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Fig. 15. Rotor Cooling Performance Index (RCPI) curves for this study.

Figure 15 Rotor Cooling Performance Index (RCPI) curves for this study.

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Fig. 1. YASA derivation topology begins with (a) NS Torus-S topology, (b) exclude the stator yoke and (c) final design changes [6]. Conventional AFPM machines are comprised of yokes on the rotor and stator to support its field system and protect the armature of the motor. The YASA machine topology is able to improve the performance of AFPM by removing the stator yoke and implementing other design changes, as illustrated in Fig. 1. The derivation of the YASA topology began with the NS Torus-S topology (Fig. 1-a), then evolved by excluding the stator yoke as it did not seriously impact the electromagnetic behaviour of the system (Fig. 1-b). In Fig. l-c, the YASA topology was formed by the pitch of the teeth is enlarged and square windings are used. This new topology improved torque density by 20% and recorded a peak efficiency of 95% with 50% less iron in the stator compared to a conventional AFPM machine [6]. Nevertheless, the full potential of the machine is currently limited by its operating temperature. Therefore, optimisation of the thermal design is required to improve the motor’s reliability and to further increase its performance.
Fig. 1. YASA derivation topology begins with (a) NS Torus-S topology, (b) exclude the stator yoke and (c) final design changes [6]. Conventional AFPM machines are comprised of yokes on the rotor and stator to support its field system and protect the armature of the motor. The YASA machine topology is able to improve the performance of AFPM by removing the stator yoke and implementing other design changes, as illustrated in Fig. 1. The derivation of the YASA topology began with the NS Torus-S topology (Fig. 1-a), then evolved by excluding the stator yoke as it did not seriously impact the electromagnetic behaviour of the system (Fig. 1-b). In Fig. l-c, the YASA topology was formed by the pitch of the teeth is enlarged and square windings are used. This new topology improved torque density by 20% and recorded a peak efficiency of 95% with 50% less iron in the stator compared to a conventional AFPM machine [6]. Nevertheless, the full potential of the machine is currently limited by its operating temperature. Therefore, optimisation of the thermal design is required to improve the motor’s reliability and to further increase its performance.
Fig. 2. The position of fan blade attached to the rotor allows introduction of cool air in the system. The initial concept of rotor cooling for the AFPM machine was first proposed by Vansompel [4]. The implementation of rotor cooling on the current YASA machine topology was accomplished by introducing an opening at the centre of the rotor and a single out et on the radial cover. This is adopted from the concept of a centrifugal fan, where the air will flow from the centre inlet t blade and exits throug hrough the system that drives by a fan h the side outlet. Fig. 2 shows that the fan blade component is attached directly to the machine rotor of non drive end side. While the machine rotates, the rotor with a fan blade will create pressure gradient inside the system, thus air flow is developed. This air flow is expected to absorb the heat from the rotor (by convection) and disperse it to the outlet. As this happens, heat from the magnet will flow to the rotor assembly through conductive heat transfer.
Fig. 2. The position of fan blade attached to the rotor allows introduction of cool air in the system. The initial concept of rotor cooling for the AFPM machine was first proposed by Vansompel [4]. The implementation of rotor cooling on the current YASA machine topology was accomplished by introducing an opening at the centre of the rotor and a single out et on the radial cover. This is adopted from the concept of a centrifugal fan, where the air will flow from the centre inlet t blade and exits throug hrough the system that drives by a fan h the side outlet. Fig. 2 shows that the fan blade component is attached directly to the machine rotor of non drive end side. While the machine rotates, the rotor with a fan blade will create pressure gradient inside the system, thus air flow is developed. This air flow is expected to absorb the heat from the rotor (by convection) and disperse it to the outlet. As this happens, heat from the magnet will flow to the rotor assembly through conductive heat transfer.
Fig. 3. The fan blade design selection with (a) backward-inclined aerofoil blade [20], (b) radial aerofoil blade [20] and (c) tear drop pillar blade [21]. Fig. 3-b, a radial aerofoil blade — from a typical fan engineering application [22] and Fig. 3-c, a tear drop pillar blade — from an automotive disc brake [23]. The backward- inclined aerofoil blade and radial aerofoil blade were selected as it is known that they provide good air flow as a pump or fan. Additionally, it is interesting to see how a tear drop pillar blade performs as this is the cooling technique used for heat removal in brake disc. For rotor cooling applications, the operation of a backward- inclined aerofoil blade is limited to an unidirectional machine, while the radial aerofoil blade and the tear drop pillar blade can be used in a machine with a bi-directional application. In this study, unidirectional operational was considered because current machine design is specific for automotive traction application with medium rotational speed in the intended directionand slow speed in the reverse.
Fig. 3. The fan blade design selection with (a) backward-inclined aerofoil blade [20], (b) radial aerofoil blade [20] and (c) tear drop pillar blade [21]. Fig. 3-b, a radial aerofoil blade — from a typical fan engineering application [22] and Fig. 3-c, a tear drop pillar blade — from an automotive disc brake [23]. The backward- inclined aerofoil blade and radial aerofoil blade were selected as it is known that they provide good air flow as a pump or fan. Additionally, it is interesting to see how a tear drop pillar blade performs as this is the cooling technique used for heat removal in brake disc. For rotor cooling applications, the operation of a backward- inclined aerofoil blade is limited to an unidirectional machine, while the radial aerofoil blade and the tear drop pillar blade can be used in a machine with a bi-directional application. In this study, unidirectional operational was considered because current machine design is specific for automotive traction application with medium rotational speed in the intended directionand slow speed in the reverse.
Fig. 4. The experimental rig with mass flow sensor at the inlet.
Fig. 4. The experimental rig with mass flow sensor at the inlet.
Fig. 5. CFD model including fluid domain (blue), rotational fluid domain (red), rotor & ducting (grey) A complete domain of the non drive end was modelled due to the non-symmetrical design of the inlet and outlet positions. The final CFD model included the stator wall, the rotor assembly, the outlet extrusion and the inlet duct with dual mass flow sensors (Fig. 5). The contact interface between the Solid-Fluid regions and the Fluid-Fluid regions was created by imprinting the mating face to allow conformal mesh between the regions. Using the automated mesh generation in STAR-CCM+, an unstructured volume mesh (polyhedral cells) was used to discretise the solid and fluid domain. The prism layer was set based on the calculated dimensionless wall distance [24] of (1)-(2) with a local Reynolds number of 3.73e5 (3).
Fig. 5. CFD model including fluid domain (blue), rotational fluid domain (red), rotor & ducting (grey) A complete domain of the non drive end was modelled due to the non-symmetrical design of the inlet and outlet positions. The final CFD model included the stator wall, the rotor assembly, the outlet extrusion and the inlet duct with dual mass flow sensors (Fig. 5). The contact interface between the Solid-Fluid regions and the Fluid-Fluid regions was created by imprinting the mating face to allow conformal mesh between the regions. Using the automated mesh generation in STAR-CCM+, an unstructured volume mesh (polyhedral cells) was used to discretise the solid and fluid domain. The prism layer was set based on the calculated dimensionless wall distance [24] of (1)-(2) with a local Reynolds number of 3.73e5 (3).
LIST OF COEFFICIENT FOR ALL SELECTED TURBULENCE MODELS
LIST OF COEFFICIENT FOR ALL SELECTED TURBULENCE MODELS
BOUNDARY CONDITIONS USED FOR ALL SIMULATIONS TABLE I
BOUNDARY CONDITIONS USED FOR ALL SIMULATIONS TABLE I
three fan blade designs. Fig. 6. Computational mesh of fluid domains for backward-inclined aerofoil blade at front cross section (top) and side cross section (bottom).
three fan blade designs. Fig. 6. Computational mesh of fluid domains for backward-inclined aerofoil blade at front cross section (top) and side cross section (bottom).
Fig. 7. Comparison CFD and experimental result of (circle) flow without mesh-filter on the outlet, (diamond) with mesh-filter on the outlet.
Fig. 7. Comparison CFD and experimental result of (circle) flow without mesh-filter on the outlet, (diamond) with mesh-filter on the outlet.
Fig. 8. a) Mass flow rate and b) pressure development of each fan design.
Fig. 8. a) Mass flow rate and b) pressure development of each fan design.
Fig. 10. Fan curve and power curve of (a) backward-inclined aerofoil blade, (b) radial aerofoil blade and (c) tear drop pillar blade. The contour plot of air temperature, Fig.1 , was recorded at Z +3mm above the front heated rotor surface for 3500rpm with the range between 26.85°C to 80°C. In Fig. 11-a, a hot air patch at 80°C can be observed on the backward -inclined lower aerofoil surface near to its trailing edge. This hot air then flows to the radial space of the machine while slightly reducing its temperature before going to the outlet. T temperature at the outlet of the backward-in he average air clined blade in
Fig. 10. Fan curve and power curve of (a) backward-inclined aerofoil blade, (b) radial aerofoil blade and (c) tear drop pillar blade. The contour plot of air temperature, Fig.1 , was recorded at Z +3mm above the front heated rotor surface for 3500rpm with the range between 26.85°C to 80°C. In Fig. 11-a, a hot air patch at 80°C can be observed on the backward -inclined lower aerofoil surface near to its trailing edge. This hot air then flows to the radial space of the machine while slightly reducing its temperature before going to the outlet. T temperature at the outlet of the backward-in he average air clined blade in
Fig. 11. Air temperature contour at z +3mm from the front heated rotor surface of (a) backward-inclined airfoil blade, (b) radial airfoil blade and (c) tear drof pillar blade.
Fig. 11. Air temperature contour at z +3mm from the front heated rotor surface of (a) backward-inclined airfoil blade, (b) radial airfoil blade and (c) tear drof pillar blade.
Fig. 12. Average air outlet temperature of each fan design. On the other hand, no hot spot is present on the air temperature contour plot of the pillar type (Fig. 11-c). Nevertheless it shows a fair temperature gradient that collects at the radial space of the machine compared to the radial blade design. The average air outlet temperature of pillar type (Fig. 12) is marked between the two others fan blade designs with increasing value as the speed increases. Furthermore, the capability of each fan design in dissipating the rotor temperature can be analysed by plotting the average air temperature within the rotating region, as presented in Fig. 13. The hot air patch of the backward- inclined and the radial blade (Fig. 11) proves that both designs have high average temperatures within the system. However, for the radial blade, this hot air remains within the system as discussed before due to the flow circulation at the downwind region of the blade which made the average air outlet temperature (Fig. 12) of this design the lowest.
Fig. 12. Average air outlet temperature of each fan design. On the other hand, no hot spot is present on the air temperature contour plot of the pillar type (Fig. 11-c). Nevertheless it shows a fair temperature gradient that collects at the radial space of the machine compared to the radial blade design. The average air outlet temperature of pillar type (Fig. 12) is marked between the two others fan blade designs with increasing value as the speed increases. Furthermore, the capability of each fan design in dissipating the rotor temperature can be analysed by plotting the average air temperature within the rotating region, as presented in Fig. 13. The hot air patch of the backward- inclined and the radial blade (Fig. 11) proves that both designs have high average temperatures within the system. However, for the radial blade, this hot air remains within the system as discussed before due to the flow circulation at the downwind region of the blade which made the average air outlet temperature (Fig. 12) of this design the lowest.
Fig. 14 is calculated by (4) where the heat flux of the rotor and magnet walls are divided by the temperature difference between the rotor and the system average temperature of Fig. 13.
Fig. 14 is calculated by (4) where the heat flux of the rotor and magnet walls are divided by the temperature difference between the rotor and the system average temperature of Fig. 13.
BOUNDARY CONDITIONS USED FOR ALL SIMULATIONS
BOUNDARY CONDITIONS USED FOR ALL SIMULATIONS
Fig. 14. Average heat transfer coefficient of each fan design.
Fig. 14. Average heat transfer coefficient of each fan design.
Related topics:
EngineeringThermal EngineeringRotor Cooling
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