Air suspension turbine power generation refrigeration integrated device

Abstract

The application discloses an air suspension turbine power generation refrigeration integrated device, which comprises a shell, a stator and a rotor main shaft, the rotor main shaft is rotationally arranged in the shell through a bearing assembly, the stator is fixed in the shell and coaxially arranged with the rotor main shaft, and a gap exists between the stator and the rotor main shaft to form a permanent magnet synchronous generator, further comprising a primary volute, a secondary volute, a primary radial flow turbine, a secondary radial flow turbine, a connecting pipe between the volutes and a cooling water jacket, the primary volute and the secondary volute are respectively fixed at two ends of the shell, the primary radial flow turbine and the secondary radial flow turbine are respectively coaxially fixed at two ends of the rotor main shaft and arranged in a back-to-back mode, the primary radial flow turbine is located in the primary volute, and the secondary radial flow turbine is located in the secondary volute, the primary volute is provided with a high-temperature and high-pressure air inlet and a primary air outlet, and the secondary volute is provided with a secondary air inlet and an expanded and cooled air outlet; the device has the advantages that high-speed stable operation can be realized in a high-altitude low-pressure environment, and high-efficiency power generation and refrigeration functions are simultaneously realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of turbine generator, in particular to an air suspension turbine power generation and refrigeration integrated device. BACKGROUND

[0002] With the rapid development of aerospace technology, long-endurance, supersonic aircrafts show great application prospects in the fields of military reconnaissance, high-speed transportation, near-space exploration, etc. Such aircrafts usually use ramjet as the main power, cruising at 3 Mach or above at 20-30 km altitude. However, supersonic aircrafts face unique energy supply and thermal management challenges. On the one hand, ramjet has no rotating parts, and there is no mature way to extract shaft power from the main power, while the demand for electric power of onboard electronic equipment, flight control system, payload, etc. is growing, on the other hand, the aerodynamic heating and equipment heating generated by high-speed flight cause the temperature in the cabin to rise sharply, threatening the normal work of electronic equipment. Therefore, developing a lightweight, high-efficiency integrated device that can provide both power and refrigeration functions is of great significance to improve the overall performance of supersonic aircrafts.

[0003] In the prior art, aircraft power supply mainly adopts ram air turbine generator, gas turbine auxiliary power device or fuel cell scheme. Ram air turbine uses high-speed airflow to drive the turbine to rotate and generate electricity, but it increases the flight resistance, and the efficiency decreases sharply at low speed, auxiliary power device needs to carry additional fuel, increasing the system weight and complexity, while fuel cell has high efficiency, but low power density, which is difficult to meet the demand for high-power electricity. For refrigeration, ram air direct cooling, evaporative cycle refrigeration system or phase change material cold storage scheme are usually used, but ram air cooling has poor effect in low-density environment at high altitude, evaporative cycle system needs to consume a large amount of electric energy to drive the compressor, and the capacity of phase change material cold storage is limited, which is not suitable for long-endurance tasks. As a kind of high-efficiency cooling technology, turbine expansion refrigeration provides cold energy by expanding compressed air in the turbine, which has been applied in the field of aviation, but most devices only focus on refrigeration function, and fail to fully utilize the expansion work.

[0004] And, the existing turbo-expander has many technical defects in high-altitude application. The traditional device is supported by rolling bearings, which requires a complex lubrication system. The viscosity of lubricating oil changes greatly in the low-temperature environment at high altitudes, affecting the performance and service life of the bearing. Although magnetic bearings do not require lubrication, the control system is complex, the power consumption is high, and the reliability is insufficient in the electromagnetic interference environment. In terms of turbo configuration, the single-stage turbo-expander has limited expansion ratio, making it difficult to fully utilize the energy potential of high-pressure air sources. The multi-stage co-rotating turbo layout generates cumulative axial force, but in the wide-range working conditions of aircraft changing height and speed, the axial force changes dramatically, easily exceeding the load limit of the thrust bearing, causing rotor instability and even mechanical failure. In addition, the existing device has poor high-altitude adaptability. At an altitude of 25 kilometers, the environmental pressure is only about 2.5 kPa, and the air density is less than 3% of that at sea level. Conventional heat dissipation design cannot effectively cool the motor stator and rotor rotating at high speed, resulting in serious problems such as high-temperature demagnetization of permanent magnets and insulation failure of windings. If an air bearing support scheme is used, a stable bearing gas film cannot be established under such low environmental pressure, directly leading to bearing failure.

[0005] Therefore, it is urgent to develop a turbo power generation and refrigeration integrated device that can overcome the above-mentioned defects and truly adapt to high-altitude extreme environments. SUMMARY

[0006] The purpose of the present application is to provide an air-suspended turbo power generation and refrigeration integrated device that can operate stably at high speed in a high-altitude low-pressure environment while achieving high-efficiency power generation and refrigeration functions.

[0007] To achieve the above-mentioned purpose, the present application provides the following technical solution: an air-suspended turbo power generation and refrigeration integrated device, comprising a housing, a stator, and a rotor main shaft, the rotor main shaft being rotatably arranged in the housing through a bearing assembly, the stator being fixed in the housing and arranged coaxially with the rotor main shaft, with an air gap formed between the two to form a permanent magnet synchronous generator, further comprising a primary volute, a secondary volute, a primary radial flow turbine, a secondary radial flow turbine, a volute interconnection pipe, and a cooling water jacket, the primary volute and the secondary volute being fixed at the two ends of the housing, respectively, the primary radial flow turbine and the secondary radial flow turbine being coaxially fixed at the two ends of the rotor main shaft, respectively, and arranged back-to-back, with the primary radial flow turbine located in the primary volute and the secondary radial flow turbine located in the secondary volute, the primary volute being provided with a high-temperature high-pressure air inlet and a primary air outlet, the secondary volute being provided with a secondary air inlet and an expanded cooling air outlet, the primary air outlet being connected in communication with the secondary air inlet through the volute interconnection pipe, and the cooling water jacket being sleeved around the periphery of the housing and forming a cooling channel with the housing.

[0008] Preferably, the first bearing seat, the second bearing seat, the flange plate and the thrust plate are further included, the first bearing seat is arranged between the casing and the primary volute, the second bearing seat is arranged between the casing and the secondary volute, the flange plate is connected between the first bearing seat and the primary volute, the bearing assembly includes a first radial air bearing, a second radial air bearing, a first thrust air bearing and a second thrust air bearing, the first radial air bearing is installed in the first bearing seat, the second radial air bearing is installed in the second bearing seat, the thrust plate is sleeved on the rotor spindle and located between the first bearing seat and the flange plate, the first thrust air bearing is installed on the flange plate, the second thrust air bearing is installed on the first bearing seat, and the first thrust air bearing, the second thrust air bearing and the thrust plate cooperate to form axial support.

[0009] Preferably, the first bearing seat is provided with a pressure relief hole, the pressure relief hole is connected between the inside of the first bearing seat and the external environment, and is used for controlling the cavity pressure of the back of the primary radial flow turbine, the second bearing seat is provided with a cooling air inlet hole, the cooling air inlet hole is connected between the inside of the secondary volute and the inside of the casing, and is used for introducing part of the expanded air into the inside of the casing and controlling the back pressure of the secondary radial flow turbine, and the casing is provided with a cooling air outlet hole, the cooling air outlet hole is connected between the inside of the casing and the external environment, and is used for discharging the air after cooling the rotor spindle and the air leaked from the sealing part of the primary radial flow turbine.

[0010] Preferably, the sealing ring is further included, the sealing ring is fixedly connected to the side of the flange plate facing the primary radial flow turbine, the inner ring surface of the sealing ring is provided with a plurality of annular sealing teeth, the sealing teeth and the outer circular surface of the boss on the back surface of the primary radial flow turbine form a labyrinth seal structure, the center of the flange plate is provided with an axially-through central hole, and a plurality of radial air guide grooves are uniformly arranged on the side of the flange plate away from the sealing ring and around the central hole, and the radial air guide grooves are respectively connected with the pressure relief hole and the central hole.

[0011] Preferably, the cooling water jacket is provided with a cooling liquid inlet and a cooling liquid outlet, the cooling liquid inlet and the cooling liquid outlet are respectively connected with the cooling channel, the two ends of the cooling water jacket and the casing are provided with a sealing structure, and the stator is in interference fit with the inner wall of the casing.

[0012] Preferably, the primary volute is provided with a vaned diffuser, and the vaned diffuser is arranged around the outer periphery of the primary radial flow turbine.

[0013] Preferably, one end of the rotor main shaft is provided with a first pull rod, and the other end is provided with a second pull rod, the first pull rod passes through the first-stage radial flow turbine and is screwed with a first locking nut at the end, and the second pull rod passes through the second-stage radial flow turbine and is screwed with a second locking nut at the end, the first locking nut axially compresses and fixes the first-stage radial flow turbine on the rotor main shaft, and the second locking nut axially compresses and fixes the second-stage radial flow turbine on the rotor main shaft.

[0014] Preferably, the installation base is fixedly connected to the lower part of the shell, the high-temperature and high-pressure air inlet is provided with an air inlet connecting flange, and the expansion cooling air outlet is provided with an air outlet connecting flange.

[0015] Compared with the prior art, the application has the advantages that during operation, high-temperature and high-pressure compressed air enters from the air inlet of the first-stage volute, drives the first-stage radial flow turbine to rotate at high speed and performs first-stage expansion work, the pressure and temperature of the air are significantly reduced in this process, the air after the primary expansion is guided into the second-stage volute through the connecting pipe between the volutes, continues to drive the second-stage radial flow turbine to perform second-stage expansion, further reduces the temperature and pressure, and finally outputs low-temperature air from the air outlet for environmental refrigeration.

[0016] The rotation of the two radial flow turbines can directly drive the intermediate rotor main shaft, the relative movement between the rotor main shaft and the stator enables the permanent magnet synchronous generator to generate electric energy, realizes efficient conversion of expansion work into electric energy, and the two radial flow turbines adopt a back-to-back layout, generate axial thrusts in opposite directions during operation, can offset each other, effectively solves the problem of overloading of the thrust bearing caused by the accumulation of axial forces in the device, especially in the wide-range working condition of the change of the height and speed of the aircraft, the self-balancing design ensures the stable operation of the rotor system, meanwhile, the device adopts a double cooling mechanism combining liquid cooling and air cooling: the stator is liquid-cooled through the peripheral cooling water jacket, effectively removes the heat generated by the stator winding and the iron core, and the high-speed rotating rotor main shaft is cooled by the low-temperature air after expansion, this design fully utilizes the low-temperature characteristics of the working medium itself, solves the problem of low efficiency of the traditional cooling method in the low-pressure environment at high altitudes, avoids a complex external cooling system, and improves the overall energy utilization efficiency and system reliability. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced as follows. Obviously, the drawings in the following description are only embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of the provided drawings.

[0018] Figure 1It is a sectional view of the present application;

[0019] Figure 2 It is a sectional view of the present application;

[0020] Figure 3 It is a sectional view of the present application Figure 2 It is a sectional view of the present application;

[0021] Figure 4 It is a sectional view of the present application;

[0022] Figure 5 It is a sectional view of the present application;

[0023] Figure 6 It is a sectional view of the present application;

[0024] In the figure, 1, housing; 2, stator; 3, rotor main shaft; 4, primary volute; 5, secondary volute; 6, primary radial flow turbine; 7, secondary radial flow turbine; 8, inter-volute connecting pipe; 9, cooling jacket; 10, high-temperature and high-pressure air inlet; 11, primary air outlet; 12, secondary air inlet; 13, expanded cooling air outlet; 14, cooling channel; 15, first bearing seat; 16, second bearing seat; 17, flange plate; 18, thrust plate; 19, first radial air bearing; 20, second radial air bearing; 21, first thrust air bearing; 22, second thrust air bearing; 23, pressure relief hole; 24, cooling air inlet hole; 25, cooling air outlet hole; 26, sealing ring; 27, sealing tooth; 28, center hole; 29, radial air guide groove; 30, cooling liquid inlet; 31, cooling liquid outlet; 32, sealing structure; 33, vane diffuser; 34, first pull rod; 35, second pull rod; 36, first locking nut; 37, second locking nut; 38, mounting base; 39, air inlet connecting flange; 40, air outlet connecting flange. DETAILED DESCRIPTION

[0025] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0026] Embodiment one: as Figures 1-6As shown, an air suspension turbine power refrigeration integrated device includes a shell 1, a stator 2 and a rotor main shaft 3, the rotor main shaft 3 is rotatably arranged in the shell 1 through a bearing assembly, the stator 2 is fixed in the shell 1 and arranged coaxially with the rotor main shaft 3, and there is an air gap between the two to form a permanent magnet synchronous generator, further comprising a primary volute 4, a secondary volute 5, a primary radial turbine 6, a secondary radial turbine 7, a volute interconnection pipe 8 and a cooling jacket 9, the primary volute 4 and the secondary volute 5 are respectively fixed at both ends of the shell 1, the primary radial turbine 6 and the secondary radial turbine 7 are respectively coaxially fixed at both ends of the rotor main shaft 3 and arranged back-to-back, and the primary radial turbine 6 is located in the primary volute 4 and the secondary radial turbine 7 is located in the secondary volute 5, the primary volute 4 is provided with a high-temperature and high-pressure air inlet 10 and a primary air outlet 11, the secondary volute 5 is provided with a secondary air inlet 12 and an expanded cooling air outlet 13, the primary air outlet 11 is connected with the secondary air inlet 12 through the volute interconnection pipe 8, and the cooling jacket 9 is sleeved on the outer periphery of the shell 1 and forms a cooling channel 14 with the shell 1.

[0027] Embodiment two: as Figures 1-6 shown, different from embodiment one, further comprising a first bearing seat 15, a second bearing seat 16, a flange plate 17 and a thrust plate 18, the first bearing seat 15 is arranged between the shell 1 and the primary volute 4, the second bearing seat 16 is arranged between the shell 1 and the secondary volute 5, the flange plate 17 is connected between the first bearing seat 15 and the primary volute 4, the bearing assembly comprises a first radial air bearing 19, a second radial air bearing 20, a first thrust air bearing 21 and a second thrust air bearing 22, the first radial air bearing 19 is installed in the first bearing seat 15, the second radial air bearing 20 is installed in the second bearing seat 16, the thrust plate 18 is sleeved on the rotor main shaft 3 and located between the first bearing seat 15 and the flange plate 17, the first thrust air bearing 21 is installed on the flange plate 17, and the second thrust air bearing 22 is installed on the first bearing seat 15, the first thrust air bearing 21, the second thrust air bearing 22 and the thrust plate 18 cooperate to form an axial support.

[0028] The working principle of the air bearing is to form an extremely thin bearing air film between the bearing surface and the rotor by using high-pressure air, and this air film has self-adapting adjustment capability, when the rotor main shaft 3 is disturbed externally, the change of the air film thickness will automatically generate a restoring force to make the rotor main shaft 3 return to the balance position. Compared with the traditional rolling bearing or magnetic suspension bearing, the air bearing has the advantages of no wear, no need for lubrication, high temperature resistance and simple maintenance, and is particularly suitable for long-time operation in high-altitude extreme environment, and its extremely low friction loss also improves the energy conversion efficiency of the whole power generation system.

[0029] The bearing support system of the device adopts a full-air suspension design, realizing non-contact and non-friction operation of the rotor, so that the entire device can work efficiently and stably. In terms of structural layout, the first bearing seat 15 and the second bearing seat 16 are respectively located at both ends of the shell 1, forming a main support frame for the rotor spindle 3, and the first radial air bearing 19 and the second radial air bearing 20 installed inside the main support frame provide radial positioning and support for the high-speed rotating rotor spindle 3, ensuring that the rotor spindle 3 maintains concentricity and stability during high-speed operation.

[0030] The balance of the axial force is realized through the thrust bearing system: the thrust disc 18 is fixed on the rotor spindle 3 and located in the narrow space between the first bearing seat 15 and the flange plate 17, and its two sides form a bidirectional axial support structure with the first thrust air bearing 21 installed on the flange plate 17 and the second thrust air bearing 22 installed on the first bearing seat 15. The advantage of this double-sided thrust design is that no matter which direction the axial force points, there is a corresponding thrust bearing to provide a counteracting support force, cooperating with the self-balancing effect generated by the back-to-back turbine, so that the entire rotor system always maintains stability in the axial position under wide-range working conditions.

[0031] In this embodiment, the first bearing seat 15 is provided with a pressure relief hole 23, which communicates the inside of the first bearing seat 15 with the external environment, and is used to control the cavity pressure at the back of the first radial turbine 6. The second bearing seat 16 is provided with a cooling air inlet hole 24, which communicates the inside of the second bearing seat 16 with the inside of the shell 1, and is used to introduce part of the expanded air into the inside of the shell 1 and control the back pressure of the second radial turbine 7. The shell 1 is provided with a cooling air outlet hole 25, which communicates the inside of the shell 1 with the external environment, and is used to exhaust the air after cooling the rotor spindle 3 and the air leaked from the seal of the first radial turbine 6.

[0032] The above design realizes the dual goals of balancing the axial force and efficient heat dissipation. The pressure relief hole 23 on the first bearing seat 15 plays a key role in pressure regulation, which communicates the internal cavity of the first bearing seat 15 with the external environment, can effectively release the high-pressure gas accumulated at the back of the first radial turbine 6, prevent the adverse effects of excessive back pressure on the balance of the axial force, and by controlling the aperture size of the pressure relief hole 23, the pressure distribution at the back of the first radial turbine 6 can be accurately adjusted, thereby controlling the size of the axial thrust acting on the turbine.

[0033] The cooling air inlet hole 24 on the second bearing seat 16 has a dual function: on the one hand, it introduces the expanded low-temperature air in the secondary volute 5 into the inside of the shell 1, and these air flows in the air gap between the stator 2 and the rotor main shaft 3, effectively cooling the high-speed rotating permanent magnet rotor to prevent demagnetization of the permanent magnet due to overheating; on the other hand, the introduced air pressure can also adjust the pressure environment at the back of the secondary radial turbine 7, and cooperates with the pressure relief hole 23 on the primary side to jointly maintain the combined axial force generated by the two-stage turbine within a controllable range.

[0034] The cooling air outlet hole 25 on the shell 1 serves as the outlet of the entire air circulation, which not only discharges the hot air after completing the cooling task, but also collects and discharges the leaked gas from the primary radial turbine 6, forming a complete internal air circulation path. The advantage of this design is that it fully utilizes the characteristics of the working medium itself, that is, the expanded low-temperature air is not only a cooling medium, but also provides the necessary working pressure for the air bearing, ensuring that the bearing can still establish a stable bearing air film in a high-altitude low-pressure environment, and achieving dynamic balance of the axial force through pressure distribution adjustment.

[0035] In this embodiment, a sealing ring 26 is also included, which is fixedly connected to the side of the flange plate 17 facing the primary radial turbine 6. The inner ring surface of the sealing ring 26 is provided with a plurality of annular sealing teeth 27, which form a labyrinth seal structure with the outer cylindrical surface of the boss on the back of the primary radial turbine 6. An axial through central hole 28 is formed in the center of the flange plate 17, and a plurality of radial air guide grooves 29 are uniformly formed around the central hole 28 on the side of the flange plate 17 away from the sealing ring 26, which are respectively communicated with the pressure relief hole 23 and the central hole 28.

[0036] The sealing system of the device adopts a labyrinth seal technology, which ensures efficient sealing while achieving control of the axial force. The sealing ring 26 is fixed to the side of the flange plate 17 facing the primary radial turbine 6, and the plurality of annular sealing teeth 27 on the inner ring surface form a non-contact labyrinth seal structure with the boss on the back of the turbine. The working principle of this design is that the high-pressure gas will undergo multiple throttling expansion when passing through the gaps between the continuous sealing teeth 27, and the gas pressure will significantly decrease after passing through each sealing tooth 27 due to flow resistance and vortex loss, and the flow rate will also decrease, thereby greatly reducing the amount of gas leakage.

[0037] The advantage of this sealing method is that it is completely contactless and wear-free, making it particularly suitable for high-speed rotating machinery. Meanwhile, the number and clearance size of the sealing teeth 27 directly determine the pressure distribution gradient at the back of the first-stage radial turbine, becoming a crucial design parameter for controlling axial force. The through hole in the center of the flange 17 and the circumferentially distributed radial air guide grooves 29 form a pressure relief channel system: a small amount of high-pressure gas leaking from the sealing ring 26 enters the inner cavity of the first bearing housing 15 and then enters the radial air guide grooves 29 on the flange 17 through the pressure relief hole 23. These radial air guide grooves 29 collect the dispersed leaked gas and guide it to the central hole 28 for unified discharge. This design not only ensures the orderly discharge of leaked gas, avoiding pressure accumulation in the bearing housing that affects bearing operation, but more importantly, by controlling the coordination of three key parameters—the sealing clearance, the diameter of the pressure relief hole 23, and the size of the air guide grooves—the pressure field distribution at the back of the first-stage radial turbine can be precisely adjusted, allowing it to work in synergy with the pressure regulation mechanism on the second-stage side. This ensures that the combined axial force generated by the two turbines remains stable in direction and controllable in magnitude throughout the entire envelope of the aircraft, creating favorable conditions for the reliable operation of the thrust bearing.

[0038] Example 3: Figures 1-6 As shown, unlike Embodiment 2, the cooling water jacket 9 is provided with a coolant inlet 30 and a coolant outlet 31. The coolant inlet 30 and the coolant outlet 31 are respectively connected to the cooling channel 14. A sealing structure 32 is provided between the two ends of the cooling water jacket 9 and the shell 1. The stator 2 is interference-fitted with the inner wall of the shell 1.

[0039] In the above structure, the cooling water jacket 9 is fitted around the outer periphery of the housing 1, forming an annular cooling channel 14 between the jacket and the housing 1. The coolant enters from the inlet and circulates within the channel, fully absorbing the heat generated by the stator 2 before being discharged from the outlet, forming a continuous cooling cycle. The sealing structures 32 at both ends of the cooling water jacket 9 ensure that the coolant will not leak during high-pressure circulation, thus guaranteeing the airtightness of the cooling system and preventing potential damage to electrical components from the coolant.

[0040] The interference fit design between the stator 2 and the inner wall of the housing 1 has the following advantages: First, the radial pressure generated by the interference fit makes the stator 2 and the housing 1 fit tightly together, eliminating contact thermal resistance and greatly improving the heat transfer efficiency from the stator 2 to the housing 1 and then to the cooling water jacket 9, ensuring that a large amount of heat generated inside the housing can be quickly conducted away. Second, the interference fit provides reliable mechanical fixation, preventing the stator 2 from vibrating or displacing under the action of a high-speed rotating magnetic field, ensuring the uniformity of the air gap and the stability of the power generation efficiency. In addition, this tight fit also enhances the rigidity of the overall structure and improves the vibration resistance of the device.

[0041] In this embodiment, the first volute 4 is provided with a vaned diffuser 33, which is arranged around the outer periphery of the first radial turbine 6.

[0042] The vaned diffuser 33 is arranged around the outer periphery of the first radial turbine 6. Its mechanism is to orderly guide and decelerate the high-speed gas flow out of the turbine through fixed guide vanes. After the high-pressure gas expands and does work in the first radial turbine 6, it is ejected from the turbine outlet at a very high tangential velocity. This part of high-speed gas flow still contains a large amount of kinetic energy, which will be wasted due to flow disorder and impact loss if directly collected into the first volute 4. The guide vanes of the vaned diffuser 33 are designed according to specific angles and profiles, which can smoothly guide the high-speed rotating gas flow into the diffuser passage. During the diffusing process, the kinetic energy of the gas flow is effectively converted into pressure energy, realizing the reduction of velocity and the partial recovery of static pressure.

[0043] The advantages of this design are: on the one hand, it improves the energy conversion efficiency of the turbine stage, so that more gas energy is converted into shaft power output, improving the power generation, on the other hand, the gas flow after deceleration by the diffuser enters the volute collection chamber at a lower speed and a higher pressure, reducing the flow loss of the gas flow in the volute, making the gas flow more stable and orderly through the volute interconnecting pipe 8 into the second turbine, improving the aerodynamic matching between stages.

[0044] In this embodiment, the first pull rod 34 is arranged at one end of the rotor main shaft 3, and the second pull rod 35 is arranged at the other end. The first pull rod 34 passes through the first radial turbine 6 and is screwed with a first locking nut 36 at the end, and the second pull rod 35 passes through the second radial turbine 7 and is screwed with a second locking nut 37 at the end. The first locking nut 36 axially compresses and fixes the first radial turbine 6 on the rotor main shaft 3, and the second locking nut 37 axially compresses and fixes the second radial turbine 7 on the rotor main shaft 3.

[0045] The first pull rod 34 and the second pull rod 35 arranged at both ends of the rotor main shaft 3 can be integrally formed with the rotor main shaft 3, or they can be independent parts connected by threads. The two pull rods apply axial pre-tightening force through the locking nuts at the ends, firmly compressing the turbines on the positioning steps or shaft shoulders of the rotor main shaft 3. This fixing method has the following advantages: first, the friction generated by axial compression can reliably transmit the huge torque in high-speed rotation, ensuring that the turbine and the main shaft will not slide or come loose relative to each other, second, the locking nuts can accurately control the size of the pre-tightening force, ensuring enough compression force to withstand the axial load and centrifugal force during turbine operation, while avoiding excessive compression that may cause stress concentration and deformation. This structure is also convenient for assembly and maintenance. When the turbine needs to be replaced or overhauled, the locking nuts only need to be loosened for disassembly, without destructive disassembly.

[0046] In order to ensure dynamic balance and concentricity during high-speed rotation, the turbine and the corresponding pull rod are usually fitted with an interference fit or a keyway fit to achieve circumferential positioning and torque transmission, and the axial positioning of the mating end face forms a complete and reliable turbine fixing system. In actual operation, the locking nuts at both ends also play the role of balance mass, and the dynamic balance adjustment of the rotor shaft 3 can be carried out by adjusting the tightening depth of the nuts or adding balance shims.

[0047] In this embodiment, a mounting base 38 is also included, which is fixedly connected to the lower part of the shell 1. The high-temperature and high-pressure air inlet 10 is provided with an inlet connecting flange 39, and the expanded cooling air outlet 13 is provided with an exhaust connecting flange 40.

[0048] In the above structure, the mounting base 38 is fixedly connected to the lower part of the shell 1, providing a stable support foundation for the entire device. This base design not only ensures the stability of the device during high-speed operation and effectively suppresses vibration transmission, but also facilitates the integration and installation of the device into the aircraft body structure. The base is usually designed with a vibration damping pad or elastic support element, which can isolate the vibrations generated during device operation and prevent vibration transmission to the aircraft main structure. At the same time, it also protects the device from external vibration interference.

[0049] Flange connection, as a mature high-pressure sealing connection method, can maintain reliable sealing under harsh conditions of high temperature and high pressure through the cooperation of circumferentially distributed pre-tightening force of bolts and metal sealing gaskets. The advantage of this standardized interface design is to achieve quick docking of the device with the aircraft air supply system. The specification of the flange usually follows the aviation industry standard, ensuring compatibility between different systems.

[0050] The above is only an embodiment of the present application, and does not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation using the content of the present application specification and drawings, or direct or indirect application in other related technical fields, is also included in the patent protection scope of the present application.

Claims

1. An air-suspension turbine power refrigeration integrated device, comprising a housing, a stator and a rotor main shaft, the rotor main shaft is rotatably arranged in the housing through a bearing assembly, the stator is fixed in the housing and arranged coaxially with the rotor main shaft, and there is an air gap between the two to form a permanent magnet synchronous generator, characterized in that: The turbine further comprises a first volute, a second volute, a first radial flow turbine, a second radial flow turbine, a connecting pipe between the volutes and a cooling jacket, the first volute and the second volute are respectively fixed at two ends of the casing, the first radial flow turbine and the second radial flow turbine are respectively coaxially fixed at two ends of the rotor shaft and arranged in back-to-back layout, the first radial flow turbine is located in the first volute, and the second radial flow turbine is located in the second volute, the first volute is provided with a high-temperature and high-pressure air inlet and a first air outlet, the second volute is provided with a second air inlet and an expanded and cooled air outlet, the first air outlet is connected with the second air inlet through the connecting pipe between the volutes, and the cooling jacket is sleeved on the outer periphery of the casing and forms a cooling channel with the casing. ​ The turbine further comprises a first bearing seat, a second bearing seat, a flange plate and a thrust plate, the first bearing seat is arranged between the casing and the first volute, the second bearing seat is arranged between the casing and the second volute, the flange plate is connected between the first bearing seat and the first volute, the bearing assembly comprises a first radial air bearing, a second radial air bearing, a first thrust air bearing and a second thrust air bearing, the first radial air bearing is installed in the first bearing seat, the second radial air bearing is installed in the second bearing seat, the thrust plate is sleeved on the rotor shaft and located between the first bearing seat and the flange plate, the first thrust air bearing is installed on the flange plate, and the second thrust air bearing is installed on the first bearing seat, the first thrust air bearing, the second thrust air bearing and the thrust plate cooperate to form axial support. A relief hole is formed in the first bearing seat and communicates the inside of the first bearing seat with the external environment, for controlling the cavity pressure at the back of the first radial flow turbine, a cooling air inlet hole is formed in the second bearing seat and communicates the inside of the second volute with the inside of the casing, for introducing part of the expanded air into the inside of the casing and controlling the back pressure of the second radial flow turbine, and a cooling air outlet hole is formed in the casing and communicates the inside of the casing with the external environment, for discharging the air after cooling the rotor shaft and the air leaked from the sealing part of the first radial flow turbine.

2. The air suspension turbine power generation refrigeration integrated device according to claim 1, characterized in that: The turbine further comprises a sealing ring, the sealing ring is fixedly connected to one side of the flange plate facing the first radial flow turbine, an inner ring surface of the sealing ring is provided with a plurality of annular sealing teeth, the sealing teeth and the outer circular surface of the boss on the back surface of the first radial flow turbine form a labyrinth seal structure, an axial through central hole is formed in the center of the flange plate, and a plurality of radial air guide grooves are uniformly formed in the side of the flange plate away from the sealing ring and around the central hole, and the radial air guide grooves are respectively communicated with the relief hole and the central hole.

3. The air suspension turbine power generation refrigeration integrated device according to claim 1, characterized in that: The cooling jacket is provided with a cooling liquid inlet and a cooling liquid outlet, which are communicated with the cooling channel respectively, and a sealing structure is arranged between the two ends of the cooling jacket and the shell.

4. The air suspension turbine power generation refrigeration integrated device according to claim 1, characterized in that: The first-stage volute is internally provided with a vaned diffuser which is arranged around the outer periphery of the first-stage radial turbine.

5. The air suspension turbine power generation refrigeration integrated device according to claim 1, characterized in that: One end of the rotor main shaft is provided with a first pull rod, and the other end is provided with a second pull rod.

6. The air suspension turbine power generation refrigeration integrated device according to claim 1, characterized in that: The installation base is fixedly connected to the lower part of the shell, the high-temperature and high-pressure air inlet is provided with an air inlet connecting flange, and the expansion cooling air outlet is provided with an air outlet connecting flange.

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