Simulation device of engine rotor supported by gas foil bearing, test system and use method

Abstract

The invention relates to the technical field of foil bearing testing, in particular to a simulation device of an engine rotor supported by a gas foil bearing, a testing system and a using method. The invention discloses a simulation device of an engine rotor supported by a gas foil bearing. The simulation device comprises a box body assembly; the rotor shaft is rotationally connected with the box body assembly, a foil bearing assembly to be detected is arranged between the rotor shaft and the box body assembly, the rotor shaft comprises a first rotating contact part, a second rotating contact part and a cantilever part, the first rotating contact part is rotationally connected with the box body assembly, the second rotating contact part is rotationally connected with the box body assembly, and the cantilever part is arranged outside the box body assembly; the foil bearing assembly to be tested comprises a first radial foil bearing and a second radial foil bearing. According to the invention, the problem of insufficient foil bearing verification caused by difficulty in simulating the influence of the dynamic characteristics of a bearing-rotor system on the performance of a foil bearing due to the fact that the two ends of a radial bearing are symmetrically distributed in an existing test device is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of foil bearing testing, and in particular to a simulation device, a testing system and a use method of an engine rotor supported by a gas foil bearing. Background Art

[0002] As a small power plant, a small gas turbine engine works by sucking air into a compressor, compressing it to a certain pressure, and then sending it into a combustion chamber. The compressed air mixes with the injected fuel under a certain pressure and burns, producing high-temperature combustion gas, which is then sent to the turbine to expand and perform work. Finally, the exhaust gas is discharged into the atmosphere. With the continuous development of industrial technology, the efficiency requirements of small gas turbine engines are constantly increasing. The dn value (product of rotor diameter and speed) of the new generation of power plants has approached 4×10 6 mm·r / min, these indicators are far beyond the capabilities of traditional rolling bearing technology.

[0003] Foil bearings are adaptive, flexible, high-speed bearings that utilize ambient gas (or specialized fluids) as their working medium. Due to their gas lubrication, they offer high operating speeds, strong shock resistance, long service life, and excellent stability. Due to their significant advantages, foil bearings can be used in small gas turbine engines to replace traditional rolling bearings, significantly improving both speed and efficiency. Consequently, in recent years, foil bearings have been increasingly adopted in small gas turbine engines due to their superior performance. Among these, the corrugated foil type is currently a commonly used type of gas foil bearing.

[0004] A bump-foil bearing consists of a top foil, a bump foil, and a bearing housing. The top foil provides a flexible, smooth surface in contact with the rotating shaft and also supports the dynamic pressure air film after it forms. The bump foil, the elastic support structure of the foil bearing, possesses a certain degree of rigidity and damping, capable of withstanding certain loads. It stabilizes the dynamic pressure air film under high-speed operating conditions, ensuring stable operation of the bump-foil bearing. The bearing housing secures and supports the top foil and bump foil.

[0005] The operating principle of foil bearings is similar to that of oil-lubricated plain bearings. When the rotor rotates at high speeds, the dynamic pressure effect forms a load-bearing dynamic pressure film between the rotor and the bearing, supporting the rotor. As a result, there is no mechanical friction between the rotor journal and the bearing surface, allowing foil bearings to operate at higher speeds.

[0006] Before foil bearings are assembled and tested on a complete aircraft, they generally undergo rig testing. The test results are used to refine simulation analysis and verify the rationality of air bearing design and processing. For foil bearings, existing rig testing generally includes performance testing (including takeoff tests and static and dynamic performance testing) and bearing-rotor system testing. Rotor system testing is used to measure the vibration response characteristics of the rotor supported by the foil bearing during acceleration and deceleration, study the nonlinear vibration behavior of the rotor system supported by the flexible air foil bearing, and examine the operating conditions of the foil bearing to verify bearing performance.

[0007] Small gas turbine engines sometimes simplify their structure, often designing the compressor and turbine coaxially. They also employ a 2-0-0 cantilever support structure, with the compressor and turbine impellers located at the cantilever ends. Existing test rigs typically place radial bearings symmetrically at both ends of the test bench rotor to ensure stable bearing operation. This setup makes it difficult to simulate the impact of the dynamic characteristics of the bearing-rotor system on the performance of the foil bearing. Furthermore, existing test schemes struggle to simulate the actual installation conditions of foil bearings, particularly the impact of rotor deflection in cantilever rotor structures on foil bearing performance. This results in inadequate testing and verification of foil bearings, hindering the overall engine development process. Summary of the Invention

[0008] In view of this, the present invention provides a simulation device, a test system and a method for using an engine rotor supported by a gas foil bearing, so as to solve the problem that existing test devices usually arrange radial bearings symmetrically at both ends of the test bench rotor to ensure stable operation of the bearings. Such a setting makes it difficult to simulate the influence of the dynamic characteristics of the bearing-rotor system on the performance of the foil bearing, and it is difficult to simulate the actual installation conditions of the foil bearing, especially the influence of the rotor deflection of the cantilever rotor structure on the performance of the foil bearing, resulting in insufficient test verification of the foil bearing.

[0009] In a first aspect, the present invention provides a simulation device for an engine rotor supported by a gas foil bearing, comprising:

[0010] Cabinet assembly;

[0011] A rotor shaft, the rotor shaft is rotatably connected to the box assembly, a foil bearing assembly to be tested is adapted to be arranged between the rotor shaft and the box assembly, the rotor shaft comprises a first rotating contact portion, a second rotating contact portion and a cantilever portion, the first rotating contact portion is rotatably connected to the box assembly, the second rotating contact portion is rotatably connected to the box assembly, the second rotating contact portion is arranged between the first rotating contact portion and the cantilever portion, the cantilever portion is arranged outside the box assembly, the foil bearing assembly to be tested comprises a first radial foil bearing and a second radial foil bearing, the first radial foil bearing is arranged between the first rotating contact portion and the box assembly, and the second radial foil bearing is arranged between the second rotating contact portion and the box assembly.

[0012] A cantilever rotor structure is realized by extending the cantilever portion outside the box assembly. When the cantilever portion is driven to rotate, the rotor shaft is driven to rotate at a preset speed, and the motion parameters of the first radial foil bearing and the second radial foil bearing in the asymmetric state of the rotor shaft are obtained to simulate the actual motion working condition. Then, the influence of the rotor deflection on the performance of the first radial foil bearing and the second radial foil bearing when the cantilever portion extends out of the box assembly is realistically simulated. The experimental verification is real and sufficient, and accurate experimental data is obtained, thereby obtaining the influence of the foil bearing performance during the rotation of the rotor shaft.

[0013] In an optional embodiment, a bearing sleeve assembly is further included, and the bearing sleeve assembly also includes a first bearing sleeve and a second bearing sleeve, the first bearing sleeve is arranged between the first radial foil bearing and the box assembly, and the outer peripheral surface of the first radial foil bearing is sleeved with the first bearing sleeve, the second bearing sleeve is arranged between the second radial foil bearing and the box assembly, and the outer peripheral surface of the second radial foil bearing is sleeved with the second bearing sleeve.

[0014] In an optional embodiment, the foil bearing assembly to be tested also includes a first thrust foil bearing and a second thrust foil bearing, an annular protrusion end is provided in the circumference of the second rotating contact portion, and the bearing sleeve assembly also includes a thrust end cover, a first thrust foil bearing is provided between one side of the annular protrusion end and the thrust end cover, and a second thrust foil bearing is provided between the other side of the annular protrusion end and the end face of the second bearing sleeve.

[0015] In an optional embodiment, the box assembly includes a first box and a second box, and a first accommodating hole and a second accommodating hole are formed between the first box and the second box, the inner circumferential surface of the first accommodating hole is in contact with the outer circumferential surface of the first bearing sleeve, and the inner circumferential surface of the second accommodating hole is in contact with the outer circumferential surface of the second bearing sleeve.

[0016] In an optional embodiment, a drive assembly is further included, which includes a simulated impeller and a turbine shell. The outer peripheral surface of the cantilever part is provided with a simulated impeller, and the turbine shell is provided on the outer periphery of the simulated impeller. The turbine shell is provided with a accommodating space, and the accommodating space is suitable for accommodating gas. The inner ring of the turbine shell is provided with a pair of nozzles, and the nozzle pair sprays gas to drive the simulated impeller to rotate.

[0017] In an optional embodiment, the driving assembly further includes a simulation disk, which is sleeved on the outer circumferential surface of the cantilever portion, and the simulation impeller is arranged between the box assembly and the simulation disk.

[0018] In an optional embodiment, a measuring component is further included, which includes a temperature meter and a rotation speed meter. The measuring angle of the temperature meter extends into the first radial foil bearing and / or the second radial foil bearing, and the rotation speed meter is used to measure the rotation speed of the rotor shaft.

[0019] In a second aspect, the present invention further provides a test system comprising the above-mentioned simulation device of an engine rotor supported by a gas foil bearing.

[0020] In an optional embodiment, it also includes a gas generating component and a gas delivery component, the gas generating component includes an air compressor and a gas storage tank, the air compressor and the gas storage tank are connected by pipeline, the gas storage tank is connected to the turbine shell pipeline, the gas delivery component includes a gas delivery pipeline and a control valve, a control valve is provided on the gas delivery pipeline, one end of the gas delivery pipeline is connected to the turbine shell, the other end of the gas delivery pipeline is connected to the gas storage tank, and the control valve is connected to the controller circuit.

[0021] In a third aspect, the present invention also provides a method for using a simulation device for an engine rotor supported by a gas foil bearing, wherein the cantilever portion is driven to rotate to drive the rotor shaft to rotate at a preset speed to obtain motion parameters of the first radial foil bearing and the second radial foil bearing under the asymmetric state of the rotor shaft.

[0022] The simulation device and test system of the engine rotor supported by the gas foil bearing provided by the present invention have the following advantages: (1) the cantilever portion extends out of the box assembly to form a cantilever rotor structure in an asymmetric state, and then combined with the setting of the drive assembly, the structure is the same as the structure of the actual engine rotor to be tested, so as to simulate the structure and dynamic characteristics of the actual rotor of the engine to be tested, and then simulate the stress conditions of the radial foil bearing and the thrust foil bearing in the experimental state, and then simulate the influence of the cantilever rotor shaft structure on the radial foil bearing and the thrust foil bearing; (2) a gas generating assembly and a gas transport assembly are provided to ensure that the gas can flow continuously and evenly into the accommodating space of the turbine shell, accurately simulate the influence of the dynamic characteristics of the radial foil bearing-rotor system on the bearing performance, and simulate The actual installation and stress state of the simulated radial foil bearing is used to drive the rotor shaft to rotate for a long time, so that personnel can more reasonably evaluate and examine the performance, life and reliability of the bearing to ensure that it meets the needs of the engine; (3) By simulating the stress conditions of the radial foil bearing and the thrust foil bearing in the experimental state, it is convenient to more reasonably evaluate and assess the performance, life and reliability of this type of bearing, and ensure that this type of bearing meets the use needs of the engine; (4) The entire test process can assess each bearing of the foil bearing assembly to be tested, that is, the experimental parameters of the first radial foil bearing, the second radial foil bearing, the first thrust foil bearing and the second thrust foil bearing are obtained, and the performance and life of a single bearing are assessed; (5) The main structure design and method of the entire test device are obtained. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0024] Figure 1 A cross-sectional view of a simulation device of an engine rotor supported by a gas foil bearing according to an embodiment of the present invention;

[0025] Figure 2 A left side view of a simulation device for an engine rotor supported by a gas foil bearing according to an embodiment of the present invention;

[0026] Figure 3 is a cross-sectional view of a rotor shaft according to an embodiment of the present invention;

[0027] Figure 4 is a schematic diagram of a test system according to an embodiment of the present invention;

[0028] Figure 5 is a schematic diagram of a simulated impeller according to an embodiment of the present invention;

[0029] Figure 6 This is a schematic diagram of a turbine casing according to an embodiment of the present invention with the flow passage of the second nozzle cut away;

[0030] Figure 7 A half-section view of a turbine housing according to an embodiment of the present invention;

[0031] Figure 8 is a schematic diagram of a turbine housing according to an embodiment of the present invention;

[0032] Figure 9 This is a schematic diagram showing a cross-section of the flow passage of the second nozzle after the simulated impeller is connected to the turbine housing according to an embodiment of the present invention.

[0033] Explanation of the reference numerals: 1. rotor shaft; 101. first rotating contact portion; 102. second rotating contact portion; 1021. annular protruding end; 103. cantilever portion; 2. housing assembly; 201. first housing; 202. second housing; 203. first accommodating hole; 204. second accommodating hole; 3. foil bearing assembly to be tested; 301. first radial foil bearing; 302. second radial foil bearing; 303. first thrust foil bearing; 304. second thrust foil bearing; 4. bearing sleeve assembly; 401. first bearing sleeve; 4011. flange portion; 402. second bearing sleeve; 403. thrust end cover; 5. drive assembly ;501, simulated impeller; 5011, blades; 502, turbine shell; 5021, accommodating space; 5022, inner ring; 5023, nozzle pair; 50231, first nozzle; 50232, second nozzle; 5024, air inlet; 503, simulated disk; 6, gas generating assembly; 601, air compressor; 602, air inlet pipe; 603, gas storage tank; 604, dryer; 605, filter; 7, gas delivery assembly; 701, stop valve; 702, gas delivery pipe; 703, solenoid valve; 704, pressure reducing valve; 705, flow control valve; 706, connecting hose; 8, carrying platform; 9, control cabinet. DETAILED DESCRIPTION

[0034] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0035] The following combination Figures 1 to 9 , describing embodiments of the present invention.

[0036] According to an embodiment of the present invention, on the one hand, a simulation device of an engine rotor supported by a gas foil bearing is provided, comprising: a housing assembly 2; a rotor shaft 1, the rotor shaft 1 being rotatably connected to the housing assembly 2, a foil bearing assembly 3 to be tested being suitable for being arranged between the rotor shaft 1 and the housing assembly 2, the rotor shaft 1 comprising a first rotating contact portion 101, a second rotating contact portion 102 and a cantilever portion 103, the first rotating contact portion 101 being rotatably connected to the housing assembly 2, the second rotating contact portion 102 being rotatably connected to the housing assembly 2, the second rotating contact portion 102 being arranged between the first rotating contact portion 101 and the cantilever portion 103, the cantilever portion 103 being arranged outside the housing assembly 2, the foil bearing assembly 3 to be tested comprising a first radial foil bearing 301 and a second radial foil bearing 302, the first radial foil bearing 301 being arranged between the first rotating contact portion 101 and the housing assembly 2, the second radial foil bearing 302 being arranged between the second rotating contact portion 102 and the housing assembly 2.

[0037] By extending the cantilever portion 103 outside the housing assembly 2 to achieve a cantilever rotor structure, when the cantilever portion 103 is driven to rotate, it drives the rotor shaft 1 to rotate at a preset speed, and obtains the motion parameters of the first radial foil bearing 301 and the second radial foil bearing 302 in the asymmetric state of the rotor shaft 1, thereby simulating actual motion conditions. Furthermore, the effect of rotor deflection on the performance of the first and second radial foil bearings 301, 302 when the cantilever portion 103 extends from the housing assembly 2 is realistically simulated. This allows for accurate experimental data to be obtained through authentic and thorough experimental verification, thereby determining the impact on the performance of the foil bearings during the rotation of the rotor shaft 1. In this embodiment, the preset speed does not refer to uniform rotation; the rotor shaft 1 may also increase or decrease in speed, and maintain a certain speed for a period of time, to realistically simulate the actual operating conditions of the first and second radial foil bearings 301, 302. In this embodiment, the preset speed of the rotor shaft 1 is 0-60000 r / min, among which different speeds such as 0, 1000 r / min, 2000 r / min, 5000 r / min, 8000 r / min, 10000 r / min, 20000 r / min, 40000 r / min, 50000 r / min, and 60000 r / min are selected for testing.

[0038] In one embodiment, Figure 1 、 Figure 2 and Figure 3As shown, it also includes a bearing sleeve assembly 4, and the bearing sleeve assembly 4 also includes a first bearing sleeve 401 and a second bearing sleeve 402. The first bearing sleeve 401 is arranged between the first radial foil bearing 301 and the box assembly 2, and the outer circumferential surface of the first radial foil bearing 301 is sleeved with the first bearing sleeve 401, and the second bearing sleeve 402 is arranged between the second radial foil bearing 302 and the box assembly 2, and the outer circumferential surface of the second radial foil bearing 302 is sleeved with the second bearing sleeve 402.

[0039] The housing assembly 2 and the first radial foil bearing 301 are separated by the first bearing sleeve 401, and the first radial foil bearing 301 carries a portion of the radial load of the rotor shaft 1 and then transfers it to the first bearing sleeve 401, avoiding direct contact between the first radial foil bearing 301 and the housing assembly 2; the housing assembly 2 and the second radial foil bearing 302 are separated by the second bearing sleeve 402, and the second radial foil bearing 302 carries another portion of the radial load of the rotor shaft 1 and then transfers it to the second bearing sleeve 402, avoiding direct contact between the second radial foil bearing 302 and the housing assembly 2. It should be noted that in order to ensure that the mechanical properties of the rotor shaft 1 are consistent with the actual rotor of the engine to be tested, the center span of the first radial foil bearing 301 and the second radial foil bearing 302 is consistent with the span of the two foil bearings of the engine to be tested, and the rotor shaft 1 of the present application has exactly the same parameters as the rotor of the engine to be tested, such as mass, length, diameter, etc., and the rotor shaft 1 is formed into a cantilever form by the arrangement of the first bearing sleeve 401 and the second bearing sleeve 402.

[0040] In one embodiment, Figure 1 、 Figure 3 As shown, the foil bearing assembly 3 to be tested further includes a first thrust foil bearing 303 and a second thrust foil bearing 304. An annular raised end 1021 is provided circumferentially on the second rotating contact portion 102. The bearing sleeve assembly 4 further includes a thrust end cap 403. The first thrust foil bearing 303 is provided between one side of the annular raised end 1021 and the thrust end cap 403, and the second thrust foil bearing 304 is provided between the other side of the annular raised end 1021 and the end surface of the second bearing sleeve 402. It should be noted that the second bearing sleeve 402 is sleeved on the outer circumference of the second rotating contact portion 102 between the annular raised end 1021 and the cantilever portion 103. The first and second thrust foil bearings 303, 304 withstand the circumferential force of the rotor shaft 1. The thrust end cap 403 and the second bearing sleeve 402 are fixedly connected to the housing assembly 2 via fasteners. Specifically, the fasteners are bolts.

[0041] In one embodiment, Figure 1 、 Figure 2 and Figure 3As shown, the housing assembly 2 includes a first housing 201 and a second housing 202. A first receiving hole 203 and a second receiving hole 204 are formed between the first housing 201 and the second housing 202. The inner circumference of the first receiving hole 203 fits the outer circumference of the first bearing sleeve 401, and the inner circumference of the second receiving hole 204 fits the outer circumference of the second bearing sleeve 402. The first receiving hole 203 accommodates a portion of the first bearing sleeve 401, and the flange portion 4011 of the first bearing sleeve 401 is fixedly connected to the first housing 201 by bolts. The second receiving hole 204 accommodates a portion of the second bearing sleeve 402. It should be noted that, as Figure 1 As shown, the first bearing sleeve 401 only occupies a portion of the first receiving hole 203, and the second bearing sleeve 402 only occupies a portion of the second receiving hole 204, and both the first receiving hole 203 and the second receiving hole 204 are through-holes to facilitate the insertion of the rotor shaft 1. Figure 2 As shown, the first box body 201 and the second box body 202 are fixedly connected by bolts.

[0042] In one embodiment, Figure 1 、 Figure 2 、 Figure 3 、 Figure 5 、 Figure 6 、 Figure 7 and Figure 8As shown, the device further includes a drive assembly 5, which includes a simulated impeller 501 and a turbine shell 502. The simulated impeller 501 is sleeved on the outer circumference of the cantilever portion 103. The turbine shell 502 is sleeved on the outer circumference of the simulated impeller 501. The turbine shell 502 is provided with a receiving space 5021, which is suitable for accommodating gas. The inner ring 5022 of the turbine shell 502 is provided with a plurality of nozzle pairs 5023. Each nozzle pair 5023 includes a first nozzle 50231 and a second nozzle 50232. The plurality of nozzle pairs 5023 eject gas to drive the simulated impeller 501 to rotate. The gas is received from the receiving space 5021 of the turbine shell 502. The gas has a certain pressure (pressure range of 0.6-1.5 MPa). The gas enters the receiving space 5021 from the outside and is then sprayed from the receiving space 5021 through the nozzle pairs 5023 onto the outer circumferential wall of the simulated impeller 501, driving the simulated impeller 501 to rotate. It should be noted that the simulated impeller 501 of the present application is circumferentially uniformly distributed, and the number of circumferentially uniformly distributed blades 5011 is an integer multiple of the number of circumferentially uniformly distributed nozzle pairs 5023 of the inner ring 5022, so as to ensure the effectiveness of the jet from the nozzle pairs 5023. Specifically, in this embodiment, the number of circumferentially uniformly distributed blades 5011 of the simulated impeller 501 is twice the number of nozzle pairs 5023 of the inner ring 5022, and the number of circumferentially uniformly distributed blades 5011 of the simulated impeller 501 is 20, and the number of nozzle pairs 5023 is 10 pairs. The radians between adjacent nozzle pairs 5023 are the same, the diameters of the first nozzle 50231 and the second nozzle 50232 are equal, and the diameter of the first nozzle 50231 is 2-3 mm, preferably 2.5 mm. Figure 5 、 Figure 6 and Figure 9 As shown, the flow path of the first nozzle 50231 or the second nozzle 50232 is not directly set towards the center point of the turbine shell 502. The flow paths of the first nozzle 50231 or the second nozzle 50232 are in the same direction, and the flow paths of the first nozzle 50231 and the second nozzle 50232 are set at an angle to the center point of the turbine shell 502. Figure 5 、 Figure 6 and Figure 9 As shown, the blades 5011 of the simulated impeller 501 are arc-shaped, with each arc corresponding to a nozzle (first nozzle 50231 or second nozzle 50232). The nozzle flow path and the arc-shaped arrangement of the blades 5011 cooperate to ensure that the direction of the gas ejected from the first nozzle 50231 or second nozzle 50232 is exactly the same as the tangential direction of the simulated impeller 501, thereby eliminating the axial force exerted by the gas ejected from the first nozzle 50231 or second nozzle 50232 on the simulated impeller 501. It should be noted that a gap is left between the inner circumference of the turbine housing 502 and the outer circumference of the blades 5011 of the simulated impeller 501, with the gap ranging from 0.3 to 0.5 mm.

[0043] In this embodiment, if Figure 1 As shown, the simulated impeller 501 is fixedly mounted on the outer periphery of the cantilever portion 103 . When the simulated impeller 501 rotates, it drives the cantilever portion 103 to rotate, thereby driving the rotor shaft 1 to rotate at high speed.

[0044] In one embodiment, Figure 1 、 Figure 2 、 Figure 3 As shown, the drive assembly 5 also includes a simulation disk 503, which is sleeved on the outer circumference of the cantilever portion 103. The simulated impeller 501 is provided between the housing assembly 2 and the simulation disk 503. The simulation disk 503, the simulated impeller 501, and the turbine housing 502 are used to simulate the actual rotor of the engine. It should be noted that, in order to be consistent with the actual impeller of the engine to be tested, the mass, center of mass position, polar moment of inertia, and diametrical moment of inertia of the simulated impeller 501 and the simulation disk 503 of the present application are consistent with the actual impeller parameters of the engine to be tested, so as to simulate the relevant parameters of the actual impeller during motion.

[0045] In one embodiment, a measuring assembly is further included, comprising a temperature meter and a speed meter. The temperature meter's measuring end extends into the first radial foil bearing 301 and the second radial foil bearing 302, and the speed meter measures the speed of the rotor shaft 1. The speed meter is preferably a laser speed sensor and the temperature meter is a thermocouple meter. In this embodiment, there are two temperature meters, each corresponding to a radial foil bearing. The temperature measuring end of the temperature meter extends into the radial foil bearing, resting against the back of the top foil to measure the internal temperature. In order to measure vibration displacement, which has a range of 0-100 microns, eddy current sensors are also provided on the first housing 201 and the second housing 202 to sense the vibration displacement of the rotor shaft 1 in the horizontal and vertical directions. The radial foil bearings in this embodiment function to bear the axial load of the rotor and to perform axial positioning of the rotor.

[0046] According to an embodiment of the present invention, on the other hand, a test system is provided, including the above-mentioned simulation device of the engine rotor supported by the gas foil bearing.

[0047] In one embodiment, Figure 4 As shown, it also includes a gas generating component 6 and a gas delivery component 7. Figure 4 As shown, the gas generation component 6 includes an air inlet pipe 602, one end of which is connected to the air compressor 601. The air inlet pipe 602 is provided with a gas storage tank 603, a dryer 604 and a filter 605 in the direction away from the air compressor 601. The gas storage tank 603 stores the high-pressure gas generated by the air compressor 601, and the high-pressure gas enters the gas transport component after being dried and filtered. Figure 4 As shown, the gas delivery component 7 includes a gas delivery pipeline 702, one end of which is provided with a shut-off valve 701, and the two ends of the shut-off valve 701 are respectively connected to the gas delivery pipeline 702 and the air inlet pipeline 602, and the gas delivery pipeline 702 is provided with a solenoid valve 703, a pressure reducing valve 704 and a flow control valve 705 in sequence in the direction away from the shut-off valve 701, and the flow control valve 705 is connected to the worm gear housing via a connecting hose 706. Specifically, the shut-off valve 701 is a manual shut-off valve 701, and the flow control valve 705 is an electric regulating ball valve, and the gas delivery pipeline 702 is connected to three flow control valves 705 after passing through the pressure reducing valve 704, and each flow control valve 705 can be connected to a connecting hose 706 for application according to actual conditions. Among them, the gas flow at the outlet of the flow control valve 705 is 200-300m 3 / h, the voltage value of the flow control valve 705 is 1-5V.

[0048] In order to realize automatic control, a control cabinet 9 is also included. The control cabinet 9 includes a controller and a display screen. The control cabinet 9 is connected to the flow control valve 705, the solenoid valve 703, the air compressor 601, and the air storage tank 603 respectively.

[0049] A method for using a test system. During a specific implementation, an air compressor 601 generates compressed gas with a certain pressure. The gas passes through an air storage tank 603, a dryer 604, and a filter 605 in sequence, then enters a gas transmission pipeline 702 through a stop valve 701. The gas passes through a solenoid valve 703, a pressure reducing valve 704, and a flow control valve 705 in sequence, and enters a accommodating space 5021 of a turbine shell 502 through a connecting hose 706. The gas is sprayed out by a nozzle 5023 to drive a simulated impeller 501 to rotate. The simulated impeller 501 drives a rotor shaft 1 to rotate at a preset speed. The vibration displacement of the rotor shaft 1 in the horizontal and vertical directions is sensed by an eddy current sensor, the temperature in the radial foil bearing is sensed by a temperature meter, and the speed of the rotor shaft 1 is sensed by a laser speed sensor. The performance parameters, lifespan, and reliability of the first radial foil bearing 301 and the second radial foil bearing 302 are simulated.

[0050] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A simulation device for an engine rotor supported by a gas foil bearing, characterized in that: include: Box assembly (2); A rotor shaft (1) is rotatably connected to a housing assembly (2); a foil bearing assembly (3) to be tested is provided between the rotor shaft (1) and the housing assembly (2); the rotor shaft (1) comprises a first rotating contact portion (101), a second rotating contact portion (102) and a cantilever portion (103); the first rotating contact portion (101) is rotatably connected to the housing assembly (2); the second rotating contact portion (102) is rotatably connected to the housing assembly (2); the second rotating contact portion (103) is rotatably connected to the housing assembly (2); 02) is arranged between the first rotating contact portion (101) and the cantilever portion (103), the cantilever portion (103) is arranged outside the box assembly (2), the foil bearing assembly (3) to be tested comprises a first radial foil bearing (301) and a second radial foil bearing (302), the first radial foil bearing (301) is arranged between the first rotating contact portion (101) and the box assembly (2), and the second radial foil bearing (302) is arranged between the second rotating contact portion (102) and the box assembly (2).

2. The simulation device for an engine rotor supported by a gas foil bearing according to claim 1, characterized in that: The invention also includes a bearing sleeve assembly (4), wherein the bearing sleeve assembly (4) further includes a first bearing sleeve (401) and a second bearing sleeve (402), wherein the first bearing sleeve (401) is arranged between the first radial foil bearing (301) and the housing assembly (2), and the outer peripheral surface of the first radial foil bearing (301) is sleeved with the first bearing sleeve (401), and the second bearing sleeve (402) is arranged between the second radial foil bearing (302) and the housing assembly (2), and the outer peripheral surface of the second radial foil bearing (302) is sleeved with the second bearing sleeve (402).

3. The simulation device for an engine rotor supported by a gas foil bearing according to claim 2, characterized in that: The foil bearing assembly (3) to be tested further comprises a first thrust foil bearing (303) and a second thrust foil bearing (304); an annular protrusion end (1021) is provided in the circumference of the second rotating contact portion (102); the bearing sleeve assembly (4) further comprises a thrust end cover (403); the first thrust foil bearing (303) is provided between one side of the annular protrusion end (1021) and the thrust end cover (403); and the second thrust foil bearing (304) is provided between the other side of the annular protrusion end (1021) and the end face of the second bearing sleeve (402).

4. The simulation device for an engine rotor supported by a gas foil bearing according to claim 3, characterized in that: The housing assembly (2) comprises a first housing (201) and a second housing (202); a first accommodating hole (203) and a second accommodating hole (204) are formed between the first housing (201) and the second housing (202); the inner circumferential surface of the first accommodating hole (203) is in contact with the outer circumferential surface of the first bearing sleeve (401); and the inner circumferential surface of the second accommodating hole (204) is in contact with the outer circumferential surface of the second bearing sleeve (402).

5. The simulation device for an engine rotor supported by a gas foil bearing according to claim 1, characterized in that: The invention also includes a driving assembly (5), wherein the driving assembly (5) includes a simulated impeller (501) and a turbine shell (502), wherein the outer peripheral surface of the cantilever portion (103) is provided with the simulated impeller (501), and the turbine shell (502) is provided on the outer periphery of the simulated impeller (501), and the turbine shell (502) is provided with a receiving space (5021), wherein the receiving space (5021) is suitable for receiving gas, and the inner ring (5022) of the turbine shell (502) is provided with a nozzle pair (5023), wherein the nozzle pair (5023) ejects gas to drive the simulated impeller (501) to rotate.

6. The simulation device for an engine rotor supported by a gas foil bearing according to claim 5, characterized in that: The driving assembly (5) further comprises a simulation disk (503), wherein the simulation disk (503) is sleeved on the outer peripheral surface of the cantilever portion (103), and the simulation impeller (501) is arranged between the box assembly (2) and the simulation disk (503).

7. The simulation device for an engine rotor supported by a gas foil bearing according to claim 1, characterized in that: The invention also comprises a measuring assembly, which comprises a temperature measuring instrument and a rotation speed measuring device. The measuring angle of the temperature measuring instrument extends into the first radial foil bearing (301) and / or the second radial foil bearing (302), and the rotation speed measuring device is used to measure the rotation speed of the rotor shaft (1).

8. A testing system, characterized in that: A simulation device comprising an engine rotor supported by a gas foil bearing according to any one of claims 1 to 7.

9. The test system according to claim 8, characterized in that: The invention also includes a gas generating assembly (6) and a gas delivery assembly (7), wherein the gas generating assembly (6) includes an air compressor (601) and a gas storage tank (603), wherein the air compressor (601) and the gas storage tank (603) are connected by a pipeline, wherein the gas storage tank (603) is connected by a pipeline to the turbine housing (502), and wherein the gas delivery assembly (7) includes a gas delivery pipeline (702) and a control valve, wherein the gas delivery pipeline (702) is provided with a control valve, wherein one end of the gas delivery pipeline (702) is connected to the turbine housing (502), and the other end of the gas delivery pipeline (702) is connected to the gas storage tank (603), and wherein the control valve is connected to a controller circuit.

10. A method for using a simulation device for an engine rotor supported by a gas foil bearing, for using the simulation device for an engine rotor supported by a gas foil bearing according to claim 1, characterized in that: The cantilever portion (103) is driven to rotate, thereby driving the rotor shaft (1) to rotate at a preset speed, so as to obtain motion parameters of the first radial foil bearing (301) and the second radial foil bearing (302) in an asymmetric state of the rotor shaft (1).

Images