CN117895715A - Phase-change cooling structure of aviation motor and phase-change medium flow determining method thereof - Google Patents
Phase-change cooling structure of aviation motor and phase-change medium flow determining method thereof Download PDFInfo
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- 238000001816 cooling Methods 0.000 title claims abstract description 159
- 238000000034 method Methods 0.000 title claims abstract description 20
- 239000012071 phase Substances 0.000 claims description 118
- 239000011555 saturated liquid Substances 0.000 claims description 17
- 229920006395 saturated elastomer Polymers 0.000 claims description 7
- 239000012808 vapor phase Substances 0.000 claims description 7
- 238000010438 heat treatment Methods 0.000 claims description 5
- 238000009835 boiling Methods 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 claims description 3
- 230000004907 flux Effects 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 238000009834 vaporization Methods 0.000 claims description 3
- 230000008016 vaporization Effects 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 230000017525 heat dissipation Effects 0.000 description 12
- 238000010586 diagram Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000018199 S phase Effects 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
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Abstract
The application belongs to the technical field of aviation motor cooling design, and in particular relates to an aviation motor phase-change cooling structure and a phase-change medium flow determining method thereof.
Description
Technical Field
The application belongs to the technical field of aviation motor cooling design, and particularly relates to an aviation motor phase-change cooling structure and a phase-change medium flow determining method thereof.
Background
With the development of aviation motors to high power density, high overload capacity and high-speed miniaturization, the heating power of the aviation motors is continuously increased to generate larger temperature rise, so that the operation efficiency, reliability and service life are reduced.
At present, an air cooling heat dissipation system and a liquid cooling heat dissipation system are adopted for cooling the aviation motor, so that heat accumulation and larger temperature rise are avoided when the aviation motor works.
The air-cooled heat dissipation system does not need complex auxiliary facilities to promote fluid flow, is reliable in operation, is suitable for low-power-density aviation motors with low heat dissipation requirements, and is low in design and use cost.
The liquid cooling heat dissipation system is higher than the air cooling heat dissipation system in heat dissipation efficiency, but needs complicated auxiliary facilities, and is relatively high in design and use cost, and is suitable for high-power density aviation motors with high heat dissipation requirements.
In addition, the current air cooling heat dissipation system and the liquid cooling heat dissipation system flow through single-phase media, so that the aviation motor is cooled, the heat transfer coefficient is smaller, the heat dissipation potential for development is limited, and the heat dissipation requirement of the high-power density aviation motor is difficult to design.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
Disclosure of Invention
The invention aims to provide an aero-motor phase-change cooling structure and a phase-change medium flow determining method thereof, which overcome or alleviate the technical defects of at least one aspect in the prior art.
The technical scheme of the application is as follows:
in one aspect, an aero-motor phase change cooling structure is provided, comprising:
the bottom cooling pipelines are internal threaded pipes and are arranged in each stator slot of the aviation motor and close to the bottoms of the stator slots;
the cooling pipelines at the openings are internal thread pipes and are arranged in each stator slot of the aviation motor and close to the opening parts of the stator slots;
the bottom cooling inlet shunt pipes are annular and connected to the inlet ends of the bottom cooling pipelines, the bottom cooling inlet pipes are arranged on the bottom cooling inlet shunt pipes, and phase change media are introduced into the bottom cooling inlet shunt pipes;
the bottom cooling outlet collecting pipe is annular and is connected to the outlet end of each bottom cooling pipeline, and a bottom cooling outlet pipe is arranged on the bottom cooling outlet collecting pipe;
the opening cooling inlet shunt pipes are annular and connected to the inlet ends of the cooling pipelines at the openings, are positioned on one side of each stator slot of the aviation motor and are identical to the bottom cooling outlet collecting pipes, are provided with opening cooling inlet pipes, and are introduced with phase change media;
the opening cooling outlet collecting pipe is annular and is connected to the outlet end of each opening cooling pipeline, and is positioned on the other side of each stator slot of the aviation motor along with the bottom cooling inlet shunt pipe, and is provided with an opening cooling outlet pipe.
According to at least one embodiment of the present application, in the phase-change cooling structure of an aero-motor, the phase-change medium is water.
According to at least one embodiment of the present application, in the above-mentioned aero-motor phase change cooling structure, further includes:
the outlet of the circulating pump is connected with a bottom cooling inlet pipe and a cooling inlet pipe at the opening;
and the hot side outlet of the condenser is connected with the inlet of the circulating pump, and the hot side inlet is connected with the bottom cooling outlet pipe and the opening cooling outlet pipe for cooling the phase change medium to a saturated liquid phase.
According to at least one embodiment of the present application, in the phase-change cooling structure of an aero-motor, the condenser adopts an air cooler.
In another aspect, a method for determining a phase change medium flow rate of a phase change cooling structure of an aero-motor is provided, which is characterized by comprising the following steps:
step one, calculating the saturation temperature T of the phase change medium under the pressure P of the phase change medium sat Latent heat of vaporization h fg ；
Step two, calculating the total flow m of the phase change medium required by phase change cooling of the aero-motor;
step three, calculating the flow velocity G of the phase medium in each internal thread pipe;
step four, calculating boiling heat exchange coefficients h of phase media in each internal thread pipe;
step five, calculating the maximum temperature difference delta T between the inner wall surface of the internally threaded pipe and the phase change medium;
step six, calculating the heat exchange quantity Q which can be achieved by the phase change medium;
and step seven, verifying the total flow m of the phase change medium required by phase change cooling of the aero-motor, if the deviation between Q and the heating power W of the aero-motor is larger than a set deviation threshold value, adjusting m, and repeating the steps three to seven until the deviation between Q and W is smaller than the set deviation threshold value.
According to at least one embodiment of the present application, in the method for determining a phase-change medium flow of an aero-motor phase-change cooling structure described above, in step seven, when the deviation between Q and W is greater than a set deviation threshold, if Q > W, then m is reduced; if Q < W, increasing m;
the deviation threshold was set to 5%.
According to at least one embodiment of the present application, in the method for determining the flow rate of the phase-change medium of the phase-change cooling structure of the aero-motor, the step two specifically includes: m=w/h fg ；
The third step is as follows:wherein d is the equivalent inner diameter of the internally threaded pipe, and n is the number of the internally threaded pipes.
According to at least one embodiment of the present application, in the method for determining a phase change medium flow rate of a phase change cooling structure of an aero-motor, the fourth step is specifically:
wherein:
p is the pitch of the internal thread pipe;
e is the rib height of the internal thread pipe;
θ is the thread lead angle of the internally threaded tube;
a is the circumferential width of the threads of the internally threaded tube;
λ L the heat conductivity coefficient of the saturated liquid phase of the phase change medium;
μ L dynamic viscosity of saturated liquid phase of phase change medium;
H w the specific enthalpy of the phase change medium at the temperature of the inner wall surface of the internal thread pipe;
H L specific enthalpy of saturated liquid phase of phase change medium;
T w taking the highest bearing temperature T of the aero-motor as the temperature of the inner wall surface of the internally threaded pipe max ；
q is the heat flux density of the inner wall surface of the internally threaded tube;
H G specific enthalpy for the saturated vapor phase of the phase change medium;
sigma is the surface tension of the phase change medium;
g is gravity acceleration;
ρ L a density of a saturated liquid phase of the phase change medium;
ρ G a density of a saturated vapor phase of the phase change medium;
p cr is the critical pressure of the phase change medium.
According to at least one embodiment of the present application, in the method for determining a phase change medium flow rate of a phase change cooling structure of an aero-motor, the fifth step is specifically: Δt=t w -T sat 。
According to at least one embodiment of the present application, in the method for determining a phase change medium flow rate of a phase change cooling structure of an aero-motor, step six specifically includes: q=Δt·h·n·pi dL, where L is the length of the internally threaded tube.
Drawings
Fig. 1 is a schematic working diagram of an aero-motor phase-change cooling structure according to an embodiment of the present application;
FIG. 2 is a schematic diagram of an aero-motor phase change cooling structure provided in an embodiment of the present application;
FIG. 3 is a schematic view of an internally threaded pipe provided in an embodiment of the present application;
fig. 4 is a schematic diagram of a method for determining a phase change medium flow of an aero-motor phase change cooling structure according to an embodiment of the present application;
wherein:
1-a bottom cooling duct; 2-cooling pipes at the openings; 3-bottom cooling inlet shunt; 4-bottom cooling outlet header; 5-cooling the inlet shunt tube at the opening; and 6, cooling the outlet collecting pipe at the opening.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only a portion related to the present application is shown in the drawings, and other related portions may refer to a general design.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The words used in the description of the present application to indicate directions are merely used to indicate relative directions or positional relationships, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed accordingly. As used in this description, the word "comprising" or "comprises" does not exclude the presence of other elements or components than those listed after the word.
Furthermore, unless specifically stated or limited otherwise, the terms "mounted," "connected," and the like as used in the description of the present application should be construed broadly, and may be used in either a fixed or a removable connection, for example; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate medium, and a person skilled in the art can understand the specific meaning in the present application according to the specific situation.
In one aspect, an aero-motor phase change cooling structure is provided, as shown in fig. 1, including:
the bottom cooling pipelines 1 are internal threaded pipes and are arranged in each stator slot of the aviation motor and close to the bottoms of the stator slots;
the cooling pipelines 2 at the openings are internal thread pipes and are arranged in each stator slot of the aviation motor and close to the opening parts of the stator slots;
the bottom cooling inlet shunt pipes 3 are annular and connected to the inlet ends of the bottom cooling pipelines 1, are provided with bottom cooling inlet pipes and are filled with phase change media;
the bottom cooling outlet collecting pipe 4 is annular and connected to the outlet end of each bottom cooling pipeline 1, and is provided with a bottom cooling outlet pipe;
the cooling inlet shunt pipes 5 at the openings are annular and connected with the inlet ends of the cooling pipelines 2 at the openings and are positioned at one side of each stator slot of the aviation motor together with the collecting pipe 4 at the bottom cooling outlet,
the cooling inlet pipe is provided with an opening and is filled with phase change medium;
the opening cooling outlet collecting pipe 6 is annular and is connected to the outlet end of each opening cooling pipeline 2, is positioned on the other side of each stator slot of the aviation motor along with the bottom cooling inlet shunt pipe 3, and is provided with an opening cooling outlet pipe.
Based on the aero-motor phase-change cooling structure disclosed by the embodiment, when the aero-motor works, the phase-change medium is introduced into the bottom cooling inlet shunt pipe 3 and the opening cooling inlet shunt pipe 5 through the bottom cooling inlet pipe and the opening cooling inlet pipe, then flows into each bottom cooling pipeline 1 and each opening cooling pipeline 2, takes away the heat productivity of the aero-motor along the way, finally converges in the bottom cooling outlet collecting pipe 4 and the opening cooling outlet collecting pipe 6, and flows out through the bottom cooling outlet pipe and the opening cooling outlet pipe.
For the phase change cooling structure of the aero-motor disclosed by the embodiment, as can be understood by those skilled in the art, each bottom cooling pipeline 1 and each opening cooling pipeline 2 are arranged in each stator slot of the aero-motor and are positioned between windings, so that the heating value of the windings can be effectively taken away, the aero-motor can be efficiently cooled, and the phase change medium is adopted as the cooling medium, the phase change can be utilized for absorbing heat, the phase change cooling structure has a larger heat exchange coefficient, each bottom cooling pipeline 1 and each opening cooling pipeline 2 are designed to adopt an internal thread pipe, the turbulence of the phase change medium can be increased, the heat exchange area can be increased, the cooling efficiency of the aero-motor can be improved, the effective lengths of each bottom cooling pipeline 1 and each opening cooling pipeline 2 can be properly shortened, and the consumption of power can be reduced.
For the phase change cooling structure of the aero-motor disclosed in the above embodiment, it can be understood by those skilled in the art that the design of each bottom cooling pipe 1 and each opening cooling pipe 2 is respectively located at the bottom and the opening of each stator slot of the aero-motor, and the design of the bottom cooling inlet shunt pipe 3 connected to the inlet end of each bottom cooling pipe 1 and the opening cooling outlet header 6 connected to the outlet end of each opening cooling pipe 2 are located at one side of each stator slot of the aero-motor, the bottom cooling outlet header 4 connected to the outlet end of each bottom cooling pipe 1 and the opening cooling inlet shunt pipe 5 connected to the inlet end of each opening cooling pipe 2 are located at the other side of each stator slot of the aero-motor, so that the phase change media of each bottom cooling pipe 1 and each opening cooling pipe 2 flow reversely, as shown in fig. 2, in order to ensure the uniformity of winding cooling of the aero-motor.
In some alternative embodiments, in the phase-change cooling structure of the aero-motor, the phase-change medium is water, and may be other phase-change media with stable properties.
In some alternative embodiments, the phase change cooling structure of an aero-motor further includes:
the outlet of the circulating pump is connected with a bottom cooling inlet pipe and a cooling inlet pipe at the opening;
the condenser, hot limit exit linkage circulating pump's import, hot limit access connection bottom cooling outlet pipe, opening part cooling outlet pipe for cool off phase change medium to saturated liquid phase, guarantee to flow into each bottom cooling pipeline 1, opening part cooling pipeline 2's phase change medium, initial state is saturated liquid phase, in order to give full play to phase change medium's heat absorption capacity and efficiency, guarantee the high efficiency cooling to aviation motor.
In some alternative embodiments, in the phase-change cooling structure of the aero-motor, the condenser adopts an air cooler, and may be other high-efficiency condensers.
On the other hand, a method for determining the flow of the phase-change medium of the phase-change cooling structure of the aero-motor is provided, as shown in fig. 4.
Determining the heating power W (kW) and the highest bearing temperature T of an aero-motor max And determining the number n of the internally threaded pipes and structural parameters including equivalent internal diameter d (m), pitch P (m), rib height e (m), thread lead angle θ (°), length L (m), thread circumferential width a (m), as shown in fig. 3, and phase change medium pressure P (Pa).
Step one, calculating the saturation temperature T of the phase change medium under the pressure P of the phase change medium sat (DEGC), latent heat of vaporization h fg (kJ/kg), and can refer to the commonly used empirical formula of the current engineering calculation.
And step two, calculating the total flow m (kg/s) of the phase-change medium required by phase-change cooling of the aero-motor.
Assuming that the inlet phase change medium of each internal thread pipe is a saturated liquid phase and the outlet phase change medium is a saturated vapor phase, the purpose of utilizing boiling heat exchange effect to the greatest extent is achieved, and the method comprises the following steps:
m＝W/h fg 。
step three, calculating the flow rate G (kg/m) of the phase medium in each internal thread pipe 2 /s)。
Step four, calculating boiling heat exchange coefficient h (W/m) of phase change media in each internal thread pipe 2 /℃)。
Wherein:
λ L the heat conductivity coefficient W/(m.DEG C) of the saturated liquid phase of the phase change medium;
μ L the dynamic viscosity of the saturated liquid phase of the phase change medium is Pa.s;
H w j/kg is specific enthalpy of the phase change medium at the temperature of the inner wall surface of the internal thread pipe;
H L the specific enthalpy of the saturated liquid phase of the phase change medium is J/kg;
T w the temperature of the inner wall surface of the internal threaded pipe is DEG C, the wall thickness of the internal threaded pipe can be ignored, and the highest bearing temperature T of the aviation motor is taken max ；
q is the heat flux density of the inner wall surface of the internally threaded pipe, W/m 2 ；
H G The specific enthalpy of saturated vapor phase of the phase change medium is J/kg;
sigma is the surface tension of the phase change medium, N/m;
g is gravity acceleration, m 2 /s；
ρ L To the density of the saturated liquid phase of the phase change medium, kg/m 3 ；
ρ G Density of saturated vapor phase of phase change medium, kg/m 3 ；
p cr Is the critical pressure Pa of the phase change medium;
the related physical parameters of the phase change medium are physical properties under the pressure of the phase change medium.
And fifthly, calculating the maximum temperature difference delta T (DEG C) between the inner wall surface of the internally threaded pipe and the phase change medium.
ΔT＝T w -T sat ＝T max -T sat 。
And step six, calculating the heat exchange quantity Q (kW) which can be achieved by the phase-change medium.
Q＝ΔT·h·n·πdL。
And step seven, verifying the total flow m of the phase-change medium required by phase-change cooling of the aero-motor.
If the deviation between Q and W is greater than the set deviation threshold, adjusting m, and repeating the steps three to seven until the deviation between Q and W is less than the set deviation threshold, wherein the set deviation threshold can be 5%.
When the deviation between Q and W is larger than the set deviation threshold, if Q > W, then m is reduced, and if Q < W, then m is increased, so as to prevent excessive or insufficient total flow m of the phase change medium.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described to be different from other embodiments, so that the same and similar parts of each embodiment are mutually referred to, and the embodiments and technical features in the embodiments can be mutually combined to obtain a new embodiment without conflict.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (10)
1. An aero-motor phase change cooling structure, comprising:
the bottom cooling pipelines (1) are internally threaded pipes and are arranged in each stator slot of the aviation motor and close to the bottoms of the stator slots;
the cooling pipelines (2) at the openings are internal thread pipes and are arranged in each stator slot of the aviation motor and close to the opening parts of the stator slots;
the bottom cooling inlet shunt pipes (3) are annular and connected to the inlet ends of the bottom cooling pipelines (1), the bottom cooling inlet pipes are arranged on the bottom cooling inlet shunt pipes, and phase change media are introduced into the bottom cooling inlet shunt pipes;
the bottom cooling outlet collecting pipe (4) is annular and is connected to the outlet end of each bottom cooling pipeline (1), and a bottom cooling outlet pipe is arranged on the bottom cooling outlet collecting pipe;
an opening cooling inlet shunt pipe (5) is annular and connected to the inlet end of each opening cooling pipeline (2), is positioned on one side of each stator slot of the aviation motor together with the bottom cooling outlet collecting pipe (4), is provided with an opening cooling inlet pipe, and is introduced with a phase change medium;
and the opening cooling outlet collecting pipe (6) is annular and is connected with the outlet end of each opening cooling pipeline (2), is positioned on the other side of each stator slot of the aviation motor along with the bottom cooling inlet shunt pipe (3), and is provided with an opening cooling outlet pipe.
2. The phase-change cooling structure of an aero-motor according to claim 1, wherein,
the phase change medium is water.
3. The phase-change cooling structure of an aero-motor according to claim 1, wherein,
further comprises:
the outlet of the circulating pump is connected with a bottom cooling inlet pipe and a cooling inlet pipe at the opening;
and the hot side outlet of the condenser is connected with the inlet of the circulating pump, and the hot side inlet is connected with the bottom cooling outlet pipe and the opening cooling outlet pipe for cooling the phase change medium to a saturated liquid phase.
4. The phase-change cooling structure of an aero-motor according to claim 1, wherein,
the condenser adopts an air cooler.
5. The method for determining the flow of the phase-change medium of the phase-change cooling structure of the aero-motor is characterized by comprising the following steps of:
step one, calculating the saturation temperature T of the phase change medium under the pressure P of the phase change medium sat Latent heat of vaporization h fg ；
Step two, calculating the total flow m of the phase change medium required by phase change cooling of the aero-motor;
step three, calculating the flow velocity G of the phase medium in each internal thread pipe;
step four, calculating boiling heat exchange coefficients h of phase media in each internal thread pipe;
step five, calculating the maximum temperature difference delta T between the inner wall surface of the internally threaded pipe and the phase change medium;
step six, calculating the heat exchange quantity Q which can be achieved by the phase change medium;
and step seven, verifying the total flow m of the phase change medium required by phase change cooling of the aero-motor, if the deviation between Q and the heating power W of the aero-motor is larger than a set deviation threshold value, adjusting m, and repeating the steps three to seven until the deviation between Q and W is smaller than the set deviation threshold value.
6. The method for determining the phase change medium flow of the phase change cooling structure of the aero-motor according to claim 5, wherein,
in the seventh step, when the deviation between Q and W is larger than the set deviation threshold, if Q > W, m is reduced; if Q < W, increasing m;
the deviation threshold was set to 5%.
7. The method for determining the phase change medium flow of the phase change cooling structure of the aero-motor according to claim 6, wherein,
the second step is specifically as follows: m=w/h fg ；
The third step is as follows:wherein d is the equivalent inner diameter of the internally threaded pipe, and n is the number of the internally threaded pipes.
8. The method for determining the phase-change medium flow of the phase-change cooling structure of the aero-motor according to claim 7, wherein,
the fourth step is specifically as follows:
wherein:
p is the pitch of the internal thread pipe;
e is the rib height of the internal thread pipe;
θ is the thread lead angle of the internally threaded tube;
a is the circumferential width of the thread of the internally threaded pipe
λ L The heat conductivity coefficient of the saturated liquid phase of the phase change medium;
μ L dynamic viscosity of saturated liquid phase of phase change medium;
H w the specific enthalpy of the phase change medium at the temperature of the inner wall surface of the internal thread pipe;
H L specific enthalpy of saturated liquid phase of phase change medium;
T w taking the highest bearing temperature T of the aero-motor as the temperature of the inner wall surface of the internally threaded pipe max ；
q is the heat flux density of the inner wall surface of the internally threaded tube;
H G specific enthalpy for the saturated vapor phase of the phase change medium;
sigma is the surface tension of the phase change medium;
g is gravity acceleration;
ρ L a density of a saturated liquid phase of the phase change medium;
ρ G a density of a saturated vapor phase of the phase change medium;
p cr is the critical pressure of the phase change medium.
9. The method for determining the phase change medium flow of the phase change cooling structure of the aero-motor according to claim 8, wherein,
the fifth step is specifically as follows: Δt=t w -T sat 。
10. The method for determining the phase change medium flow of the phase change cooling structure of the aero-motor according to claim 9, wherein,
the sixth step is specifically as follows: q=Δt·h·n·pi dL, where L is the length of the internally threaded tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311772532.2A CN117895715A (en) | 2023-12-21 | 2023-12-21 | Phase-change cooling structure of aviation motor and phase-change medium flow determining method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311772532.2A CN117895715A (en) | 2023-12-21 | 2023-12-21 | Phase-change cooling structure of aviation motor and phase-change medium flow determining method thereof |
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| CN117895715A true CN117895715A (en) | 2024-04-16 |
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| CN202311772532.2A Pending CN117895715A (en) | 2023-12-21 | 2023-12-21 | Phase-change cooling structure of aviation motor and phase-change medium flow determining method thereof |
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