CN107817107B - Elastic support structure and turbine engine rotor test bed - Google Patents
Elastic support structure and turbine engine rotor test bed Download PDFInfo
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- CN107817107B CN107817107B CN201610818092.3A CN201610818092A CN107817107B CN 107817107 B CN107817107 B CN 107817107B CN 201610818092 A CN201610818092 A CN 201610818092A CN 107817107 B CN107817107 B CN 107817107B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M1/00—Frames or casings of engines, machines or apparatus; Frames serving as machinery beds
- F16M1/04—Frames or casings of engines, machines or apparatus; Frames serving as machinery beds for rotary engines or similar machines
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Abstract
The invention relates to an elastic support structure and a turbine engine rotor test stand, wherein the turbine engine rotor test stand comprises: the supporting part is arranged on one side of the supporting seat in a suspending mode through the at least two elastic supporting rods, and the rigidity of the elastic supporting structure can be adjusted by changing the length, the number and/or the cross section area of the cantilever of each elastic supporting rod. Through set up two at least elastic support rods on the supporting seat, the supporter is hung through two at least elastic support rods and is established in one side of supporting seat, and the rigidity of elastic support structure is adjustable can only need to realize convenient and fast, easy to carry out through cantilever length, quantity and/or the cross-sectional area that changes elastic support rod.
Description
Technical Field
The invention relates to the technical field of turbine engines, in particular to an elastic supporting structure and a turbine engine rotor test bed.
Background
Squeeze film dampers are generally required to be designed in modern aeroengines and gas turbines so as to reduce vibration of rotors when the rotors pass through critical rotating speed, reduce external force transmission, prolong the service life of force bearing parts and improve the stability of rotor systems. In order to ensure the normal operation of the squeeze film damper and adjust the critical rotation speed of the rotor-support system, an elastic support is usually designed while the squeeze film damper is arranged, and the elastic support is matched with the pressurized oil film damper for use, so that the purposes of critical rotation speed adjustment and vibration reduction are achieved.
The damping of the squeeze film damper and the rigidity of the elastic support must be carefully matched to achieve the purposes of vibration reduction and load reduction, and improper combination cannot play a role in vibration reduction, but aggravates the vibration of a rotor system. Due to the complex mechanism of the squeeze film damper, the structural parameters (such as gap, width and end seal) of the squeeze film damper generally need to be verified by tests; in addition, the rigidity of the spring bearing also needs to be determined by tests. The conventional test method needs to design and process a plurality of groups of elastic supports with different rigidities and a plurality of groups of squeeze film dampers with different structural parameters to carry out a vibration response verification test of the elastic support-squeeze film damper-rotor system, and has the main reasons of high test cost and long period that the rigidity of the conventional elastic support cannot be adjusted after the conventional elastic support is processed, and the structural adjustment of the squeeze film damper is difficult.
Due to the complex mechanism of the squeeze film damper, the selection of the elastic support stiffness is closely related to the characteristics of the rotor system, and the elastic support stiffness and the damping of the squeeze film damper are matched with each other, the design of the elastic support and the squeeze film damper in engineering usually needs to be further verified through a rotor-elastic support-squeeze film damper system test, as shown in fig. 1, the rotor-elastic support-squeeze film damper system comprises an elastic support a1, a squeeze film damper a2, a rotor a3 and a bearing seat a 4. In the proof test, it was necessary to change the elastic support stiffness as well as the damping of the squeeze film damper. The conventional test method is to adjust the rigidity of the elastic support by designing and manufacturing a plurality of groups of elastic supports a1 with different rigidities, wherein the elastic supports shown in fig. 1 and 2 are squirrel-cage elastic supports, and the elastic support structure of the type cannot be adjusted once the rigidity is determined; and the damping of the squeeze film damper a2 is adjusted by processing a plurality of groups of dampers with different structural parameters. In the test, the elastic support a1 and the squeeze film damper a2 with different structures are replaced to realize the adjustment of the elastic support rigidity and the squeeze film damper, so that the cost is high and the period is long; and the test piece needs to be disassembled and assembled for many times in the test, which wastes time and labor.
Disclosure of Invention
In order to overcome the technical defects, the invention provides an elastic supporting structure and a turbine engine rotor test bed, which can conveniently realize adjustable supporting rigidity.
In order to solve the above technical problem, the present invention provides an elastic support structure for elastically supporting a rotating shaft, comprising: the supporting part is arranged on one side of the supporting seat in a suspending mode through the at least two elastic supporting rods, and the rigidity of the elastic supporting structure can be adjusted by changing the length, the number and/or the cross section area of the cantilever of each elastic supporting rod.
Further, at least two elastic support rods are arranged at equal intervals in the circumferential direction with respect to the axis of the rotating shaft.
Furthermore, one ends of the at least two elastic supporting rods are detachably and fixedly connected with the supporting seat through locking nuts or tensioning sleeves, and the other ends of the at least two elastic supporting rods are detachably and fixedly connected with the supporting piece through locking nuts or tensioning sleeves.
Further, still include the squeeze film attenuator, the squeeze film attenuator includes oil film outer loop, end seal and oil film inner ring, and the supporter includes the oil film inner ring, is equipped with the several mounting hole on the oil film inner ring, and the elastic support pole can insert in the mounting hole in order to support fixedly the oil film inner ring.
Furthermore, the damping of the squeeze film damper is adjustable, and the adjustable damping of the squeeze film damper can be realized by replacing oil film outer rings with different inner diameter sizes, replacing oil film inner rings with different outer diameter sizes, changing the distance between clamping grooves of the end seal and/or replacing the end seal with different structures.
Furthermore, the oil film inner ring is provided with an extension section outside the end seal, and the elastic supporting structure further comprises at least two displacement sensors arranged at different circumferential positions of the extension section and used for detecting an oil film gap between the oil film inner ring and the oil film outer ring and the radial displacement of the oil film inner ring.
Further, the number of displacement sensors is two and is arranged vertically on the same cross section.
Further, the extension section is located in the oil film outer ring, and the at least two displacement sensors are arranged at different circumferential positions of the extension section by penetrating the oil film outer ring.
The invention also provides a turbine engine rotor test bed which comprises the elastic supporting structure.
Furthermore, the device also comprises a rotating shaft, a wheel disc and an installation tensioning sleeve, wherein the wheel disc is detachably installed on different positions of the rotating shaft through the installation tensioning sleeve.
Further, the installation tight cover that rises is including the outer sleeve that is used for top tight rim plate inner ring, the inner skleeve that is used for compressing tightly the pivot and the screw up taper sleeve of setting between outer sleeve and inner skleeve, screws up the taper sleeve and can form wedge fit structure when deepening between outer sleeve and the inner skleeve to make the outer sleeve outwards expand the inner ring that comes the top tight rim plate and make the inner skleeve inwards shrink and compress tightly the pivot.
Furthermore, the installation tensioning sleeve further comprises a limiting nut arranged at the extending end of the inner sleeve, the limiting nut is rotated to push the tightening taper sleeve to penetrate between the outer sleeve and the inner sleeve, and the tightening taper sleeve is limited.
Further, the device also comprises a limiter for limiting the non-driving end of the rotating shaft.
Therefore, based on the technical scheme, the elastic supporting structure is provided with the at least two elastic supporting rods on the supporting seat, the supporting piece is suspended on one side of the supporting seat through the at least two elastic supporting rods, the rigidity of the elastic supporting structure can be adjusted only by changing the length, the number and/or the cross-sectional area of the cantilever of each elastic supporting rod, and the elastic supporting structure is convenient, quick and easy to implement. The turbine engine rotor test bed provided by the invention has the beneficial effects correspondingly.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a schematic cross-sectional view of a conventional rotor-spring-squeeze film damper system;
FIG. 2 is a schematic structural view of an embodiment of a prior art elastic support structure;
FIG. 3 is a schematic diagram of the overall explosive structure of the resilient support structure of the present invention;
FIG. 4 is a cross-sectional view of the elastic support structure of the present invention;
FIG. 5 is a schematic diagram of an exploded view of one embodiment of the flexible support structure of the present invention;
FIG. 6 is a schematic overall structure view of an embodiment of the elastic support structure of the present invention;
FIG. 7 is a cross-sectional view of an embodiment of the elastic support structure of the present invention;
FIG. 8 is an exploded view of a squeeze film damper in an elastomeric support structure of the present invention;
FIG. 9 is a schematic view, partially in section, of a squeeze film damper in an elastomeric support structure of the present invention;
FIG. 10 is a schematic cross-sectional view of a squeeze film damper in an elastomeric support structure of the present invention;
FIG. 11 is a cross-sectional view of the overall construction of the turbine engine rotor test stand of the present invention;
FIG. 12 is a cross-sectional view of the turbine engine rotor test stand with the expansion sleeve installed thereon;
FIG. 13 is a sectional view of the structure of the limiter of the turbine engine rotor test stand according to the present invention.
Detailed Description
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
The embodiments of the present invention are intended to explain the concept of the present invention, the technical problems to be solved, the technical features constituting the technical solutions, and the technical effects to be brought about. The description of the embodiments is not intended to limit the present invention. In addition, the technical features related to the following embodiments of the present invention may be combined with each other as long as they do not conflict with each other.
In an exemplary embodiment of the elastic support structure of the present invention, as shown in fig. 3 to 11, the elastic support structure is used for elastically supporting the rotary shaft 104, and includes: the supporting seat 202, a supporting member for supporting the rotating shaft 104 and at least two elastic supporting rods 203, wherein the supporting member is suspended at one side of the supporting seat 202 through the at least two elastic supporting rods 203, and the adjustable rigidity of the elastic supporting structure can be realized by changing the cantilever length, the number and/or the cross-sectional area of the elastic supporting rods 203.
In this exemplary embodiment, the elastic supporting structure is realized by providing at least two elastic supporting rods 203 on the supporting base 202, the supporting member is suspended on one side of the supporting base 202 by the at least two elastic supporting rods 203, the at least two elastic supporting rods 203 can ensure better supporting stability and prevent the rotation of the fixing portion of the supporting member, and the adjustable rigidity of the elastic supporting structure can be realized by:
(1) changing the cantilever length of the flexible support rod 203: the adjusting mode does not need to process any parts, only needs to adjust the relative position of the elastic supporting rod 203 relative to the supporting seat 202, and then locks one end of the elastic supporting rod 203 again, and the method has the advantages that any rigidity in a certain rigidity range can be obtained;
(2) changing the number of the elastic support rods 203: according to the rigidity requirement, the number of the elastic supporting rods 203 is increased or reduced, and the purpose of adjusting the rigidity of the elastic supporting can be achieved. The method can obtain several groups of fixed elastic supporting rigidity;
(3) changing the cross-sectional area of the elastic support rod 203: the elastic support rod 203 is designed into a variable circular section form, the section shapes of the installation parts at the two ends of the elastic support rod 203 are kept unchanged, the size of the middle circular section of the elastic support rod 203 is changed, and the elastic support with the required rigidity is formed by combination. Of course, the flexible support rod 203 may be designed to have a uniform cross-sectional structure, and the cross-sectional area of the flexible support rod 203 may be changed by replacing the flexible support rod with a different cross-sectional area.
In addition, the three adjusting methods can be optionally combined for use, so that the elastic support with any rigidity in a wider rigidity range can be obtained, the adjustment of any support rigidity in a certain rigidity range can be realized by using one group of elastic support assemblies at lower cost, a plurality of sets of elastic support test pieces do not need to be processed, and the flexibility of the test is greatly improved.
The rigidity of the elastic supporting structure can be divided into static rigidity and dynamic rigidity. The static stiffness represents the ability of the elastic support to resist deformation under a unit static load; the dynamic stiffness characterizes the ability of the elastic support to resist deformation under unit external loads of different excitation frequencies.
The measuring method of the static rigidity comprises the following steps: the method comprises the following steps of suspending a weight with a certain mass on a supporting member, namely a certain static load F, measuring the sinking amount of the supporting member by using a displacement sensor, namely displacement X, and then, the elastic support static rigidity is as follows: k is F/X. The main disadvantage of static stiffness is that the influence of the spring support and the inertia of the bearing cannot be taken into account.
The measurement principle of the dynamic stiffness is as follows: the spring bearing can be simplified to a spring-mass system with a resonance circle frequency of:
so that a rigidity of:
K＝mω2＝m(2πF)2(b)
the specific measurement method comprises the following steps: firstly, the supporting member and the rotor supporting bearing 302 are assembled together, an acceleration sensor 301 is installed on the supporting member, then the supporting member is knocked by a hammer, namely, an excitation is applied to the elastic support, the response of the supporting member can be measured by the acceleration sensor 301, so that a frequency response curve is obtained, the resonance frequency F of the elastic supporting structure can be obtained from the frequency response curve, and the elastic support rigidity K can be obtained by calculation according to a formula (b). The rigidity of the elastic support structure measured by the method can be taken into account of the influence of the self mass of the elastic support and the mass of the bearing, and the critical rotating speed and the accuracy of vibration response analysis of the rotor-support system can be further improved.
Regarding the arrangement positions of the elastic support rods 203, in a preferred embodiment, at least two elastic support rods 203 are arranged at equal intervals in the circumferential direction relative to the axis of the rotating shaft 104, which is beneficial to improving the supporting stability of the supporting member and avoiding the occurrence of accidents due to uneven supporting.
In order to facilitate the change of the cantilever length, number and/or cross-sectional area of the flexible support rods 203, in a preferred embodiment, as shown in fig. 3 to 5, one end of at least two flexible support rods 203 is detachably and fixedly connected to the support base 202 through a lock nut 201 or a tension sleeve, and the other end is detachably and fixedly connected to the support member through a lock nut 209 or a tension sleeve. The elastic support rod 203 can be conveniently detached by using the tensioning sleeve or the locking nut, and the elastic support rod has higher fixing stability and higher implementability.
As a further improvement to the above embodiment, as shown in fig. 3 to 10, the elastic support structure further includes a squeeze film damper, the squeeze film damper includes an oil film outer ring 206, an end seal 208, and an oil film inner ring 205, the support includes an oil film inner ring 205, a plurality of mounting holes are provided on the oil film inner ring 205, and the elastic support rod 203 can be inserted into the mounting holes to support and fix the oil film inner ring 205. The elastic support structure of this embodiment forms a combined elastic support-squeeze film damper in which an oil film inner ring 205 serves as a support member for elastically supporting the rotary shaft 104. Specifically, as shown in fig. 3, the squeeze film damper includes an upper base half 207 and a lower base half 210 that constitute a base, and an end cap 204 to which an oil film outer ring 206 is fixed by the upper base half 207 and the lower base half 210, the end cap 204 being used to press the oil film outer ring 206.
Preferably, the damping of the squeeze film damper is adjustable, and the adjustment of the damping of the squeeze film damper can be realized by replacing oil film outer rings 206 with different inner diameter sizes, replacing oil film inner rings 205 with different outer diameter sizes, changing the slot pitch of the end seal 208 and/or replacing end seals 204 with different structures.
The damping of squeeze film dampers depends mainly on the oil film gap, oil film width, end seal form and oil supply conditions, and the above structural components of the damper need to be replaced to change the damping. The inner ring of a conventional squeeze film damper is usually integral with the elastomeric support, so that the elastomeric support must be replaced to adjust the damping of the squeeze film damper. When the combined elastic support-squeeze film damper is adopted, only part of components need to be replaced. The test of multiple elastic support stiffness and squeeze film damper damping matching can be carried out in a short period at a low cost, the efficiency of the design verification test of the elastic support and the squeeze film damper is improved, and the reasonability of the design of the elastic support and the squeeze film damper is ensured.
The damping of the squeeze film damper can be adjusted by adjusting the thickness, the width, the end seal and the like of an oil film, and the specific method comprises the following steps:
(1) adjusting the thickness of an oil film A: the oil film outer ring 206 with different inner diameter sizes is replaced, or the oil film inner ring 205 with different outer diameter sizes is replaced, other components are kept unchanged, and the thickness of the oil film A can be changed by changing the inner diameter size of the oil film outer ring 206 or the outer diameter size of the oil film inner ring 205;
(2) adjusting the width of an oil film A: the oil film inner ring 205 is replaced to change the distance of the end seal clamping groove, so that the oil film width can be adjusted, and other components can be kept unchanged;
(3) adjustment of end seal form: the squeeze film damper without end seal and with end seal can be designed, and the piston ring end seal, disc seal and the like can be arranged according to the requirement. Taking the piston ring type end seal as an example, the opening size of the piston ring can be adjusted, thereby achieving the purposes of adjusting the leakage amount and oil film damping.
The adjusting methods can be combined and used at will, so that the squeeze film damper with different damping in a wider damping range can be obtained, and the flexibility of the test can be greatly improved.
The oil film thickness of squeeze film dampers is the most important parameter for determining their damping and generally requires that the eccentricity of the damper inner ring relative to the outer ring cannot exceed 0.4. Due to the fact that the oil film gap is small, improper installation and assembly errors or deformation of the elastic support under the gravity of the rotor can cause relative eccentricity of the inner ring and the outer ring of the squeeze oil film damper, even contact can be generated in serious cases, and normal work of the SFD is affected; additionally squeeze film dampers are typically internal to the structure and it is difficult to check the oil film clearance after assembly is complete. According to the invention, the oil film clearance of the squeeze film damper, namely the oil film inner ring axis track monitoring function, is introduced into the test bed, so that the oil film clearance and the axis track can be obtained in real time in the test, and effective data support is provided for judging the working state of the squeeze film damper and analyzing the oil film dynamic characteristics in the test.
To ensure that the measurement of the oil film clearance does not destroy the integrity of the oil film, the measurement of the oil film clearance is outside the oil film zone. In a preferred embodiment, as shown in fig. 9, oil film inner ring 205 has an extension outside end seal 208, and the elastic support structure further includes at least two displacement sensors 211 disposed at different circumferential positions of the extension for detecting an oil film gap between oil film inner ring 205 and oil film outer ring 206, and a radial displacement of oil film inner ring 205. The oil film gap between the oil film inner ring 205 and the oil film outer ring 206 is the thickness of the oil film a. Preferably, the extension section is located in the oil film outer ring 206, the at least two displacement sensors 211 are arranged at different circumferential positions of the extension section by penetrating the oil film outer ring 206, measuring holes and sensor thread mounting holes are respectively arranged at corresponding positions of the oil film outer ring 206 and the upper half 207 of the base, the displacement sensors 211 are arranged at the measuring holes of the oil film outer ring, and the vector sum of the displacements measured by the at least two displacement sensors is the eccentric distance and the eccentric phase of the oil film inner ring. As shown in fig. 10, two displacement sensors 211 perpendicular to each other are installed on the same transverse section, the eccentricity can be obtained from the eccentricity, whether the inner ring and the outer ring of the oil film are in contact or not can be judged, and the axis locus of the inner ring of the oil film can be obtained by combining the two displacements.
The invention also provides a turbine engine rotor test bed which comprises the elastic supporting structure. The elastic supporting structure can conveniently realize adjustable supporting rigidity, and accordingly, the turbine engine rotor test stand also has the beneficial technical effects, and the details are not repeated.
Specifically, as shown in fig. 11, the turbine engine rotor test stand includes a driving motor 101, a flexible coupling 102, a bearing and bearing seat 103, a rotating shaft 104, a wheel disc 105, a combined elastic support-squeeze film damper 106, a platform 107, a wheel disc 108, and a limiter 109. The driving motor 101 is connected with the rotating shaft 104 through the flexible coupling 102 and drives the rotating shaft 104 to rotate; the rotating shaft 104 is provided with a wheel disc 105 and a wheel disc 108, the wheel disc 105 and the wheel disc 108 are used for balancing weight, balancing dynamic and adjusting the critical rotating speed of the rotor system, the rotating shaft 104 is supported on a bearing seat 103 and a combined elastic supporting-squeezing oil film damper 106, and the bearing seat 103 and the combined elastic supporting-squeezing oil film damper 106 are fixed on a platform 107 through bolts.
In a conventional rotor test bed, a wheel disc and a rotating shaft are usually connected in a key way, the relative position of the wheel disc on the rotating shaft is fixed, and when the position of the wheel disc needs to be adjusted, a new rotating shaft needs to be machined again. In order to solve the problem of adjusting the positions of the disk and the shaft, the turbine engine rotor test bed further comprises an installation tensioning sleeve, and the wheel disc 108 is detachably installed on different positions of the rotating shaft 104 through the installation tensioning sleeve. Preferably, the installation tensioning sleeve comprises an outer sleeve 401 for pressing against the inner ring of the wheel disc 108, an inner sleeve 403 for compressing the rotating shaft 104, and a tightening taper sleeve 402 arranged between the outer sleeve 401 and the inner sleeve 403, wherein the tightening taper sleeve 402 can form a wedge-shaped matching structure when penetrating into the space between the outer sleeve 401 and the inner sleeve 403, so that the outer sleeve 401 expands outwards to press against the inner ring of the wheel disc 108 and the inner sleeve 403 contracts inwards to compress the rotating shaft 104.
Specifically, as shown in fig. 12, the inner hole of the outer sleeve 401 is divided into two sections, one section is a cylindrical hole, the other section is a tapered hole, the outer circle is a cylindrical surface, and axial grooves are uniformly milled on the cylindrical surface to facilitate expansion of the outer sleeve when the outer sleeve is extruded, and a certain radial thickness is reserved at the bottom of each groove to ensure that the outer sleeve is an integral body; the inner surface and the outer surface of the tightening taper sleeve 402 are both provided with a cylindrical section and a conical section, and the inner hole section of the cylinder is provided with internal threads and a tightening nut; the inner sleeve 403 has inner cylindrical surface, inner cylindrical surface with homogeneously distributed axial grooves for deformation under pressure, and grooves with certain radial thickness in the bottom for the inner sleeve to be one whole, outer circle divided into two sections, front section being cylindrical surface and with outer thread and back end being conic section.
In the installation process, firstly, the whole tensioning sleeve is installed in an inner hole of the wheel disc 108 through the outer sleeve 401, and at the moment, the outer cylindrical surface of the outer sleeve 401 is in clearance fit with the inner circle of the wheel disc 108; then, the rotating shaft 104 passes through the inner hole of the inner sleeve 403, and the two parts are also in clearance fit; finally, the tightening sleeve 402 is tightened, the tightening sleeve 402 generates axial movement relative to the inner sleeve and the outer sleeve, and the inner sleeve and the outer sleeve are pressed tightly through the conical surface; under the compression of the tightening cone 402, the outer sleeve 401 expands, compressing and forming an interference connection with the disc 108; the inner sleeve 403 is compressed by the tightening taper sleeve 402 to tighten the connection with the shaft 104, thereby achieving an interference fit. Furthermore, the installation tensioning sleeve further comprises a limiting nut arranged at the extending end of the inner sleeve 403, the limiting nut is rotated to push the tightening taper sleeve 402 to penetrate into the space between the outer sleeve 401 and the inner sleeve 403, the tightening taper sleeve 402 is limited, the limiting nut is favorable for jacking the tightening taper sleeve 402 and limiting, and high practicability is achieved.
In order to prevent the rotor from being damaged by personnel or test equipment due to excessive vibration or other abnormal conditions during operation, in the above embodiment, the limiter 109 preferably limits the amplitude of the non-driving end of the shaft 104, as shown in fig. 13, and the limiter 109 includes a limit shaft 501 bearing, a limit bearing seat upper half 502 and a limit bearing seat lower half 503. According to the outer diameter of the rotating shaft 104 and the maximum allowable vibration displacement of the rotor, the size of the limit bearing 501 is selected, and the rotating shaft 104 and the limit bearing 501 keep a safe distance and are not in contact during normal operation. The limit bearing 501 is installed in the upper limit bearing seat half 502 and the lower limit bearing seat half 503, and the axial and radial positioning is realized by the limit bearing seat to provide enough protection strength.
The above-described embodiments are described in detail with reference to examples, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, equivalents and variations can be made in these embodiments without departing from the spirit and scope of the invention.
Claims (12)
1. An elastic support structure for elastically supporting a rotary shaft (104), characterized by comprising:
the supporting seat (202), a supporting piece for supporting the rotating shaft (104) and at least two elastic supporting rods (203), wherein the supporting piece is suspended at one side of the supporting seat (202) through the at least two elastic supporting rods (203), and the rigidity of the elastic supporting structure can be adjusted by changing the cantilever length, the number and/or the cross-sectional area of the elastic supporting rods (203); and
squeeze oil film attenuator, squeeze oil film attenuator includes oil film outer ring (206), end seals (208) and oil film inner ring (205), the bearing includes oil film inner ring (205) be equipped with the several mounting hole on oil film inner ring (205), elastic support pole (203) can insert in the mounting hole in order to right oil film inner ring (205) support fixedly.
2. The elastic support structure according to claim 1, characterized in that the at least two elastic support rods (203) are arranged at equal intervals in the circumferential direction with respect to the axis of the rotating shaft (104).
3. The elastic support structure of claim 1, wherein one end of each of the at least two elastic support rods (203) is detachably and fixedly connected with the support base (202) through a lock nut or a tension sleeve, and the other end of each of the at least two elastic support rods is detachably and fixedly connected with the support member through a lock nut or a tension sleeve.
4. The elastomeric support structure of claim 1, wherein the squeeze film damper has adjustable damping, which can be achieved by replacing the oil film outer ring (206) with different inner diameter dimensions, replacing the oil film inner ring (205) with different outer diameter dimensions, changing the slot pitch of the end seal (208), and/or replacing the end seal (208) with different configurations.
5. The elastic support structure according to claim 1, characterized in that said oil film inner ring (205) has an extension outside said end seal (208), said elastic support structure further comprising at least two displacement sensors (211) arranged at different circumferential positions of said extension for detecting an oil film gap between said oil film inner ring (205) and said oil film outer ring (206), and a radial displacement of said oil film inner ring (205).
6. The elastic support structure according to claim 5, characterized in that said displacement sensors (211) are two in number and are arranged vertically on the same cross section.
7. The elastic support structure according to claim 5, characterized in that said extension is located inside said oil film outer ring (206), said at least two displacement sensors (211) being arranged at different circumferential positions of said extension by penetrating said oil film outer ring (206).
8. A turbine engine rotor test stand, characterized by comprising a resilient support structure according to any one of claims 1 to 7.
9. The turbine engine rotor test bed according to claim 8, further comprising a rotating shaft (104), a wheel disc (108) and a mounting tension sleeve, wherein the wheel disc (108) is detachably mounted on different positions of the rotating shaft (104) through the mounting tension sleeve.
10. The turbine engine rotor test stand according to claim 9, characterized in that the mounting tension sleeve comprises an outer sleeve (401) for pressing against the inner ring of the wheel disc (108), an inner sleeve (403) for pressing against the rotating shaft (104), and a tightening cone (402) arranged between the outer sleeve (401) and the inner sleeve (403), the tightening cone (402) being capable of forming a wedge-shaped fit structure when penetrating between the outer sleeve (401) and the inner sleeve (403) so that the outer sleeve (401) expands outward to press against the inner ring of the wheel disc (108) and the inner sleeve (403) contracts inward to press against the rotating shaft (104).
11. The turbine engine rotor test bed according to claim 10, characterized in that the mounting expansion sleeve further comprises a limiting nut arranged at the extending end of the inner sleeve (403), and the limiting nut is rotated to push the tightening cone sleeve (402) to penetrate between the outer sleeve (401) and the inner sleeve (403) and limit the tightening cone sleeve (402).
12. The turbine engine rotor test stand of claim 8, further comprising a limiter (109) that limits a non-drive end of the shaft (104).
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| CN108663214B (en) * | 2018-04-28 | 2020-09-18 | 北京航天动力研究所 | Supporting assembly for high-speed rotor analog simulation test and test method |
| CN110320044B (en) * | 2019-05-27 | 2020-12-08 | 西北工业大学 | Active load reduction device after sudden loading of aircraft engine tester |
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| CN111608749B (en) * | 2020-05-29 | 2022-07-26 | 中国航发湖南动力机械研究所 | Radial rigidity adjusting device and method for squirrel-cage elastic support device and aero-engine |
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