Air suspension turbine power generation and refrigeration integrated device

Abstract

The invention discloses an air suspension turbine power generation and refrigeration integrated device which comprises a shell, a stator and a rotor spindle, the rotor spindle is rotationally arranged in the shell through a bearing assembly, the stator is fixed in the shell and is coaxial with the rotor spindle, and an air gap exists between the stator and the rotor spindle to form a permanent magnet synchronous generator. The rotor further comprises a first-stage volute, a second-stage volute, a first-stage radial flow turbine, a second-stage radial flow turbine, a volute connecting pipe and a cooling water jacket, the first-stage volute and the second-stage volute are fixed to the two ends of the shell respectively, and the first-stage radial flow turbine and the second-stage radial flow turbine are coaxially fixed to the two ends of the rotor spindle respectively and are arranged back to back; the first-stage radial flow turbine is located in the first-stage volute, the second-stage radial flow turbine is located in the second-stage volute, the first-stage volute is provided with a high-temperature and high-pressure air inlet and a first-stage air outlet, and the second-stage volute is provided with a second-stage air inlet and an expansion cooling air exhaust port; the device has the advantages of being capable of stably running at a high speed in a high-altitude low-pressure environment and simultaneously achieving efficient power generation and refrigeration functions.

Description

Technical Field

[0001] This invention relates to the field of turbine generator technology, and in particular to an integrated air-suspended turbine power generation and refrigeration device. Background Technology

[0002] With the rapid development of aerospace technology, long-endurance, supersonic aircraft have shown great promise in military reconnaissance, high-speed transportation, and near-space exploration. These aircraft typically use ramjet engines as their main propulsion, cruising at speeds exceeding Mach 3 at altitudes of 20-30 kilometers. However, supersonic aircraft face unique challenges in energy supply and thermal management. On the one hand, ramjet engines have no rotating parts, and there is no mature method for extracting shaft work from the main propulsion, while the power demands of avionics, flight control systems, and payloads are increasing. On the other hand, the aerodynamic heating and equipment heat generated by high-speed flight cause a sharp rise in cabin temperature, threatening the normal operation of electronic equipment. Therefore, developing a lightweight, high-efficiency integrated device that can simultaneously provide power and cooling is of great significance for improving the overall performance of supersonic aircraft.

[0003] In existing technologies, aircraft power supply mainly employs solutions such as ram-air turbine generators, gas turbine auxiliary power units, or fuel cells. Ram-air turbines utilize high-speed airflow to drive turbine rotation and generate electricity, but this increases flight drag and its efficiency drops sharply at low speeds. Auxiliary power units require additional fuel, increasing system weight and complexity. While fuel cells offer higher efficiency, their low power density makes them unsuitable for high-power applications. For cooling, common solutions include direct ram-air cooling, evaporative cooling systems, or phase change material (PCM) cold storage. However, ram-air cooling is ineffective in high-altitude, low-density environments. Evaporative cooling systems consume significant electrical energy to drive compressors, and PCM cold storage capacity is limited, making them unsuitable for long-endurance missions. Turbine expansion cooling, as a highly efficient cooling technology, provides cooling by expanding and cooling compressed air within a turbine. While already used in aviation, most systems focus solely on cooling and fail to fully utilize the expansion work.

[0004] Furthermore, existing turbine expanders suffer from numerous technical drawbacks when used at high altitudes. Traditional devices often employ rolling bearings, requiring complex lubrication systems. The viscosity of the lubricating oil varies significantly in the low-temperature environment of high altitudes, affecting bearing performance and lifespan. While magnetic levitation bearings require no lubrication, their control systems are complex, they consume a lot of power, and their reliability is insufficient in environments with electromagnetic interference. Regarding turbine configuration, single-stage turbines have limited expansion ratios, making it difficult to fully utilize the energy potential of high-pressure air sources. Multi-stage, co-directional turbine layouts generate cumulative axial forces, but under the wide-range operating conditions of varying altitudes and speeds in aircraft, these axial forces change drastically, easily exceeding the thrust bearing's load-bearing limit, leading to rotor instability or even mechanical failure. Additionally, existing devices have 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 designs cannot effectively cool the high-speed rotating motor stator and rotor, leading to serious problems such as high-temperature demagnetization of permanent magnets and winding insulation failure. If an air bearing support scheme is used, a stable load-bearing air film cannot be established under such low environmental pressure, directly causing bearing failure.

[0005] Therefore, there is an urgent need to develop a new type of turbine-powered refrigeration integrated device that can overcome the above-mentioned defects and truly adapt to the extreme environment at high altitudes. Summary of the Invention

[0006] The purpose of this invention is to provide an integrated air-suspended turbine power generation and cooling device that can operate at high speed and stably in a high-altitude, low-pressure environment, while achieving efficient power generation and cooling functions.

[0007] To achieve the above objectives, the present invention provides the following technical solution: an integrated air-suspended turbine power generation and cooling device, comprising a housing, a stator, and a rotor main shaft. The rotor main shaft is rotatably mounted within the housing via a bearing assembly. The stator is fixed within the housing and coaxially arranged with the rotor main shaft, with an air gap between them forming a permanent magnet synchronous generator. The device also includes a primary volute, a secondary volute, a primary radial turbine, a secondary radial turbine, a connecting pipe between the volutes, and a cooling water jacket. The primary and secondary volutes are respectively fixed at both ends of the housing. The primary and secondary radial turbines are coaxially fixed at both ends of the rotor main shaft, arranged back-to-back. The primary radial turbine is located within the primary volute, and the secondary radial turbine is located within the secondary volute. The primary volute is provided with a high-temperature, high-pressure air inlet and a primary air outlet. The secondary volute is provided with a secondary air inlet and an expansion cooling air exhaust outlet. The primary air outlet is connected to the secondary air inlet via the connecting pipe between the volutes. The cooling water jacket is fitted around the outer periphery of the housing and forms a cooling channel with the housing.

[0008] Preferably, the assembly further includes a first bearing housing, a second bearing housing, a flange, and a thrust plate. The first bearing housing is disposed between the housing and the first-stage volute, and the second bearing housing is disposed between the housing and the second-stage volute. The flange connects the first bearing housing and the first-stage 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 housing, and the second radial air bearing is installed in the second bearing housing. The thrust plate is sleeved on the rotor spindle and located between the first bearing housing and the flange. The first thrust air bearing is installed on the flange, and the second thrust air bearing is installed on the first bearing housing. The first thrust air bearing, the second thrust air bearing, and the thrust plate cooperate to form axial support.

[0009] Preferably, the first bearing housing has a pressure relief hole that connects the interior of the first bearing housing to the external environment, and is used to control the cavity pressure at the back of the first-stage radial turbine. The second bearing housing has a cooling air inlet that connects the interior of the second-stage volute to the interior of the housing, and is used to introduce some of the expanded air into the housing and control the pressure at the back of the second-stage radial turbine. The housing has a cooling exhaust hole that connects the interior of the housing to the external environment, and is used to exhaust the air cooled after cooling the rotor shaft and the air leaking from the seal of the first-stage radial turbine.

[0010] Preferably, it further includes a sealing ring, which is fixedly connected to the side of the flange facing the first-stage radial turbine. The inner ring surface of the sealing ring is provided with a plurality of annular sealing teeth, and the sealing teeth form a labyrinth-type sealing structure with the outer circular surface of the boss on the back of the first-stage radial turbine. An axially penetrating central hole is opened at the center of the flange. On the side of the flange away from the sealing ring, a plurality of radial air guide grooves are evenly opened around the central hole. The radial air guide grooves are respectively connected to the pressure relief hole and the central hole.

[0011] Preferably, the cooling water jacket is provided with a coolant inlet and a coolant outlet, the coolant inlet and the coolant outlet are respectively connected to the cooling channel, a sealing structure is provided between the two ends of the cooling water jacket and the housing, and the stator is interference-fitted with the inner wall of the housing.

[0012] Preferably, a bladed diffuser is provided inside the first-stage volute, and the bladed diffuser is arranged around the outer periphery of the first-stage radial turbine.

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

[0014] Preferably, the device further includes a mounting base, which is fixedly connected to the lower part of the housing. The high-temperature and high-pressure air inlet is provided with an inlet connection flange, and the expansion cooling air outlet is provided with an exhaust connection flange.

[0015] Compared with the prior art, the advantages of the present invention are as follows: During operation, high-temperature and high-pressure compressed air enters from the air inlet of the first-stage volute, driving the first-stage radial turbine to rotate at high speed and perform first-stage expansion work. During this process, the air pressure and temperature drop significantly. The air that has undergone primary expansion is introduced into the second-stage volute through the connecting pipe between the volutes, which continues to drive the second-stage radial turbine to perform second-stage expansion, further reducing the temperature and pressure. Finally, low-temperature air is output from the exhaust port for environmental cooling.

[0016] The rotation of the two radial turbines directly drives the central rotor shaft. The relative motion between the rotor shaft and the stator enables the permanent magnet synchronous generator to produce electrical energy, achieving a highly efficient conversion of expansion work into electrical energy. Furthermore, the two radial turbines are arranged back-to-back, generating axial thrust in opposite directions during operation, which cancels each other out. This effectively solves the problem of thrust bearing overload caused by axial force accumulation in this device. Especially under the wide range of operating conditions of the aircraft with varying altitudes and speeds, this self-balancing design ensures the stable operation of the rotor system. At the same time, the device adopts a dual heat dissipation mechanism combining liquid cooling and air cooling: the stator is cooled by liquid through an external cooling water jacket, effectively removing the heat generated by the stator windings and core, while the high-speed rotating rotor shaft is cooled by the expanded, low-temperature air. This design fully utilizes the low-temperature characteristics of the working medium itself, solving the problem of low efficiency of traditional heat dissipation methods in high-altitude, low-pressure environments, and avoiding complex external cooling systems, thereby improving the overall energy utilization efficiency and system reliability. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0018] Figure 1This is a three-dimensional structural diagram of the present invention; Figure 2 This is a cross-sectional view of the present invention; Figure 3 For the present invention Figure 2 A magnified view of a portion of point A in the middle; Figure 4 This is a schematic diagram of the internal structure of the cooling water jacket in this invention; Figure 5 This is a three-dimensional structural diagram of the flange in this invention; Figure 6 This is a three-dimensional structural diagram of the disassembled state of the present invention; In the diagram, 1. Housing; 2. Stator; 3. Rotor spindle; 4. First-stage volute; 5. Second-stage volute; 6. First-stage radial turbine; 7. Second-stage radial turbine; 8. Connecting pipe between volutes; 9. Cooling water jacket; 10. High-temperature and high-pressure air inlet; 11. First-stage air outlet; 12. Second-stage air inlet; 13. Expansion cooling air exhaust port; 14. Cooling channel; 15. First bearing housing; 16. Second bearing housing; 17. Flange; 18. Thrust plate; 19. First radial air bearing; 20. Second radial air bearing; 2 1. First thrust air bearing; 22. Second thrust air bearing; 23. Pressure relief hole; 24. Cooling air inlet; 25. Cooling exhaust hole; 26. Sealing ring; 27. Sealing teeth; 28. Center hole; 29. ​​Radial air guide groove; 30. Coolant inlet; 31. Coolant outlet; 32. Sealing structure; 33. Vaned diffuser; 34. First tie rod; 35. Second tie rod; 36. First lock nut; 37. Second lock nut; 38. Mounting base; 39. Inlet connection flange; 40. Exhaust connection flange. Detailed Implementation

[0019] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0020] Example 1: As Figures 1-6As shown, an integrated air-suspended turbine power generation and cooling device includes a housing 1, a stator 2, and a rotor main shaft 3. The rotor main shaft 3 is rotatably mounted inside the housing 1 via a bearing assembly. The stator 2 is fixed inside the housing 1 and coaxially arranged with the rotor main shaft 3, with an air gap between them forming a permanent magnet synchronous generator. It also includes a first-stage volute 4, a second-stage volute 5, a first-stage radial flow turbine 6, a second-stage radial flow turbine 7, a connecting pipe 8 between the volutes, and a cooling water jacket 9. The first-stage volute 4 and the second-stage volute 5 are respectively fixed at both ends of the housing 1, and the first-stage radial flow turbine 6 and the second-stage radial flow turbine 7 are connected by a connecting pipe 8 between the volutes. The radial flow turbines 7 are coaxially fixed at both ends of the rotor main shaft 3 and arranged back to back. The first-stage radial flow turbine 6 is located in the first-stage volute 4, and the second-stage radial flow turbine 7 is located in the second-stage volute 5. The first-stage volute 4 is provided with a high-temperature and high-pressure air inlet 10 and a first-stage air outlet 11. The second-stage volute 5 is provided with a second-stage air inlet 12 and an expansion cooling air exhaust outlet 13. The first-stage air outlet 11 is connected to the second-stage air inlet 12 through the volute connecting pipe 8. The cooling water jacket 9 is sleeved on the outer periphery of the shell 1 and forms a cooling channel 14 between the jacket and the shell 1.

[0021] Example 2: Figures 1-6 As shown, unlike Embodiment 1, this embodiment also includes a first bearing housing 15, a second bearing housing 16, a flange 17, and a thrust plate 18. The first bearing housing 15 is disposed between the housing 1 and the first-stage volute 4, and the second bearing housing 16 is disposed between the housing 1 and the second-stage volute 5. The flange 17 connects the first bearing housing 15 and the first-stage volute 4. The bearing assembly includes 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 inside the first bearing housing 15, and the second radial air bearing 20 is installed inside the second bearing housing 16. The thrust plate 18 is sleeved on the rotor spindle 3 and located between the first bearing housing 15 and the flange 17. The first thrust air bearing 21 is installed on the flange 17, and the second thrust air bearing 22 is installed on the first bearing housing 15. The first thrust air bearing 21, the second thrust air bearing 22, and the thrust plate 18 cooperate to form axial support.

[0022] The working principle of an air bearing is to utilize high-pressure air to form an extremely thin load-bearing air film between the bearing surface and the rotor. This air film has self-adjusting capabilities; when the rotor shaft 3 is subjected to external disturbances, the change in the thickness of the air film automatically generates a restoring force, causing the rotor shaft 3 to return to its equilibrium position. Compared to traditional rolling bearings or magnetic levitation bearings, air bearings have significant advantages such as no wear, no lubrication required, high temperature resistance, and simple maintenance. They are particularly suitable for long-term operation in extreme high-altitude environments, and their extremely low frictional loss also improves the energy conversion efficiency of the entire power generation system.

[0023] The bearing support system of this device adopts a fully air-suspended design, realizing contactless and frictionless operation of the rotor, enabling the entire device to operate efficiently and stably. In terms of structural layout, the first bearing housing 15 and the second bearing housing 16 are located at both ends of the housing 1, forming the main support frame of the rotor spindle 3. The first radial air bearing 19 and the second radial air bearing 20 installed inside 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.

[0024] The axial force balance is achieved through the thrust bearing system: the thrust plate 18 is fixed on the rotor main shaft 3 and located in the narrow space between the first bearing housing 15 and the flange 17. Its two sides form a bidirectional axial support structure with the first thrust air bearing 21 installed on the flange 17 and the second thrust air bearing 22 installed on the first bearing housing 15, respectively. 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 reverse support force. Combined with the self-balancing effect generated by the back-to-back turbines, the entire rotor system can always maintain the stability of the axial position under wide operating conditions.

[0025] In this embodiment, a pressure relief hole 23 is provided on the first bearing housing 15, which connects the interior of the first bearing housing 15 with the external environment and is used to control the cavity pressure at the back of the first-stage radial turbine 6. A cooling air inlet hole 24 is provided on the second bearing housing 16, which connects the interior of the second-stage volute 5 with the interior of the housing 1 and is used to introduce some of the expanded air into the interior of the housing 1 and control the pressure at the back of the second-stage radial turbine 7. A cooling exhaust hole 25 is provided on the housing 1, which connects the interior of the housing 1 with the external environment and is used to exhaust the air after cooling the rotor main shaft 3 and the air leaking from the seal of the first-stage radial turbine 6.

[0026] The above design achieves the dual goals of axial force balance and efficient heat dissipation. The pressure relief hole 23 on the first bearing housing 15 plays a key role in pressure regulation. It connects the inner cavity of the first bearing housing 15 with the external environment, effectively releasing the high-pressure gas accumulated on the back of the first-stage radial turbine 6, preventing excessive back pressure from adversely affecting the axial force balance. By controlling the diameter of the pressure relief hole 23, the pressure distribution on the back of the first-stage radial turbine 6 can be precisely adjusted, thereby controlling the magnitude of the axial thrust acting on the turbine.

[0027] The cooling air inlet 24 on the second bearing housing 16 has a dual function: on the one hand, it introduces the expanded low-temperature air from the second-stage volute 5 into the housing 1. This 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 and preventing demagnetization of the permanent magnet due to overheating; on the other hand, the introduced air pressure can also regulate the pressure environment on the back of the second-stage radial turbine 7, working in conjunction with the pressure relief hole 23 on the first-stage side to maintain the combined axial force generated by the two-stage turbine within a controllable range.

[0028] The cooling exhaust port 25 on the housing 1 serves as the outlet for the entire airflow circulation. It not only discharges the hot air after the cooling task is completed, but also collects and discharges the gas leaked from the seal of the first-stage radial turbine 6, forming a complete internal airflow circulation path. The advantage of this design is that it makes full use of the characteristics of the working medium itself. That is, the expanded low-temperature air is both a cooling medium and can provide the necessary working pressure for the air bearing, ensuring that the bearing can still establish a stable load-bearing air film in a high-altitude, low-pressure environment. At the same time, the dynamic balance of axial force is achieved by adjusting the pressure distribution.

[0029] In this embodiment, a sealing ring 26 is also included. The sealing ring 26 is fixedly connected to the side of the flange 17 facing the first-stage radial turbine 6. The inner ring surface of the sealing ring 26 is provided with a plurality of annular sealing teeth 27. The sealing teeth 27 and the outer circular surface of the boss on the back of the first-stage radial turbine 6 form a labyrinth-type sealing structure. An axially penetrating central hole 28 is opened at the center of the flange 17. On the side of the flange 17 away from the sealing ring 26, a plurality of radial air guide grooves 29 are evenly opened around the central hole 28. The radial air guide grooves 29 are respectively connected to the pressure relief hole 23 and the central hole 28.

[0030] The sealing system of this device employs labyrinth sealing technology, which ensures efficient sealing while controlling axial force. The sealing ring 26 is fixed to the side of the flange 17 facing the first-stage radial turbine 6. Multiple annular sealing teeth 27 on its 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 to allow high-pressure gas to undergo multiple throttling expansions as it passes through the gaps between the continuous sealing teeth 27. Each time it passes through a sealing tooth 27, the gas pressure drops significantly due to flow resistance and eddy current losses, and the flow velocity also decreases accordingly, thereby greatly reducing gas leakage.

[0031] 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.

[0032] 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.

[0033] 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.

[0034] 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.

[0035] In this embodiment, a bladed diffuser 33 is provided inside the first-stage volute 4, and the bladed diffuser 33 is arranged around the outer periphery of the first-stage radial turbine 6.

[0036] A vaned diffuser 33 surrounds the first-stage radial turbine 6. Its working mechanism involves using fixed guide vanes to guide, decelerate, and pressurize the high-speed airflow exiting the turbine. After the high-pressure gas expands and performs work through the first-stage radial turbine 6, it is ejected from the turbine outlet at a very high tangential velocity. This high-speed airflow still contains a large amount of kinetic energy. If it were to directly enter the first-stage volute 4 for collection, a significant amount of energy would be wasted due to turbulent flow and impact losses. The guide vanes of the vaned diffuser 33 are designed with specific angles and profiles to smoothly guide the high-speed rotating airflow into the diffusion channel. During the diffusion process, the kinetic energy of the airflow is effectively converted into pressure energy, achieving a reduction in velocity and partial recovery of static pressure.

[0037] The advantages of this design are: on the one hand, it improves the energy conversion efficiency of the turbine stage, enabling more gas energy to be converted into shaft power output and increasing power generation; on the other hand, the airflow after being decelerated by the diffuser enters the volute collection chamber at a lower speed and higher pressure, reducing the flow loss of the airflow in the volute and allowing the airflow to enter the second-stage turbine more smoothly and orderly through the volute connecting pipe 8, thus improving the aerodynamic matching between stages.

[0038] In this embodiment, a first tie rod 34 is provided at one end of the rotor main shaft 3, and a second tie rod 35 is provided at the other end. The first tie rod 34 passes through the first-stage radial flow turbine 6 and is screwed with a first locking nut 36 at its end. The second tie rod 35 passes through the second-stage radial flow turbine 7 and is screwed with a second locking nut 37 at its end. The first locking nut 36 axially presses and fixes the first-stage radial flow turbine 6 onto the rotor main shaft 3, and the second locking nut 37 axially presses and fixes the second-stage radial flow turbine 7 onto the rotor main shaft 3.

[0039] The first tie rod 34 and the second tie rod 35, respectively located at both ends of the rotor main shaft 3, can be integrally machined with the rotor main shaft 3 or are independent components connected by threads. The two tie rods apply axial preload through the locking nuts at their ends, firmly pressing the turbine onto the positioning step or shoulder of the rotor main shaft 3. This fixing method has the following advantages: First, the frictional force generated by axial compression can reliably transmit the huge torque during high-speed rotation, ensuring that there is no relative slippage or loosening between the turbine and the main shaft. Second, the locking nuts can precisely control the magnitude of the preload, ensuring sufficient compression force to withstand the axial load and centrifugal force during turbine operation, while avoiding stress concentration and deformation caused by excessive compression. This structure is also convenient for assembly and maintenance; when the turbine needs to be replaced or repaired, it can be disassembled simply by loosening the locking nuts, without destructive disassembly.

[0040] To ensure dynamic balance and concentricity during high-speed rotation, the turbine and the corresponding tie rod are usually fitted with an interference fit or a keyway fit to achieve circumferential positioning and torque transmission. 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 a role in balancing the mass. The dynamic balance of the rotor spindle 3 can be adjusted by adjusting the tightening depth of the nuts or adding balance shims.

[0041] In this embodiment, a mounting base 38 is also included. The mounting base 38 is fixedly connected to the lower part of the housing 1. The high temperature and high pressure air inlet 10 is provided with an air inlet connection flange 39, and the expansion cooling air outlet 13 is provided with an exhaust connection flange 40.

[0042] In the above structure, the mounting base 38 is fixedly connected to the lower part of the housing 1, providing a stable support foundation for the entire device. This base design not only ensures the stability of the device when it is running at high speed and effectively suppresses vibration transmission, but also facilitates the integration of the device into the airframe structure of the aircraft. The base is usually designed with vibration damping pads or elastic support elements, which can isolate the vibration generated during the operation of the device, prevent the vibration from being transmitted to the main structure of the aircraft, and also protect the device from external vibration interference.

[0043] 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 pre-tightening force of the bolts distributed around the circumference and the cooperation of the metal sealing gasket. The advantage of this standardized interface design is that it enables the rapid docking of this device with the air supply system of the aircraft. The specifications of the flange usually follow the aerospace industry standards, ensuring compatibility between different systems.

[0044] The above description is merely an embodiment of this application and does not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. An integrated air-suspended turbine power generation and cooling device, comprising a housing, a stator, and a rotor main shaft, wherein the rotor main shaft is rotatably mounted within the housing via a bearing assembly, the stator is fixed within the housing and coaxially arranged with the rotor main shaft, and an air gap exists between the two to form a permanent magnet synchronous generator, characterized in that: It also includes a primary volute, a secondary volute, a primary radial turbine, a secondary radial turbine, a connecting pipe between the volutes, and a cooling water jacket. The primary and secondary volutes are respectively fixed at both ends of the housing. The primary and secondary radial turbines are respectively coaxially fixed at both ends of the rotor main shaft and arranged back-to-back. The primary radial turbine is located inside the primary volute, and the secondary radial turbine is located inside the secondary volute. The primary volute is provided with a high-temperature and high-pressure air inlet and a primary air outlet. The secondary volute is provided with a secondary air inlet and an expansion cooling air exhaust outlet. The primary air outlet is connected to the secondary air inlet through the connecting pipe between the volutes. The cooling water jacket is sleeved on the outer periphery of the housing and forms a cooling channel with the housing.

2. The air-suspended turbine power generation and refrigeration integrated device according to claim 1, characterized in that: It also includes a first bearing housing, a second bearing housing, a flange, and a thrust plate. The first bearing housing is disposed between the housing and the first-stage volute, and the second bearing housing is disposed between the housing and the second-stage volute. The flange connects the first bearing housing and the first-stage 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 housing, and the second radial air bearing is installed in the second bearing housing. The thrust plate is sleeved on the rotor spindle and located between the first bearing housing and the flange. The first thrust air bearing is installed on the flange, and the second thrust air bearing is installed on the first bearing housing. The first thrust air bearing, the second thrust air bearing, and the thrust plate cooperate to form axial support.

3. The air-suspended turbine power generation and refrigeration integrated device according to claim 2, characterized in that: The first bearing housing has a pressure relief hole that connects the interior of the first bearing housing to the external environment and is used to control the cavity pressure at the back of the first-stage radial turbine. The second bearing housing has a cooling air inlet that connects the interior of the second-stage volute to the interior of the housing and is used to introduce some of the expanded air into the housing and control the pressure at the back of the second-stage radial turbine. The housing has a cooling exhaust hole that connects the interior of the housing to the external environment and is used to exhaust the air cooled after cooling the rotor shaft and the air leaking from the seal of the first-stage radial turbine.

4. The air-suspended turbine power generation and refrigeration integrated device according to claim 3, characterized in that: It also includes a sealing ring, which is fixedly connected to the side of the flange facing the first-stage radial turbine. The inner ring surface of the sealing ring is provided with multiple annular sealing teeth, and the sealing teeth form a labyrinth-type sealing structure with the outer circular surface of the boss on the back of the first-stage radial turbine. An axially penetrating central hole is opened at the center of the flange. Multiple radial air guide grooves are evenly opened around the central hole on the side of the flange away from the sealing ring. The radial air guide grooves are respectively connected to the pressure relief hole and the central hole.

5. The air-suspended turbine power generation and refrigeration integrated device according to claim 1, characterized in that: The cooling water jacket is provided with a coolant inlet and a coolant outlet, which are respectively connected to the cooling channel. A sealing structure is provided between the two ends of the cooling water jacket and the housing. The stator is interference-fitted with the inner wall of the housing.

6. The integrated air-suspended turbine power generation and refrigeration device according to claim 1, characterized in that: The first-stage volute is equipped with a bladed diffuser, which is arranged around the outer periphery of the first-stage radial turbine.

7. The air-suspended turbine power generation and refrigeration integrated device according to claim 1, characterized in that: A first tie rod is provided at one end of the rotor main shaft, and a second tie rod is provided at the other end. The first tie rod passes through the first-stage radial turbine and is screwed with a first locking nut at its end. The second tie rod passes through the second-stage radial turbine and is screwed with a second locking nut at its end. The first locking nut axially presses and fixes the first-stage radial turbine on the rotor main shaft, and the second locking nut axially presses and fixes the second-stage radial turbine on the rotor main shaft.

8. The air-suspended turbine power generation and refrigeration integrated device according to claim 1, characterized in that: It also includes a mounting base, which is fixedly connected to the lower part of the housing. The high-temperature and high-pressure air inlet is provided with an inlet connection flange, and the expansion cooling air exhaust port is provided with an exhaust connection flange.

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