CN216199232U - Fan rotor and air cycle machine - Google Patents
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- CN216199232U CN216199232U CN202122674354.2U CN202122674354U CN216199232U CN 216199232 U CN216199232 U CN 216199232U CN 202122674354 U CN202122674354 U CN 202122674354U CN 216199232 U CN216199232 U CN 216199232U
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Abstract
The utility model provides a fan rotor and an air cycle machine, the fan rotor includes: the blade comprises a blade root and a blade tip, wherein the blade root is connected with the peripheral surface of the hub to form a blade root section ShThe blade tip is the end surface of one side opposite to the blade root, and the end surface of the blade tip is a blade tip section S with an arc-shaped surfacec(ii) a The included angle between the tangential direction of the mean camber line at the leading edge of the blade root and the tangential direction of the mean camber line at the trailing edge of the blade root is a blade root bend angle, and the blade tip comprises a blade tip leading edge and a bladeAnd the tip tail edge is positioned on the upstream side of the tip tail edge along the airflow flowing direction, the included angle between the tangential direction of the mean camber line at the tip tail edge and the tangential direction of the mean camber line at the tip tail edge is a tip bend angle, and the tip bend angle is larger than the tip bend angle. According to the utility model, the pressure ratio of the transonic fan blades is reduced, the power consumption of the fan is reduced, and the pressurization of the compressor and the refrigeration capacity of an air conditioner of the airplane are improved.
Description
Technical Field
The utility model relates to the technical field of air cycle machines, in particular to a fan rotor and an air cycle machine.
Background
The air cycle machine is a core component of an aircraft air conditioning refrigeration unit, and a rotor system of a typical three-wheel boosting type air cycle machine is a coaxial mechanism formed by a turbine, a compressor and a fan three-impeller. The operation of the fan and the compressor is powered by the power output by the turbine, wherein the fan mainly functions to provide cold side flow for the secondary heat dissipation of high-temperature bleed air of the engine.
The air flow of the fan comes from a stamping air channel on the surface of the cabin and is directly discharged out of the cabin after heat exchange, so that the flow channel of the whole fan is short, the resistance is small, and the pressure ratio requirement on the fan is also small. However, because the rotor system of the air cycle machine is supported by oil-free gas bearings, the speed of rotation is as high as tens of thousands of revolutions per minute, the relative mach number at the fan inlet is often in the transonic region, and transonic fans often have typical high pressure ratio characteristics.
Fan rotor designs tend to deviate from the peak efficiency point due to the typical characteristics of high pressure ratio, transonic speed. This results in a very low fan rotor efficiency and a high power consumption of the fan, which affects the distribution ratio of the turbine output power between the compressor and the fan, even weakens the supercharging effect of the compressor, and reduces the refrigeration capacity of the air-conditioning cold side of the aircraft. Transonic speed is suitable for high pressure ratio operating mode, so there is the consumption big (because the structure of blade itself causes) when aiming at low pressure ratio operating mode.
Because the fan of the air cycle machine in the prior art is in a transonic working condition and has the characteristic of high pressure ratio, the pressure ratio of a fan rotor is high, the power consumed by the fan is higher, the supercharging effect of an air compressor is poor, the refrigerating capacity of an airplane air conditioner is low and the like, and therefore the utility model researches and designs the fan rotor and the air cycle machine.
SUMMERY OF THE UTILITY MODEL
Therefore, the technical problem to be solved by the utility model is to overcome the defects that the power consumed by the fan of the air cycle machine in the prior art is higher, the supercharging effect of the air compressor is poor, and the air conditioning refrigerating capacity of the airplane is low, so that the fan rotor and the air cycle machine are provided.
In order to solve the above problems, the present invention provides a fan rotor, comprising:
the blade comprises a blade root and a blade tip, wherein the blade root is connected with the peripheral surface of the blade hub to form a blade root section ShThe blade tip is the end surface of one side opposite to the blade root, and the end surface of the blade tip is a blade tip section S with an arc-shaped surfacec；
The blade root includes blade root leading edge and blade root trailing edge, along the air current direction of flow the blade root leading edge is located the upstream side of blade root trailing edge, the camber line tangential direction at blade root leading edge with contained angle between the camber line tangential direction at blade root trailing edge is the blade root bent angle, the blade tip includes blade tip leading edge and blade tip trailing edge, along the air current direction of flow the blade tip leading edge is located the upstream side of blade tip trailing edge, the camber line tangential direction at blade tip leading edge with contained angle between the camber line tangential direction at blade tip trailing edge is the blade tip bent angle, and has the blade root bent angle is greater than the blade tip bent angle.
In some embodiments, the blade comprises a plurality of layers of sections perpendicular to the radial direction along the radial direction of the hub, and a section S along the radial direction of the hub and from the blade roothTo said tip section ScThe angle of bend of each section of the blade gradually decreases.
In some embodiments, the outer peripheral surface of the hub is a cylindrical hub surface having a radius RhThe blade is provided with a plurality of blades, the blade tip sections Sc of the plurality of blades are all positioned on the cylindrical peripheral surface concentric with the peripheral surface of the hub, and the circle is formed byThe column circumference is a cylindrical blade top surface, and the radius of the cylindrical blade top surface is RcAnd has Rh/Rc＝0.47～0.54。
In some embodiments, the blade root section ShAxial chord length C of Sc blade profile of blade tip sectionmDetermining a base length, wherein the axial chord length CmFor the length of the blade from the leading edge to the trailing edge in a blade section perpendicular to the radial direction in the axial direction of the hub, for a blade root section ShLength of blade Cm/Rh0.2764-0.3054, for tip section ScLength of blade thereof
Cm/Rc＝0.0473～0.0584。
In some embodiments, the blade root section ShSection S of vane tipcThe blade profiles are represented by cylindrical coordinate systems r, m and r theta, wherein r represents a radial coordinate, m represents an axial coordinate, and r theta represents a circumferential coordinate; r is the same in the same blade section, and the blade profile in the same blade section is represented by m and r theta;
the blade comprises a blade suction surface and a blade pressure surface, the blade suction surface and the blade pressure surface are positioned on two opposite sides of the axial direction of the hub, a blade mean camber line L is arranged in the same blade section, and the distances between each point on the blade mean camber line L and the blade suction surface and the blade pressure surface are equal along the normal direction of each point;
and the blade angle at the point P on the blade mean camber line L is an included angle between the tangent line at the point P and the direction of the circumferential coordinate r theta, and is represented by beta.
In some embodiments, the blade root section ShThe distribution of blade angles at a first position on the mean camber line of (a) is a linear function: beta ═ B + A (m 1/C)m100%), wherein B is 31.78-35.12, A is 0.1052-0.1162, and m1 is the axial length in the m direction at the first position;
the blade tip section ScThe distribution of blade angles at the second location on the mean camber line of (a) is a linear function: beta ═ b + a (m 2/C)m100%), wherein b is 17.41 to 19.25 and a is 0.0061-0.0067, m2 is the axial length in the m-direction at the second position.
In some embodiments, the thickness t of the midpoint P of the blade mean camber line L is the normal length at that point, and P is the mean position, the blade root section ShThe thickness t of the blade profile is gradually increased along m and then decreased, and the section S of the blade tipcThe thickness t of the blade profile is gradually increased along m, increased and then reduced, and the relative chord length m/CmThe thickness when 100% ═ 0 is the blade leading edge thickness tLERelative chord length m/CmThe thickness at 100% is the thickness t of the trailing edge of the bladeTEAnd m is the length of the set point on the blade in the axial direction from the leading edge of the blade.
In some embodiments, the blade root section ShThe profile thickness distribution of (a) is a cubic function: t ═ G + F (m/C)m*100％)+H*(m/Cm*100％)^2+D*(m/C m100%), wherein G is 1.43-1.58, F is 5.9689E-2-6.5972E-2, H is-9.8016E-4-8.8682E-4, and D is 2.2310E-6-2.4658E-6.
In some embodiments, the tip section ScThe profile thickness distribution of (a) is a cubic function: t ═ g + f (m/C)m*100％)+e*(m/Cm*100％)^2+d*(m/C m100%), wherein g is 0.55-0.61, f is 5.5566E-2-6.1415E-2, h is-9.9641E-4-9.0151E-4, and d is 3.2692E-6-3.6134E-6.
The utility model also provides an air cycle machine comprising a fan rotor as described in any one of the preceding claims.
The fan rotor and the air cycle machine provided by the utility model have the following beneficial effects:
1. according to the utility model, the root of the fan blade adopts a larger bend angle, the root supercharging capacity is increased by utilizing air flow turning, and meanwhile, the tip bend angle adopts a smaller bend angle, so that the pneumatic load of the tip is reduced, the uniform pneumatic load from the root to the tip is ensured, the uniformity of air flow parameters is improved, and the efficiency is increased; meanwhile, a certain bending angle is reduced from the root to the tip in proportion, so that the pneumatic load of the fan is reduced; the scheme effectively reduces the high pressure ratio characteristic of the transonic fan blades, reduces the power consumed by the fan, improves the supercharging effect of the compressor by adjusting the power distribution of the fan, and improves the air conditioning refrigeration capacity of the airplane;
2. the utility model can ensure the load of the blade on the chord direction to be approximately uniformly distributed through the approximately linear blade angle distribution function, and improve the pneumatic efficiency of the blade. The utility model also can ensure the static strength of the axial flow blade to resist the influence of the centrifugal force of the blade on one hand and can generate good aerodynamic performance by combining with the blade bend angle and the mean camber line distribution on the other hand through the blade thickness distributed by the cubic function.
Drawings
FIG. 1 is a three-dimensional block diagram of an air cycle machine of the present invention;
FIG. 2 is a block diagram of a fan rotor in the air cycle machine of the present invention;
FIG. 3 is a blade profile cross-sectional view of the root and tip of a blade in a fan rotor of the present invention;
FIG. 4 is a geometric block diagram of a blade of the present invention;
FIG. 5 is a bar graph comparing the optimized fan pressure ratio of the present invention to the prior art at a typical operating point;
FIG. 6 is a bar graph comparing power consumption of the optimized fan of the present invention with that of the prior art at a typical operating point;
FIG. 7 is a graph comparing the optimized fan speed field of the present invention to the prior art under the design disclosure;
FIG. 8 is a graph of camber line blade angle distribution (blade root versus blade tip) for a fan blade of the present invention;
FIG. 9 is a graph of a blade thickness profile (blade root compared to blade tip) for a fan blade of the present invention.
The reference numerals are represented as:
1. a hub; 2. a blade; 2a, the leading edge of the blade; 2b, the tail edge of the blade; 21. a blade root; 211. a blade root leading edge; 212. a root trailing edge; 22. a blade tip; 221. a tip leading edge; 222. a trailing edge of the blade tip; 23. a blade suction surface; 24. a blade pressure face; 3. a cylindrical hub surface; 4. the top surface of the cylindrical blade; 100. a fan rotor; 200. an air cycle machine.
Detailed Description
Referring to fig. 1 to 9, the present invention provides a fan rotor, which includes:
the blade root 21 includes blade root leading edge 211 and blade root trailing edge 212, along the air current direction blade root leading edge 211 is located the upstream side of blade root trailing edge 212, the camber line tangential direction of blade root leading edge 211 department with contained angle between the camber line tangential direction of blade root trailing edge 212 department is the blade root bent angle, blade tip 22 includes blade tip leading edge 221 and blade tip trailing edge 222, along the air current direction blade tip leading edge 221 is located the upstream side of blade tip trailing edge 222, the camber line tangential direction of blade tip leading edge 221 department with contained angle between the camber line tangential direction of blade tip trailing edge 222 department is the blade tip bent angle, and has the blade root is greater than the blade tip bent angle. Each point on the blade mean camber line L is equidistant from the blade suction surface 23 and the blade pressure surface 24, respectively, in the normal direction thereof.
According to the utility model, the root of the fan blade adopts a larger bend angle, the root supercharging capacity is increased by utilizing air flow turning, and meanwhile, the tip bend angle adopts a smaller bend angle, so that the pneumatic load of the tip is reduced, the uniform pneumatic load from the root to the tip is ensured, the uniformity of air flow parameters is improved, and the efficiency is increased; meanwhile, a certain bending angle is reduced from the root to the tip in proportion, so that the pneumatic load of the fan is reduced; the scheme effectively reduces the high pressure ratio characteristic of the transonic fan blades, reduces the power consumed by the fan, improves the pressurization effect of the compressor by adjusting the power distribution of the fan, and improves the air conditioning refrigeration capacity of the airplane. (the larger bend angle of the root is relative to the tip, and the smaller bend angle of the tip is relative to the root.A shaft fan has a weaker power-applying capability at the root and a stronger power-applying capability at the tip, and the bend angle of the root is larger than that of the tip in order to ensure uniform pneumatic load from the root to the tip.A pressure ratio is reduced by reducing the bend angles of the root and the tip in a certain proportion.)
The utility model provides a heat radiation fan meeting the atypical characteristics of low pressure ratio and transonic speed, and aims to solve the problems that the boosting effect of an air compressor is poor and the refrigerating capacity of an air conditioner of an airplane is low due to the fact that the power consumed by a fan of an air cycle machine is high. The transonic axial flow fan of the air cycle machine provided by the utility model reduces the camber angle of the blade. Blade root section ShMaximum bend angle is about 11 degrees, blade tip section ScThe maximum bend angle of the mean camber line is about 1 degree, and the blade angles of the mean camber line are linearly distributed along with the axial coordinate. The blade angle distribution is beneficial to controlling the fan pressure ratio under the transonic speed condition, reducing the power consumed by the fan, optimizing the power distribution of the whole air cycle machine and improving the refrigeration capacity of the air conditioner of the airplane.
In some embodiments, the blade 2 comprises a plurality of layers of sections perpendicular to the radial direction along the radial direction of the hub 1, and the sections S are taken along the radial direction of the hub 1 and from the blade roothTo said tip section ScThe angle of bend of each section of the blade gradually decreases. The utility model also can further ensure the uniform pneumatic load from the root to the tip, improve the uniformity of the airflow parameters and further reduce the pneumatic load of the fan by gradually reducing the bending angle of each section of the blade in the direction from the blade root section to the blade tip section; the pressure ratio is reduced, the power consumed by the fan is further reduced, the pressurization effect of the air compressor is improved, and the refrigerating capacity of the air conditioner of the airplane is improved. (the tip is mainly supercharged by shock wave and not by bend angle; the root is mainly supercharged by bend angle. the change of bend angle of the existing blade is small, resulting in uneven pneumatic loadThe fan corresponds to the Mach number range of 0.85-1.1 from subsonic speed at the root to supersonic speed at the tip. )
Fig. 5 and 6 compare the pressure ratio and power of the fan rotor to the original rotor for near design conditions of the present invention, where the dashed horizontal line is the design target. It can be seen that the originally designed fan rotor pressure ratio and power are significantly higher due to the typical characteristics of transonic fans. By optimizing the present invention, the power is reduced by about 58% at maximum with the pressure ratio meeting the design objective. As can be seen in FIG. 7, the optimized fan rotor blade channels of the present invention have a lower maximum speed and therefore reduced blade loading, which reduces the fan blade pressure ratio and reduces fan power requirements.
The fan rotor 100, which primarily takes on the cooling, heat dissipating, and exhaust functions of the hot edge bleed air in the air cycle machine 200, is a key component in an aircraft air conditioning air cycle machine 200, as shown in FIG. 1. Due to the high rotational speed of the fan rotor 100, the inlet airflow tends to be transonic. The compressibility of the transonic airflow results in a higher fan rotor pressure ratio, which also results in higher power being consumed by the fan.
The utility model provides a low pressure ratio, transonic air cycle machine cooling fan for an aircraft air conditioning refrigeration system for reducing the pressure ratio of the fan rotor and reducing the power consumed by the fan, as shown in fig. 2. By reducing the power distribution of the fan, the power distribution of the air compressor in the air cycle machine can be improved, so that the supercharging effect is improved, and the refrigeration capacity of an air conditioner of the airplane is improved.
In some embodiments, the outer peripheral surface of the hub 1 is a cylindrical hub surface, and the radius of the cylindrical hub surface 3 is RhThe number of the blades 2 is multiple, and the tip sections S of the multiple blades 2cAre all positioned on the circumferential surface of the cylinder concentric with the circumferential surface of the hub, the circumferential surface of the cylinder is a cylindrical blade top surface 4, and the radius of the cylindrical blade top surface 4 is RcAnd has Rh/RcThe optimum value is 0.47 to 0.54, and 0.51 is preferred.
The fan rotor 100 is formed by uniformly distributing 11 axial flow blades on a cylindrical impeller and directly forming a column shape by five-axis side millingAnd finishing processing in the blank. The blade intersects the cylindrical hub surface 3 to form a blade root section ShThe radius of the cylindrical hub surface 3 is RhThe blade and the top surface 4 of the cylindrical blade are intersected to form a blade tip section ScThe radius of the top surface 4 of the cylindrical blade is RcAs shown in fig. 3. Limit Rh/RcThe optimum value is 0.47 to 0.54, and 0.51 is preferred. Blade root section ShSection S of vane tipcThe fan blade is formed by the linear difference, so the fan blade is a ruled surface. Fan rotor 1 according to blade root section ShSection S of vane tipcThe leaf profile of (A) can be completely determined.
In some embodiments, the blade root section ShSection S of vane tipcAxial chord length C of blade profilemDetermining a base length, wherein the axial chord length CmFor the length of the blade 2 from the leading edge to the trailing edge in a blade section perpendicular to the radial direction along the axial direction of the hub 1, for a blade root section ShLength of blade Cm/Rh0.2764-0.3054, for tip section ScLength of blade Cm/Rc0.0473-0.0584. According to the utility model, through the setting of the parameters, the length range of the blade can be set in an optimal range, so that the larger friction loss caused by the overlong blade is avoided, the separation loss of the shorter blade is also avoided, the friction loss and the separation loss can be simultaneously reduced, the blade efficiency is improved, and the power consumption is reduced.
In some embodiments, the blade root section ShSection S of vane tipcThe blade profiles are represented by cylindrical coordinate systems r, m and r theta, wherein r represents a radial coordinate, m represents an axial coordinate, and r theta represents a circumferential coordinate; r is the same in the same blade section, and the blade profile in the same blade section is represented by m and r theta;
the blade 2 comprises a blade suction surface 23 and a blade pressure surface 24, the blade suction surface 23 and the blade pressure surface 24 are located on two opposite sides of the axial direction of the hub 1, a blade mean camber line L is arranged in the same blade section, and the distances between each point on the blade mean camber line L and the blade suction surface 23 and the blade pressure surface 24 are equal along the normal direction of the point;
and the blade angle at the point P on the blade mean camber line L is an included angle between the tangent line at the point P and the direction of the circumferential coordinate r theta, and is represented by beta. The structure of the utility model can determine the axial chord length C of the blademAnd the distribution of the blade angle beta can completely determine the mean camber line L and the blade root section ShSection S of vane tipcThe mean camber line blade angle β distribution of the profile is shown in fig. 8. It can be seen that the blade angle of the blade root section increases with the increase of the axial length m, i.e. a larger bend angle is formed; and the blade angle of the blade tip section is almost kept unchanged along with the increase of the axial length m to form a smaller bent angle, so that the uniform pneumatic load from the root to the tip is ensured, the uniformity of airflow parameters is improved, the pneumatic load of a fan is reduced, the power consumption of the fan is reduced, and the refrigerating capacity of an air conditioner of an airplane is improved.
In some embodiments, the blade root section ShThe distribution of blade angles at a first position on the mean camber line of (a) is a linear function: beta ═ B + A (m 1/C)m100%), wherein B is 31.78-35.12, A is 0.1052-0.1162, and m1 is the axial length in the m direction at the first position; and/or the presence of a gas in the gas,
the blade tip section ScThe distribution of blade angles at the second location on the mean camber line of (a) is a linear function: beta ═ b + a (m 2/C)m100%), wherein b is 17.41 to 19.25, a is 0.0061 to 0.0067, and m2 is the axial length along the m direction at the second position.
According to the utility model, the approximately linear blade angle distribution function on the blade root section and the blade angle distribution function on the blade tip section can further ensure that the loads of the blades in the chord direction are approximately uniformly distributed, so that the pneumatic efficiency of the blades is further improved, the pneumatic load of the fan is reduced, the power consumption of the fan is reduced, and the air-conditioning refrigeration capacity of the airplane is improved.
In some embodiments, the thickness t of the midpoint P of the blade mean camber line L is the normal length at that point, and P is the mean position, the blade root section ShThe thickness t of the blade profile is gradually increased along m and then decreased, and the section S of the blade tipcThe thickness t of the blade profile is gradually increased along m, and the thickness t is increased firstly and thenReduced relative chord length m/CmThe thickness when 100% ═ 0 is the blade leading edge thickness tLERelative chord length m/CmThe thickness at 100% is the thickness t of the trailing edge of the bladeTEAnd m is the length of the set point on the blade in the axial direction from the leading edge of the blade. As shown in fig. 9, the thickness of the blade root section is increased and then decreased along with the increase of m, and the thickness of the blade tip section is increased and then decreased along with the increase of m, so that on one hand, the static strength of the axial flow blade can be ensured to resist the influence of the centrifugal force of the blade, and on the other hand, the static strength of the axial flow blade can be combined with the blade bend angle and the camber line distribution to generate good aerodynamic performance; the thickness of the blade root section is larger than that of the blade tip section, so that the uniform distribution of loads on the blade can be further improved, the pneumatic load of the fan is further reduced, and the power consumption of the fan is reduced.
In some embodiments, the blade root section ShThe profile thickness distribution of (a) is a cubic function: t ═ G + F (m/C)m*100％)+H*(m/Cm*100％)^2+D*(m/C m100%), wherein G is 1.43-1.58, F is 5.9689E-2-6.5972E-2, H is-9.8016E-4-8.8682E-4, and D is 2.2310E-6-2.4658E-6.
In some embodiments, the tip section ScThe profile thickness distribution of (a) is a cubic function: t ═ g + f (m/C)m*100％)+e*(m/Cm*100％)^2+d*(m/C m100%), wherein g is 0.55-0.61, f is 5.5566E-2-6.1415E-2, h is-9.9641E-4-9.0151E-4, and d is 3.2692E-6-3.6134E-6.
According to the utility model, through the thickness of the blades distributed by the cubic function within the certain range, on one hand, the static strength of the axial flow blades can be ensured to resist the influence of the centrifugal force of the blades, and on the other hand, the axial flow blades can be mutually combined with the distribution of the blade bending angle and the mean camber line to generate good aerodynamic performance.
The transonic axial flow fan of the air cycle machine provided by the utility model reduces the camber angle of the blade. Blade root section ShMaximum bend angle is about 11 degrees, blade tip section ScThe maximum bend angle of the mean camber line is about 1 degree, and the blade angles of the mean camber line are linearly distributed along with the axial coordinate. Such blade angleThe distribution is favorable for controlling the fan pressure ratio under the transonic speed condition, reducing the power consumed by the fan, optimizing the power distribution of the whole air cycle machine and improving the refrigeration capacity of the air conditioner of the airplane.
The utility model also provides an air cycle machine comprising a fan rotor as described in any one of the preceding claims.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the utility model, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, 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 invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A fan rotor, characterized by: the method comprises the following steps:
wheel hub (1) and blade (2), wheel hub (1) is the cylinder structure, blade (2) include blade root (21) and apex (22), blade root (21) with wheel hub 'S (1) outer peripheral face meets, apex (22) be with the terminal surface of one side that blade root (21) carried on the back mutually, blade root (21) with wheel hub' S (1) outer peripheral face meets and forms blade root cross-section ShThe end surface of the blade tip is a blade tip section S with an arc-shaped surfacec；
The blade root (21) includes blade root leading edge (211) and blade root trailing edge (212), along the air current direction of flow blade root leading edge (211) is located the upstream side of blade root trailing edge (212), the camber line tangential direction of blade root leading edge (211) department with contained angle between the camber line tangential direction of blade root trailing edge (212) department is the blade root bent angle, blade tip (22) is including blade tip leading edge (221) and blade tip trailing edge (222), along the air current direction of flow blade tip leading edge (221) is located the upstream side of blade tip trailing edge (222), the camber line tangential direction of blade tip leading edge (221) department with contained angle between the camber line tangential direction of blade tip trailing edge (222) department is the blade tip bent angle, and has the blade root bent angle is greater than the blade tip bent angle.
2. The fan rotor as set forth in claim 1, wherein:
along the radial direction of the hub (1), the blade (2) comprises a plurality of layers of sections perpendicular to the radial direction, and along the radial direction of the hub (1) and from the blade root section ShTo said tip section ScThe angle of bend of each section of the blade gradually decreases.
3. The fan rotor as set forth in claim 1, wherein:
the outer peripheral surface of the hub (1) is a cylindrical hub surface (3), and the radius of the cylindrical hub surface (3) is RhThe number of the blades (2) is multiple, and the tip sections S of the multiple blades (2)cAre all positioned on the circumferential surface of the cylinder concentric with the circumferential surface of the hub, the circumferential surface of the cylinder is a cylindrical blade top surface (4), and the radius of the cylindrical blade top surface (4) is RcAnd has Rh/Rc＝0.47～0.54。
4. The fan rotor as set forth in claim 3, wherein:
blade root section ShSection S of vane tipcAxial chord length C of blade profilemDetermining a base length, wherein the axial chord length CmFor the length of the blade (2) from the leading edge to the trailing edge in a blade section perpendicular to the radial direction of the hub (1) in the axial direction of the hub (1), for a blade root section ShLength of blade Cm/Rh0.2764-0.3054, for tip section ScLength of blade Cm/Rc＝0.0473～0.0584。
5. The fan rotor as set forth in claim 1, wherein:
blade root section ShSection S of vane tipcThe blade profiles are all expressed by a cylindrical coordinate system r, m and r theta, wherein r represents a radial coordinate, and m represents an axial coordinateAnd r θ represents a circumferential coordinate; r is the same in the same blade section, and the blade profile in the same blade section is represented by m and r theta;
the blade (2) comprises a blade suction surface (23) and a blade pressure surface (24), the blade suction surface (23) and the blade pressure surface (24) are located on two opposite sides of the axial direction of the hub (1), a blade mean camber line L is arranged in the same blade section, and the distance between each point on the blade mean camber line L and the blade suction surface (23) and the distance between each point on the blade mean camber line L and the blade pressure surface (24) are equal along the normal direction of the point;
and the blade angle at the point P on the blade mean camber line L is an included angle between the tangent line at the point P and the direction of the circumferential coordinate r theta, and is represented by beta.
6. The fan rotor as set forth in claim 5, wherein:
the blade root section ShThe distribution of blade angles at a first position on the mean camber line of (a) is a linear function: beta ═ B + A (m 1/C)m100%), wherein B is 31.78-35.12, A is 0.1052-0.1162, and m1 is the axial length in the m direction at the first position; and/or the presence of a gas in the gas,
the blade tip section ScThe distribution of blade angles at the second location on the mean camber line of (a) is a linear function: beta ═ b + a (m 2/C)m100%), wherein b is 17.41 to 19.25, a is 0.0061 to 0.0067, and m2 is the axial length along the m direction at the second position.
7. The fan rotor as set forth in claim 5, wherein:
the thickness t of the midpoint P of the camber line L of the blade is the normal length of the midpoint, P is the middle position, and the section S of the blade roothThe thickness t of the blade profile is gradually increased along m and then decreased, and the section S of the blade tipcThe thickness t of the blade profile is gradually increased along m, increased and then reduced, and the relative chord length m/CmThe thickness when 100% ═ 0 is the blade leading edge thickness tLERelative chord length m/CmThe thickness at 100% is the thickness t of the trailing edge of the bladeTEM is the axial distance of the set point on the bladeThe length of the leading edge of the blade.
8. The fan rotor as set forth in claim 7, wherein:
the blade root section ShThe profile thickness distribution of (a) is a cubic function: t ═ G + F (m/C)m*100％)+H*(m/Cm*100％)^2+D*(m/Cm100%), wherein G is 1.43-1.58, F is 5.9689E-2-6.5972E-2, H is-9.8016E-4-8.8682E-4, and D is 2.2310E-6-2.4658E-6.
9. The fan rotor as set forth in claim 7, wherein:
the blade tip section ScThe profile thickness distribution of (a) is a cubic function: t ═ g + f (m/C)m*100％)+e*(m/Cm*100％)^2+d*(m/Cm100%), wherein g is 0.55-0.61, f is 5.5566E-2-6.1415E-2, h is-9.9641E-4-9.0151E-4, and d is 3.2692E-6-3.6134E-6.
10. An air cycle machine, characterized by: comprising a fan rotor according to any of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122674354.2U CN216199232U (en) | 2021-11-03 | 2021-11-03 | Fan rotor and air cycle machine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122674354.2U CN216199232U (en) | 2021-11-03 | 2021-11-03 | Fan rotor and air cycle machine |
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| Publication Number | Publication Date |
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| CN216199232U true CN216199232U (en) | 2022-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202122674354.2U Active CN216199232U (en) | 2021-11-03 | 2021-11-03 | Fan rotor and air cycle machine |
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| CN (1) | CN216199232U (en) |
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