R0 ═ a8 (m%)6+b8(m％)5–c8(m％)4+d8(m％)3–e8(m％)2+ f8 (m%) + g8, wherein m is more than or equal to 0 and less than or equal to 100; a8 is 0-3; b8 is 1-4; c8 is 2-6; d8 is 1-5; e8 is 0-3; f8 is 0-1; g8 is 0-0.5. Preferably, a8 ═ 1.1072; b8 ═ 2.9701; c8 ═ 3.5876; d8 ═ 2.4932; e8 ═ 1.0589; f8 ═ 0.2608; g8 ═0.0571。
In one embodiment, the short blade root thickness t is generated by symmetrically superposing the short blade wheel disc midline 010202 in the normal direction, and t satisfies t/R0 ═ a9 (m%)6–b9(m％)5+c9(m％)4–d9(m％)3–e9(m％)2+ f9 (m%) -g 9, wherein 22. ltoreq. m.ltoreq.100; a9 is 0-3; b9 is 3-8; c9 is 5-9; d9 is 0-4; e9 is 0-4; f9 is 0-4; g9 is 0-0.5. Preferably, a9 ═ 1.4419; b9 ═ 5.9499; c9 ═ 7.1843; d9 ═ 2.1425; e9 ═ 1.6498; f9 ═ 1.2462; g9 ═ 0.0991.
In one embodiment, the short blade top thickness t is generated by symmetrically superposing the short blade top midline 010302 in the normal direction, and t satisfies t/R0 ═ a10 (m%)6–b10(m％)5+c10(m％)4–d10(m％)3–e10(m％)2+ f10 (m%) -g 10, wherein 22. ltoreq. m.ltoreq.100; a10 is 0-3; b10 is 2-7; c10 is 4-8; d10 is 0-4; e10 is 0-2; f10 is 0-2; g10 is 0-0.5. Preferably, a10 ═ 1.2623; b10 ═ 4.9586; c10 ═ 6.1411; d10 ═ 2.3459; e10 ═ 0.8054; f10 ═ 0.8037; g10 ═ 0.0696.
In one embodiment, the long blade 0108 further comprises a long blade leading edge arc surface midline 010401 and a long blade trailing edge surface midline 010501. The long blade wheel disc central line 010201, the long blade tip central line 010301, the long blade leading edge arc surface central line 010401 and the long blade trailing edge surface central line 010501 form a long blade middle plane, the long blade middle plane inclination angle is alpha, the rotation direction side is positive, and alpha/beta is2＝a11(m％)6–b11(m％)5+c11(m％)4–d11(m％)3–e11(m％)2+ f11 (m%) -g 11 wherein β230-60 degrees; a11 is 11-16; b11 is 28-33; c11 is 27-31; d11 is 11-16; e11 is 0-4; f11 is 1-6; g11 is 0-0.5, m is more than or equal to 0 and less than or equal to 100. Preferably, beta2＝45°；a11＝13.601；b11＝30.815；c11＝29.159；d11＝13.311；e11＝2.2932；f11＝3.6712；g11＝0.0059。
In one embodiment, the short blade 0109 further comprises a short blade leading edge camber line 010402 and a short blade trailing edge face camber line 010502. Short bladeThe middle plane of the short blade is composed of a wheel disc middle line 010202, a short blade top middle line 010302, a short blade front edge arc surface middle line 010402 and a short blade rear edge surface middle line 010502, the inclination angle of the middle plane of the short blade is alpha, the rotation direction side is positive, and alpha/beta is2＝a11(m％)6–b11(m％)5+c11(m％)4–d11(m％)3–e11(m％)2+ f11 (m%) -g 11 wherein β230-60 degrees; a11 is 11-16; b11 is 28-33; c11 is 27-31; d11 is 11-16; e11 is 0-4; f11 is 1-6; g11 is 0-0.5, m is more than or equal to 22 and less than or equal to 100. Preferably, beta2＝45°；a11＝13.601；b11＝30.815；c11＝29.159；d11＝13.311；e11＝2.2932；f11＝3.6712；g11＝0.0059。
The blade profile can be determined according to the profile parameters in 4 aspects such as the blade center line, the blade angle, the blade thickness and the blade inclination angle, so that the twisted blade can be determined, the twisted blade can better adapt to airflow flow, the aerodynamic loss is reduced, and the aerodynamic efficiency of the impeller is improved.
According to an embodiment of the present application, there is provided a compressor including a compression impeller 01, a diffuser 02, and a housing 03.
According to an embodiment of the present application, there is provided an air cycle machine including a compression impeller 01, the compression impeller 01 being the above-described compression impeller.
The air cycle machine for compressed air refrigerating system has the advantages that after the air flows into the T01 and works through the expansion machine, the pressure and the temperature are reduced, and the air flows out of the T02, so that the aim of regulating the pressure and the temperature of the air is fulfilled. The work of expansion drives the compressor and fan. One air flow is sucked from the C01, is compressed by the compression impeller and then is discharged from the C02, and the compressed air is supplied to the expander, so that the inlet pressure of the expander is improved, the expansion ratio is increased, the temperature drop of the expander is enlarged, and the aims of small air-entraining amount, small compensation loss, low oil consumption of an engine and good economical efficiency of a system under the same refrigeration requirement are fulfilled. At the same time, another air flow is sucked in by the fan F01 and discharged at F02, thereby achieving the purpose of providing cooling air flow for the compressed air refrigeration system.
It is readily understood by a person skilled in the art that the advantageous ways described above can be freely combined, superimposed without conflict.
The present invention is not intended to be limited to the particular embodiments shown and described, but is to be accorded the widest scope consistent with the principles and novel features herein disclosed. The foregoing is only a preferred embodiment of the present application, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present application, and these modifications and variations should also be considered as the protection scope of the present application.
Claims (15)
1. The compression impeller is characterized by comprising a meridian flow passage, wherein the meridian flow passage comprises a wheel disc molded line and a blade top molded line, the wheel disc molded line is formed by mapping a wheel disc curved surface to a meridian plane, the blade top molded line is formed by mapping a blade top curved surface to a meridian plane, a Z axis is arranged along a rotating shaft of the compression impeller, a cross section where an inlet is connected with a hub is taken as an original point O, the original point O is positive, an R axis is determined by the original point O and the vertical Z axis, and the wheel disc molded line is R/R0 ═ a1(Z/R0)6–b1(Z/R0)5+c1(Z/R0)4–d1(Z/R0)3+e1(Z/R0)2-f 1(Z/R0) + g1, wherein a1 is 1-3; b1 is 8-11; c1 is 15-19; d1 is 12-16; e1 is 3-7; f1 is 0-1; g1 is 0-2, and the tip profile is R/R0 is a2(Z/R0)6–b2(Z/R0)5+c2(Z/R0)4–d2(Z/R0)3+e2(Z/R0)2-f 2(Z/R0) + g2, wherein a2 is 7-11; b2 is 28-32; c2 is 36-41; d2 is 20-24; e2 is 4-8; f2 is 0-1; g2 is 0-3, wherein R0 is the impeller inlet radius.
2. The compressor impeller according to claim 1, wherein a meridian plane streamline from an inlet to an outlet of the impeller is mapped in a meridian plane as an impeller meridian coordinate direction m, a tangential direction around a rotation axis is a circumferential coordinate θ, a reverse direction of rotation of the impeller is a positive direction, a blade intersecting plane is formed by intersecting the meridian streamline with the blade, and the blade intersecting plane is located in the meridian coordinate direction m and the circumferential directionThe standard theta is developed to form the blade section, the profile line of the blade section comprises a midline, the included angle between the tangent line of the midline and the meridian plane is the blade angle beta, and the included angle between the tangent line of the midline at the end point of the outlet end and the meridian plane is the outlet blade angle beta2，β2＝30°～60°。
3. The compressor impeller of claim 2, wherein β is β2＝45°。
4. The compressor impeller as claimed in claim 2, wherein the blades include long blades and short blades alternately arranged in a circumferential direction, and a length of the long blades in an axial direction of the impeller is greater than a length of the short blades in the axial direction of the impeller.
5. The compressor impeller according to claim 4, wherein the blade angle β corresponding to the disk center line of the long blade satisfies: (beta/. beta.)2)＝-a3(m％)6+b3(m％)5+c3(m％)4–d3(m％)3+e3(m％)2+ f3 (m%) + g3, in which2＝30°～60°；0≤m≤100；a3＝1～4；b3＝1～4；c3＝2～5；d3＝8～12；e3＝4～8；f3＝0～1；g3＝0～2。
6. The compressor impeller according to claim 4, wherein the blade angle β corresponding to the tip center line of the long blade satisfies: (beta/. beta.)2)＝-a4(m％)6+b4(m％)5–c4(m％)4+d4(m％)3–e4(m％)2+ f4 (m%) + g4, in which2＝30°～60°；0≤m≤100；a4＝11～15；b4＝32～36；c4＝35～39；d4＝19～23；e4＝5～9；f4＝0～3；g4＝0～2。
7. The compressor impeller according to claim 4, wherein the blade angle β corresponding to the disk center line of the short blade satisfies: (beta/. beta.)2)＝-a5(m％)6+b5(m％)5–c5(m％)4+d5(m％)3–e5(m％)2+ f5 (m%) + g5, in which2＝30°～60°；22≤m≤100；a5＝10～14；b5＝37～41；c5＝47～51；d5＝26～30；e5＝6～10；f5＝1～5；g5＝0～2。
8. The compressor impeller according to claim 4, wherein the blade angle β corresponding to the tip center line of the short blade satisfies: (beta/. beta.)2)＝-a6(m％)6+b6(m％)5–c6(m％)4+d6(m％)3–e6(m％)2+ f6 (m%) + g6, in which2＝30°～60°；22≤m≤100；a6＝35～39；b6＝121～126；c6＝164～169；d6＝114～119；e6＝42～47；f6＝6～11；g6＝0～1。
9. The compressor impeller as claimed in claim 4, wherein the long blade root thickness t, t satisfying t/R0-a 7 (m%)6+b7(m％)5–c7(m％)4+d7(m％)3–e7(m％)2+ f7 (m%) + g7, wherein m is more than or equal to 0 and less than or equal to 100; a7 is 0-4; b7 is 2-7; c7 is 3-8; d7 is 1-6; e7 is 0-4; f7 is 0-1; g7 is 0-1.
10. The compressor impeller as claimed in claim 4, wherein the long blade tip thickness t, t satisfying t/R0-a 8 (m%)6+b8(m％)5–c8(m％)4+d8(m％)3–e8(m％)2+ f8 (m%) + g8, wherein m is more than or equal to 0 and less than or equal to 100; a8 is 0-3; b8 is 1-4; c8 is 2-6; d8 is 1-5; e8 is 0-3; f8 is 0-1; g8 is 0-0.5.
11. The compressor impeller as claimed in claim 4, wherein the short blade root thickness t, t satisfying t/R0 a9 (m%)6–b9(m％)5+c9(m％)4–d9(m％)3–e9(m％)2+ f9 (m%) -g 9, wherein 22. ltoreq. m.ltoreq.100; a9 is 0-3; b9 is 3-8; c9 is 5-9; d9 is 0-4; e9 is 0-4; f9 is 0-4; g9 is 0-0.5.
12. The compressor impeller as claimed in claim 4, wherein the short blade tip thickness t, t satisfying t/R0 ═ a10 (m%)6–b10(m％)5+c10(m％)4–d10(m％)3–e10(m％)2+ f10 (m%) -g 10, wherein 22. ltoreq. m.ltoreq.100; a10 is 0-3; b10 is 2-7; c10 is 4-8; d10 is 0-4; e10 is 0-2; f10 is 0-2; g10 is 0-0.5.
13. The compressor impeller as claimed in claim 4, wherein the long blade disk center line, the long blade tip center line, the long blade leading edge arc surface center line and the long blade trailing edge surface center line constitute a long blade middle plane, the long blade middle plane has an inclination angle of α, the rotation direction side is positive, and α/β2＝a11(m％)6–b11(m％)5+c11(m％)4–d11(m％)3–e11(m％)2+ f11 (m%) -g 11 wherein β2＝30°～60°；a11＝11～16；b11＝28～33；c11＝27～31；d11＝11～16；e11＝0～4；f11＝1～6；g11＝0～0.5，0≤m≤100。
14. The compressor impeller as claimed in claim 4, wherein the short blade disk center line, the short blade tip center line, the short blade leading edge arc surface center line and the short blade trailing edge surface center line constitute a short blade middle plane, the short blade middle plane has an inclination angle of α, the rotation direction side is positive, and α/β2＝a11(m％)6–b11(m％)5+c11(m％)4–d11(m％)3–e11(m％)2+ f11 (m%) -g 11 wherein β2＝30°～60°；a11＝11～16；b11＝28～33；c11＝27～31；d11＝11～16；e11＝0～4；f11＝1～6；g11＝0～0.5，22≤m≤100。
15. An air cycle machine comprising a compressor wheel, wherein the compressor wheel is as claimed in any one of claims 1 to 14.
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